There is provided a turbine housing comprising a housing dividing wall circumferentially extending around a central axis of the turbine housing. The housing dividing wall axially separates a first inlet volute and a second inlet volute. The housing dividing wall comprises a circumferentially extending tip configured to receive a nozzle ring. The tip is shaped to impart a tortuous geometry upon a leakage passage defined between the first inlet volute and the second inlet volute.
A nozzle ring for a variable geometry turbine comprises: a generally annular wall; an inner flange; an outer flange; and two protrusions. The inner flange is generally perpendicular to the generally annular wall and extends from a radially inner edge of the generally annular wall. The outer flange is generally perpendicular to the generally annular wall and extends from a radially outer edge of the generally annular wall. The two protrusions extend from one of the inner or outer flange towards the other one of the inner or outer flange. At least one of the two protrusions extends only partially towards the other one of the inner or outer flange. The two protrusions define a first gap therebetween. The generally annular wall and the two protrusions define a second gap between the generally annular wall and both of the two protrusions. In some embodiments, the two protrusions are such that the first gap is tapered so that a dimension of the gap is smaller at a distal end of the protrusions and larger proximate to the inner or outer flange from which the two protrusions extend. In some embodiments, a radial extent of the second gap is less than a radial extent of the two protrusions. In use, the second gap receives an arcuate head portion of a support and the first gap receives an intermediate portion of the support. The nozzle ring may be suitable for use in a variable geometry turbocharger.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02B 37/22 - Commande des pompes en modifiant la section des conduits d'échappement ou des conduits d'air
There is disclosed a method of operating an exhaust system for receiving exhaust gas from an internal combustion engine. The exhaust system comprises: a turbine, a dosing module, at least one of a variable geometry mechanism and a bypass control valve, and a controller. The turbine is configured to receive exhaust gas from the internal combustion engine. The turbine comprises a turbine wheel configured to extract energy from the exhaust gas. The dosing module is configured to deliver an aftertreatment fluid to the exhaust gas at a position downstream of the turbine wheel. The variable geometry mechanism is configured to control the flow of exhaust gas delivered to the turbine wheel. The bypass control valve is configured to bypass a portion of the exhaust gas from a position upstream of the turbine wheel to a position downstream of the turbine wheel. The controller is configured to execute the method, the method comprising: determining a current property of the exhaust gas at a position downstream of the turbine wheel; determining a difference between the current property of the exhaust gas at the position downstream of the turbine wheel and a reference property of the exhaust gas at the position downstream of the turbine wheel; and in response to the difference, adjusting the at least one of the variable geometry mechanism and the bypass control valve.
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
F01N 5/04 - Silencieux ou dispositifs d'échappement combinés ou associés à des dispositifs bénéficiant de l'énergie des gaz évacués les dispositifs utilisant l'énergie cinétique
4.
TURBINE HOUSINGS FOR A TURBOCHARGER, TURBINE AND TURBOCHARGER
There is disclosed a turbine housing for a turbocharger. The turbine housing comprises a flange and a volute. The flange has an engagement surface and a first inlet opening in the engagement surface. The volute extends around an axis and defines at least part of a flow passage through the turbine housing. The flow passage extends from the first inlet opening at a first end of the flow passage. The engagement surface of the flange is defined by a periphery of material which extends around the first inlet opening between the first inlet opening and an outer edge of the engagement surface. A thickness of a first portion of the periphery, at a radially inner side of the first inlet opening, is greater than a thickness of a second portion of the periphery, at a radially outer side of the first inlet opening, along at least a full extent of a radially inner edge of the first inlet opening.
A turbine comprising a wastegate chamber (28): a turbine housing (12) defining a turbine inlet (14), the turbine housing (12) comprising: a wastegate inlet passageway (30) defining a flow path between the turbine inlet (14) and the wastegate chamber (28), wherein the wastegate inlet passageway (30) comprises a turbine port (38) proximal the turbine inlet (14) and a non-circular valve port (36) proximal the wastegate chamber (28), and a raised rim (52) surrounding the non-circular valve port (36) and conformal to the shape of the non-circular valve port (36), wherein the raised rim comprises a first sealing surface (52); and a valve member (42) comprising a second sealing surface (50), wherein the valve member (42) is moveable between a closed position in which the second sealing surface (50) forms a seal with the first sealing surface (54) to prevent fluid flow along the flow path and an open position in which the second scaling surface (50) is spaced apart from the first sealing surface (54) to permit fluid flow along the flow path.
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F16K 1/20 - Soupapes ou clapets, c.-à-d. dispositifs obturateurs dont l'élément de fermeture possède au moins une composante du mouvement d'ouverture ou de fermeture perpendiculaire à la surface d'obturation à éléments de fermeture articulés à pivot comportant disque ou volet pivotant dont l'axe de rotation est disposé à l'extérieur du corps de soupape
WUXI CUMMINS TURBO TECHNOLOGIES COMPANY LTD. (Chine)
CUMMINS LTD (Royaume‑Uni)
Inventeur(s)
Kumar V, Sai Pavan
Gehlot, Sarendra S.
Sonawane, Sumit
Shaikh, Mudassar
Wu, Shengquan
Tian, Yan
Abrégé
A turbine housing for a turbocharger comprises: an inlet portion; a second portion for housing a turbine wheel; and an outlet portion. The inlet portion defines a first inlet and a second inlet. The inlet portion and the second portion define: a first volute which defines a first flow passage between the first inlet and a first volute outlet, and which extends around an axis of the turbine housing; and a second volute which defines a second flow passage between the second inlet and a second volute outlet, and which extends around the axis of the turbine housing. The first volute and the second volute are separated, in an axial direction, by a dividing wall. For at least a portion of the dividing wall upstream of a tongue of the first volute and a tongue of the second volute a thickness of the dividing wall varies in a first direction that is generally perpendicular to a second direction that, in use, gas will flow along through the first and second volutes such that the thickness increases in a direction generally away from the second portion of the turbine housing.
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
A turbine arrangement comprises a turbine wheel, a nozzle ring and an annular spring retainer member. The turbine wheel (4) is located within a turbine chamber (30) defined at least in part by a turbine housing (5). The turbine wheel is mounted to a shaft, the shaft and mounted turbine wheel being supported for rotation about a turbine axis by a bearing arrangement. The bearing arrangement is located in a bearing housing (3), the bearing housing having an axially extending spigot feature (32), and the bearing housing being attached to the turbine housing. The nozzle ring (34) is received by the turbine housing. The nozzle ring includes one or more flow directing vanes (36) located in a flow path (F) between an inlet volute (9) and the turbine wheel, the inlet volute being defined by an inlet volute portion of the turbine housing. The annular spring retainer member (38) is compressed between the nozzle ring and the bearing housing, the spring retainer member defining a central aperture (40) which receives the spigot feature. An axial extent (E') of the spring retainer member, in an uncompressed state, is greater than an axial spacing (S) between a back face of the turbine wheel and the spigot feature.
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
A mounting body for electrochemically machining a cavity of a component is disclosed. The mounting body comprises: an engagement face, at least part of an electrode and a plurality of electrode channels. The engagement face is engageable with the component to align the mounting body with the component. The at least part of an electrode is coupled to the mounting body. The plurality of electrolyte channels extend at least partway through the mounting body. Downstream ends of the plurality of electrolyte channels are distributed around the at least part of an electrode.
There is provided a turbine for a turbocharger, comprising: a turbine inlet passage configured to receive exhaust gas from an internal combustion engine, the exhaust gas received by the turbine inlet passage defining a turbine bulk flow; a turbine wheel chamber configured to receive the turbine bulk flow from the turbine inlet passage, the turbine wheel chamber configured to contain a turbine wheel supported for rotation about a turbine axis; a turbine outlet passage configured to receive the turbine bulk flow from the turbine wheel chamber; a dosing module configured to deliver a spray of aftertreatment fluid into a spray region of the turbine outlet passage through which the turbine bulk flow passes; and an auxiliary passage configured to receive a portion of the turbine bulk flow, the portion of the turbine bulk flow received by the auxiliary passage defining an auxiliary flow; wherein the auxiliary passage is configured to direct the auxiliary flow into the spray region of the turbine outlet passage.
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
F01N 3/22 - Réglage de l'alimentation en air additionnel uniquement, p. ex. utilisant des bipasses ou des entraînements variables de pompes à air
10.
Turbine Dosing System with Bypass Take Off and Delivery
There is provided a turbine for a turbocharger, comprising: a turbine inlet passage configured to receive exhaust gas from an internal combustion engine, the exhaust gas received by the turbine inlet passage defining a turbine bulk flow; a turbine wheel chamber configured to receive the turbine bulk flow from the turbine inlet passage, the 5 turbine wheel chamber configured to contain a turbine wheel supported for rotation; a turbine outlet passage configured to receive the turbine bulk flow from the turbine wheel chamber, the turbine outlet passage being at least partially defined by a turbine outlet passage surface and defining a centreline; an auxiliary passage configured to receive a portion of the turbine bulk flow, the portion of the turbine bulk flow received by 10 the auxiliary passage defining an auxiliary flow; and a dosing module configured to deliver a spray of aftertreatment fluid into the turbine outlet passage; wherein the auxiliary passage is configured to direct the auxiliary flow along the turbine outlet passage surface in an auxiliary flow layer.
F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
There is a provided an exhaust gas conduit for an exhaust system of an internal combustion engine. The exhaust gas conduit includes a main passage for a main flow of exhaust gases passing through the exhaust gas conduit, a chamber configured to receive an aliquot of exhaust gases separated from the main flow of exhaust gases. A mounting point is provided in the chamber for mounting an exhaust gas sensor. The chamber being configured to modify the velocity and/or the pressure of exhaust gases passing therethrough.
There is disclosed a turbine dosing system for a turbocharger. The turbine dosing system comprises a turbine inlet passage, a turbine wheel chamber, a turbine outlet passage and a plurality of dosing modules. The turbine inlet passage is configured to receive exhaust gas from an internal combustion engine. The turbine wheel chamber configured to receive exhaust gas from the turbine inlet passage. The turbine wheel chamber contains a turbine wheel supported for rotation about a turbine wheel axis. The turbine wheel comprises an exducer which defines an exducer diameter. The turbine outlet passage is downstream of the turbine wheel chamber and is configured to receive exhaust gas from the turbine wheel chamber. The turbine outlet passage defines a flow axis which extends from a downstream end of the turbine wheel. The plurality of dosing modules are configured to inject aftertreatment fluid into exhaust gas in the turbine outlet passage.
F01N 13/00 - Silencieux ou dispositifs d'échappement caractérisés par les aspects de structure
F02B 39/00 - Parties constitutives, détails ou accessoires non couverts par les groupes , et relatifs aux pompes d'alimentation ou de balayage entraînées
There is disclosed a turbine dosing system for a turbocharger. The turbine dosing system comprises a turbine inlet passage (112), a turbine wheel chamber and a turbine outlet passage (116). The turbine inlet passage is configured to receive exhaust gas from an internal combustion engine. The turbine wheel chamber is configured to receive exhaust gas from the turbine inlet passage. The turbine wheel chamber contains a turbine wheel supported for rotation about a turbine wheel axis. The turbine wheel comprises an exducer defining an exducer diameter. The turbine outlet passage is downstream of the turbine wheel chamber and is configured to receive exhaust gas from the turbine wheel chamber. The turbine outlet passage is at least partly defined by a structure which comprises a dosing module mount (122) configured to receive a dosing module (32). The turbine outlet passage defines a flow axis which extends from a downstream end of the turbine wheel. The dosing module mount is located within around 10 exducer diameters, along the flow axis, downstream of the downstream end of the turbine wheel.
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
14.
CHASSIS ASSEMBLY AND FUEL TANK FOR GENERATOR SET AND METHOD OF ASSEMBLING CHASSIS ASSEMBLY
A chassis assembly for a generator set includes a frame. The frame includes a first side rail and a second side rail. The chassis assembly includes a fuel tank disposed between the first side rail and the second side rail. The fuel tank includes a top surface. The chassis assembly includes at least one crossmember disposed at least partially in the fuel tank. The at least one crossmember includes a top plate disposed level with or below the top surface of the fuel tank. The at least one crossmember includes a sidewall that extends from the top plate. The sidewall is disposed in the fuel tank and defines an opening for fluid to flow through.
F02B 63/04 - Adaptations des moteurs pour entraîner des pompes, des outils tenus à la main ou des génératrices électriquesCombinaisons portatives de moteurs avec des dispositifs entraînés par des moteurs pour génératrices électriques
F02M 37/00 - Appareils ou systèmes pour transférer le combustible liquide des réservoirs de stockage aux carburateurs ou aux injecteursDispositions d'épuration du combustible liquide spécialement conçues pour les moteurs à combustion interne ou aménagées sur ceux-ci
A flexible hybrid system is provided. The flexible hybrid system includes a first power source and a gearbox. The gearbox is removably coupled with the first power source. The gearbox includes a flange with a first interface, the first power source removably coupled with the first interface; a housing coupled with the flange, the housing comprising a second interface; and a clutch system disposed at least partially in the housing, the clutch system comprising a first clutch mechanism and a second clutch mechanism. The flexible hybrid system includes a second power source. The second power source is removably coupled with the second interface, wherein the first clutch mechanism is configured to selectively engage the first power source to provide power to the flexible hybrid system; and the second clutch mechanism is configured to selectively engage the second power source to provide power to the flexible hybrid system.
B60K 6/36 - Agencement ou montage de plusieurs moteurs primaires différents pour une propulsion réciproque ou commune, p. ex. systèmes de propulsion hybrides comportant des moteurs électriques et des moteurs à combustion interne les moteurs primaires étant constitués de moteurs électriques et de moteurs à combustion interne, p. ex. des VEH caractérisés par des appareils, des organes ou des moyens spécialement adaptés aux VEH caractérisés par les transmissions à engrenages
B60K 6/387 - Embrayages actionnés, c.-à-d. embrayages mis en prise ou désaccouplés par des moyens d'actionnement électriques, hydrauliques ou mécaniques
There is provided a seal assembly comprising: a first component and a second component spaced apart from the first component so as to define a passage for the transfer of fluid from an inlet of the seal assembly to an outlet of the seal assembly, wherein the first component comprises a concavity at least partially defining the passage, and wherein no part of the second component extends into the portion of the passage bounded by the concavity.
F16K 5/04 - Robinets à boisseau consistant seulement en un dispositif obturateur dont au moins une des faces d'obturation a la forme d'une surface de solide de révolution plus ou moins complète, le mouvement d'ouverture et de fermeture étant essentiellement rotatif dont les boisseaux sont à surface cylindriqueLeurs garnitures d'étanchéité
F04D 29/16 - Joints d'étanchéité entre le côté du refoulement et celui de l'aspiration
An assembly for a turbomachine is disclosed, comprising a bush (74) defining a bore (71) along a bore axis for receiving at least part of a shaft (39), with an end of the bush (74) including a recess (76) for a seal (44), and a cap (86) at least partly received in the recess to retain the seal (44).
There is provided a turbocharger for a fuel cell system. The turbocharger comprises: a shaft, a compressor wheel, a turbine wheel, a motor, and a gas-lubricated thrust bearing. The shaft is supported for rotation about a central axis (A). The compressor wheel is rotationally connected to the shaft. The turbine wheel is rotationally connected to the compressor via the shaft. The motor is electro-magnetically connected to the shaft for rotationally driving the shaft. The gas-lubricated thrust bearing is arranged to react a resultant axial load applied to the shaft by the compressor wheel and the turbine wheel. The turbine wheel comprises a blade defining a leading edge, the leading edge defining a blade incline angle (φ) being inclined relative to a radial direction (r) originating from the central axis (A) in a positive angular direction relative to the direction of rotation (ω) of the turbine during use.
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F04D 29/28 - Rotors spécialement adaptés aux fluides compressibles pour pompes centrifuges ou hélicocentrifuges
There is provided a manufacturing intermediate for a turbine housing. The manufacturing intermediate being configured for engagement with an abutment portion of a holding device during machining. The manufacturing intermediate comprising a connection portion comprising a connection surface defining a first radius from a central axis. The manufacturing intermediate comprising an inlet portion defining a turbine inlet having two inlet volutes axially separated by a dividing wall, the dividing wall comprising a terminal edge defining a second radius from the central axis. The second radius is smaller than the first radius such that the dividing wall defines an alignment surface configured to abut the abutment portion to align the dividing wall with the abutment portion.
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02B 37/02 - Passages pour les gaz entre l'orifice d'échappement du moteur et l'entraînement de la pompe, p. ex. réservoirs
A rotor for an electric machine that is formed of a shaft onto which are mounted a plurality of permanent magnets. The shaft has one or more axial grooves formed in the radial outer surface of the shaft. The grooves extend longitudinally along a least a partial longitudinal length of the shaft.
H02K 1/278 - Aimants montés en surfaceAimants sertis
H02K 7/00 - Dispositions pour la mise en œuvre d'énergie mécanique associées structurellement aux machines dynamo-électriques, p. ex. association structurelle avec des moteurs mécaniques d'entraînement ou des machines dynamo-électriques auxiliaires
21.
Chassis assembly and fuel tank for generator set and method of assembling chassis assembly
A chassis assembly for a generator set includes a frame. The frame includes a first side rail and a second side rail. The chassis assembly includes a fuel tank disposed between the first side rail and the second side rail. The fuel tank includes a top surface. The chassis assembly includes at least one crossmember disposed at least partially in the fuel tank. The at least one crossmember includes a top plate disposed level with or below the top surface of the fuel tank. The at least one crossmember includes a sidewall that extends from the top plate. The sidewall is disposed in the fuel tank and defines an opening for fluid to flow through.
F02B 63/04 - Adaptations des moteurs pour entraîner des pompes, des outils tenus à la main ou des génératrices électriquesCombinaisons portatives de moteurs avec des dispositifs entraînés par des moteurs pour génératrices électriques
F02M 37/00 - Appareils ou systèmes pour transférer le combustible liquide des réservoirs de stockage aux carburateurs ou aux injecteursDispositions d'épuration du combustible liquide spécialement conçues pour les moteurs à combustion interne ou aménagées sur ceux-ci
There is provided a nozzle ring for a turbine of a turbocharger. The nozzle ring comprises: a nozzle dividing wall, at least on nozzle vane, and a circumferentially extending outer rim. The nozzle dividing wall extends generally perpendicular to a longitudinal axis of the nozzle ring. The at least one nozzle vane extends from the nozzle dividing wall and has a leading edge defining a first radius relative to the longitudinal axis. The circumferentially extending outer rim defines a second radius relative to the longitudinal axis. The ratio of the second radius to the first radius is at least around 1.05.
A turbo machine assembly comprises a first turbo machine component (58); a second turbo machine component (2); and a wave retaining ring (72) which frictionally secures the first turbo machine component to the second turbo machine component via clamping of the wave retaining ring between a first clamp surface of the first turbo machine component and a second clamp surface of the second turbo machine component. The first turbo machine component is rotatable relative to the second turbo machine component about a first axis. An axial height of the first clamp surface changes as a function of angular position about the first axis. An axial spacing between a portion of the second clamp surface and the first clamp surface changes as the rotational position of the first turbo machine component relative to the second turbo machine component changes.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F16F 1/32 - Ressorts en forme de coupellesRessorts en forme de disques légèrement concaves
There is provided a centrifugal impeller for a compressor of a turbocharger. The impeller comprises a hub and a blade. The hub extends along an impeller axis. The blade extends from the hub. The blade defines a pressure surface and a suction surface. The pressure surface comprises a concave portion.
Variable geometry turbines having new configurations of vanes are disclosed. New methods for designating new configurations of vanes for geometry turbines having are also disclosed.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
Nozzle rings for variable geometry turbines comprise: a generally annular wall; an inner flange; an outer flange; and two protrusions. Inner flange is generally perpendicular to the generally annular wall, from which a radially inner edge extends. Outer flange is generally perpendicular to the generally annular wall and extends from a radially outer edge of the generally annular wall. The two protrusions extend from one of the inner or outer flange towards the other one of the inner or outer flange. At least one of the two protrusions extends only partially towards the other one of the inner or outer flange. The two protrusions define a first gap therebetween. Generally annular wall and the two protrusions define a second gap therebetween to receive a support arcuate head portion during use. First gap receives a support intermediate portion. The nozzle rings may be suitable for use in variable geometry turbochargers.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F02B 37/24 - Commande des pompes en utilisant des pompes ou des turbines à aubes distributrices réglables
There is disclosed a turbine housing for a turbomachine. The turbine housing comprises a volute which extends around an axis and defines at least part of a flow passage through the turbine housing. The flow passage extends from a first inlet opening. The turbine housing further comprises a flange that surrounds the first inlet opening, and an external surface that defines a rib. The rib defines a first portion that adjoins the flange, and a second portion that is angled with respect to the first portion.
There is provided a turbine housing comprising a housing dividing wall circumferentially extending around a central axis of the turbine housing. The housing dividing wall axially separates a first inlet volute and a second inlet volute. The housing dividing wall comprises a circumferentially extending tip configured to receive a nozzle ring. The tip is shaped to impart a tortuous geometry upon a leakage passage defined between the first inlet volute and the second inlet volute.
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
A nozzle ring (312) for a variable geometry turbine comprises: a generally annular wall (18); an inner flange (19); an outer flange (20); and two protrusions (330, 332). The inner and outer flanges are generally perpendicular to the generally annular wall and extend from a radially inner and outer edge of the generally annular wall. The two protrusions extend from one of the inner or outer flange towards the other one of the inner or outer flange. At least one of the two protrusions extends only partially towards the other one of the inner or outer flange. The two protrusions define a first gap (136) therebetween. The generally annular wall and the two protrusions define a second gap (338) between the generally annular wall and both of the two protrusions. In some embodiments, the two protrusions are such that the first gap is tapered so that a dimension of the gap is smaller at a distal end of the protrusions and larger proximate to the inner or outer flange from which the two protrusions extend. In some embodiments, a radial extent of the second gap is less than a radial extent of the two protrusions. In use, the second gap receives an arcuate head portion (48) of a support (124) and the first gap receives an intermediate portion (56) of the support. The nozzle ring may be suitable for use in a variable geometry turbocharger.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02B 37/22 - Commande des pompes en modifiant la section des conduits d'échappement ou des conduits d'air
F02B 37/24 - Commande des pompes en utilisant des pompes ou des turbines à aubes distributrices réglables
30.
ELECTRODE ASSEMBLY AND ELECTROCHEMICAL MACHINING METHOD
An electrode assembly for electrochemically machining a cavity of a component is disclosed. The electrode assembly comprises: an electrode, a mounting body, and an urging means. The electrode comprises a plurality of conductive elements, including an outermost conductive element. The mounting body is coupled to the electrode and engageable with the component to align the electrode within the cavity. The urging means is configured to transition the electrode from a movable configuration to a conforming configuration. In the movable configuration the conductive elements are moveable relative to one another. In the conforming configuration adjacent conductive elements align to define a substantially continuous outer electrode surface.
There is disclosed a method of electro-chemically machining a cavity of a component using a flexible electrode. The flexible electrode comprises: a flexible core; a conductive body electrically coupled to the core; and a non-conductive body. The method comprises: inserting the flexible electrode through an opening and along the cavity, the non-conductive body engaging an internal wall of the cavity; and applying a negative charge to the flexible electrode, and providing a flow of electrolyte through the cavity to remove material from the internal wall.
A turbine assembly comprising a housing comprising first and second volutes which define a respective first and second flow passage. A circumferential outlet portion of each volute is defined by first and second tongues. The housing further comprises a first aperture in which a vane assembly is received. The vane assembly comprises a plurality of vanes circumferentially distributed about a turbine wheel-receiving bore, each vane comprising a leading edge and a trailing edge. Each vane has a fixed orientation. The vanes comprise a first vane and a second vane. The first vane having its leading edge disposed in closest proximity to a tip of the first tongue. The second vane having its leading edge disposed in closest proximity to a tip of the second tongue. The leading edge of each vane at least partly overlaps the tip of the proximate tongue circumferentially.
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02B 37/02 - Passages pour les gaz entre l'orifice d'échappement du moteur et l'entraînement de la pompe, p. ex. réservoirs
F02B 37/24 - Commande des pompes en utilisant des pompes ou des turbines à aubes distributrices réglables
A compressor cover for a turbomachine is disclosed. The compressor cover defines a central axis. The compressor cover comprises an inlet. The inlet is in fluid communication with a downstream outlet via a passage. The passage is at least partly defined between a first wall and a second wall of the compressor cover. One or more vanes extend across the passage, between the first and second walls. The one or more vanes are integrally formed with the first and second walls.
There is disclosed a method of operating an exhaust system for an internal combustion engine. The exhaust system comprises: a turbine, a dosing module, which is configured to deliver an aftertreatment fluid to the exhaust gas at a position downstream of the turbine wheel, and at least one of a variable geometry mechanism configured to control the flow of exhaust gas delivered to the turbine wheel and a bypass control valve configured to bypass a portion of the exhaust gas. The method comprises: determining a current property of the exhaust gas at a position downstream of the turbine wheel; determining a difference between the current property of the exhaust gas at the position downstream of the turbine wheel and a reference property of the exhaust gas at the position downstream of the turbine wheel; andin response to the difference, adjusting the at least one of the variable geometry mechanism and the bypass control valve.
F02D 41/00 - Commande électrique de l'alimentation en mélange combustible ou en ses constituants
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F02D 41/02 - Dispositions de circuits pour produire des signaux de commande
A vane arrangement for a compressor is disclosed. The vane arrangement comprises a generally annular vane deck and at least one vane. The generally annular vane deck extends at least partway around a longitudinal axis, defining a deck thickness b in the axial direction. The at least one vane projects from a first surface of the vane deck. The at least one vane comprises a leading edge, a trailing edge, and first and second pressure surfaces. The leading edge is proximate the longitudinal axis. The trailing edge is distal the longitudinal axis. The first and second pressure surfaces extend between the leading edge and the trailing edge. The at least one vane defines a neck thickness t, proximate the leading edge, in a plane normal to the longitudinal axis, wherein t/b≥about 0.21.
A turbine dosing sealing arrangement is disclosed. The sealing arrangement comprises a sealing member and a conduit. The sealing member is configured to engage a turbine housing element at an interface. The conduit projects from the sealing member, the conduit defining at least part of a reductant fluid pathway across the interface.
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
An adapter element for a turbine is disclosed. The adapter element defines a longitudinal axis and comprises a first connection portion, a second connection portion, an outer wall and a dosing structure. The first connection portion is configured to engage the turbine. The second connection portion is configured to engage a conduit. The outer wall extends between the first and second connection portions, the outer wall defining an inner surface and an outer surface. The dosing structure is configured to receive, and expel, reductant.
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
B33Y 50/00 - Acquisition ou traitement de données pour la fabrication additive
B33Y 80/00 - Produits obtenus par fabrication additive
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
38.
TURBINE HOUSINGS FOR A TURBOCHARGER, TURBINE AND TURBOCHARGER
There is disclosed a turbine housing (2) for a turbocharger. The turbine housing comprises a flange (4) and a volute 6. The flange (4) has an engagement surface (14) and a first inlet opening (12) in the engagement surface (14). The volute (6) extends around an axis (22) and defines at least part of a flow passage (24) through the turbine housing (2). The flow passage (24) extends from the first inlet opening (12) at a first end of the flow passage (24). The engagement surface (14) of the flange (4) is defined by a periphery of material 18 which extends around the first inlet opening 12 between the first inlet opening (12) and an outer edge 16 of the engagement surface (14). A thickness (64) of a first portion (26) of the periphery of material (18), at a radially inner side (27) of the first inlet opening (12), is greater than a thickness (66) of a second portion (28) of the periphery, at a radially outer side (29) of the first inlet opening (12), along at least a full extent of a radially inner edge (34) of the first inlet opening (12). There are also disclosed a turbine and a turbocharger.
A butterfly valve assembly for an engine arrangement is disclosed. The butterfly valve assembly comprise a valve housing and a valve member. The valve housing defines at least part of a conduit. The valve member is disposed within the conduit and rotatable about an axis between an open configuration, in which fluid flow is permitted through the conduit across the valve member, and a closed configuration, in which the valve member seals the conduit. The valve member is rotatable in a first direction from the open configuration to the closed configuration. The valve member comprises a blocking surface, a secondary surface and a peripheral surface. The blocking surface extends across the conduit, in the closed configuration, to seal the conduit. The secondary surface generally opposes the blocking surface. The peripheral surface extends between the blocking surface and the secondary surface and defines a thickness of the valve member. A first end portion of the peripheral surface extends around the axis at a first end of the valve member. A clearance is defined between the conduit and a vertex of the first end portion closest to the conduit. The clearance is at a minimum, as the valve member pivots from the open configuration to the closed configuration, when the valve member is in the closed configuration.
F02D 9/10 - Obturateurs d'étranglement spécialement adaptés à cet effetAménagements de ces obturateurs sur les conduits comportant des volets pivotants
F16K 1/22 - Soupapes ou clapets, c.-à-d. dispositifs obturateurs dont l'élément de fermeture possède au moins une composante du mouvement d'ouverture ou de fermeture perpendiculaire à la surface d'obturation à éléments de fermeture articulés à pivot comportant disque ou volet pivotant dont l'axe de rotation traverse le corps de soupape, p. ex. régulateurs à papillon
F16K 1/226 - Forme ou disposition du joint d'étanchéité
F02D 9/04 - Commande des moteurs par étranglement des conduits d'amenée de l'air ou du mélange air-combustible ou par étranglement des conduits d'échappement par étranglement des conduits d'échappement
F02M 26/70 - Soupapes à clapetValves rotativesSoupapes à coulisseSoupapes souples
A turbine comprising a wastegate chamber (28); a turbine housing (12) defining a turbine inlet (14), the turbine housing (12) comprising: a wastegate inlet passageway (30) defining a flow path between the turbine inlet (14) and the wastegate chamber (28), wherein the wastegate inlet passageway (30) comprises a turbine port (38) proximal the turbine inlet (14) and a non-circular valve port (36) proximal the wastegate chamber (28), and a raised rim (52) surrounding the non-circular valve port (36) and conformal to the shape of the non-circular valve port (36), wherein the raised rim comprises a first sealing surface (52); and a valve member (42) comprising a second sealing surface (50), wherein the valve member (42) is moveable between a closed position in which the second sealing surface (50) forms a seal with the first sealing surface (54) to prevent fluid flow along the flow path and an open position in which the second sealing surface (50) is spaced apart from the first sealing surface (54) to permit fluid flow along the flow path.
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F16K 1/20 - Soupapes ou clapets, c.-à-d. dispositifs obturateurs dont l'élément de fermeture possède au moins une composante du mouvement d'ouverture ou de fermeture perpendiculaire à la surface d'obturation à éléments de fermeture articulés à pivot comportant disque ou volet pivotant dont l'axe de rotation est disposé à l'extérieur du corps de soupape
A mounting body for electrochemically machining a cavity of a component is disclosed. The mounting body comprises: an engagement face, at least part of an electrode and a plurality of electrode channels. The engagement face is engageable with the component to align the mounting body with the component. The at least part of an electrode is coupled to the mounting body. The plurality of electrolyte channels extend at least partway through the mounting body. Downstream ends of the plurality of electrolyte channels are distributed around the at least part of an electrode.
There is a provided an exhaust gas conduit for an exhaust system of an internal combustion engine. The exhaust gas conduit includes a main passage for a main flow of exhaust gases passing through the exhaust gas conduit, a chamber configured to receive an aliquot of exhaust gases separated from the main flow of exhaust gases. A mounting point is provided in the chamber for mounting an exhaust gas sensor. The chamber being configured to modify the velocity and/or the pressure of exhaust gases passing therethrough.
F02B 77/08 - Dispositifs de sécurité, d'indication ou de surveillance
F01N 11/00 - Dispositifs de surveillance ou de diagnostic pour les appareils de traitement des gaz d'échappement
F01N 13/00 - Silencieux ou dispositifs d'échappement caractérisés par les aspects de structure
G01M 15/10 - Test des moteurs à combustion interne par contrôle des gaz d'échappement
G01N 1/22 - Dispositifs pour prélever des échantillons à l'état gazeux
G01N 33/00 - Recherche ou analyse des matériaux par des méthodes spécifiques non couvertes par les groupes
F02B 39/00 - Parties constitutives, détails ou accessoires non couverts par les groupes , et relatifs aux pompes d'alimentation ou de balayage entraînées
There is provided a turbine for a turbocharger, comprising: a turbine inlet passage configured to receive exhaust gas from an internal combustion engine, the exhaust gas received by the turbine inlet passage defining a turbine bulk flow; a turbine wheel chamber configured to receive the turbine bulk flow from the turbine inlet passage, the turbine wheel chamber configured to contain a turbine wheel supported for rotation about a turbine axis; a turbine outlet passage configured to receive the turbine bulk flow from the turbine wheel chamber; a dosing module configured to deliver a spray of aftertreatment fluid into a spray region of the turbine outlet passage through which the turbine bulk flow passes; and an auxiliary passage configured to receive a portion of the turbine bulk flow, the portion of the turbine bulk flow received by the auxiliary passage defining an auxiliary flow; wherein the auxiliary passage is configured to direct the auxiliary flow into the spray region of the turbine outlet passage.
There is provided a turbine for a turbocharger, the turbine comprising: a turbine inlet passage (510) configured to receive exhaust gas from an internal combustion engine, the exhaust gas received by the turbine inlet passage defining a turbine bulk flow (511); a turbine wheel chamber (512) configured to receive the turbine bulk flow from the turbine inlet passage, the turbine wheel chamber configured to contain a turbine wheel (504) supported for rotation about a turbine axis; a turbine outlet passage (514) configured to receive the turbine bulk flow from the turbine wheel chamber; and an auxiliary passage (522) configured to receive a portion of the turbine bulk flow from a first position of the turbine upstream of the turbine outlet passage, the portion of the turbine bulk flow received by the auxiliary passage defining an auxiliary flow, the auxiliary passage further configured to deliver the auxiliary flow to the turbine bulk flow at a second position of the turbine downstream of the turbine wheel chamber; wherein the turbine is configured such that the auxiliary flow is always permitted to flow from the first position of the turbine to the second position of the turbine.
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
There is disclosed a turbine dosing system for a turbocharger. The turbine dosing system comprises a turbine inlet passage (112), a turbine wheel chamber and a turbine outlet passage (116). The turbine inlet passage is configured to receive exhaust gas from an internal combustion engine. The turbine wheel chamber is configured to receive exhaust gas from the turbine inlet passage. The turbine wheel chamber contains a turbine wheel supported for rotation about a turbine wheel axis. The turbine wheel comprises an exducer defining an exducer diameter. The turbine outlet passage is downstream of the turbine wheel chamber and is configured to receive exhaust gas from the turbine wheel chamber. The turbine outlet passage is at least partly defined by a structure which comprises a dosing module mount (122) configured to receive a dosing module (32). The turbine outlet passage defines a flow axis which extends from a downstream end of the turbine wheel. The dosing module mount is located within around 10 exducer diameters, along the flow axis, downstream of the downstream end of the turbine wheel.
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
46.
TURBINE DOSING SYSTEM FOR DOSING INTO REGIONS OF DESIRABLE FLOW PROPERTIES
There is disclosed a turbine dosing system for a turbocharger. The turbine dosing system comprises a turbine inlet passage, a turbine wheel chamber, a turbine outelte passage and a plurality of dosing modules. The turbine inlet passage is configured to receive exhaust gas from an internal combustion engine. The turbine wheel chamber configured to receive exhaust gas from the turbine inlet passage. The turbine wheel chamber contains a turbine wheel supported for rotation about a turbine wheel axis. The turbine wheel comprises an exducer which defines an exducer diameter. The turbine outlet passage is downstream of the turbine wheel chamber and is configured to receive exhaust gas from the turbine wheel chamber. The turbine outlet passage defines a flow axis which extends from a downstream end of the turbine wheel. The plurality of dosing modules are configured to inject aftertreatment fluid into exhaust gas in the turbine outlet passage.
M&C PM359732GB 386 69050154-1 ABSTRACT: There is provided a turbine for a turbocharger, comprising: a turbine inlet passage configured to receive exhaust gas from an internal combustion engine, the exhaust gas received by the turbine inlet passage defining a turbine bulk flow; a turbine wheel chamber configured to receive the turbine bulk flow from the turbine inlet passage, the 5 turbine wheel chamber configured to contain a turbine wheel supported for rotation; a turbine outlet passage configured to receive the turbine bulk flow from the turbine wheel chamber, the turbine outlet passage being at least partially defined by a turbine outlet passage surface and defining a centreline; an auxiliary passage configured to receive a portion of the turbine bulk flow, the portion of the turbine bulk flow received by 10 the auxiliary passage defining an auxiliary flow; and a dosing module configured to deliver a spray of aftertreatment fluid into the turbine outlet passage; wherein the auxiliary passage is configured to direct the auxiliary flow along the turbine outlet passage surface in an auxiliary flow layer. 15 [Figure 33]
There is provided an assembly for a turbocharger, the assembly comprising a turbine housing and a nozzle ring, wherein one of the turbine housing and the nozzle ring comprises a tongue and the other of the turbine housing and the nozzle ring comprises a corresponding slot, the tongue and slot being configured to engage and prevent relative rotation of the turbine housing and the nozzle ring. Also provided is a method of manufacturing a turbine housing, assembly for use in a turbocharger, or a turbocharger.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
There is provided a nozzle ring for a turbine of a turbocharger. The nozzle ring comprises: a nozzle dividing wall, at least on nozzle vane, and a circumferentially extending outer rim. The nozzle dividing wall extends generally perpendicular to a longitudinal axis of the nozzle ring. The at least one nozzle vane extends from the nozzle dividing wall and has a leading edge defining a first radius relative to the longitudinal axis. The circumferentially extending outer rim defines a second radius relative to the longitudinal axis. The ratio of the second radius to the first radius is at least around 1.05.
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
There is provided a centrifugal impeller for a compressor of a turbocharger. The impeller comprises a hub and a blade. The hub extends along an impeller axis. The blade extends from the hub. The blade defines a pressure surface and a suction surface. The pressure surface comprises a concave portion.
F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
Variable geometry turbines having a turbine housing with an inlet and an outlet, a turbine wheel rotatably mounted between the inlet and the outlet, a movable wall member having an inlet passageway between the inlet of the turbine housing and the turbine wheel, and a plurality of vanes circumferentially spaced and extending across the inlet passageway, the plurality of vanes having a specified shape. Methods for designing configurations of vanes for variable geometry turbines.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
53.
CENTRIFUGAL COMPRESSOR IMPELLER WITH A PARTICULAR BLADE TIP SHAPE
An impeller element for a compressor is formed with an upstream region in which the radial extent of each impeller blade decreases in the downstream axial direction. At positions axially in register with this region, the radial position of the shroud surface is constant or increasing in the downstream axial direction, so the spacing between the free edge of the blade and the shroud surface increases in the downstream axial direction. This is found to lead to surprising increases in the efficiency of the compressor, particularly for low rotational speeds.
F04D 29/16 - Joints d'étanchéité entre le côté du refoulement et celui de l'aspiration
F04D 29/42 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes radiales ou hélicocentrifuges
F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
A nozzle ring for a variable geometry turbine comprises: a generally annular wall; an inner flange; an outer flange; and two protrusions. The inner flange is generally perpendicular to the generally annular wall and extends from a radially inner edge of the generally annular wall. The outer flange is generally perpendicular to the generally annular wall and extends from a radially outer edge of the generally annular wall. The two protrusions extend from one of the inner or outer flange towards the other one of the inner or outer flange. At least one of the two protrusions extends only partially towards the other one of the inner or outer flange. The two protrusions define a first gap therebetween. The generally annular wall and the two protrusions define a second gap between the generally annular wall and both of the two protrusions. In use, the second gap receives an arcuate head portion of a support and the first gap receives in intermediate portion of the support. The nozzle ring may be suitable for use in a variable geometry turbocharger.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
A pin member is proposed for a turbo-machine having a shroud arranged to rotate within a turbine housing. The pin member is configured to limit this rotation. It is a one-piece element comprising a cylindrical body and a limit surface for opposing motion of the shroud.
A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extend from a nozzle ring though slots in a shroud. The nozzle ring has a radially-inner corner which is a gentler curve than in a conventional system, and this is found to lead to improved efficiency of the turbine.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
57.
ELECTRODE ASSEMBLY AND ELECTROCHEMICAL MACHINING METHOD
An electrode assembly for electrochemically machining a cavity of a component is disclosed. The electrode assembly comprises: an electrode, a mounting body, and an urging means. The electrode comprises a plurality of conductive elements, including an outermost conductive element. The mounting body is coupled to the electrode and engageable with the component to align the electrode within the cavity. The urging means is configured to transition the electrode from a movable configuration to a conforming configuration. In the movable configuration the conductive elements are moveable relative to one another. In the conforming configuration adjacent conductive elements align to define a substantially continuous outer electrode surface.
There is disclosed a method of electro-chemically machining a cavity of a component using a flexible electrode. The flexible electrode comprises: a flexible core; a conductive body electrically coupled to the core; and a non-conductive body. The method comprises: inserting the flexible electrode through an opening and along the cavity, the non-conductive body engaging an internal wall of the cavity; and applying a negative charge to the flexible electrode, and providing a flow of electrolyte through the cavity to remove material from the internal wall.
A seal system for a bearing chamber of a turbomachine includes a baffle element encircling the axis of the machine. The baffle element is formed with front surface including a plurality of gutter surfaces which are angularly spaced about the rotational axis. The seal system can thus be mounted in any one of a plurality of orientations with respect to the direction of gravity, such that in any of the orientations one of the gutter surfaces is directed downwardly.
A variable geometry turbine comprising: a wheel supported for rotation about an axis; a housing comprising a first volute for receiving gas from a first source and a second volute for receiving gas from a second source; the first and second volutes being separated by a dividing wall; and an inlet passageway surrounding the wheel and fluidly connected to the volutes; the inlet passageway at least partially defined between a first wall and an opposite second wall, the first wall being moveable along the axis to vary the size of the inlet passageway; wherein a tip of the dividing wall defines a first radius relative to the axis, and a radially outermost part of the first wall positioned within the inlet passageway defines a second radius relative to the axis, and wherein the first radius is at least around 1% larger than the second radius.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
There is disclosed a bearing housing for a turbocharger. The bearing housing comprises a body and a mounting flange. The body is configured to receive one or more bearings. The one or more bearings are configured to support rotation of a shaft about an axis. The mounting flange extends around the body. The mounting flange comprises a plurality of bores, a first face and a plurality of cavities. The plurality of bores configured to receive a fastener therethrough. The first face is configured to engage a corresponding mounting flange of a turbine housing. The plurality of cavities are in communication with the plurality of bores. The plurality of cavities are axially recessed relative to the first face.
A turbine assembly comprising a housing comprising first and second volutes which define a respective first and second flow passage. A circumferential outlet portion of each volute is defined by first and second tongues. The housing further comprises a first aperture in which a vane assembly is received. The vane assembly comprises a plurality of vanes circumferentially distributed about a turbine wheel-receiving bore, each vane comprising a leading edge and a trailing edge. Each vane has a fixed orientation. The vanes comprise a first vane and a second vane. The first vane having its leading edge disposed in closest proximity to a tip of the first tongue. The second vane having its leading edge disposed in closest proximity to a tip of the second tongue. The leading edge of each vane at least partly overlaps the tip of the proximate tongue circumferentially.
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02B 37/02 - Passages pour les gaz entre l'orifice d'échappement du moteur et l'entraînement de la pompe, p. ex. réservoirs
F02B 37/24 - Commande des pompes en utilisant des pompes ou des turbines à aubes distributrices réglables
A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F02B 37/22 - Commande des pompes en modifiant la section des conduits d'échappement ou des conduits d'air
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
There is disclosed a bush comprising an internal surface and an external surface. The internal surface defines a bore and is configured to support movement of a body received in the bore. The external surface defines an outer radius. The external surface comprises one or more recesses.
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
A turbine dosing sealing arrangement is disclosed. The sealing arrangement comprises a sealing member and a conduit. The sealing member is configured to engage a turbine housing element at an interface. The conduit projects from the sealing member, the conduit defining at least part of a reductant fluid pathway across the interface.
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
B01F 23/213 - Mélange de gaz avec des liquides par l’ajout de liquides dans les milieux gazeux par pulvérisation ou atomisation des liquides
B01F 25/74 - Mélangeurs à pulvérisation, p. ex. pour mélanger des feuilles de matière entrecroisées avec des pièces rotatives, p. ex. des disques
F02B 37/00 - Moteurs caractérisés par l'utilisation de pompes entraînées au moins temporairement par les gaz d'échappement
F02B 39/00 - Parties constitutives, détails ou accessoires non couverts par les groupes , et relatifs aux pompes d'alimentation ou de balayage entraînées
An adapter element for a turbine is disclosed. The adapter element defines a longitudinal axis and comprises a first connection portion, a second connection portion, an outer wall and a dosing structure. The first connection portion is configured to engage the turbine. The second connection portion is configured to engage a conduit. The outer wall extends between the first and second connection portions, the outer wall defining an inner surface and an outer surface. The dosing structure is configured to receive, and expel, reductant.
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
A diffuser for a turbine is disclosed. The diffuser comprises an inlet, an outlet, a diffuser wall and a reductant barrier. The inlet has a first cross-sectional area and is configured to receive fluid. The outlet is in fluid communication with the inlet, and has a second cross-sectional area, the second cross-sectional area being larger than the first cross- sectional area. The outlet is spaced apart from the inlet. The diffuser wall extends between the inlet and the outlet, and defines an inner surface and an opposing outer surface. The reductant barrier extends, at least in part, from the outer surface of the diffuser wall. The reductant barrier defines a blocking face impermeable to the passage of liquids.
F01N 13/18 - Structure facilitant la fabrication, l'assemblage ou le démontage
F02B 37/00 - Moteurs caractérisés par l'utilisation de pompes entraînées au moins temporairement par les gaz d'échappement
F02B 39/00 - Parties constitutives, détails ou accessoires non couverts par les groupes , et relatifs aux pompes d'alimentation ou de balayage entraînées
A valve system comprising a valve chamber at a junction of an inlet port, an outlet port and a bypass port, the inlet port configured for fluid communication with exhaust gas, the outlet port configured for fluid communication with an inlet of a turbine, and the bypass port configured for fluid communication with an exhaust aftertreatment device; a rotary valve comprising a valve rotor which rotates about a valve axis within the valve chamber between a first position to permit gas flow through the bypass port and a second position to block gas flow. At least one of the valve rotor and the valve chamber comprises a protrusion and the other comprises a recess, wherein, in the first position, the protrusion and recess are spaced from one another, and, in the second position the recess receives the protrusion such that gas flow between the protrusion and recess is substantially prevented.
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
F02D 41/12 - Dispositions de circuits pour produire des signaux de commande introduisant des corrections pour des conditions particulières de fonctionnement pour la décélération
F16K 5/18 - Dispositions particulières pour tenir écartées les faces d'obturation ou pour les presser l'une contre l'autre dans le cas des boisseaux à surface cylindrique
F16K 5/20 - Dispositions particulières pour tenir écartées les faces d'obturation ou pour les presser l'une contre l'autre dans le cas des boisseaux à surface sphérique
F16K 11/085 - Soupapes ou clapets à voies multiples, p. ex. clapets mélangeursRaccords de tuyauteries comportant de tels clapets ou soupapesAménagement d'obturateurs et de voies d'écoulement spécialement conçu pour mélanger les fluides dont toutes les faces d'obturation se déplacent comme un tout comportant uniquement des robinets à boisseau à noix cylindrique
There is provided a seal assembly comprising: a first component and a second component spaced apart from the first component so as to define a passage for the transfer of fluid from an inlet of the seal assembly to an outlet of the seal assembly, wherein the first component comprises a concavity at least partially defining the passage, and wherein no part of the second component extends into the portion of the passage bounded by the concavity.
F16K 5/04 - Robinets à boisseau consistant seulement en un dispositif obturateur dont au moins une des faces d'obturation a la forme d'une surface de solide de révolution plus ou moins complète, le mouvement d'ouverture et de fermeture étant essentiellement rotatif dont les boisseaux sont à surface cylindriqueLeurs garnitures d'étanchéité
A vane arrangement for a compressor is disclosed. The vane arrangement comprises a generally annular vane deck and at least one vane. The generally annular vane deck extends at least partway around a longitudinal axis, defining a deck thickness b in the axial direction. The at least one vane projects from a first surface of the vane deck. The at least one vane comprises a leading edge, a trailing edge, and first and second pressure surfaces. The leading edge is proximate the longitudinal axis. The trailing edge is distal the longitudinal axis. The first and second pressure surfaces extend between the leading edge and the trailing edge. The at least one vane defines a neck thickness t, proximate the leading edge, in a plane normal to the longitudinal axis, wherein t/b≥ about 0.21.
A compressor cover for a turbomachine is disclosed. The compressor cover defines a central axis. The compressor cover comprises an inlet. The inlet is in fluid communication with a downstream outlet via a passage. The passage is at least partly defined between a first wall and a second wall of the compressor cover. One or more vanes extend across the passage, between the first and second walls. The one or more vanes are integrally formed with the first and second walls.
A vane arrangement for a compressor is disclosed. The vane arrangement comprises a generally annular vane deck and at least one vane. The generally annular vane deck extends at least partway around a longitudinal axis, defining a deck thickness b in the axial direction. The at least one vane projects from a first surface of the vane deck. The at least one vane comprises a leading edge, a trailing edge, and first and second pressure surfaces. The leading edge is proximate the longitudinal axis. The trailing edge is distal the longitudinal axis. The first and second pressure surfaces extend between the leading edge and the trailing edge. The at least one vane defines a neck thickness t, proximate the leading edge, in a plane normal to the longitudinal axis, wherein t/b≥ about 0.27.
A seal system for a bearing chamber (22) of a turbomachine includes the baffle element (70) encircling the axis (25) of the machine. The baffle element is formed with front surface including both a recess (73) which defines a circumferentially-extending oil-receiving channel (74), and an oil-deflecting surface (78) on a gutter (77). The channel decreases in cross-sectional area close to the oil-deflecting surface, and a circular line which is within the channel distant from the gutter, intersects with the oil-deflection surface. This forces the oil to change direction at the gutter, and urges the oil radially outward. Thus, a high rotational velocity of the body of oil may be maintained, whilst improving the drainage efficiency of the seal system at the gutter.
A two-part wastegate valve member assembly comprises a support member and a valve member. The support member defines an aperture. The valve member comprises a central portion extending through the aperture and two opposed end portions disposed on opposite sides of the aperture. Each of the two end portions has dimensions such that the valve member is held captive by the support member. The central portion and two opposed end portions of the valve member are integrally formed. A method for forming the two-part wastegate valve member assembly comprises casting a single manufacturing intermediate and subsequently processing the manufacturing intermediate so as to form the two-part assembly.
B23P 15/00 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
There is provided an assembly for a turbocharger, the assembly comprising a turbine housing (7) and a nozzle ring (1), wherein one of the turbine housing (7) and the nozzle ring (1) comprises a tongue (6) and the other of the turbine housing (7) and the nozzle ring (1) comprises a corresponding slot (4), the tongue (6) and slot (4) being configured to engage and prevent relative rotation of the turbine housing (7) and the nozzle ring (1). Also provided is a method of manufacturing a turbine housing, assembly for use in a turbocharger, or a turbocharger.
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
A rotary turbine bypass valve comprises a valve chamber and a valve rotor. The chamber is positioned at a junction of an inlet port, an outlet port and a bypass port. The inlet port is configured to receive exhaust gas, the outlet port is configured to fluidly communicate with a turbine inlet, and the bypass port is configured to fluidly communicate with an exhaust aftertreatment device.
The rotor comprises a first and second recess, the first recess defining a primary flow passage, the second recess defining a secondary flow passage. The rotor is rotatable between a first position in which the rotor substantially blocks exhaust gas flow through the bypass port and a second position in which the rotor permits such. The secondary flow passage is configured to selectively permit fluid communication between the inlet port and the bypass port when the primary flow passage is partially blocked.
F16K 11/076 - Soupapes ou clapets à voies multiples, p. ex. clapets mélangeursRaccords de tuyauteries comportant de tels clapets ou soupapesAménagement d'obturateurs et de voies d'écoulement spécialement conçu pour mélanger les fluides dont toutes les faces d'obturation se déplacent comme un tout comportant uniquement des tiroirs à éléments de fermeture articulés à pivot à faces d'obturation épousant la surface d'un solide de révolution
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F02D 35/00 - Commande non électrique des moteurs en fonction des conditions extérieures ou intérieures aux moteurs, non prévue ailleurs
F02B 37/22 - Commande des pompes en modifiant la section des conduits d'échappement ou des conduits d'air
F02D 9/16 - Obturateurs d'étranglement spécialement adaptés à cet effetAménagements de ces obturateurs sur les conduits comportant des éléments d'obturateurs glissantsObturateurs d'étranglement spécialement adaptés à cet effetAménagements de ces obturateurs sur les conduits comportant des éléments d'obturateurs se déplaçant le long du conduit les éléments étant rotatifs
F01N 3/021 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour refroidir ou pour enlever les constituants solides des gaz d'échappement au moyen de filtres
F01N 3/10 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opérationCommande spécialement adaptés à la conversion catalytique
A seal assembly for use in a turbomachine, the seal assembly comprising an oil seal plate; a rotatable component which defines a central axis and is received in a central aperture of the oil seal plate; and an annular seal which comprises a base and a sealing portion, the base being held by the rotatable component; wherein the sealing portion is configured to form a seal with the oil seal plate when the rotatable component and annular seal are rotating below a predetermined rotational speed; and wherein the sealing portion is configured to move radially outwards with respect to the central axis such that the sealing portion loses contact with the oil seal plate when the rotatable component and annular seal are rotating above the predetermined rotational speed.
A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02B 37/22 - Commande des pompes en modifiant la section des conduits d'échappement ou des conduits d'air
80.
Turbine wastegate having a fluidic sealing arrangement and a method of testing thereof
A turbine comprising: a turbine housing, a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state in which a first gas may pass between a turbine inlet a turbine outlet via the wastegate passage and a closed state in which the valve member substantially prevents said first gas from passing between the turbine inlet and the turbine outlet. The valve member is mounted to an actuation member that passes through a bore of the turbine housing. The actuation member is movable to move the wastegate valve between the open and closed states. The turbine comprises a fluid conduit configured to deliver a second gas to the bore to form a fluidic seal between the bore and the actuation member to substantially prevent the passage of said first gas along the bore.
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F01D 11/02 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages par obturation non contact, p. ex. du type labyrinthe
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F02C 7/28 - Agencement des dispositifs d'étanchéité
F16J 15/34 - Joints d'étanchéité entre deux surfaces mobiles l'une par rapport à l'autre par bague glissante pressée contre la face plus ou moins radiale d'une des deux parties
G01M 3/26 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par mesure du taux de perte ou de gain d'un fluide, p. ex. avec des dispositifs réagissant à la pression, avec des indicateurs de débit
81.
INTERNAL COMBUSTION ENGINE SYSTEM WITH EXHAUST GAS FLOW CONTROL
An engine system comprises an internal combustion engine (34), a turbocharger (30) and an exhaust gas recirculation system (EGR), wherein the cylinders (35a-35f) of the engine (34) are partitioned into two sets. A first set (81) of cylinders is used to provide both EGR and a first exhaust gas flow (path 42) as a first input to a turbine (29) of the turbocharger. The other set (82) of cylinders, comprising fewer cylinders than the first set, is used to provide a second exhaust gas flow (path 43) as a second input to the turbine. A controllable valve is provided in a flow housing (107) between the gas flows to selectively permit exhaust gas to be transferred between them, to control the degree of asymmetry of the flow areas, thereby controlling the backpressures and in turn controlling the ratio of the first and second exhaust gas flows. At least part of the inlet of the turbine (29) may be symmetrical with respect to the two gas flows.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01N 13/00 - Silencieux ou dispositifs d'échappement caractérisés par les aspects de structure
F02B 37/00 - Moteurs caractérisés par l'utilisation de pompes entraînées au moins temporairement par les gaz d'échappement
F02M 26/02 - Systèmes RGE spécialement adaptés pour les moteurs suralimentés
Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The vanes are formed with a leading portion which is arranged to contact a leading portion of a corresponding slot, and a trailing portion which is shaped, when the leading portion of the vane and slot are together, to be spaced from a corresponding trailing portion of the slot with a substantially constant spacing at room temperature. The contact may be a point contact, e.g. close to the leading edge of the vane. Alternatively, the vane may include a leading surface portion which conforms closely with the shape of a corresponding leading surface portion of one of the slots.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
A pin member is proposed for a turbo-machine having a shroud arranged to rotate within a turbine housing. The pin member is configured to limit this rotation. It is a one- piece element comprising a cylindrical body and a limit surface for opposing motion of the shroud.
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
There is provided a diffuser for a turbine, comprising: a support configured to mount to a turbine housing; a diffuser body configured to receive fluid from an outlet of the turbine, the diffuser body defining a longitudinal axis and having a perimeter with a length measured in a plane normal to the longitudinal axis; and a bridge configured to connect the support to the diffuser body, wherein the connection between the bridge and the diffuser body is confined to a continuous portion of the perimeter of the diffuser body that is not more than around 50% of the total length of the perimeter of the diffuser body.
F04D 29/44 - Moyens de guidage du fluide, p. ex. diffuseurs
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
A turbocharger assembly (1) comprises a turbine (4), a compressor (6), a housing (8), one or more electronic components (38, 40, 41, 42, 45, 47, 50, 51, 52, 54, 58) and a pettier device (46). The pettier device (46) is configured to provide electrical power to the one or more electronic components (38, 40, 41, 42, 45, 47, 50, 51, 52, 54, 58).
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F01N 5/02 - Silencieux ou dispositifs d'échappement combinés ou associés à des dispositifs bénéficiant de l'énergie des gaz évacués les dispositifs utilisant la chaleur
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F02D 41/04 - Dispositions de circuits pour produire des signaux de commande introduisant des corrections pour des conditions particulières de fonctionnement
F02G 5/02 - Utilisation de la chaleur perdue dans les gaz d'échappement
H01L 35/30 - DISPOSITIFS À SEMI-CONDUCTEURS; DISPOSITIFS ÉLECTRIQUES À L'ÉTAT SOLIDE NON PRÉVUS AILLEURS - Détails fonctionnant exclusivement par effet Peltier ou effet Seebeck caractérisés par les moyens d'échange de chaleur à la jonction
F02D 41/24 - Commande électrique de l'alimentation en mélange combustible ou en ses constituants caractérisée par l'utilisation de moyens numériques
90.
BAFFLE ELEMENT, DIFFUSER PLATE, AND SEAL SYSTEM INCORPORATING A BAFFLE ELEMENT AND A DIFFUSER PLATE
A seal system for a bearing chamber of a turbomachine includes a baffle element (100) encircling the axis of the machine. The baffle element is formed with front surface including a plurality of gutter surfaces (110,111) which are angularly spaced about the rotational axis. The seal system can thus be mounted in any one of a plurality of orientations with respect to the direction of gravity, such that in any of said orientations one of the gutter surfaces is directed downwardly.
F02B 39/14 - Lubrification des pompesMesures de sécurité à cet effet
F02B 39/00 - Parties constitutives, détails ou accessoires non couverts par les groupes , et relatifs aux pompes d'alimentation ou de balayage entraînées
A turbine comprises a turbine housing defining a turbine inlet upstream of a turbine wheel and a turbine outlet downstream of the turbine wheel; and a wastegate valve assembly comprising at least one movable valve member mounted on a movable support member within a wastegate chamber which communicates with the turbine inlet upstream of the turbine, and has one or more chamber outlets which communicate with an outlet of the turbine. The valve member is permitted to articulate slightly about the support member, with the amount of articulation in respective directions being limited by collisions between a respective limit point on a limit area on a rear surface of a sealing portion of the valve member and a respective limit point on limit area on a front surface of the support member.
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F16C 17/02 - Paliers à contact lisse pour mouvement de rotation exclusivement pour charges radiales uniquement
There is disclosed a bearing housing for a turbocharger. The bearing housing comprises a body and a mounting flange. The body is configured to receive one or more bearings. The one or more bearings are configured to support rotation of a shaft about an axis. The mounting flange extends around the body. The mounting flange comprises a plurality of bores, a first face and a plurality of cavities. The plurality of bores configured to receive a fastener therethrough. The first face is configured to engage a corresponding mounting flange of a turbine housing. The plurality of cavities are in communication with the plurality of bores. The plurality of cavities are axially recessed relative to the first face.
A turbine wheel consists of a first shroud component and a second bladed disc component. The shroud component comprises a shroud structure, a hub structure and a spoke formed integrally therewith and extending between the shroud structure and the hub structure. The bladed disc component comprises a hub member having inner and outer rims, turbine blades disposed on the outer rim, and at least one receiving zone for receiving the spoke, said at least one receiving zone extending radially between the inner and outer rims. The shroud component and the bladed disc component are connected and thus provide the turbine wheel with a shrouded portion. A shrouded turbine wheel can therefore be conveniently assembled starting from at least two components. Further, these components have simplified geometries for easy manufacture, for example using a casting technique, while the overall mechanical performance of the turbine is preserved or improved.
F01D 1/02 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue
F01D 5/22 - Connections aube à aube, p. ex. par emboîtement
F01N 5/04 - Silencieux ou dispositifs d'échappement combinés ou associés à des dispositifs bénéficiant de l'énergie des gaz évacués les dispositifs utilisant l'énergie cinétique
A turbine assembly for a turbocharger is disclosed. The turbine assembly comprises a housing and a vane assembly. The housing defines a flow path between an inlet and an outlet, the housing extending around an axis. The housing comprises first and second volutes which define a respective first and second flow passage. A circumferential outlet portion of each of the first and second volutes is defined by first and second tongues. The housing further comprises a first aperture in which a vane assembly is received. The vane assembly comprises a plurality of vanes circumferentially distributed about a turbine wheel-receiving bore, each of the plurality of vanes comprising a leading edge and a trailing edge. Each of the plurality of vanes has a fixed orientation. The plurality of vanes comprises a first vane and a second vane. The first vane is the vane having its leading edge disposed in closest proximity to a tip of the first tongue. The second vane is the vane having its leading edge disposed in closest proximity to a tip of the second tongue. For each of the first vane and the second vane, the leading edge at least partly overlaps the tip of the proximate tongue circumferentially.
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F02B 37/02 - Passages pour les gaz entre l'orifice d'échappement du moteur et l'entraînement de la pompe, p. ex. réservoirs
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
There is provided a variable geometry turbine comprising: a turbine wheel supported for rotation about a turbine axis; a turbine housing comprising a first volute for receiving a first exhaust gas stream from a first fluid source and a second volute for receiving a second exhaust gas stream from a second fluid source; the first volute and the second volute being separated by a dividing wall; and an inlet passageway surrounding the turbine wheel and fluidly connected to the first volute and the second volute; the inlet passageway at least partially defined between a first wall member and a second wall member opposite the first wall member, the first wall member being moveable along the turbine axis to vary the size of the inlet passageway; wherein a tip of the dividing wall defines a first radius (R1) relative to the turbine axis, and a radially outermost part of the first wall member positioned within the inlet passageway defines a second radius (R2) relative to the turbine axis, and wherein the first radius (R1) is at least around 1% larger than the second radius (R2).
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 17/00 - Régulation ou commande par variation de flux
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
A turbine comprises a turbine housing defining a turbine inlet upstream of a turbine wheel and a turbine outlet downstream of the turbine wheel; and a wastegate valve assembly comprising at least one movable valve member mounted on a movable support member within a wastegate chamber which communicates with the turbine inlet upstream of the turbine, and has one or more chamber outlets which communicate with an outlet of the turbine. The valve member is permitted to articulate slightly about the support member, with the amount of articulation being limited by collisions between respective limit areas on a rear surface of a sealing portion of the valve member and a front surface of the support member. Each valve member is connected to the support member using a pin portion of the valve member which passes through a washer with a non-circular outer profile, and rotation of the washer is limited by contact surfaces of the support member.
A turbine with multiple gas inlets is designed by a process of, for a given engine, obtaining time series data characterizing the power bias of the engine, obtaining an isentropic power associated with each data point of the time series, and using the isentropic powers to obtain a design point. The turbine is then designed based on the design point, such as by optimising one or more design parameters of the turbine based on the design point.
There is disclosed a bush comprising an internal surface and an external surface. The internal surface defines a bore and is configured to support movement of a body received in the bore. The external surface defines an outer radius. The external surface comprises one or more recesses.
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
There is provided a turbine comprising: a turbine housing; a turbine wheel; an inlet upstream of the turbine wheel, the inlet defining a first inlet portion and a second inlet portion; an outlet downstream of the turbine wheel, the outlet defining a first outlet portion and a second outlet portion; and a wastegate arrangement configured to selectively vent exhaust gas from the first inlet portion to the first outlet portion via a first bypass passage, and further configured to selectively vent exhaust gas from the second inlet portion to the second outlet portion via a second bypass passage; wherein the first outlet portion and the second outlet portion are separated by a baffle of the turbine housing.
A variable geometry turbine comprising a turbine wheel (5) supported for rotation about a turbine axis (4a); an annular inlet passageway (9) surrounding the turbine wheel (5) and defined between a first radial inlet surface (10) of a first wall member (11) and a second radial inlet surface of a second wall member (12), at least one of said first and second wall members (11, 12) being moveable along the turbine axis to vary the size of the inlet passageway (9); an array of vanes (14) extending across the inlet passageway (9), said vanes (14) being connected to said first wall member (11); a plurality of cavities (13) located in the second wall member (12) or to a rear side of the second wall member, wherein the rear side of the second wall member (12) is located axially beyond the second wall member (12) with respect to the first wall member (11); an array of vane slots (25) in the second radial inlet surface, complementary to said array of vanes (14), said vane slots being configured to receive said vanes and permit the vanes to travel into said plurality of cavities (13), to accommodate relative movement between the first and second wall members (11, 12); wherein the plurality of cavities (13) comprises a first cavity (41), and a second cavity (42) separated from the first cavity by a separating portion (48).
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
