An aircraft fuel heating arrangement comprises an exhaust cone for a gas turbine engine, the exhaust cone having an outer body defining an internal cone cavity, the internal cone cavity comprising one or more conduits passing therethrough for communicating fuel through the cavity, and wherein the outer body of the exhaust cone comprises at least one inlet and at least one outlet to allow exhaust gas to pass into through and out of the exhaust cone.
The present invention relates to electrical network comprising an electrical conductor and, a cryogen source configured to hold cryogen, the cryogen source arranged so that, in use, cryogen is provided to the conductor to maintain the conductor in a hyperconductive state.
A controller arrangement for an electrical power propulsion system of an electrically powered aircraft, the controller arrangement configured to: determine a flight characteristic of the aircraft; detect a fault associated with a first sub-system of the electrical power propulsion system; determine whether the fault affects more than one sub-system of the electrical power propulsion system; and in response to determining that the fault affects more than one sub-system of the electrical power propulsion system and based on the determined flight characteristic, perform an action.
The present invention relates to a thermal management system (100) for an aircraft comprising: an air inlet (110) portion arranged to receive ambient air into the thermal management system from an external environment; an air outlet (120) portion arranged to provide fluid communication between the thermal management system and an external environment; a flow path from the air inlet portion to the air outlet portion, wherein the flow path comprises at least one turn (132); an air manipulation portion (140) arranged to provide controlled manipulation to an airflow in the flow path; a thermal exchanger (150) arranged to provide thermal energy exchange with the airflow in the flow path; wherein the air manipulation portion is arranged to provide controlled turning of the airflow in the flow path around at least one turn of the flow path.
The present invention relates to an electrical conduit for transporting cryogenic material and electrical current, the conduit comprising: a cryogenic conduit for transporting cryogenic material; a current conductor comprising a main portion and a fusible portion, wherein the current conductor is in thermal communication with the cryogenic conduit; a fusing element arranged to affect the fusible portion; a controller arrangement arranged to detect a change in condition of the electrical conduit and, in response to the detected change in condition, provide a signal to the fusing element, wherein the fusing element is arranged to actuate in response to the signal from the controller arrangement, wherein the fusible portion is arranged to structurally alter, in response to actuation of the fusing element, to prevent the flow of current through the fusible portion.
H01H 39/00 - Switching devices actuated by an explosion produced within the device and initiated by an electric current
H01H 85/00 - Protective devices in which the current flows through a part of fusible material and this current is interrupted by displacement of the fusible material when this current becomes excessive
H01H 85/10 - Fusible members characterised by the shape or form of the fusible member with constriction for localised fusing
The present invention relates to laser deposition system. The laser deposition system comprises a laser module configured to generate a laser beam (120) having one or more recesses (130) in its intensity profile, an intensity of the laser beam (122) being lower in the recesses (130) than in the remainder of the laser beam (120), and each recess (130) being at least partly surrounded by the remainder of the laser beam (120); and a wire feeding module configured to feed one or more wires (110) through the one or more recesses (130) in the laser beam profile, for deposition onto a substrate..
There is disclosed herein propulsion system (100) for an aircraft, comprising a first propulsor (102), a second propulsor (112), and an air diversion means (122). The first propulsor (102) has a first air intake (104) feeding a first air flow path (106), a first compressor (108) arranged in the first air flow path 5 (106), and a first exhaust (110). The second propulsor (112) has a second air intake (114), separate to the first air flow path (106), feeding a second air flow path (116), a second compressor (118) arranged in the second air flow path (116), and a second exhaust (120), wherein the second propulsor (112) is configured for a lower exhaust velocity than the first propulsor (102). The air 10 diversion means (122) is configured to controllably divert air (M) away from the first air intake (M1, 104) to the second air intake (M2, 114) based on the airspeed of the aircraft, such that a lower airspeed of the aircraft corresponds to more air (M) diverted by the air diversion means (122). There is further disclosed herein an aircraft comprising such a propulsion system.
A drive shaft assembly for a motor vehicle, has at least a first tripod joint having a first outer part and a first inner part having three first trunnions with first trunnion axes. A second sliding joint has a second outer part and a second inner part, and a connecting shaft which extends along an axial direction between a first end and a second end and which is connected in a torque-transmitting manner via the first end to the first tripod joint and via the second end to the second sliding joint. At least the trunnion axes of the first trunnions are inclined relative to a radial direction by a first angle of inclination which is greater than zero angular degree.
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
B60K 17/22 - Arrangement or mounting of transmissions in vehicles characterised by arrangement, location, or type of main drive shafting, e.g. cardan shaft
A tripod joint has an outer joint part having a first longitudinal axis, a cavity parallel to the first longitudinal axis and an open end. Three recesses extending parallel to the first longitudinal axis are formed in the outer joint part. An inner joint part has a second longitudinal axis, at least one central body on which three journals are formed, a roller body arranged on each of the journals and at least an outer ring and an inner ring which can be rotated relative to the latter about a common axis of rotation. When the axes are coaxial and a torque is transmitted during intended operation of the tripod joint between the journal and the inner ring via two contact points which, in a cross-section of the tripod joint running transversely to the longitudinal axes, are arranged spaced apart from one another along the radial direction.
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
A turbine rear structure for a gas turbine engine. The turbine rear structure comprises an outer shroud and an inner hub, wherein a gas flow path is defined between the shroud and the hub. The turbine rear structure further comprises a plurality of struts extending radially between the shroud and the hub, each strut intersecting with the shroud at a first end and the hub at an opposing end and at least two primary engine mounts on an outer radial side of the shroud configured to mount the turbine rear structure in an aircraft. The primary engine mounts are arranged circumferentially in between adjacent struts. The turbine rear structure further comprises a catcher mounting lug between the primary engine mounting lugs, wherein the catcher mounting lug is radially aligned with one of the plurality of struts.
A constant velocity plunging joint having an outer joint part, an inner joint part, balls which are arranged in pairs of tracks each comprising an outer ball track and an inner ball track, and a ball cage with circumferentially distributed cage windows, in each of which one of the balls is accommodated. An outer ring line through all ball centers on the outer ball tracks has an irregular shape with a largest and smallest outer ring line diameter. The inner ball tracks are produced in such a way that an inner ring line through all ball centers has an irregular shape with a largest and smallest inner ring line diameter, and wherein the inner joint part is mounted relative to the outer joint part such that an angle formed between the largest inner ring line diameter and the largest outer ring diameter is smaller than 30°.
F16D 3/227 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts the groove centre-lines of each coupling part lying on a cylinder co-axial with the respective coupling part the joints being telescopic
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
A multipod joint having an outer joint part with a first longitudinal axis and a cavity which runs parallel to the first longitudinal axis and which has an open end. At least two recesses running parallel to the first longitudinal axis are distributed along a circumferential direction, which extends around the first longitudinal axis. The joint has a joint inner part with a second longitudinal axis, comprising at least one central body on which at least two trunnions are formed with trunnion axes extending radially from the second longitudinal axis. A roller body rotatable at least about the trunnion axis is arranged on each trunnion.
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
F16D 3/202 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints
The present invention is concerned with a turbine engine component. The turbine engine component comprises a hub portion comprising a plurality of circumferentially extending sectors. Each sector is joined to a circumferentially adjacent sector by two weld lines. The weld lines comprise a first weld line on a first axial side of the hub portion and a second weld line on a second axial side of the hub portion opposite the first axial side. The first and second weld lines extend from a radially outermost side of the hub portion to a radially innermost side of the hub portion.
The present invention relates to an electrical aircraft propulsion arrangement comprising: at least one electrically operated prime mover for providing thrust for the aircraft; at least one source of electrical energy arranged to provide electrical energy to at least one electrically operated prime mover; a controller arranged to control production, storage and provision of electrical energy from the at least one source of electrical energy; a sensor arrangement arranged to provide data to the controller, the data relating to flight condition, aircraft condition, and electrical energy source condition.
The present invention relates to a power source system for an electrically powered aircraft, the system comprising: a high energy density power source arrangement for providing electrical power; a bi-directional electrical power source arrangement for providing and receiving electrical power; a busbar arranged to receive electrical power from the high energy density power source arrangement, and to receive electrical power from and provide electrical power to the bi-directional electrical power source arrangement, a controller arrangement arranged to: detect a flight characteristic of an aircraft; detect a power characteristic of the power source system; and, control a power output of the high energy density power source arrangement and the bi-directional electrical power source arrangement, wherein, the controller arrangement is further arranged, in use, to: detect a propulsive power requirement for an aircraft; detect a flight characteristic of an aircraft; detect a power characteristic of the power source system; control the power output of the high energy density power source arrangement and the bi-directional electrical power source arrangement based on the propulsive power requirement, flight characteristic of an aircraft and power characteristic of the power source system, the power output of the high energy density power source arrangement and the bi-directional electrical power source arrangement provided to the busbar.
A thermal energy transfer device is provided for use in transferring thermal energy from a coil of an electrically drivable motor, the device comprising: a plurality of thermally conductive members arranged to thermally communicate with at least one coil of an electrically drivable motor; and, a thermally conductive portion connected to the plurality of thermally conductive members, wherein each of the plurality of thermally conductive members is directly electrically insulated from any other of the plurality of thermally conductive members.
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
17.
A PROPULSION SYSTEM FOR AN AIRCRAFT AND A METHOD OF POWER MANAGEMENT SYSTEM IN AN AIRCRAFT
The present invention relates to a propulsion system for an aircraft, the system comprising: a first cryogenic fuel propulsion system; and, a second cryogenic fuel propulsion system; the first cryogenic fuel propulsion system comprising: a first cryogenic fuel source; a first propulsion source arranged to generate propulsion from a cryogenic fuel; a first flow path for transporting cryogen from the first cryogenic fuel source to the first propulsion source; the second cryogenic fuel propulsion system comprising: a second cryogenic fuel source; a second propulsion source arranged to generate propulsion from a cryogenic fuel; a second flow path for transporting cryogen from the second cryogenic fuel source to the second propulsion source; the system further comprising: a first conduit, arranged to transport fluid cryogen from the first cryogenic fuel propulsion system to the second cryogenic fuel propulsion system, a second conduit, arranged to transport fluid cryogen from the second cryogenic fuel propulsion system to the first cryogenic fuel propulsion system.
The present invention is concerned with a heat exchanging apparatus for a gas turbine engine. The heat exchanging apparatus comprises a first end, a second end, and a plurality of radially offset portions extending between the first and second ends, each portion comprising at least two radially offset rows of fluid passageways configured to transport fluid between the first end and the second end. Each portion is fixed at the first end and is axially moveable at the second end with respect to adjacent portions.
F28D 7/16 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation
F28F 9/013 - Auxiliary supports for elements for tubes or tube-assemblies
19.
FUEL MANAGEMENT SYSTEM FOR AN ELECTRICALLY POWERED AIRCRAFT AND METHOD OF CONTROLLING A FUEL MANAGEMENT SYSTEM IN AN AIRCRAFT
The present invention relates to a fuel management system for an electrically powered aircraft, the system comprising: a cryogenic fuel source; a refuel arrangement; a conduit providing fluid communication between the cryogenic fuel source and the refuel arrangement; a controller arrangement arranged to detect a stage of flight, wherein the stage of flight is at least one of: cruise; descent; landing; taxi; and, stationary, wherein the controller arrangement is arranged to provide a signal to the cryogenic fuel source to provide a cryogenic fuel into the conduit upon detection of a stage of flight having changed to a predetermined stage of flight.
The present invention relates to a propulsion system for an electrically powered aircraft, the system comprising: a first cryogenic fuel propulsion system; and, a second cryogenic fuel propulsion system; the first cryogenic fuel propulsion system comprising: a first cryogenic fuel source; a first propulsion source arranged to generate propulsion from a cryogenic fuel; a first conduit for transporting cryogen from the first cryogenic fuel source; the second cryogenic fuel propulsion system comprising a second cryogenic fuel source; a second propulsion source arranged to generate propulsion from a cryogenic fuel; a second conduit for transporting cryogen from the second cryogenic fuel source; wherein the first conduit is arranged to transport cryogen from the first cryogenic fuel propulsion system to the second cryogenic fuel propulsion system; and wherein the second conduit is arranged to transport cryogen from the second cryogenic fuel propulsion system to the first cryogenic fuel propulsion system, the system further comprising: a third conduit, arranged to transport a liquid cryogen from the first cryogenic fuel propulsion system to the second cryogenic fuel propulsion system, wherein the third conduit is in thermal communication with the first conduit, a fourth conduit, arranged to transport a liquid cryogen from the second cryogenic fuel propulsion system to the first cryogenic fuel propulsion system, wherein the fourth conduit is in thermal communication with the second conduit.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
21.
ELECTRICAL POWER DISTRIBUTION NETWORK FOR AN ELECTRICALLY POWERED AIRCRAFT
The present invention relates to a electrical power distribution network for an electrically powered aircraft comprising: at least one electrical power source; at least one essential power user; at least one non-essential power user; a busbar arrangement comprising a plurality of busbars, wherein each busbar is connected to at least one of the at least one electrical power source, at least one of the at least one essential power user and at least one of the at least one non-essential power user; a controller arrangement arranged to: control electrical power delivery via the busbar arrangement from the at least one electrical power source, detect an operating failure state; detect essential power usage; and, detect non-essential power usage wherein the busbar arrangement is arranged to provide a different connection route for each busbar to at least one essential power user and at least one non-essential power user.
The present invention relates to a power management system for an electrically powered aircraft, the system comprising: at least one electrical power source; at least one propulsion source arranged to generate propulsion from electrical power; a busbar arrangement comprising a plurality of busbars, wherein each busbar is connected to at least one electrical power source and at least one propulsion source and wherein each busbar has a connection to at least one other busbar; a re-configuration element arranged to controllably re-configure connections between the plurality of busbars; a controller arrangement arranged to: control electrical power delivery via the busbar arrangement from the at least one electrical power source to the at least one propulsion source; detect an operating failure state; detect propulsive power requirement; and, provide a signal to the re-configuration element based on the operating failure state and the propulsive power requirement.
The present invention relates to a thermal energy transfer device for use in transferring thermal energy from a coil of an electrically drivable motor, the device comprising: a plurality of elongate thermally conductive members each arranged to thermally communicate with at least a portion of a coil of an electrically drivable motor; at least one thermally conductive portion arranged to thermally communicate with a plurality of elongate thermally conductive members, wherein each of the plurality of elongate thermally conductive members is electrically insulated from any other of the plurality of thermally conductive members, and wherein the first plurality of elongate thermally conductive members are arranged to have a longitudinal axis in a first axis, and wherein the at least one thermally conductive portion is arranged to have a longitudinal axis in a second axis, wherein the first axis and the second axis are arranged between 45 degrees and 135 degrees apart, and wherein the at least one thermally conductive portion has a thermal conductivity of at least 100 Wm-1K-1 and an electrical conductivity of less than 10-14 Sm-1.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
A rear engine mounting structure for connecting an engine system to an aircraft structure, the rear engine mounting structure comprising: an elongate body having a first end arranged in use for connection to an aft side of a turbine exhaust case, the elongate body comprising one or more mounting points for connection to the aircraft structure, wherein the one or more mounting points are spaced from the first end in an axial direction.
The present invention relates to a thermal energy management system for use in an electrically powered aircraft, the system comprising: a passive cooling system (110); an active cooling system (120); and, a controller (130) arranged to control the active cooling system based on detected characteristics of flight, wherein the passive cooling system operates at all stage of flight; and wherein the active cooling system is controllably operable by the controller for all stages of flight.
The present invention relates to an electrical aircraft propulsion arrangement comprising: at least one fuel cell arranged to generated electrical power for use in propelling an aircraft; a fluid source arranged to provide fluid to at least one fuel cell for use in generating electrical power; at least one centrifugal compressor arranged to compress a fluid prior to provision to at least one fuel cell; at least one axial compressor arranged to compress a fluid prior to provision to at least one fuel cell, wherein at least one axial compressor is upstream of at least one centrifugal compressor.
B64D 27/355 - Arrangements for on-board electric energy production, distribution, recovery or storage using fuel cells
H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
A ball constant velocity sliding joint, comprises an outer joint part with an axis of rotation and with outer ball tracks and outer center lines, an inner joint part with inner ball tracks and inner center lines, a plurality of torque-transmitting balls, which are each guided in outer ball tracks and inner ball tracks assigned to one another and forming track pairs; and a cage, which is provided with a plurality of cage windows, which each receive one or more of the balls; wherein the cage has a web along a circumferential direction between the cage windows, which web is guided via a respective spherical contact surface at least on the outer joint part or on the inner joint part.
F16D 3/227 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts the groove centre-lines of each coupling part lying on a cylinder co-axial with the respective coupling part the joints being telescopic
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
28.
TURBINE ENGINE CASING FABRICATION AND HEAT TREATMENT
The invention concerns a method of heat treatment for a component comprising a first portion formed of a first nickel-based alloy. The method comprises heating the component to a temperature from 920°C to 1120°C for less than about 0.75 hours.
C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
The present invention relates to a repeatable unit for a segmented stator for an electric machine, the unit comprising: a back-iron stator segment; a stator tooth segment comprising a top portion, a main body portion and a base portion; and a connection portion for connecting the back-iron stator segment to the stator tooth segment, wherein the base portion of the stator tooth segment has a width that is greater than a width of the top portion and the width of the main body portion, wherein, in use, a furthest radial distance of the back-iron stator segment is broadly the same as a furthest radial distance for the stator tooth segment.
H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
H02K 15/02 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
A component can be formed from a non-crimp fibre material, by using a forming tool over which a layer of non-crimp fibre is to be drawn, wherein the layer of non-crimp material is drawn over the tool by forming boards extending around all or part of the periphery of the tool using an elastic material.
B29C 70/56 - Tensioning reinforcements before or during shaping
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
A counter track joint comprises an outer joint part and an inner joint part, wherein first pairs of tracks widen towards the opening side of the outer joint part when the counter track joint is aligned, and second pairs of tracks widen towards the connecting side of the outer joint part when the counter track joint is aligned; a ball in each first and second pair of tracks respectively; a ball cage with circumferentially distributed cage windows, each of which accommodates one of the balls, the ball cage having a non-circular shape with at least three maxima and three minima when viewed in cross-section.
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
The present invention relates to an aircraft propulsion arrangement comprising a cryogenic source, there is presented an aircraft propulsion arrangement comprising: a cryogenic source comprising a cryogenic resource, wherein the cryogenic resource is arranged to, initially, provide a heat exchanger function and to, subsequently, function as a fuel for a fuel cell; at least one heat exchanger, arranged in use to exchange thermal energy between generators of thermal energy and the cryogenic resource; at least one fuel cell, arranged to generate electrical power from the cryogenic resource for motive power, wherein the cryogenic resource is arranged to flow from the cryogenic source to the at least one heat exchanger and from the at least one heat exchanger to the at least one fuel cell.
The present invention relates to a thermal energy transfer device for use in transferring thermal energy from a coil of an electrically drivable motor, the device comprising: a first plurality of elongate thermally conductive members each arranged to thermally communicate with at least a portion of a coil of an electrically drivable motor; a second plurality of elongate thermally conductive members each arranged to thermally communicate with at least a portion of a coil of the electrically drivable motor, wherein each of the first and second plurality of elongate thermally conductive members is directly electrically insulated from any other of the plurality of thermally conductive members, and wherein the first plurality of elongate thermally conductive members are arranged to have a longitudinal axis in a first axis, and wherein the second plurality of elongate thermally conductive members are arranged to have a longitudinal axis in a second axis, wherein the first axis and the second axis are arranged between 45 degrees and 135 degrees apart.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
A casing structure for a gas turbine engine comprising a plurality of struts defining a plurality of annular circumferentially extending airflow passages and where the strut side surfaces comprise recesses.
A tool damper for a machine tool, such as a milling machine, is arranged around the tool stem of the machine or the tool holder of the machine and arranged to damper vibrations of the tool.
Drive shaft arrangement (1) for a motor vehicle (2), comprising at least a first tripod joint (3) having a first outer part (4) and a first inner part (13), wherein the first inner part (10) has three first pins (11) with first pin axes (9); a second, sliding joint (6) having a second outer part (8) and a second inner part (6); and a connecting shaft (17) which extends in an axial direction (18) between a first end (19) and a second end (20) and which is connected for torque transmission via the first end (19) to the first tripod joint (3) and via the second end (20) to the second, sliding joint (10); wherein at least the pin axes (9, 40) of the first pins (8) are inclined relative to a radial direction (25) by a first inclination angle (29) which is greater than zero degrees.
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
The invention concerns a compressor case for a gas turbine engine, the case comprising a generally cylindrical body formed of a plurality of adjacent cylindrical sub-sections being formed of Ti-6242 and Ti-64.
A bellows for a joint arrangement extends between a first end and a second end as a hollow body along an axis and is formed by a wall which encloses the axis between the ends along a circumferential direction and forms an inner space; wherein the wall is formed at least by a plurality of pleats arranged side by side along the axis; wherein each pleat extends along the axis starting from a first smallest diameter via a first flank to a first largest diameter and via a second flank to a second smallest diameter and a flank of at least one pleat has a plurality of structures arranged distributed along the circumferential direction.
F16J 15/52 - Sealings between relatively-movable members, by means of a sealing without relatively-moving surfaces, e.g. fluid-tight sealings for transmitting motion through a wall by means of sealing bellows or diaphragms
The invention relates to a tripod joint (1) comprising: an outer joint part (2) having a first longitudinal axis (3) and a cavity (4) that extends parallel to the first longitudinal axis (3) and has an open end (5), wherein three recesses (6) extending parallel to the first longitudinal axis (3) are formed in the outer joint part (2); and an inner joint part (7) having a second longitudinal axis (8) and comprising at least one central body (9) on which three pins (10) are moulded, wherein a roller body (13) is arranged on each of the pins (10), which roller body has at least one outer ring (14) and an inner ring (16) which can rotate about a common axis of rotation (15) with respect thereto; wherein, at least when the longitudinal axes (3, 8) are arranged coaxially, force is transmitted between the pin (10) and the inner ring (16) in a peripheral direction (18) via two contact points (19, 20) which are at a distance from one another along the radial direction (11) in a cross-section (21) of the tripod joint (1) extending transversely to the longitudinal axes (3, 8).
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
The present disclosure provides compositions comprising iron, about 0.01 to about 0.4% w/w of manganese; about 1.3 to about 1.9% w/w of chromium; about 0.1% w/w or less of nickel; about 1.2 to about 1.7% w/w of molybdenum; about 0.01 to about 0.4% w/w of niobium; about 0.01 to about 0.4% w/w of vanadium; about 1.5 to about 2% w/w of silicon; and about 0.01 to about 0.20% w/w of carbon. The present disclosure also provides methods of preparing a metal powder, comprising atomizing a composition described herein and methods of preparing a metal object, comprising subjecting metal powder described herein to metal binder jetting.
C22C 38/48 - Ferrous alloys, e.g. steel alloys containing chromium with nickel with niobium or tantalum
B22F 1/052 - Metallic powder characterised by the size or surface area of the particles characterised by a mixture of particles of different sizes or by the particle size distribution
B22F 9/08 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
B22F 10/14 - Formation of a green body by jetting of binder onto a bed of metal powder
B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
A cryocooled electric motor (500) comprising: a stator (510) comprising a magnetic core (510,510a), a rotor (520), an armature arrangement (550) and a cryogen source arranged to provide a cryonic fluid (544) to the armature arrangement (550), in order to cool the armature arrangement (550) below a temperature of 77 K, wherein the armature arrangement (550) comprises a plurality of Litz wires (552) and wherein the armature arrangement (550) is able to provide during operation of the motor a current density of more than 25 A/mm2.
H02K 3/14 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors arranged in slots with transposed conductors, e.g. twisted conductors
H02K 55/02 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
The invention concerns a method of turbine blade repair in which a damaged region (Di) is machined away (Rz) and repaired with a directed energy deposition process before being machined to a desired and predetermined aerodynamic profile.
A tripod joint can include a joint outer part with a first longitudinal axis and a cavity running parallel to the first longitudinal axis with an open end, three recesses running parallel to the first longitudinal axis being formed in the joint outer part, and a joint inner part with a second longitudinal axis., The tripod joint can include at least one central body on which three trunnions are formed with trunnion axes extending radially from the second longitudinal axis, wherein a roller body is arranged on each of the trunnions, which roller body has at least one outer ring and an inner ring rotatable therewith about a common axis of rotation, as well as bearing bodies arranged between the outer ring and the inner ring; wherein each roller body is movably received in the recesses along the first longitudinal axis.
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
A gas turbine engine has a core flow path and an outer flow path, the outer flow path positioned at a greater radial displacement from a rotational axis of the engine than the core flow path. The gas turbine engine also has a cavity to provide fluid communication between a bleed passage and a duct, the bleed passage for communicating air from the core flow path to the cavity and the duct for communicating air from the cavity to the outer flow path. The cavity has a downstream wall. The duct has a circumferentially extending opening that provides a passage through the downstream wall adjacent to a radially outer wall of the cavity.
F02C 3/13 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows
A counter track joint comprises an outer joint part, an inner joint part, first pairs of tracks widening towards the opening side of the outer joint part when the counter track joint is aligned, and second pairs of tracks widening towards the connecting side of the outer joint part when the counter track joint is aligned; a ball in each of the first and second pairs of tracks; a ball cage having circumferentially distributed cage windows each receiving one of the balls, wherein one of the outer ball track group and the inner ball track group is hardened and hard machined, and the other of the outer ball track group and the inner ball track group is soft finished and subsequently hardened. A method of manufacturing a counter track joint is provided.
F16D 3/224 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts the groove centre-lines of each coupling part lying on a sphere
46.
TRIPOD JOINT AND INNER JOINT PART OF A TRIPOD JOINT
The invention relates to a tripod joint (1) at least comprising an outer joint part (2) and an inner joint part (3) as well as a plurality of roller bodies (4), wherein: the outer joint part (2) has a receptacle (6) for the inner joint part (3), which receptacle extends along a first axis of rotation (5), and has three raceways (9) extending along the first axis of rotation (5) and distributed in a circumferential direction (7, 8); the inner joint part (3) has a central body (11) extending along a second axis of rotation (10) and three pins (14) which extend from the central body (11) along a radial direction (12), each have a pin axis (13) and are distributed in the circumferential direction (7, 8); and one of the roller bodies (4) is arranged on each pin (14), the inner circumferential face (15) of which roller body contacts the pin (14), and the outer circumferential face (16) of which contacts the relevant raceway (9). The invention also relates to an inner joint part (3).
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
A fluid release system for a fuel cell comprises a conduit for communicating water from the fuel cell to one or more outlets; and, a water discharge arrangement arranged to selectively release water from the one or more outlets, wherein the water discharge arrangement is arranged to controllably open the one or more outlets to selectively release water from the one or more outlets.
H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyteHumidifying or dehumidifying
The present invention is concerned with an aircraft comprising an elongate fuselage for containing cargo or passengers. The fuselage comprises a lower floor and an upper ceiling and opposing fuselage sides extending between the ceiling and floor. The fuselage sides each comprise at least one door which can be selectively opened and closed. The fuselage is divided into multiple zones between the fore and aft of the aircraft, each zone being associated with one of said doors adjacent to said zone and wherein the doors alternate in position between sides of the aircraft such that adjacent zones from fore to aft of the aircraft are associated with a door on an opposing side of the aircraft.
The present invention relates to a power unit suitable for use in an aircraft comprising: at least one fuel cell; at least two fuel sources for providing fuel to the at least one fuel cell; wherein a first fuel source is a hydrogen supply arranged to provide hydrogen to a first fuel cell of the at least one fuel cell, and wherein a second fuel source is an air gas supply arranged to provide air gas to a first fuel cell of the at least one fuel cell.
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
H01M 8/04082 - Arrangements for control of reactant parameters, e.g. pressure or concentration
H01M 8/249 - Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
The present invention relates to an electrical transmission comprising: an electrical conductor; and, a cryogen carrying portion arranged so that, in use, cryogen is carried in the cryogen carrying portion to maintain the conductor in a hyperconductive state.
The present invention relates to a propulsion system for providing controllable propulsion comprising: a fuel cell arrangement (210) for generating electrical energy; a gas generator (250) comprising a compressor (256), a combustor (254) and a turbine (252), wherein the output from turbine is arranged to provide propulsion from rotational movement; a hydrogen source (212) for providing hydrogen to the fuel cell arrangement and the gas generator; an oxygen source (214) for providing oxygen to the gas generator (250), wherein, in use, the gas generator is used selectively to provide electrical energy for additional propulsion.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 41/00 - Power installations for auxiliary purposes
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
B64D 27/02 - Aircraft characterised by the type or position of power plants
The present invention relates to electrical network comprising an electrical conductor and, a cryogen source configured to hold cryogen, the cryogen source arranged so that, in use, cryogen is provided to the conductor to maintain the conductor in a hyperconductive state.
The present invention relates to an aircraft propulsion system (100) comprising: a fuel cell arrangement comprising at least one fuel cell (110); an air source (130) for providing air to the fuel cell arrangement; a compressor arrangement comprising a first compressor (120) in fluid communication with the air source and a fuel cell of the fuel cell arrangement; and, a turbine arrangement comprising a first turbine (124) mechanically coupled to the first compressor, wherein the first turbine is in fluid communication with the at least one fuel cell (110), the system being arranged so that, in use, air from the air source (130) flows in turn to the first compressor (120), the fuel cell arrangement and the first turbine (124).
B64D 41/00 - Power installations for auxiliary purposes
F02C 6/10 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
The invention concerns an aircraft fuel heating arrangement comprising an exhaust cone for a gas turbine engine, the exhaust cone having an outer body defining an internal cone cavity, the internal cone cavity comprising one or more conduits passing therethrough for communicating fuel through the cavity, and wherein the outer body of the exhaust cone comprises at least one inlet and at least one outlet to allow exhaust gas to pass into through and out of the exhaust cone.
F02C 7/224 - Heating fuel before feeding to the burner
F02C 7/10 - Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
F02K 1/04 - Mounting of an exhaust cone in the jet pipe
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
The present invention provides a grease composition for constant-velocity joints comprising (a) a base oil, (b) a diurea thickener, (c) molybdenum dithiocarbamate, (d) molybdenum dithiophosphate, (e) overbased calcium sulfonate, and (f) neutral zinc sulfonate. The composition of the present invention is excellent in durability at high temperature and vibration suppression.
C10M 169/00 - Lubricating compositions characterised by containing as components a mixture of at least two types of ingredient selected from base-materials, thickeners or additives, covered by the preceding groups, each of these compounds being essential
C10M 115/08 - Lubricating compositions characterised by the thickener being a non-macromolecular organic compound other than a carboxylic acid or salt thereof containing nitrogen
C10M 135/18 - Thio-acidsThiocyanatesDerivatives thereof having a carbon-to-sulfur double bond thiocarbamic type, e.g. containing the groups
C10M 135/10 - Sulfonic acids or derivatives thereof
C10M 141/10 - Lubricating compositions characterised by the additive being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being an organic phosphorus-containing compound
A boot comprising a central axis and an inner surface and an outer surface. The boot having a first fastening region the inner surface of which is adapted to seal against a first component and a second fastening region the inner surface of which is adapted to seal against a second component. The boot having an interior volume between the first fastening region and the second fastening region. The boot having an intermediate region connected at a first end to the first fastening region and connected at a second end to the second fastening region. The intermediate region having a convolution located between the first end and second end, wherein the outer surface of the convolution is convex.
F16D 3/84 - Shrouds, e.g. casings, coversSealing means specially adapted therefor
F16D 3/226 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts the groove centre-lines of each coupling part lying on a cylinder co-axial with the respective coupling part
The invention relates to a countertrack joint comprising: an outer joint part (12), an inner joint part (13), wherein first track pairs (22A, 23A) widen towards the open side of the outer joint part (12) when the countertrack joint is straight, and second track pairs (22B, 23B) widen towards the connection side of the outer joint part (12) when the countertrack joint is straight; one ball (14A, 14B) in each first and second track pair; a ball cage (15) with peripherally distributed cage windows (18), each of which receives one of the balls (14). A second outer track base line (G22B) of the outer joint part (12) extends from the central joint plane (EM) in the direction of the joint base (19) at least starting from a track deflection angle (β') of ± 20° radially within a second outer reference circular arc (CRB12) which is defined by a second outer radius (R22Bp) which forms the second outer track base line (G22B) in the second offset plane (EB).
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
F16D 3/2233 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts where the track is made up of two curves with a point of inflexion in between, i.e. S-track joints
The invention relates to a method for producing a counter track joint, comprising: pro-ducing a first joint part (12) with first and second ball tracks (22A, 22B) that are soft-finished and hardened, i.e. remain unmachined after hardening; determining a first working PCD value (WPCD12) from a first curvature of the first ball tracks (22A) and a second curvature of the second ball tracks (22B); classifying the first joint part (12) to a size class of at least two different size classes (C12a, C12b, C12c); producing a second joint part (13) with first and second ball tracks (23A, 23B); assigning the second joint part (13) to the first joint part (12), with a difference between WPCD12 and WPCD13 being greater than 20 and smaller than 80 micrometers; producing a ball cage (15) and balls (14A, 14B); mounting the joint parts; wherein in the mounted con-dition, a first axial play (So) of the ball cage (15) to the first joint part (12) differs from a second axial play (Si) of the ball cage (15) to the second joint part (13). Figure 6D
F16D 3/2233 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts where the track is made up of two curves with a point of inflexion in between, i.e. S-track joints
The present invention relates to a thermal energy transfer device for use in transferring thermal energy from a coil of an electrically drivable motor, the device comprising: a plurality of thermally conductive members arranged to thermally communicate with at least one coil of an electrically drivable motor; and, a thermally conductive portion connected to the plurality of thermally conductive members, wherein each of the plurality of thermally conductive members is directly electrically insulated from any other of the plurality of thermally conductive members.
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
The invention relates to a constant velocity slip ball joint (1) comprising at least an outer joint part (2) having an axis of rotation (4) and having outer ball tracks (5) and outer centre lines (6), an inner joint part (7) having inner ball tracks (8) and inner centre lines (9), a plurality of torque transmitting balls (10) each guided in outer ball tracks (5) and inner ball tracks (8) associated with each other and forming track pairs (11); and a cage (12) provided with a plurality of cage windows (13) each receiving one or more of said balls (10); wherein the centre lines (6, 9) extend along the ball tracks (5, 8) from a first end region (14) along the axial direction (3) to a second end region (15); wherein the centre lines (6, 9) of each track pair (11) each extend at an angle of inclination (16), i.e. inclined with respect to a radial direction (17), and at a helix angle (18), i.e. inclined with respect to a circumferential direction (19), and thereby each extend in opposite directions.
F16D 3/227 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts the groove centre-lines of each coupling part lying on a cylinder co-axial with the respective coupling part the joints being telescopic
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
The invention relates to a constant-velocity slip ball joint (1), at least comprising: a joint outer part (2) having an axis of rotation (3) and having outer ball tracks (4) and outer centre lines (5); a joint inner part (6) having inner ball tracks (8); a plurality of torque-transmitting balls (9) which are each guided in mutually associated outer ball tracks (4) and inner ball tracks (7) and forming track pairs (10); and a cage (11) which is provided with a large number of cage windows (12) that each receive one or more of the balls, wherein, the cage (11) having, along a circumferential direction (13) between the cage windows (12), respectively one web (14) which is guided respectively via one spherical contact surface (15) at least on the outer joint part (2) or on the inner joint part (6).
F16D 3/227 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts the groove centre-lines of each coupling part lying on a cylinder co-axial with the respective coupling part the joints being telescopic
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
A bracket for a rotating shaft includes a base and a retainer assembly. The base has a mount body and a receiver, first and second tabs extending from receiver and overlapping spaced apart portions of the mount body. The retainer assembly has a first retainer and a second retainer that overlap the tabs and trap the tabs against the mount body to hold the receiver on the mount body, and the first retainer overlaps part of the second retainer and the second retainer overlaps part of the first retainer to maintain the positions of the retainers relative to the mount body and receiver.
F16M 13/02 - Other supports for positioning apparatus or articlesMeans for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
In at least some implementations, a bracket for a rotating shaft includes a base and a retainer. The base has a mount body and a receiver having a first portion coupled to the mount body, a second portion extending from the first portion at a first end of the second portion to a second end of the second portion, a seat and an opening. The opening is defined at least in part by an inner surface disposed around a center axis. The retainer has a first surface engaged with the seat and a second surface engaged with a retention surface of the mount body and the retainer prevents separation of the seat from the retention surface by a distance greater than the distance between the first surface and the second surface.
F16M 13/02 - Other supports for positioning apparatus or articlesMeans for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
An outlet guide vane (OGV) structure for a gas turbine engine can comprise a plurality of radially extending guide vanes having inlets and outlets to allow cooling of a medium within the guide vanes.
A gas turbine engine comprises at least one radially extending bleed passage optionally in fluid communication with at least one generally circumferentially extending plenum. The passage has an upstream inlet in fluid communication with a bleed passage and an outlet for releasing air from the plenum. The upstream leading edge of the inlet or the downstream trailing edge of the inlet has a non-uniform profile.
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
Constant-velocity ball joint, having at least a joint outer part with an axis of rotation and with outer ball tracks and with outer center lines, a joint inner part with inner ball tracks and inner center lines, and a large number of torque-transmitting balls which are each guided in mutually associated outer ball tracks and inner ball tracks.
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
The present disclosure relates to a motor drive system comprising: a fuel cell; a motor, electrically connected to the fuel cell; and, a cryogenic system arranged to contain a cryogen, wherein the fuel cell is arranged to output current to the motor, and wherein the cryogenic system is arranged to communicate a cryogen from the cryogenic system to the fuel cell.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
B60L 50/71 - Arrangement of fuel cells within vehicles specially adapted for electric vehicles
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
The present disclosure provides compositions comprising iron, about 0.01 to about 0.4% w/w of manganese; about 1.3 to about 1.9% w/w of chromium; about 0.1% w/w or less of nickel; about 1.2 to about 1.7% w/w of molybdenum; about 0.01 to about 0.4% w/w of niobium; about 0.01 to about 0.4% w/w of vanadium; about 1.5 to about 2% w/w of silicon; and about 0.01 to about 0.20% w/w of carbon. The present disclosure also provides methods of preparing a metal powder, comprising atomizing a composition described herein and methods of preparing a metal object, comprising subjecting metal powder described herein to metal binder jetting.
B22F 9/08 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
B22F 10/14 - Formation of a green body by jetting of binder onto a bed of metal powder
09 - Scientific and electric apparatus and instruments
Goods & Services
Laser welding machines; laser welding devices in the nature of laser welding machines; laser welding devices in the nature of
component parts for laser welding machines, namely, laser optics, vision systems, seam tracking systems, fixtures, robot dress
package, optical sensors, focus positioning system, control system for regulating process parameters, station human machine
interface, media panel for regulating, distributing, and measuring flows, temperature, and pressures, laser safety enclosures Laser equipment for non-medical purposes
09 - Scientific and electric apparatus and instruments
Goods & Services
Laser welding machines; laser welding devices in the nature of laser welding machines; laser welding devices in the nature of
component parts for laser welding machines, namely, laser optics, vision systems, seam tracking systems, fixtures, robot dress
package, optical sensors, focus positioning system, control system for regulating process parameters, station human machine
interface, media panel for regulating, distributing, and measuring flows, temperature, and pressures, laser safety enclosures Laser equipment for non-medical purposes
Disclosed are polyurethane-polysiloxane hybrid coating compositions (PUPSHCC) and their uses, processes for their preparation, and substrates incorporating the coating compositions.
C09D 4/00 - Coating compositions, e.g. paints, varnishes or lacquers, based on organic non-macromolecular compounds having at least one polymerisable carbon-to-carbon unsaturated bond
The disclosure concerns a compressor blade for gas turbine engine. Specifically the blades of the compressor are modified according to predetermined requirements for both aerodynamic stability and fuel economy in multiple planes.
The invention relates to a countertrack joint comprising: an outer joint part (12) and an inner joint part (13), wherein first track pairs (22A, 23A) widen towards the open side of the outer joint part (12) when the countertrack joint is straight, and second track pairs (22B, 23B) widen towards the connection side of the outer joint part (12) when the countertrack joint is straight; one ball (14A, 14B) in each first and second track pair; a ball cage (15) with peripherally distributed cage windows (18), each of which receives one of the balls (14), wherein the ball cage (15), in a cross-sectional view, has a non-circular shape with at least three maxima and three minima.
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
The invention concerns a tool damper for a machine tool, such as a milling machine, wherein the damper is arranged around the tool stem of the machine or the tool holder of the machine and arranged in use to damper vibrations of the tool.
A shaft connection 1 for a longitudinal shaft assembly, has at least a first shaft having a first and second ends, and a second shaft, disposed so as to be coaxial with the first shaft, having first and second ends; the shafts extending axially. The first end forms a hollow portion. The first shaft end forms a first journal having a displacement portion. The first shaft end at least in an initial position of the shaft connection extends through the hollow portion which axially by the displacement portion forms a guide portion and circumferentially forms a form-fitting first connection. In the initial position a mutual axial displacement of the first and second shafts is prevented by an axial securing feature. In a crash the axial securing feature; is releasable by an axial release force. The first shaft is axially displaceable relative to the second shaft.
B60K 17/22 - Arrangement or mounting of transmissions in vehicles characterised by arrangement, location, or type of main drive shafting, e.g. cardan shaft
F16D 3/227 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts the groove centre-lines of each coupling part lying on a cylinder co-axial with the respective coupling part the joints being telescopic
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
In manufacturing an electrothermal heater mat, there is provided a preform which comprises a laminated stack of dielectric layers which are made of thermoplastic material and include a central layer or group of layers which include(s) reinforcement and first and second outer groups of layers which do not include reinforcement. The preform includes a heater element and the preform has a first configuration. The preform is then heated to a temperature (e.g. 180° C.) between the glass-transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform is formed into a second configuration which is different to the first configuration so as to produce the heater mat.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material
A front centre body (FCB) structure for a geared turbofan engine comprises a plurality of vanes extending across the inlet duct to a low pressure compressor and integrates a heat exchanging arrangement to control the temperature of the gearbox of the turbofan engine.
The invention relates to a constant-velocity slip ball joint (1), at least comprising: a joint outer part (2) having an axis of rotation (3) and having outer ball tracks (4); a joint inner part (5) having inner ball tracks (6); a large number of torque-transmitting balls which are each guided in mutually associated outer ball tracks (4) and inner ball tracks (6); and a cage (8) which is provided with a large number of cage windows (9) that each receive one or more of the balls, wherein, proceeding from a home position (10) of the constant-velocity slip ball joint (1), the joint inner part (5) can be slipped in both directions along the axis of rotation (3) with respect to the joint outer part (2). The slip path (15) of the joint inner part (5) with respect to the cage (8) along the axis of rotation (3) is provided by contact between an inner contact surface (16) of the cage (8) and an outer contact surface (17) of the joint inner part (5). The outer contact surfaces (17) of the cage are each situated on a first radius (21) so as to have offset first midpoints (22) on the axis of rotation (3), and the inner contact surfaces (16) of the cage are each situated on a second radius (24). The second radius (24) is greater than the first radii (21), or the second radii (24) are situated on the axis of rotation (3) so as to have mutually offset second midpoints (25).
F16D 3/227 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts the groove centre-lines of each coupling part lying on a cylinder co-axial with the respective coupling part the joints being telescopic
A constant velocity joint comprises a male element having arms, a female element having a central axis and defining a pair of symmetrical tracks and an outer roller which can roll on one or other of the two tracks via a peripheral rolling surface. The female element comprises at least one bearing surface which limits the rotation of the outer roller around an axis perpendicular to the axis' of the female element and of the arm. With respect to each arm the cross-section profile of each track comprises either two circular arcs having centers of radii offset one from another, or one single circular arc extending over a female element median plane, and the rolling surface has a part spherical shape or a part torical shape. Each track and the rolling surface are capable of contacting each other at a first and second contact points spaced radially from one another. The tilting of the roller is controlled by proximal and distal rails on the female element and by proximal and distal breaking surfaces on the outer roller.
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
F16D 3/202 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints
A method of forming a component from a non-crimp fibre material, the method comprising a forming tool (6) over which a layer (10, 8) of non-crimp fibre is to be drawn, wherein the layer (8) of non-crimp material is drawn over the tool by forming boards (9A, 9B) extending around all or part of the periphery of the tool using an elastic material (10).
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/56 - Tensioning reinforcements before or during shaping
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
A grease composition is disclosed which is intended primarily for use in constant velocity joints (CV joints), especially ball joints and/or tripod joints, which are used in the driveline of motor vehicles. The grease composition for use in constant velocity joints comprises at least one base oil, at least one thickener, zinc sulfide, at least one copper sulfide and molybdenum disulfide and/or tungsten disulfide. Further, the present disclosure relates to a constant velocity joint comprising such a grease composition.
C10M 169/00 - Lubricating compositions characterised by containing as components a mixture of at least two types of ingredient selected from base-materials, thickeners or additives, covered by the preceding groups, each of these compounds being essential
C10M 107/02 - Hydrocarbon polymersHydrocarbon polymers modified by oxidation
C10M 111/04 - Lubricating compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being a macromolecular organic compound
C10M 115/08 - Lubricating compositions characterised by the thickener being a non-macromolecular organic compound other than a carboxylic acid or salt thereof containing nitrogen
C10M 117/02 - Lubricating compositions characterised by the thickener being a non-macromolecular carboxylic acid or salt thereof having only one carboxyl group bound to an acyclic carbon atom, cycloaliphatic carbon atom or hydrogen
C10M 125/22 - Compounds containing sulfur, selenium or tellurium
C10M 135/18 - Thio-acidsThiocyanatesDerivatives thereof having a carbon-to-sulfur double bond thiocarbamic type, e.g. containing the groups
C10M 141/10 - Lubricating compositions characterised by the additive being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being an organic phosphorus-containing compound
C10N 50/10 - Form in which the lubricant is applied to the material being lubricated semi-solidForm in which the lubricant is applied to the material being lubricated greasy
A method of bonding a composite vane to at least one support. The method includes positioning an end of a vane within a support, causing an adhesive to flow between the vane and the support from an inlet to an outlet, and reversing the flow of adhesive from the outlet towards the inlet.
A milling machine includes a spindle which is arranged to receive a tool holder and in use to cause rotation of the tool holder within the spindle. A portion of the spindle housing surrounding the tool holder is provided with at least one pair of opposing damping units.
B23Q 1/70 - Stationary or movable members for carrying working-spindles for attachment of tools or work
B23Q 11/00 - Accessories fitted to machine tools for keeping tools or parts of the machine in good working condition or for cooling workSafety devices specially combined with or arranged in, or specially adapted for use in connection with, machine tools
F16F 7/108 - Vibration-dampersShock-absorbers using inertia effect the inertia member being resiliently mounted on plastics springs
F16F 15/08 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system using elastic means with rubber springs
87.
Grease composition including copper sulfide for constant velocity joints
A grease composition is intended primarily for use in constant velocity joins (CV joints), especially ball joints and/or tripod joints, which are used in the drivelines of motor vehicles. The grease composition for use in constant velocity joints comprises at least one base oil, and least one thickener, at least one copper sulfide in an amount of approximately 0.01 wt-% up to approximately 1.5 wt-% of the grease composition, molybdenum disulfide and/or at least one phosphorus-free organic molybdenum complex in an amount of approximately 0.1 wt-% up to approximately 5.0 wt-% of the grease composition. Further, a constant velocity joint comprises the grease composition.
C10M 169/00 - Lubricating compositions characterised by containing as components a mixture of at least two types of ingredient selected from base-materials, thickeners or additives, covered by the preceding groups, each of these compounds being essential
C10M 107/02 - Hydrocarbon polymersHydrocarbon polymers modified by oxidation
C10M 111/04 - Lubricating compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being a macromolecular organic compound
C10M 117/02 - Lubricating compositions characterised by the thickener being a non-macromolecular carboxylic acid or salt thereof having only one carboxyl group bound to an acyclic carbon atom, cycloaliphatic carbon atom or hydrogen
C10M 125/22 - Compounds containing sulfur, selenium or tellurium
C10M 135/18 - Thio-acidsThiocyanatesDerivatives thereof having a carbon-to-sulfur double bond thiocarbamic type, e.g. containing the groups
C10M 141/08 - Lubricating compositions characterised by the additive being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being an organic sulfur-, selenium- or tellurium-containing compound
C10M 159/00 - Lubricating compositions characterised by the additive being of unknown or incompletely defined constitution
C10M 163/00 - Lubricating compositions characterised by the additive being a mixture of a compound of unknown or incompletely defined constitution and a non-macromolecular compound, each of these compounds being essential
C10N 30/10 - Inhibition of oxidation, e.g. anti-oxidants
C10N 50/10 - Form in which the lubricant is applied to the material being lubricated semi-solidForm in which the lubricant is applied to the material being lubricated greasy
A grease composition is intended primarily for use in constant velocity joints (CV joints), especially ball joints and/or tripod joints, which are used in the driveline of motor vehicles. The grease composition for use in constant velocity joints comprises at least one base oil, at least one thickener, zinc sulfide, as well as molybdenum disulfide and/or tungsten disulfide. Further, a constant velocity joint comprises the grease composition.
C10M 169/00 - Lubricating compositions characterised by containing as components a mixture of at least two types of ingredient selected from base-materials, thickeners or additives, covered by the preceding groups, each of these compounds being essential
C10M 117/04 - Lubricating compositions characterised by the thickener being a non-macromolecular carboxylic acid or salt thereof having only one carboxyl group bound to an acyclic carbon atom, cycloaliphatic carbon atom or hydrogen containing hydroxy groups
C10M 125/22 - Compounds containing sulfur, selenium or tellurium
C10M 141/10 - Lubricating compositions characterised by the additive being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being an organic phosphorus-containing compound
C10N 30/10 - Inhibition of oxidation, e.g. anti-oxidants
C10N 50/10 - Form in which the lubricant is applied to the material being lubricated semi-solidForm in which the lubricant is applied to the material being lubricated greasy
An aircraft, such as an unmanned aerial vehicle or single-seat aircraft, including a main body and a pair of wing sections, each wing section including a front wing and a rear wing, wherein the front wing and the rear wing each include a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing. The main body is located between the pair of wing sections, and each wing section includes a propulsion unit located between the front wing and the rear wing of the wing section. Each propulsion unit may include a first rotor and a second rotor, which may be pivotable with respect to the rest of the aircraft.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
A gear-tooth system can be produced on a component of a shaft/hub connection. The component can have a first axis of rotation and a gear-tooth system; wherein the gear-tooth system of the component comprises a plurality of teeth, disposed next to one another along a circumference direction, wherein a tooth interstice is disposed between two teeth, in each instance, and each tooth has a head region and a flank region, in each instance, between head region and a foot region disposed in the tooth interstice, wherein the tooth interstice has a tooth gap width in the flank region; wherein the gear-tooth system has at least a first region and subsequently a second region along an axial direction parallel to the first axis of rotation; wherein the first region has a first tooth gap width and the second region has a second tooth gap width, which is less in comparison.
B21H 5/02 - Making gear wheels with cylindrical outline
F16D 1/116 - Quick-acting couplings in which the parts are connected by simply bringing them together axially having retaining means rotating with the coupling and acting by interengaging parts, i.e. positive coupling the interengaging parts including a continuous or interrupted circumferential groove in the surface of one of the coupling parts
F16D 1/10 - Quick-acting couplings in which the parts are connected by simply bringing them together axially
An airflow arrangement for a gas turbine engine in which air can be selectively directed to and from a bypass channel of the engine and into a duct communicating air into a compressor of a gas turbine engine.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
F02K 3/075 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type controlling flow ratio between flows
An apparatus and corresponding method for machining at least one spline in an aeronautical component. The apparatus comprises a holder defining an axial direction about which the holder is moveable, and a cutting insert attachable to the holder. The apparatus further comprises a coupling for attaching the cutting insert to the holder about a second direction that is perpendicular to the axial direction of the holder. The holder may comprise a first alignment feature for orientating the cutting insert at a single orientation with respect to the holder. The cutting insert may comprise at least one cutting tooth, wherein each cutting tooth comprises a cutting edge. The cutting insert may comprise a first datum surface which is spaced from each cutting edge by a respective predetermined spacing.
B23C 5/22 - Securing arrangements for bits or teeth
B23C 5/28 - Features relating to lubricating or cooling
B23D 3/02 - Planing or slotting machines cutting by relative movement of the tool and workpiece in a vertical or inclined straight line for cutting grooves
The invention relates to a counter track joint comprising: a joint outer part (12) and a joint inner part (13), with first track pairs (22A, 23A) widening toward the opening side of the joint outer part (12) when the counter track joint is straight, and second track pairs (22B, 23B) widening toward the connection side of the joint outer part (12) when the counter track joint is straight; a ball (14A, 14B) in each first and second track pair; a ball cage (15) with peripherally distributed cage windows (18), each of which receives one of the balls (14), one of the outer ball track group and the inner ball track group being hardened and hard-machined, and the other of the outer ball track group and the inner ball track group being soft-finish-machined and then hardened. The invention further relates to a method for producing a counter track joint (11).
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
The present invention provides a grease composition for constant-velocity joints which comprises (a) a base oil, (b) a diurea-based thickening agent, (c) molybdenum dithiocarbamate, (d) molybdenum dithiophosphate, (e) a perbasic calcium sulfonate, and (f) a neutral zinc sulfonate. This composition is excellent in terms of high-temperature durability and vibration diminution.
C10M 141/02 - Lubricating compositions characterised by the additive being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being an organic oxygen-containing compound
C10M 141/08 - Lubricating compositions characterised by the additive being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being an organic sulfur-, selenium- or tellurium-containing compound
C10M 141/10 - Lubricating compositions characterised by the additive being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being an organic phosphorus-containing compound
C10M 141/12 - Lubricating compositions characterised by the additive being a mixture of two or more compounds covered by more than one of the main groups , each of these compounds being essential at least one of them being an organic compound containing atoms of elements not provided for in groups
C10M 169/06 - Mixtures of thickeners and additives
C10N 30/00 - Specified physical or chemical property which is improved by the additive characterising the lubricating composition, e.g. multifunctional additives
C10N 50/10 - Form in which the lubricant is applied to the material being lubricated semi-solidForm in which the lubricant is applied to the material being lubricated greasy
An aircraft engine circulation system comprises a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase at a predetermined temperature.
The disclosure provides iron-based metallurgical compositions comprising iron and alloying elements of about (0.01) to about (0.65) wt %, based on the weight of the composition, of carbon; about (1) to about (2.0) wt %, based on the weight of the composition, of molybdenum; about (0.25) to about (2.0) wt %, based on the weight of the composition, of manganese; about (0.25) to about (2.0) wt %, based on the weight of the composition, of silicon; and about (0.05) to about (0.6) wt %, based on the weight of the composition, of vanadium. In some embodiments, the iron-based metallurgical composition is a powder metallurgical composition.
A gas turbine engine comprising at least one radially extending bleed passage optionally in fluid communication with at least one generally circumferentially extending plenum. The passage has an upstream inlet in fluid communication with a bleed passage and an outlet for releasing air from the plenum. The upstream leading edge of the inlet or the downstream trailing edge of the inlet has a non-uniform profile.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
A multi-source aircraft propulsion arrangement comprises a cryogenic propulsion source and a combustion propulsion source wherein the cryogenic propulsion source and the combustion propulsion source may be selectively and independently operated to generate propulsive force for an aircraft.
The present invention relates to a motor drive system comprising: a fuel cell; a motor, electrically connected to the fuel cell; and, a cryogenic system arranged, in use, to contain a cryogen, wherein the fuel cell is arranged to output current to the motor, and wherein the cryogenic system is arranged in use to communicate a cryogen from the cryogenic system to the fuel cell.
H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
B60L 15/00 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train
B60L 50/71 - Arrangement of fuel cells within vehicles specially adapted for electric vehicles
B60L 50/72 - Constructional details of fuel cells specially adapted for electric vehicles
B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
A constant velocity joint comprises an outer joint part with outer ball tracks and an inner joint part with inner ball tracks. An outer ball track and an inner ball track respectively form a pair of tracks with one another; in each, a torque-transmitting ball is guided. The torque-transmitting balls are accommodated in a ball cage with circumferentially distributed cage windows. In any angular position of the constant velocity joint an opening angle is formed between an outer tangent to the outer ball track and an inner tangent to the inner ball track. At an articulation angle of zero degrees the opening angle is greater than zero degrees. A central articulation angle range is defined with articulation angles less than fifteen degrees. The opening angle increases by at least two degrees within the central articulation angle range, and is less than twelve degrees for all articulation angles within the central articulation angle range.
F16D 3/223 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts
F16D 3/2237 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members the rolling members being balls, rollers, or the like, guided in grooves or sockets in both coupling parts the rolling members being guided in grooves in both coupling parts where the grooves are composed of radii and adjoining straight lines, i.e. undercut free [UF] type joints
