An airfoil wall that includes a wishbone-shaped fiber layup structure that has first and second arms that merge into a single leg. The leg includes fiber tows from each of the arms and the tows are interwoven in the leg. Each of the arms includes a first section that is distal from the leg and a second section that is proximal to the leg. The first section defines a first thickness and a first fiber tow count. The second section defines a second thickness that is greater than the first thickness and a second fiber tow count that is greater than the first fiber tow count. The single leg defines a third thickness that is greater than the second thickness and a third fiber tow count that is greater than the second fiber tow count.
A method is provided for an HEP system that includes a gas turbine engine and an electric motor configured to assist the gas turbine engine by rotating a first shaft of the gas turbine engine. The method includes receiving a throttle command, and determining, based on an amount of electric power available to the electric motor, a power allocation between the gas turbine engine and the electric motor for an acceleration period during which a rotational speed of the first shaft is accelerated to implement the throttle command. The method also includes determining a target clearance between a tip of a rotor blade and a case structure for the acceleration period and, during the acceleration period, implementing the power allocation and operating an active clearance control (ACC) system to establish the target clearance. A system for an aircraft and a method for a HEP system are also disclosed.
A hollow vane assembly including an open body including an interior; at least one cover support structure formed in said open body proximate the interior; a cover brazed to the open body to form at least one flow passage; and the open body and the cover configured as two piece substantially symmetrical halves.
A method of producing an operational data for an aircraft turbine engine is provided that including: sensing an inlet airflow to an aircraft turbine engine for CMAS particulate matter, the sensing performed during one or more ground portions of a flight operational cycle of the turbine engine, the sensing producing sensor signals indicative of the presence or absence of the CMAS particulate matter; determining a presence or absence of an exposure by the turbine engine to a CMAS environment based on the sensor signals; and producing an operational data indicative of the presence or absence of said exposure by the turbine engine to said CMAS environment.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
A ceramic article includes a ceramic matrix composite that has a porous reinforcement structure and a ceramic matrix within pores of the porous reinforcement structure. The ceramic matrix composite includes a surface zone comprised of an exterior surface of the ceramic matrix composite and pores that extend from the exterior surface into the ceramic matrix composite. A glaze material seals the surface zone within the pores of the surface zone and on the exterior surface of the surface zone as an exterior glaze layer on the ceramic matrix composite. The glaze material is a glass or glass-ceramic material. The ceramic matrix composite includes an interior zone under the surface zone, and the interior zone is free of any of the glaze material and has a greater porosity than the surface zone.
C04B 41/50 - Coating or impregnating with inorganic materials
C03C 8/02 - Frit compositions, i.e. in a powdered or comminuted form
C03C 8/20 - Glass frit mixtures having non-frit additions, e.g. opacifiers, colorants, mill additions containing zirconium compounds
C03C 10/00 - Devitrified glass ceramics, i.e. glass ceramics having a crystalline phase dispersed in a glassy phase and constituting at least 50% by weight of the total composition
C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
A gas turbine engine is provided. The gas turbine engine includes a case having a wall that provides a manifold cavity, the wall including an aperture and a bore; a tube assembly with a flange that provides a fluid passage aligned with the aperture; a mixing feature arranged in the manifold cavity and including a plate with a hole; and an insert having a body and a head, the body received in the hole and sealed in the bore, the head capturing the plate against the wall. The mixing feature is configured to divert a flow of cooling fluid in at least a counterclockwise direction improving jet mixing and placement of the cooling fluid.
A combustor panel is disclosed herein. The combustor panel includes a top side, a bottom side opposite the top side, a feature coupled to the top side and extending orthogonally away from the top side, the feature defining a first space on the bottom side beneath the feature, a first plurality of cooling holes extending in a first direction from the top side to the bottom side, a second plurality of cooling holes extending in a second direction from the top side to the bottom side, the second direction being rotated about 1° to about 60° counter-clockwise from the first direction, and a third plurality of cooling holes extending in a third direction from the top side to the bottom side, the third direction being about rotated 1° to about 60° clockwise from the first direction.
A method for determining coating thicknesses of a coated fiber embedded in a matrix is presented. A scanning electron microscope (SEM) image is captured of a composite material having multiple coated fibers embedded in a matrix. This image depicts a cross-sectional portion of the composite material. A processor identifies a region of the image depicting a cross-section of one among the plurality of coated fibers, and generates a line graph of a gradient of grayscale values as a function of a line scan. The line scan traverses across the image along a radius of the coated fiber, and extends between an interior location of the coated fiber and an exterior region outside the coated fiber. The processor identifies inflection points in the line graph of the gradient of grayscale values as a function of the line scan traverse location, and determines coating thickness based on these inflection points.
A method of forming a ceramic matrix composite includes forming a preform by weaving a plurality of warp tows with a plurality of weft tows, weaving a plurality of fugitive yarns into a region of the preform in at least one of a warp position or weft position, and subsequently, decomposing the fugitive yarns to transform the region into a pre-weakened region, the pre-weakened region having a higher porosity than a remainder of the preform.
D02G 3/02 - Yarns or threads characterised by the material or by the materials from which they are made
D02G 3/44 - Yarns or threads characterised by the purpose for which they are designed
D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
D03D 15/242 - Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads inorganic, e.g. basalt
D03D 15/283 - Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads synthetic polymer-based, e.g. polyamide or polyester fibres
D03D 25/00 - Woven fabrics not otherwise provided for
An article includes a ceramic matrix composite article including ceramic-based reinforcements disposed in a ceramic-based matrix and a barrier layer present at least in part within bounds of the ceramic-based matrix of the ceramic matrix composite article. A method of applying a barrier layer to an article is also disclosed.
A method of forming a component utilizing material extrusion includes the steps of (1) delivering a hopper of particulate media formed of a primary material into an extruder, (2) selectively providing an infill material into the primary material within the extruder, (3) delivering a filament of the primary material and the infill material downstream to a nozzle where it is then deposited to form the component, and (4) a control associated with the nozzle selectively delivering the infill material into the primary material, or blocking a delivery of the infill material into the primary material dependent on an area in the component which is being formed.
B29C 64/165 - Processes of additive manufacturing using a combination of solid and fluid materials, e.g. a powder selectively bound by a liquid binder, catalyst, inhibitor or energy absorber
An acoustic treatment for use in an acoustic treatment for a gas turbine engine includes a sheath having a plurality of perforations. A plurality of cell structures extends from the sheath such that the sheath and the cell structures are a monolithic component. The plurality of perforations of the sheath are formed by filaments of a first material that define a first dimension of the perforations having a linear edge and filaments of a second material crossing the filaments of the first material that define a second dimension of the perforations having a linear edge. Such perforations have a non-cylindrical shape defined by the linear edges of the filaments of the first material and the filaments of the second material. A gas turbine engine is also disclosed.
B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
A method of forming a component by material extrusion includes the steps of forming a plurality of first filaments extending along at least a first axis of a three dimensional space and forming a plurality of second filaments crossing the plurality of first filaments by extending in a direction with at least a component along second and third axes in the three dimensional space.
B29C 64/118 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using filamentary material being melted, e.g. fused deposition modelling [FDM]
An aircraft system is provided that includes an aircraft airframe, a drive unit, a mechanical load, an energy module and an ejection system. The aircraft airframe has an internal compartment. The drive unit is mounted with the aircraft airframe. The mechanical load includes a mechanical load rotor. The drive unit is coupled to and configured to drive rotation of the mechanical load rotor. The energy module is disposed within the internal compartment. The energy module includes an energy source configured to power or fuel operation of the drive unit. The ejection system is configured to eject the energy module out of the internal compartment and away from the aircraft airframe.
An example method of automatically facilitating redaction of a digital model including obtaining at least metadata of a first digital model of a first system and a second digital model of a second system, wherein the first digital model and second digital model each include a plurality of respective discrete subsystems representing different functions of their respective systems, each subsystem including a plurality of respective discrete model elements, and design responsibility for the plurality of discrete subsystems is assigned to a plurality of different engineering teams. The method includes, based on the at least metadata of the first digital model indicating that the first digital model includes a first digital redaction, and further based on the first digital model and second digital model meeting at least one similarity criterion, automatically facilitating a second digital redaction in the second digital model that is based on the first digital redaction.
An example method includes storing in memory a digital model that includes a plurality of subsystems representing different functions of a system, where each subsystem includes model elements, and design responsibility for different ones of the model elements is assigned to different engineering teams. The method includes receiving, from a user not part of a first engineering team, a request to access a particular model element of a particular subsystem, wherein design responsibility for the particular model element is assigned to the first engineering team, and the particular model element includes at least one redaction implemented according to a security policy of the first engineering team. The method includes performing at least one of facilitating delivery of a redacted version of the particular model element to the user that includes the at least one redaction, and facilitating delivery of an unredacted version of the particular model element to the user.
A fluid system is provided for an aircraft engine. This fluid system includes a lubricant reservoir and a pressure relief system. The lubricant reservoir includes an internal volume. The pressure relief system includes a sensor system, a pressure relieve valve and a controller. The sensor system is configured to provide sensor data indicative of an air pressure within the internal volume. The pressure relief valve is fluidly coupled with the internal volume. The controller is configured to control operation of the pressure relieve valve based on the sensor data.
A ceramic matrix composite laminate comprises a ceramic matrix that encapsulates a plurality of layers. Each layer comprises fibers. Each layer comprises a plurality of fill fibers and a plurality of warp fibers or a plurality of bias fibers. The outermost layer contains a different concentration of fibers per unit volume than a layer located near an interior of the ceramic matrix composite laminate. A gradient in the number of fibers exists between the outermost layer and the layer located at the interior of the ceramic matrix composite laminate, or a combination thereof. A combined ceramic matrix composite comprises a plurality of composite laminates; wherein each laminate has a different fiber concentration gradient from another laminate that it is in contact with.
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
A resonator array panel includes a perforated first sheet, a second sheet, and a resonator core. The perforated first sheet includes a first sheet body. The second sheet includes a second sheet body. The second sheet body includes a second exterior side surface and a second interior side surface. The first resonator core is disposed between the perforated first sheet and the second sheet. The first resonator core includes a first plurality of sidewalls. The first plurality of sidewalls forms a first plurality of resonators between the perforated first sheet and the second sheet. The first plurality of resonators includes a first resonator. The first resonator includes a first viscoelastic body disposed within the first resonator cavity.
A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.
A turbine engine assembly includes a turbine section including at plurality of turbine stages through which the gas flow expands to generate a mechanical power output. An inter-turbine burner between at least two of the plurality of turbine stages reheats the gas flow. A condenser extracts water from the gas flow exhausted from the turbine section, and an evaporator heats the water extracted by the condenser to generate a steam flow with the steam flow communicated to the inter-turbine burner and added to the gas flow expanded through the turbine section.
Direct pin-fin cooling assemblies are disclosed for a high-power printed circuit boards (PCBs). The disclosure can solve the classical coldplate problem associated with liquid cooling of high-power PCBs namely: (1) Inhomogeneous cooling due to the calorimetric heating up of the coolant, (2) thermal interface material (TIM) related quality issues such as dry-out effects, (3) high cost due to complicated metal coldplate structure, and (4) low thermal conductivity due to multi-layer structure. This includes incorporating pin-fin direct cooling into high-power PCB structures without additional coldplate structure or TIM. In this approach, a TIM and a top plate of coldplate can be removed. Thus, the cooling performance can be improved because the thermal conductivity between a liquid coolant and a power device is increased.
A chemical vapor deposition system comprises a reactor including at least one wall extending between an inlet end and an outlet end, and an internal volume defined by the at least one wall, the inlet end, and the outlet end. The reactor further comprises a heat source in thermal communication with the internal volume, and a solid precursor container removably placed within the internal volume. The solid precursor container includes at least one internal cavity for holding an amount of the solid precursor, and an opening fluidly connecting the at least one internal cavity to the internal volume of the reactor. The solid precursor comprises at least one of aluminum, zirconium, hafnium, and a rare earth metallic element.
C23C 16/448 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for generating reactive gas streams, e.g. by evaporation or sublimation of precursor materials
A coating for an article includes a seal coat comprising self-healing particles disposed in a seal coat matrix and a bond coat disposed on the seal coat. The bond coat includes a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix. A coating for an article and a method of applying a coating to an article are also disclosed.
An energy supply system includes an electrolysis system to perform electrolysis on a first source of water, and break the water into hydrogen and oxygen components. The hydrogen and oxygen components are supplied to a power generation system. The power generation system includes a combustor receiving the hydrogen and oxygen components and is operable to combust the hydrogen and oxygen components. The combustor also receives a source of steam. Products of combustion downstream of the combustor pass over a top turbine rotor, driving the top turbine rotor to rotate. A first generator generates electricity from the rotation of the top turbine rotor.
Baffles (126) for installation within airfoils include a baffle body (1004, 704, 804) defining a feed cavity (420) and extending between inner and outer diameter (316) ends. A forward standoff shelf (812) is formed along an exterior surface of the baffle (126, 302) and defined by a depression, bend, or channel in a material of the baffle body (1004, 704, 804) extending between the inner and outer diameter (316) ends. The forward standoff shelf (812) is configured to engage with a forward rail (502) of the airfoil body (402, 702, 704, 802), and an aft standoff shelf (814) is formed along an exterior surface of the baffle body (1004, 704, 804) and configured to engage with an aft rail (504) of the airfoil body (402, 702, 704, 802). A surface of the baffle body (1004, 704, 804) between the forward standoff shelf (812) and the aft standoff shelf (814) defines a side channel surface extending in a radial direction along the baffle body (1004, 704, 804) between the outer diameter end (430, 506, 706, 914) and the inner diameter end (432, 508, 708, 916).
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix; a topcoat; and a porous interlayer disposed between the topcoat and the bond coat. The porous interlayer has a porosity that is greater than a porosity of the topcoat. A slurry composition for applying an interlayer to an article and method of applying a top coat to an article are also disclosed.
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix. At least about 10 % of the gettering particles are in a crystalline phase. The article also includes a top coat. An article is also disclosed.
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
C04B 35/14 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silica
C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C04B 41/50 - Coating or impregnating with inorganic materials
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix; and a topcoat including a constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS). An article and a method applying a calciummagnesium- alumino-silicate (CMAS)-resistant topcoat are also disclosed.
A bearing compartment seal for a gas turbine engine includes a seal ring that defines an axis and has a radially inward facing sealing surface. A seal runner is configured to rotate relative to the seal ring. The seal runner has a runner surface facing the radially inward facing sealing surface. A plurality of grooves are spaced circumferentially along the runner surface. The plurality of grooves have a length in an axial direction that is at least 50% of an axial length of the runner surface.
A gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gaspath side and an internal side that borders a cooling air cavity. The external combustion gaspath side has an associated combustion gas flow direction there along. An array of cooling holes extends through the silicon-containing ceramic wall and connects the internal side with the external combustion gaspath side. The cooling holes are oriented to discharge cooling air to the external gaspath side in a direction counter to the combustion gas flow direction.
A redox flow battery includes a cell that has first and second electrodes and an ion-exchange layer there between, first and second circulation loops that are fluidly connected with, respectively, the first and second electrodes, first and second electrolyte storage tanks in, respectively, the first and second circulation loops, first and second electrolytes contained in, respectively, the first and second circulation loops, and a Raman spectrometer on at least one of the first or second circulation loops for determining a state-of-charge of at least one of the first or second electrolytes. The Raman spectrometer includes a laser source that is rated to emit a laser of a wavelength of 694 nanometers to 1444 nanometers.
Aircraft engines and methods of operation include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section. A core condenser is arranged downstream of the turbine section of the core assembly along the core flow path, the core condenser being configured to condense water from the core flow path. A refrigeration system is operably coupled to the core condenser and configured to direct a cold stream flow path into thermal interaction with the core flow path at the core condenser and configured to control a delta temperature at which heat exchange occurs between the core flow path and the cold stream flow path.
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
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
F02C 7/16 - Cooling of plants characterised by cooling medium
F02C 7/224 - Heating fuel before feeding to the burner
F02K 3/06 - 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 with front fan
F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
A method of damping vibrations in a seal includes inserting a first wave spring between a first beam and a second beam of the seal. The seal can be for a gas turbine engine and can include a full hoop outer ring, a shoe coupled to the full hoop outer ring via the first beam (e.g., an outer beam) and the second beam (e.g., an inner beam), and the first wave spring in contact with the first beam and the second beam.
F16F 15/06 - Suppression of vibrations of non-rotating, e.g. reciprocating, systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating system using elastic means with metal springs
Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.
Vane assemblies for gas turbine engines are described. The vane assemblies 400 include a platform 404 having an interior platform surface, a forward rail 420, and an aft rail 422 defining a plenum 424. An airfoil 402 extends radially inward from the platform on a side opposite the forward and aft rails and includes a leading edge cavity 412 that is open at the platform. A platform feed structure 426 is arranged on the platform about the leading edge cavity 412 and in the plenum 424 and defines a fluid path through the forward rail 420 and into the leading edge cavity 412. A cover plate 726 is arranged on a top surface of the platform feed structure 426 and configured to fluidly separate the plenum of the platform from the leading edge cavity and define a turning plenum. The cover plate 726 defines a turning contour surface that is shaped to turn an airflow from an axial flow direction to a radial flow direction.
Vane assemblies for gas turbine engines are described. The vane assemblies 400 include a platform 404 having an interior platform surface, a forward rail 420, and an aft rail 422, wherein the interior platform surface, the forward rail, and the aft rail define a plenum 424, an airfoil 402 extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity 412 and a baffle 416 installed within the leading edge cavity, and a platform feed structure 426 arranged on the platform 404 in the plenum 424 and defining a fluid path through the forward rail 420 and into the baffle 416 of the leading edge cavity 412.
Aircraft propulsion systems and aircraft are described. The aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and an expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the expander, prior to being injected into the burner for combustion.
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
F02C 7/224 - Heating fuel before feeding to the burner
An apparatus has: a first member (120); a shaft (40; 50) rotatable relative to the first member about an axis; and a seal system (100). The seal system has a seal carrier (150) having: an axially-extending wall (156) having an inner diameter (ID) surface (160); and a radially-extending wall (154) having a first surface (158). A seal (102) is carried by the first member and has: an outer diameter (OD) surface (206); and a seal face (106). A seat (104) is carried by the shaft and has a seat face (108) in sliding sealing engagement with the seal face. One or more springs (132) bias the seal carrier relative to the first member so as to bias the seal face against the seat face. A key (240; 280; 300; 338) spans an interface between the seal carrier and the seal.
A method for producing a ceramic matrix composite component is disclosed. The method includes providing a plurality of first ceramic fiber plies including a plurality of interconnected tows and a plurality of first pores positioned between adjacent tows. The method includes applying a plurality of first ceramic particles within the plurality of first pores. Next, the method includes applying a plurality of second ceramic fiber plies onto an outer surface of the plurality of first ceramic fiber plies. The second ceramic fiber plies include a plurality of interconnected tows and a plurality of second pores positioned between adjacent tows. The method then includes applying a plurality of second ceramic particles within the plurality of second pores. Further, the plurality of second ceramic particles are larger than the plurality of first ceramic particles. Lastly, the method includes densifying the ceramic matrix composite preform to form the ceramic matrix composite component.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
An interconnect layer for an integrated circuit device includes a low radio frequency (RF) loss primary coating that forms a main portion of the interconnect layer, an opening formed in the primary coating, a high aspect ratio patternable secondary coating within the opening, and a via formed in the secondary coating. An aspect ratio of the via is greater than an aspect ratio of the opening.
H01L 23/532 - Arrangements for conducting electric current within the device in operation from one component to another including external interconnections consisting of a multilayer structure of conductive and insulating layers inseparably formed on the semiconductor body characterised by the materials
42.
SACRIFICIAL YARNS FOR USE IN CERAMIC MATRIX COMPOSITES, METHODS OF MANUFACTURE THEREOF AND ARTICLES COMPRISING THE SAME
Disclosed herein is a composite co-fiber comprising a plurality of ceramic tows; one or more sacrificial yarns; where the sacrificial yarns are operative to undergo dissolution, decomposition or melting upon being subjected to an elevated temperature; and wherein the sacrificial yarns leave open spaces in the co-fiber upon being subjected to decomposition, dissolution or melting.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C04B 38/06 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof by burning-out added substances
C22C 49/02 - Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
C22C 49/14 - Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
43.
POLYMER YARNS FOR FABRIC STABILITY AND UNIFORMITY, PLIES MANUFACTURED THEREFROM AND ARTICLES COMPRISING THE SAME
Disclosed herein is a composite ply comprising fill and warp tows; or optional axial and bias tows; wherein one or more of the fill tows and/or the warp tows or wherein one or more of the optional axial and/or bias tows comprise a polymer yarn while the remaining portion of the fill tows and/or the warp tows or the remaining portion of the bias and/or optional axial tows comprise the polymer yarn; and wherein the polymer yarn is melted to bond to the fill or warp tows to prevent removal from the ply.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
C04B 35/01 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides
C04B 35/515 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides
44.
SACRIFICAL YARN FILAMENT FOR USE IN CERAMIC MATRIX COMPOSITES AND METHODS OF MANUFACTURE THEREOF
Disclosed herein is a composite tow comprising a plurality of ceramic filaments; one or more sacrificial yam filaments; where the sacrificial yarn filaments are operative to undergo decomposition or melting upon being subjected to an elevated temperature; and wherein the sacrificial yarn filaments leave open spaces in the tow upon being subjected to decomposition, dissolution or melting; where the filaments have an average filament diameter of 5 to 15 micrometers.
Disclosed herein is a ceramic matrix composite comprising a preform comprising a plurality of plies; a ceramic matrix encompassing the plies and distributed through the plies; and thermally conducting particles distributed through the ceramic matrix. Disclosed herein is a method comprising distributing thermally conducting particles between plies in a preform; infiltrating chemical vapors of a ceramic precursor into the plies; and reacting the ceramic precursor to form a matrix.
B05D 3/10 - Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by other chemical means
B23B 7/02 - Automatic or semi-automatic machines for turning of stock
37 - Construction and mining; installation and repair services
Goods & Services
Maintenance and repair of aircraft, satellite, and weapon systems and components thereof; Information with relation to aircraft repair and maintenance; Aerospace vehicle maintenance, repair and overhaul, including parts and components thereof.
42 - Scientific, technological and industrial services, research and design
Goods & Services
Research, development, design, and testing services relating to aerospace including aeronautics systems and vehicles, electronic systems, information systems, energy systems, materials technology, environmental enhancement, satellite and weapons technology; Technology consultation and research in the field of aerospace engineering; Engineering and computer programming services for aircraft and aerospace vehicles, parts, and components; Aircraft product development, including parts and components thereof.
48.
METHOD FOR MACHINING CERAMIC WORKPIECE WITH COMPOSITE VIBRATION
A method for machining a ceramic workpiece includes providing a sonotrode that has a transducer and a horn arranged along an axis, and the horn has helical slots and terminates at a tip, bringing the tip into proximity of the ceramic workpiece and providing an abrasive media to a work zone around the tip, using the transducer to produce ultrasonic vibration that axially propagates down the horn and causes axial vibration at the tip, and the helical slots convert a portion of the axial vibration to torsional vibration at the tip, and the axial vibration and the torsional vibration causing the abrasive media to abrade the ceramic workpiece in the work zone and thereby remove a localized portion of the ceramic workpiece.
B06B 3/04 - Processes or apparatus specially adapted for transmitting mechanical vibrations of infrasonic, sonic or ultrasonic frequency involving focusing or reflecting
In a redox flow battery (RFB), the base solvent of the electrolytes tends to migrate across the barrier layer from one electrode toward the other. This can result in a volume and concentration imbalance between the electrolytes that is detrimental to battery efficiency and capacity. Compatible electrolytes can be mixed to rebalance the system, but for incompatible electrolytes mixing is not a viable option. To this end, the RFB herein includes a separator that recovers base solvent from the vapor phase of one of the electrolytes and returns the recovered base solvent to the other electrolyte to thereby reverse the imbalance.
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
51.
CELL FOR ELECTROCHEMICALLY DETERMINING ACTIVE SPECIES CONCENTRATIONS IN REDOX FLOW BATTERIES
A redox flow battery system with a redox flow battery includes a redox flow cell, and a supply/storage system external of the redox flow cell. The supply/storage system includes first and second electrolytes for circulation through the redox flow cell. At least the first electrolyte is a liquid electrolyte that has electrochemically active species with multiple, reversible oxidation states. A secondary cell is fluidly connected with the first electrolyte and is operable to monitor concentration of one or more of the electrochemically active species. The secondary cell includes a counter electrode, a working microelectrode, and an ionically conductive path formed by the first electrolyte between the counter electrode and the working microelectrode.
Disclosed is a coated composite comprising a seal coat disposed on a composite material wherein the seal coat comprises protective particles and a matrix.
A turbine engine system includes an aircraft systems including at least one hydrogen fuel tank, engine systems comprising a compressor section, a combustor section having a burner, and a turbine section, and a hydrogen fuel flow supply line configured to supply hydrogen fuel from the at least one hydrogen fuel tank into the burner for combustion. The turbine engine system has a bypass ratio between 5 to 20.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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
F02C 7/16 - Cooling of plants characterised by cooling medium
A method is provided for treating a fuel system of a turbine engine. During this method, a treatment system is connected to the turbine engine. Preservation fluid is drawn out of the fuel system using the treatment system.
F02M 63/00 - SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF - Details, component parts or accessories of fuel-injection apparatus, not provided for in, or of interest apart from, the apparatus of groups or
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
F01D 25/32 - Collecting of condensation water; Drainage
A preform comprising a first sub-laminate comprising a plurality of layers and a second sub-laminate comprising a plurality of layers. The first sub-laminate comprises a first unit cell comprising a first volume fraction of tows, where the first volume fraction of tows comprise first tows having a first tow spacing between successive first tows. The second sub-laminate comprises a second unit cell comprising a second volume fraction of tows, where the second volume fraction of tows comprise second tows having a second tow spacing between successive second tows. The first volume fraction of tows in the first unit cell is equal to the second volume fraction of tows in the second unit cell. The second tow spacing is less than the first tow spacing.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 19/06 - Layered products essentially comprising natural mineral fibres or particles, e.g. asbestos, mica next to a fibrous or filamentary layer
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
A ceramic matrix composite laminate comprises a ceramic matrix that encapsulates a plurality of layers. Each layer comprises fibers. Each layer comprises a plurality of fill fibers and a plurality of warp fibers or a plurality of bias fibers. The outermost layer contains a different concentration of fibers per unit volume than a layer located near an interior of the ceramic matrix composite laminate. A gradient in the number of fibers exists between the outermost layer and the layer located at the interior of the ceramic matrix composite laminate, or a combination thereof. A combined ceramic matrix composite comprises a plurality of composite laminates; wherein each laminate has a different fiber concentration gradient from another laminate that it is in contact with.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 19/06 - Layered products essentially comprising natural mineral fibres or particles, e.g. asbestos, mica next to a fibrous or filamentary layer
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool, a high speed spool, and a combustor; a lubrication circuit comprising a bearing compartment, a supply pump, and a scavenger pump; an electric motor configured to augment rotational power of the low speed spool or the high speed spool; and a controller operable to: control the electric motor based upon a pressure differential between an interior of the bearing compartment and an exterior of the bearing compartment and to drive rotation of the low speed spool and/or the high speed spool via the electric motor responsive to a thrust command while fuel flow to the combustor is inhibited.
Apparatus and associated methods relate to providing robust synchronization of a Radio-Frequency (RF) communication in a severe-fading environment. A first portion of a detected RF signal is auto-correlated with a second portion of the detected RF signal. The first and second portions are time-separated by the predetermined time delay separating the first and second code-sequences. A third portion of the detected RF signal is sync-correlated with a sync-sequence so as to generate a sync-correlation signal. The third portion is of the predetermined length of the sync sequence and includes the first and second portions of the detected RF signal used to generate the auto-correlation signal. The auto-correlation signal is multiplied by the sync-correlation signal so as to generate a combined synchronization signal. A peak in the combined synchronization signal is then detected. This peak can be indicative of a synchronization time of an authorized communication.
A system and method for automatically assessing pilot readiness via a plurality of biometric sensors includes continuously receiving biometric data including vision-based data; the biometric vision-based data is compared to a task specific set of movements and facial expressions as defined by known anchor points. A deviation is calculated based on the vision-based data and task specific set of movements and expressions, and the deviation is compared to an acceptable threshold for pilot readiness. Other biometric data may be included to refine the readiness assessment.
A61B 5/308 - Input circuits therefor specially adapted for particular uses for electrocardiography [ECG]
A61B 5/31 - Input circuits therefor specially adapted for particular uses for electroencephalography [EEG]
A61B 5/00 - Measuring for diagnostic purposes ; Identification of persons
G10L 13/02 - Methods for producing synthetic speech; Speech synthesisers
G10L 25/57 - Speech or voice analysis techniques not restricted to a single one of groups specially adapted for particular use for comparison or discrimination for processing of video signals
G06V 20/40 - Scenes; Scene-specific elements in video content
G06V 20/59 - Context or environment of the image inside of a vehicle, e.g. relating to seat occupancy, driver state or inner lighting conditions
G06V 40/18 - Eye characteristics, e.g. of the iris
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
60.
ENVIRONMENTAL BARRIER COATING AND METHOD OF FORMING THE SAME
A method of applying a coating to a substrate includes forming a slurry by mixing elemental precursors of gettering particles, diffusive particles, matrix material, and a carrier fluid; applying the slurry to a substrate; and sintering the slurry to form a composite material. The sintering causes the elemental precursors to react with one another to form gettering particles. An article is also disclosed.
C23C 16/22 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the deposition of inorganic material, other than metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
A redox flow battery includes a redox flow cell and a supply and storage system external of the redox flow cell. The supply and storage system includes first and second electrolytes for circulation through the redox flow cell. The first electrolyte is a liquid electrolyte having electrochemically active manganese species with multiple, reversible oxidation states in the redox flow cell. The electrochemically active manganese species may undergo reactions that cause precipitation of manganese oxide solids. The first electrolyte includes an inhibitor that limits the self-discharge reactions. The inhibitor includes an oxoanion compound.
A method for configuring a fixture for use in machining of sequential parts via a machine tool, for a planned machining movement of the machining element, uses a model of the part and fixture. Respective reaction forces at the plurality of part contact references are computed. Responsive to computation of a negative reaction force at a said part contact reference, a modification is made to a machining parameter.
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control (DNC), flexible manufacturing systems (FMS), integrated manufacturing systems (IMS), computer integrated manufacturing (CIM)
In a method for forming an abradable material (36), the abradable material has at least 20% by volume rutile titania (44) and hBN (46). The method includes: blending a first titania powder having an oxygen debit of at least 5.0% with a second titania powder having an oxygen debit, if any, of less than 1.0%. The blend is thermal sprayed. The sprayed blend is then oxidized.
C04B 35/46 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on titanium oxides or titanates
C04B 35/20 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in magnesium oxide
C04B 35/22 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in calcium oxide
C04B 35/462 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on titanium oxides or titanates based on titanates
C04B 35/583 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides based on boron nitride
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
Apparatus and associated methods relate to a pick & place system that uses a magnetic core for both magnetic coupling with an assembly component and heating of the assembly component. The magnetic core has a component engagement surface configured to magnetically and thermally engage the component. A controller is configured to provide both AC current and DC current to an inductive coil wound about the magnetic core. DC current provided to the inductive coil induces a magnetic field within the magnetic core, thereby magnetically attracting the component when engaged with the component engagement surface. AC current provided to the magnetic core inductively heats the magnetic core, thereby heating the component when engaged with the component engagement surface.
Disclosed is a heat exchanger having: an inlet manifold configured to receive a cooling fluid; a reservoir; first and second condenser arms connected between and that respectively fluidly couple the inlet manifold to the reservoir, so that fluid received at the inlet manifold travels from the inlet manifold into the reservoir; and an outlet pump having a pump inlet port coupled to the reservoir and having a pump outlet port, wherein the inlet manifold, the reservoir, the first and second condensers, in combination, form a continuous shape.
F28D 7/00 - 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
66.
HEADER GUIDING FLUID FLOW TO AND FROM COOLING CHANNELS IN A HIGH DENSITY MOTOR
A header for an electric machine that include a stator core and one or more windings that include coolant passages formed therein. The header includes an inlet to receive a coolant, an outlet though which the coolant exits the header, an inlet plenum fluidly connected to the inlet, and an outlet plenum fluidly separated from the inlet plenum and fluidly connected to the outlet. The inlet and outlet plenums each have a varying cross section that varies from a top of the header as compared to a bottom of the header.
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 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
A stator includes a stator hub, a plurality of stator teeth extending from stator hub that define a stator slot and at least one winding disposed in the stator slot, the winding including a cooling passage formed therein through. The cooling passage is connected to an inlet plenum and an outlet plenum. The stator can also include coil separators that include cooling passages.
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 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
Electric motors and stators thereof are described. The stators of the electric motors include a first header, a second header fluidly connected to the first header, a plurality of windings fluidly connected to the first header and the second header to receive a cooling fluid passing from the first header to the second header along one or more flow channels, and one or more phase-change material elements arranged to thermally interact with at least one of the first header, the second header, the one or more flow channels, and the plurality of windings.
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 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 9/20 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil wherein the cooling medium vaporises within the machine casing
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
A method for maintaining a redox flow includes draining a first battery electrolyte solution from a redox flow battery cell, the cell including a separator layer arranged between a first electrode and a second electrode, a first circulation loop configured to provide the first battery electrolyte solution to the first electrode and a second circulation loop configured to provide a second battery electrolyte solution to the second electrode; and flowing a non-battery electrolyte solution through the first electrode. The non-battery electrolyte removes at least a portion of the solid precipitates from at least one of the first electrode and the separator layer. The method also includes draining the non-battery electrolyte solution from the cell and returning the first battery electrolyte solution to the cell. A method for a redox flow battery and a redox flow battery are also disclosed.
A method for a redox flow battery includes using a cell of a redox flow battery to store electrical energy and discharge the stored electrical energy. The using includes circulating a first electrolyte solution through a first circulation loop in fluid connection with the first electrode of the cell; circulating a second electrolyte solution through a second circulation loop in fluid connection with the second electrode of the cell; and at least one of a first element from the first electrolyte solution in the first electrode permeates through the separator layer and precipitates as a first solid product in the second electrode and a second element from the second electrolyte solution permeates through the separator layer and precipitates a second solid product in the first electrode. The method also includes removing at least a portion of the first solid product or the second solid product from the first electrode and the second electrode, respectively.
C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
A coated substrate has a substrate and a coating system having one or more ceramic layers. At least a first layer of one of the one or more ceramic layers is a columnar layer having as-deposited columns and intercolumn gaps. The intercolumn gaps have a mean width at least one of: at least 4.0 micrometers; and at least 1.5% of a thickness of said first layer.
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C04B 35/50 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare earth compounds
C22C 19/03 - Alloys based on nickel or cobalt based on nickel
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
73.
INTERMEDIATE TEMPERATURE METAL SUPPORTED SOLID OXIDE ELECTROLYZER
A metal-supported electrolyzer includes an electrolysis cell that has, in stacked order, an electrode unit having a first solid oxide electrode layer, a solid oxide electrolyte layer that is proton-conductive in a temperature range of 650° C. or lower, and a second solid oxide electrode layer. A porous metal sheet in contact with the second solid oxide electrode layer supports the electrode unit, a metal separator sheet bonded to the porous metal sheet, and a metal interconnect backing the metal separator sheet.
C25B 9/73 - Assemblies comprising two or more cells of the filter-press type
C25B 9/23 - Cells comprising dimensionally-stable non-movable electrodes; Assemblies of constructional parts thereof with diaphragms comprising ion-exchange membranes in or on which electrode material is embedded
H01M 8/126 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte characterised by the process of manufacturing or by the material of the electrolyte the electrolyte consisting of oxides the electrolyte containing cerium oxide
C25B 15/08 - Supplying or removing reactants or electrolytes; Regeneration of electrolytes
H01M 4/86 - Inert electrodes with catalytic activity, e.g. for fuel cells
74.
Redox flow battery with electrolyte balancing and compatibility enabling features
A redox flow battery includes first and second cells. Each cell has electrodes and a separator layer arranged between the electrodes. A first circulation loop is fluidly connected with the first electrode of the first cell. A polysulfide electrolyte solution has a pH 11.5 or greater and is contained in the first recirculation loop. A second circulation loop is fluidly connected with the second electrode of the second cell. An iron electrolyte solution has a pH 3 or less and is contained in the second circulation loop. A third circulation loop is fluidly connected with the second electrode of the first cell and the first electrode of the second cell. An intermediator electrolyte solution is contained in the third circulation loop. The cells are operable to undergo reversible reactions to store input electrical energy upon charging and discharge the stored electrical energy upon discharging.
A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.
A heat exchanger plate provides heat transfer between a first flow along a first flowpath and a second flow along a second flowpath. The heat exchanger plate has a substrate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal portion having a plurality of inlet ports along the first flowpath and a plurality of outlet ports along the first flowpath; and a plurality of passageways along the first flowpath. Each passageway extends between a respective associated said inlet port of the plate and a respective associated said outlet port of the plate.
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
F28F 3/00 - Plate-like or laminated elements; Assemblies of plate-like or laminated elements
F28D 7/08 - 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 otherwise bent, e.g. in a serpentine or zig-zag
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/12 - Elements constructed in the shape of a hollow panel, e.g. with channels
An alloy that may include nickel, aluminum from 4.8 wt.% to 5.15 wt.%;cobalt from 18 wt.% to 19 wt.%, chromium from 11.9 wt.% to 12.9 wt.%, molybdenum from 2.8 wt.% to 3.6 wt.%, and niobium from 0.05 wt.% to 0.1 wt.%. The alloy may further include tungsten from 0.05 wt.% to 0.1 wt.%. The alloy may further include tantalum from 0.05 wt.% to 0.1 wt.%.
A heat exchanger for providing thermal energy transfer between a first flow along a first flowpath and a second flow along a second flowpath has a plate bank having a plurality of plates, each plate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. An inlet manifold has at least one inlet port and at least one outlet port. An outlet manifold has at least one outlet port and at least one inlet port. The first flowpath passes from the at least one inlet port of the inlet manifold, through the at least one passageway of each of the plurality of plates, and through the at least one outlet port of the outlet manifold.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/08 - Elements constructed for building-up into stacks, e.g. capable of being taken apart for cleaning
B21D 53/04 - Making other particular articles heat exchangers, e.g. radiators, condensers of sheet metal
F28F 1/26 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending transversely the means being integral with the element
F28F 9/26 - Arrangements for connecting different sections of heat-exchange elements, e.g. of radiators
F28F 3/04 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
A turbine engine has: a first member (22) having a surface bearing an abradable coating, the abradable coating (36) being at least 90% by weight ceramic; and a second member (24) having a surface bearing an abrasive coating. The abrasive coating (56) has a metallic matrix (64) and a ceramic oxide abrasive (66) held by the metallic matrix, the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating. At least 50% by weight of the ceramic abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
B01J 21/06 - Silicon, titanium, zirconium or hafnium; Oxides or hydroxides thereof
C04B 35/20 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in magnesium oxide
C04B 35/5831 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides based on boron nitride based on cubic boron nitride
A turbine engine includes a duct defining an annular passage, at least two heat exchangers arranged within the annular passage and spaced circumferentially apart, a passage between the at least two heat exchangers, and a forward flow control device operable for controlling airflow through the passages.
A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the article wall between the inner portion and the outer portion of the article wall. A plurality of second cooling passage networks each define second dimensions and are embedded into the article wall between the inner portion and the outer portions of the article wall. The plurality of first and second cooling passage networks are arranged in one of a first column of radially positioned networks and a second column of radially positioned networks. At least one cooling hole in the first column of radially positioned networks is located upstream of and radially aligned with at least one second mid-span wall between adjacent networks in the second column of networks.
A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.
A brake roller may comprise a brake shaft and a brake stack assembly located around the brake shaft. A one-way jaw clutch assembly may be configured to apply a force to the brake stack. A roller shell may be located radially outward of the brake stack. The one-way jaw clutch assembly may be configured to vary the force applied to the brake stack in response to a rotation of the roller shell in a circumferential direction.
F16D 11/10 - Clutches in which the members have interengaging parts actuated by moving a non-rotating part axially with clutching members movable only axially
F16D 41/18 - Freewheels or freewheel clutches with non-hinged detent
F16D 55/39 - Brakes with a plurality of rotating discs all lying side by side mechanically actuated by means of an intermediate leverage
84.
CMC COMPONENT ARRANGEMENT AND METHOD OF MANUFACTURE
A method of manufacturing a component includes forming an inner wrap about a mandrel. The inner wrap has first and second walls joined by a base portion and an outer wall. A rod is arranged at each of the first and second walls. An outer wrap is formed about the inner wrap and the rods to form a body. Features are formed in the first and second walls.
An acoustic liner for a gas turbine engine includes an acoustic panel that is curved about a central axis. The acoustic panel includes a support backing, a face sheet, and a cellular structure disposed between the support backing and the face sheet. The face sheet has elongated slots that extend along respective slot centerlines in the plane of the face sheet. The slot centerlines are sloped at oblique angles to the central axis.
An airfoil for a gas turbine engine includes an airfoil body extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suction sides separated in a thickness direction. The airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region. A plurality of cover skins is welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets.
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
F04D 29/26 - Rotors specially adapted for elastic fluids
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
An occupant camera system for an aircraft ejection assembly may comprise a fixed structure and a camera mounted to the fixed structure. A digital video recorder may be mounted to the fixed structure and electrically coupled to the camera. A switch may be electrically coupled to the digital video recorder, and a battery may be electrically coupled to the switch.
A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the ECU being configured to determine whether the electric motor system and/or the heat engine system are in a normal mode such that the electric motor system and/or the heat engine can provide a predetermined amount of torque (e.g., full power). The ECU can be configured to receive a total torque setting and split output power between the electric motor system and the heat engine system in accordance with the normal mode as a function of the total torque setting. The ECU can be configured to detect and command recharging or regenerating of the battery system in some flight conditions.
A hybrid electric engine control module (ECU) can be configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to determine whether at least one of the electric motor system or the heat engine system are in a normal mode such that one of the electric motor system and/or the heat engine can provide a predetermined amount of torque. The ECU can be configured to switch to a degraded mode if either of the electric motor system or the heat engine system cannot provide the predetermined amount of torque. In the degraded mode the ECU can be configured to control the electric motor system and the heat engine system differently than in the normal mode or to not control one or both of the electric motor system or the heat engine system.
An electrical power system is disclosed for an aircraft having a hybrid-electric propulsion system, which includes a battery assembly for storing energy, an electric motor controller operatively connected to the battery assembly for conditioning and controlling power to an electric motor, and an electric motor receiving power through the motor controller for delivering torque to a shaft of the hybrid-electric propulsion system.
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
B60L 15/20 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performance; Adaptation 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 for control of the vehicle or its driving motor to achieve a desired performance, e.g. speed, torque, programmed variation of speed
H02H 3/00 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection
H02J 1/00 - Circuit arrangements for dc mains or dc distribution networks
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H02P 7/00 - Arrangements for regulating or controlling the speed or torque of electric DC motors
H05K 10/00 - Arrangements for improving the operating reliability of electronic equipment, e.g. by providing a similar stand-by unit
B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
91.
Systems and methods for brake failure detection using retract braking
A system for detecting aircraft brake failure using retract braking may comprise a landing gear including a wheel, a brake coupled to the wheel, and a wheel sensor coupled to the wheel. A brake controller may be coupled to the brake and the wheel sensor. The brake controller may be configured to receive a begin retract braking signal, command the brake to apply a braking force to the wheel, calculate a wheel speed characteristic using data from the wheel sensor, and determine whether the wheel speed characteristic indicates a failure of the brake.
B60T 8/32 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
B60T 8/88 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration with failure responsive means, i.e. means for detecting and indicating faulty operation of the speed responsive control means
B60T 17/22 - Devices for monitoring or checking brake systems; Signal devices
B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
A gas turbine engine includes a core engine, a fan section, and a superposition gearbox that includes a sun gear. A plurality of intermediate gears are engaged to the sun gear and supported in a carrier and a ring gear circumscribing the intermediate gears. The core engine drives the sun gear and an output from the superposition gearbox driving the fan section. An electric motor is coupled to a portion of the superposition gearbox to provide a portion of power to drive the fan section through the superposition gearbox.
F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/06 - 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 with front fan
93.
Adjustable upper thoracic support for aircraft seat
A seat for an aircraft may comprise a seat pan and a back support coupled to the seat pan. An upper thoracic support may be located proximate an end of the back support opposite the seat pan. The upper thoracic support may be configured to rotate relative to the back support. A headrest may be coupled to the upper thoracic support.
Brake disks with integrated heat sink are provided. Brake disk includes a fiber-reinforced composite material and an encapsulated heat sink material impregnated into the fiber-reinforced composite material. The encapsulated heat sink material comprises a heat sink material encapsulated within a silicon-containing encapsulation layer. Methods for manufacturing the brake disk with integrated heat sink and methods for producing the encapsulated heat sink material are also provided.
An aircraft system includes a component configured to operate with a minimum power demand. The aircraft system also includes an auxiliary power unit including an engine. The auxiliary power unit is configured to power the component and to operate the engine in a plurality of operating modes including a power mode and a standby mode. The auxiliary power unit generates a first power output at least equal to the minimum power demand during the power mode. The auxiliary power unit generates a second power output less than the minimum power demand during the standby mode.
37 - Construction and mining; installation and repair services
Goods & Services
Providing technical support, namely, technical advice and predictive analysis concerning maintenance and repair of individual aircraft engines and fleets of aircraft engines utilizing operational data.
A system and methods are provided for removing core elements of cast components. In one embodiment, a method includes controlling a first high temperature autoclave cycle for a cast component in a vessel with a first solution concentration to remove at least a first portion of core elements, wherein the first solution concentration, temperature and pressure in the vessel are controlled to expose one or more casting pins in the cast component. The method may also include controlling a second high temperature autoclave cycle for the cast component in the vessel with second solution concentration, wherein the second solution concentration, temperature and pressure in the vessel during the second high temperature autoclave cycle are controlled to loosen one or more of the casting pins from the cast component, and controlling one or more low temperature autoclave cycles to remove core and casting pins from the cast component.
A horizontal support tool for an engine build stand, the horizontal support tool includes a support tube along an axis and a tie shaft between a handle and a puck assembly, said puck assembly including a puck selectively extendable and retractable transverse to the axis in response to rotation of the handle. A method of horizontally assembling a portion of a gas turbine engine including mounting a first module to an engine build stand; installing a horizontal support tool into the first module, the horizontal support tool supported in a spherical bearing supported by the engine build stand; and installing a second module to the first module, the horizontal support tool operable to at least partially support second module.
F16M 11/20 - Undercarriages with or without wheels
B64F 5/50 - Handling or transporting aircraft components
B25H 1/00 - Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
F16M 1/04 - Frames or casings of engines, machines, or apparatus; Frames serving as machinery beds for rotary engines or similar machines
