Hamilton Sundstrand Patente

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A compressor outlet housing with a housing body (119) has a volute and a radially inwardly extending wall (58) extending from a radially inner surface of the volute. The radially inwardly extending wall extends inwardly to a ledge (39). A radially inwardly extending web (38) extends to a bearing support (32). A fillet (148) which will face an impeller when the compressor outlet housing is mounted in a compressor. The fillet connects the ledge to the web. An erosion resistant coating (200) is formed on the fillet. In addition, a compressor incorporating the compressor housing is disclosed as is a method of repairing a compressor outlet housing.

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A method of forming a housing for an ACM (10), having steps of: forming a base (80): a first section (100) adjacent to a seal (23) of an ACM compressor rotor (22) when installed; a second section (100) that is fixed to an ACM forward frame member (25) when installed; a third section (100) adjacent to a bearing (32) and sleeve (58) disposed around an ACM compressor rotor shaft (54) when installed, forming the base (80) includes: printing thermoplastic polymer surfaces (200, 210) from thermoplastic polymers that are disposed against each other, the thermoplastic polymer surface having differing CTEs; forming a lower support section (82) on the base (80) by printing, layer by layer, along the plurality of discrete sections of the base (80) a mixture of a third thermoplastic polymer and a catalyst (240) formed with metal; and forming an upper support section (84) on the housing (46) by depositing on the lower support section (82), along each of the discrete sections, via electrolysis deposition, a metallic coating.

A method of forming a seal plate (46) for an ACM (10), having steps of: forming a base (80) having a first section (100) exposed to flow from an ACM first stage turbine inlet (38) when installed; a second section (110) secured to an ACM compressor shroud (18); a third section (120) secured to a first stage nozzle and ACM shroud (32) when installed; a fourth section (130) that is adjacent to a rotor blade of the ACM compressor rotor (14) when installed, forming the base (80) includes: printing thermoplastic polymer surfaces from thermoplastic polymers, that are disposed against each other, the thermoplastic polymer surfaces having differing CTEs; forming a lower support section (82) on the base (80) by printing along the discrete sections a mixture of a third thermoplastic polymer and a catalyst (240) formed with metal; and forming an upper support section (84) on the seal plate (46) by depositing on the lower support section (82), along the discrete sections, via electrolysis deposition, a metallic coating.

An engine system (30) for an aircraft (1) comprising a propulsor (10) configured to drive the aircraft (1), a thermal combustion engine (14) configured to drive the propulsor (10), an electric motor (16) connected to the thermal combustion engine (14) and configured to drive the propulsor (10), a power converter (18) configured to apply a torque to the electric motor (16) and generate electric energy from the torque applied to the electric motor (16), and an engine controller (24), the engine controller (24) being configured to determine a current power output (P) of the thermal combustion engine (14), determine an optimum power output (P2) of the thermal combustion engine (14) based on current operating conditions, and vary the torque applied to the electric motor (16) so as to vary a load on the thermal combustion engine (14), wherein the torque may be varied by an amount required to vary the power output of the thermal combustion engine (14) to the determined optimum power output (P2).

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This disclosure relates to the use of fibre optics for distributed environmental condition and/or air quality sensing such as, but not limited to, sensing air quality in enclosed areas of an aircraft such as the passenger cabin. Fibre optics can be used for sensing and for communication and are therefore well suited to the distributed sensing of environmental conditions such as temperature, relative humidity, gas and particulate composition within spaces of the aircraft e.g. the cabin, cargo space, cockpit, electronics bay etc. and in related systems such as the environmental control system (ECS), the cabin recirculation system, bleed air system etc.

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A system includes a fuel cell stack (102). A heat exchanger (104) has an air passage (106) in thermal communication with an H<2>O passage (108) for heat exchange between air and H<2>O. An exhaust outlet (110) of the fuel cell stack is connected in fluid communication with an H<2>O inlet (112) of the heat exchanger for supplying H<2>O to the heat exchanger.

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A ram air turbine (RAT) restow system (100) includes an actuator assembly (26) with a piston (42) interposed between an upper fluid compartment (53) and a lower fluid compartment (52). The actuator assembly (26) is configured to selectively move the piston (42) between a deployed position and a stowed position. A hydraulic restow circuit is interposed between the actuator assembly (26) and a hydraulic fluid system that is configured to output fluid. The hydraulic restow circuit includes a restow valve configured to operate in a first position that establishes a first fluid path to deliver the fluid to the upper fluid compartment and a second position that establishes a second fluid path to deliver the fluid to the lower fluid compartment.

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An example method of making a component includes providing a digital model of a component to software, the software operable to slice the model into layers and raster each layer into segments, the segments delineated by raster lines. The method further includes depositing a layer of powder onto a platform, compacting the layer of power into a compacted layer, sintering the compacted layer along lines corresponding to the raster lines using a laser, wherein the laser operates at a first power and a first scan speed, the first power being between about 200 and 230 W, then sintering the compacted layer along a perimeter of the compacted layer using the laser to form a unitary layer, wherein the laser operates at a second power and a second scan speed, the second power being between about 100 and 200 W. An apparatus for making a component is also disclosed.

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A method of tracking an engine cooler (28) in an aircraft includes recording an orientation of the engine cooler as orientation N. Prognostic health management data (52) of the aircraft is tracked. A maintenance check of the aircraft is performed based on the tracked prognostic health management data. Whether to rotate an orientation of the engine cooler is determined with an aircraft maintenance database (50) based on the tracked prognostic health management data of the aircraft. A recommendation is provided by the aircraft maintenance database as to whether to rotate the engine cooler. The orientation of the engine cooler is recorded as orientation N+1.

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