Hamilton Sundstrand Patente

A heat exchanger header includes a first end (103) including a port (115) configured to receive a first fluid flowing in a first direction. The heat exchanger header includes a second end (120) configured to output the first fluid in the first direction. A length of the heat exchanger header in a second direction different from the first direction decreases from a longest portion of the heat exchanger header to the first end (103) and from the longest portion of the heat exchanger header to the second end (120). The heat exchanger header is absent internal supports.

Aircraft air cycle machines include a first stage turbine (126), a second stage turbine (132), and a duct (204) arranged between the first stage turbine (126) and the second stage turbine (132). A plate-fin coalescer (210) is arranged along the duct (204). The plate-fin coalescer (210) includes a housing (302), a first fin layer arranged within the housing (302), a second fin layer arranged within the housing (302), and a first parting sheet arranged between the first fin layer and the second fin layer. Each of the first fin layer and the second fin layer include a plurality of fin elements (402) arranged in substantially parallel orientation relative an axis through the housing (302), and channels (406) are defined between adjacent fin elements of the plurality of fin elements (402) of each of the first fin layer and the second fin layer. Moisture carried on a flow through the channels (406) will impinge upon surfaces of the fin elements and coalesce into water droplets for removal.

An environmental control system of a vehicle includes an inlet (22) configured to receive a medium and an outlet for receiving a conditioned form of the medium. The conditioned form of the medium at the outlet is for a cabin of the vehicle. A thermodynamic device (40) in fluid communication with the inlet (22). includes a compressor (42) having a compressor outlet (52) and a turbine (44) having a turbine inlet (45). The turbine (44) and the compressor (42) are operably coupled by a shaft. The compressor outlet (52) is fluidly connected to the turbine inlet (45) such that at least a portion of the medium is provided to the compressor (42) and the turbine (44) in series. The outlet and the turbine (44) are arranged in parallel relative to a flow of the medium, and the flow of the medium at a location downstream from the turbine (44) is configured as a heat sink to cool the medium to be provided to the cabin.

A fuel system (200) for managing the flow of fuel to an engine having a metering valve (201), a bypass valve (211), and a shutoff valve. The system is configured to allow a primary flow of fuel in a first state to flow through the shutoff valve to the metering valve and out to an output line. In a second state the fuel system is configured to shut off the primary flow at the shutoff valve and metering valve to prevent the primary flow from traveling to the output line. The bypass valve is configured to receive the primary flow and is closed in the first state. In the second state, the metering valve closes, opening a window (220) for a secondary flow path to a return line (237). When fuel flows through the secondary flow path the bypass valve opens. Wherein when the bypass valve is open the primary flow flows through the bypass valve to a return line. In addition, the bypass valve provides a secondary flow path to the shutoff valve which closes the shutoff valve.

A seal system for controlling dampening in a journal bearing system. The seal system includes a plurality of seals that include a first seal (24) and a second seal (26). The first seal (24) is operable to provide a first range of dampening compliance under a first range of journal bearing operating conditions. The second seal (26) is operable to provide a second range of dampening compliance under a second range of journal bearing operating conditions. The first range of dampening compliance is different from the second range of dampening compliance.

An aircraft system, having: a section of a fuselage (2) surrounding an interior portion of an aircraft; an aperture (130) defined along the section of the fuselage (2); an inlet scoop at the aperture (130); an inlet channel (140) extending away from the inlet scoop to the interior portion of the aircraft; and a Ram Air Turbine (RAT) connected to the inlet channel, wherein the RAT is fixed within the interior portion of the aircraft.

A hydraulically driven fluid injection system comprising a reservoir (140) having a first and second chamber and a piston (142) separating the first and second chamber. A reservoir control valve (124) to control the input of a first fuel source to the first chamber. The reservoir control may operate by having an open and a closed state. Alternatively, the reservoir control may have a first mode, a second mode, and a third mode. A second fuel may be provided to the second chamber and a metering valve may be utilized to control the flow of the second fuel to an injector. When the secondary fuel is desired, the reservoir control valve may open to allow the primary fuel to pressurize the first chamber. The result of the pressure on the first chamber causes the piston to apply a pressure to the second chamber. The metering valve may then allow the secondary fuel to flow from the second chamber to an injector.

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A fuel system (100) can include a selection and shutoff valve, SSOV, (101) configured to allow a primary flow having a primary flow pressure (P3) to pass therethrough in a first state such that the primary flow can travel to an output line (103). The SSOV can also be configured to shut off the primary flow in a second state to prevent the primary flow from travelling to the output line. In the second state, the SSOV can be configured to allow a secondary flow from a secondary flow source (105) to pass therethrough such that the secondary flow can travel to the output line (103).

A method for detecting an insulation fault in an unearthed electrical system, the system comprising a first rail and a second rail, each rail having an insulation resistance. The method comprises, in an initial stage: connecting the first rail to a relative ground through a first resistive component, wherein the first rail has an initial stage first rail voltage in the initial stage; and charging a capacitor to a capacitor voltage using the first rail, wherein the capacitor voltage is indicative of the initial stage first rail voltage. In a subsequent stage: connecting the second rail to the relative ground through a second resistive component; wherein the first rail has a subsequent stage first rail voltage; and determining if a fault has occurred by using the capacitor voltage and the subsequent stage first rail voltage.

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A heat exchanger includes a first set of fins (82), a second set of fins (90), and an exterior wall. The first set of fins extend radially and are coaxial with each other. The first set of fins forms a first set of channels. The second set of fins extend radially and are coaxial with each other. The second set of fins forms a second set of channels. Channels (118) of the first and second sets of channels are disposed in an alternating pattern in a circumferential direction of the heat exchanger. The first and second sets of fins are integrally formed together. A cross-sectional width of a channel of at least one of the first set of channels and the second set of channels increases as a radial distance from a centerline axis of the heat exchanger increases.

A pressure relief valve controller (PRVC) (100) includes a housing (102) having a spring (104), a spring seat (106) connected to the spring (104), a piston (108), and a portion of which is disposed between the spring seat (106) and the piston, wherein one or more grooves and/or protrusions are disposed on at least one of the spring seat (106) or the piston (108). The diaphragm (110) can conform to the one or more grooves (116) of the spring seat (106) thus preventing diaphragm rupture due to excess pressure without affecting calibrations of current PRVCs.

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A pressure sensing system includes a housing (102) that houses one or more pressure transducers (104) therein. A tube (110) is sealed to the housing at a first end (111) of the tube. One or more pressure transducers (104) are in fluid communication with a second end (113) of the tube through an inner passage of the tube for sensing pressure at the second end of the tube.

A power generation system for an aircraft, the power generation system comprising: a hydrogen fuel cell; an air supply system configured to supply air to the aircraft, the air supply system comprising an ORC-air heat exchanger; and an organic Rankine cycle (ORC) system comprising an organic fluid circuit, wherein the organic fluid circuit is configured to receive excess fuel cell heat from the hydrogen fuel cell to heat organic fluid in the organic fluid circuit, wherein the organic fluid circuit passes through the ORC-air heat exchanger such that the supply air heats the organic fluid in the organic fluid circuit, wherein the ORC system is configured to extract power from the organic fluid.

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A rotor for a rotary machine includes a hub (100) centered on a central axis, the hub (100) comprising a shaft portion (118) extending along the central axis, a disk portion (120) circumferentially disposed about the shaft portion (118), a platform portion as a radially outermost extent of the shaft portion (118) and the disk portion (120), and a branched support structure extending radially inward from the platform portion. The rotor further includes a plurality of blades extending outward from the platform portion of the hub (100). The branched support structure comprises a hub region and a blade support region associated with one blade of the plurality of blades.

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A wedge (32) for use in an electric machine includes a central portion (40) comprising at least a first material, a first wing (46) integrally attached to the central portion (40), and a second wing (48) integrally attached to the central portion (40) opposite the first wing (46), wherein the first wing (46), and the second wing (48) include a second material.

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A blower (142) including: a forward end (202); an aft end (204) located opposite the forward end; a shaft (210) located at the aft end (204); a flange (250) located at the forward end (202); an internal surface (216) defining an axial passageway (212) within the blower; an external surface (214) radially outward of the internal surface (216); one or more radial passageway (256) formed within the flange (250) and fluidly connected to the axial passageway (212), the radial passageway (256) extending from the internal surface (216) to the external surface (214); and a plurality of blower blades (230) located within the flange (250) and defining the radial passageway (256).

A shaftless rotary machine includes an impeller (116), a motor (118) positioned radially outward from the impeller (116), and a housing (120). The impeller (116) includes a hub (126), blades (130) connected to the hub (126), and a shroud (132) connected to the blades (130). The motor (118) includes a rotor (136) connected to the shroud (132) and a stator (138). The housing (120) includes an inlet (152), an outlet (156), and a duct (154). The duct (154) extends from the inlet (152) to the outlet (156). The duct (154) partially surrounds the motor (118) and the impeller (116).

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A pin for a core layer of a heat exchanger past which fluid flowing through the layer passes, the pin (100) having a leading edge, a trailing edge, a first and a second end and, an outer surface between leading edge and trailing edge and the first and second ends, and wherein the pin (100) comprises a pin core (300) extending from the first end to the second end and defining the leading edge and the trailing edge, and a plurality of vanes (310) extending from the pin core each vane extending between the leading edge and the trailing edge, and the vanes arranged one above another in the direction from the first end to the second end.

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