Hamilton Sundstrand

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 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.

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.

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.

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).

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