Abstract: An air conditioning apparatus that includes a turbine and a compressor with rotors mounted on and fixed to a common rotatable shaft with a heat exchanger located between the turbine and the compressor. The air conditioning apparatus turbine has an inlet that is connected to a source of air such as aircraft ram air the outlet from the turbine and is positioned to direct outlet air from the turbine to the heat exchanger. The compressor which is located adjacent to and downstream from the heat exchanger has an inlet that is positioned to receive air exiting from the heat exchanger. In one embodiment, no external power is necessary to obtain cooling of liquid coolant located within the heat exchanger that is integral with the air conditioning apparatus and another embodiment includes test equipment.

Abstract: Aircraft air control valve apparatus for controlling the flow of pressurized aircraft engine bleed air. The control valve apparatus includes a hollow housing with two end portions with each end portion having an aperture located therein with one end portion being connected to a source of pressurized aircraft engine bleed air. A shut-off valve is located in one end portion of the hollow housing for starting and stopping the flow of pressurized aircraft engine bleed air through the hollow housing and a modulating valve is located in the other end portion of the hollow housing for modulating the flow of pressurized aircraft engine bleed air through the hollow housing. The shut-off valve and the modulating valve are operated by the use of pressurized aircraft engine bleed air.

Abstract: Aircraft air control valve apparatus for controlling the flow of pressurized aircraft engine bleed air. The control valve apparatus includes a hollow housing with two end portions with each end portion having an aperture located therein with one end portion being connected to a source of pressurized aircraft engine bleed air. A shut-off valve is located in one end portion of the hollow housing for starting and stopping the flow of pressurized aircraft engine bleed air through the hollow housing and a modulating valve is located in the other end portion of the hollow housing for modulating the flow of pressurized aircraft engine bleed air through the hollow housing. The shut-off valve and the modulating valve are operated by the use of pressurized aircraft engine bleed air.

Abstract: Nozzle control apparatus for an axial flow air turbine having an inlet nozzle for air entering the turbine and an associated turbine inlet housing for channeling air flowing to the inlet nozzle for at least partially blocking air flow from the turbine inlet housing to the turbine inlet nozzle. The nozzle control apparatus uses an axially movable annular slider member that is biased to its open position by an annular spring and is moved axially by bleed air pressure exerted on a portion of the annular slider member.

Abstract: An air cycle machine (10) has four wheels mounted on a common shaft (20) for rotation therewith about a longitudinal axis (12), including a second stage turbine rotor (30) mounted to a first end (20a) of the shaft, a fan rotor (40) mounted to a second end (20b) of the shaft, a first stage turbine rotor (50) mounted to a central portion (20c) of the shaft, a compressor rotor (60) mounted to the central portion of the shaft in back to back relation to the first stage turbine rotor, the first and second stage turbine rotors being operative to extract energy from a flow of compressed air for driving the shaft (20), and the fan rotor (40) and the compressor rotor (60), in rotation about the axis, and first and second hydrodynamic gas film foil bearings (70, 80) for supporting the shaft for rotation about the longitudinal axis (12).

Abstract: An air cycle machine (10) a plurality of wheels mounted on a common shaft (20) for rotation therewith about a longitudinal axis (12), including a compressor rotor (60) and a turbine rotor (50) mounted to a central portion (20c) of the shaft in back to back relationship, the turbine rotor (50) being operative to extract energy from a flow ofcompressed air for driving the shaft (20), and the compressor rotor (60), in rotation about the axis. The compressor rotor (60) and the compressor outlet flow passing through duct (164) are thermally isolated from the turbine rotor (50) and the turbine inlet flow passing through duct (152), respectively, by an annular disc-like member (14) of a low thermal conductivity, fiber reinforced resin composite disposed about the shaft 20 and extending radially outwardly between the turbine rotor (50) and the compressor rotor (60).

Abstract: An air cycle machine (10) having a plurality of wheels mounted on a common shaft (20) for rotation therewith about a longitudinal axis (12), including a compressor rotor (60) and a turbine rotor (50) mounted to a central portion (20c) of the shaft in back to back relationship, the turbine rotor (50) being operative to extract energy from a flow of compressed air for driving the shaft (20), and the compressor rotor (60), in rotation about the axis. An annular disc-like member (14) is disposed coaxially about the shaft (20) and extends radially outwardly between the turbine rotor (50) and the compressor rotor (60). A venting and sealing assembly (210, 220, 230) is operatively disposed between the shaft (20) and the annular member (14) intermediate the turbine rotor (50) and the compressor rotor (60) whereby a limited flow of compressor outlet air and a limited flow of turbine inlet air are vented to a low pressure region other than the turbine air flow circuit.

Abstract: During assembly, individual segments (10, 12, 14) comprising a housing (18) designed to encase and support a rotating assembly are positioned on a fixture (16) and releasably joined. The fixture (16) is adapted to engage the annular volumes (20, 22, 24, 26) that locate the radial support means chosen to support the rotating assembly.

Abstract: In air cycle machines with hydrodynamic bearings, the mass flow rate of coolant (36) passing through a series of bearings (32, 28, 30) is metered before the coolant passes through the final bearing (30). The final bearing operates at an internal pressure equivalent to that present in the region (72) into which coolant exhausts after exiting the final bearing. Since coolant in the final bearing is at the same pressure as air immediately downstream from the bearing, no rotating seal is required at the outlet of the bearing cooling flowpath.