Abstract: A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit to the tail section of the aircraft.

Abstract: The present invention relates to an electrical power and cooling system for use in an aircraft having at least one engine. The electrical power and cooling system comprises a single shaft, a power turbine mounted on the shaft for receiving fresh pressurized air from the at least one engine, a cooling turbine mounted on the shaft and receiving the fresh pressurized air from the at least one engine, a generator mounted on the shaft, and a fan mounted on the shaft for creating a flow of cooling air. The system further has a condenser for removing moisture from the air exiting the cooling turbine and a mixing chamber for mixing the cooled dry air with recirculated cabin air. The electrical power and cooling system delivers conditioned air to a cabin and/or a flight deck onboard the aircraft and electrical power to the aircraft's electrical systems.

Abstract: The present invention relates to an integrated enviromental control system for an aircraft. The system uses bleed air from a propulsion engine to drive an air turbine which provides power to at least one aircraft component such as an aircraft mounted accessory drive. The system uses the bleed air exiting the air turbine as an air source for the cabin and/or flight deck enviromental control system.

Abstract: A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit to the tail section of the aircraft.

Abstract: A system for the management of thermal transfer in a gas turbine engine includes a heat generating sub-system disposed in operable communication with the engine, a fuel source configured to supply a fuel, a fuel stabilization unit configured to receive the fuel from the fuel source and to provide the fuel to the engine, and a heat exchanger disposed in thermal communication with the fuel to effect the transfer of heat from the heat generating sub-system to the fuel. A method of managing thermal transfer in an aircraft includes removing oxygen from a stream of a fuel fed to an engine used to drive the aircraft, transferring heat from a heat generating sub-system of the aircraft to the fuel, and combusting the fuel.

Abstract: The present invention relates to an integrated air turbine driving system for providing aircraft environmental control. The system has at least one air driven turbine for providing power to an aircraft mounted accessory drive and for providing heated air to an aircraft anti-ice system. The system further has a subsystem for supplying cooled pressurized air to a flight deck and/or cabin and to aircraft avionics. Still further, the subsystem provides cooling air to other aircraft components such as a generator and/or an aircraft mounted accessory drive.

Abstract: The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system.

Abstract: The present invention relates to an electrical power and cooling system for use in an aircraft having at least one engine. The electrical power and cooling system comprises a single shaft, a power turbine mounted on the shaft for receiving fresh pressurized air from the at least one engine, a cooling turbine mounted on the shaft and receiving the fresh pressurized air from the at least one engine, a generator mounted on the shaft, and a fan mounted on the shaft for creating a flow of cooling air. The system further has a condenser for removing moisture from the air exiting the cooling turbine and a mixing chamber for mixing the cooled dry air with recirculated cabin air. The electrical power and cooling system delivers conditioned air to a cabin and/or a flight deck onboard the aircraft and electrical power to the aircraft's electrical systems.

Abstract: A screw compressor includes a housing containing at least one rotor for generating a discharge flow in a discharge flow direction; a diffuser communicated with the housing and having a collecting portion for receiving the discharge flow, a diffuser throat and a diffuser portion, said diffuser extending from the housing in a diffuser direction; and at least one turning vane positioned in the collecting portion and adapted to guide flow from the discharge flow direction to the diffuser direction.

Abstract: A screw compressor includes a housing containing at least one rotor for generating a discharge flow in a discharge flow direction; a diffuser communicated with the housing and having a collecting portion for receiving the discharge flow, a diffuser throat and a diffuser portion, said diffuser extending from the housing in a diffuser direction; and at least one turning vane positioned in the collecting portion and adapted to guide flow from the discharge flow direction to the diffuser direction.

Abstract: The present invention relates to a vapor compression cycle environmental control system for use on aircraft. The system includes an environmental control subsystem which supplies pressurized ram air at a desired temperature to the aircraft's flight deck and/or cabin. The environmental control subsystem uses a vapor compression cycle subsystem to provide the ram air at the desired temperature. The system further includes an air turbine driven by engine bleed air to provide power to an aircraft mounted accessory drive and to provide heated air to an anti-ice system. The aircraft mounted accessory drive provides power to an air compressor which forms part of the environmental control subsystem and to a working fluid compressor which forms part of the vapor compression cycle subsystem.

Abstract: An integrated aircraft system which comprises an aircraft frame, a nacelle cowl mounted to the aircraft frame, a primary gas turbine engine mounted within the nacelle cowl, a secondary power system incorporated within the nacelle cowl and being driven by a flow of air created by or through the engine, and an electrical power and cooling unit for supplying electrical power and cabin cooling air. The electrical power and cooling unit is pneumatically driven by engine bleed air.

Abstract: The present invention relates to an engine integrated auxiliary power unit. The engine comprises a high pressure spool which includes a high pressure compressor connected to a high pressure turbine and a low pressure spool which includes a low pressure compressor connected to a low pressure turbine. The engine further has a system for independently operating the high pressure spool and thus allowing the high pressure spool to function as an auxiliary power unit.

Abstract: The present invention relates to an integrated aircraft system which comprises an aircraft frame, a nacelle cowl mounted to the aircraft frame, a primary gas turbine engine mounted within the nacelle cowl, a secondary power system incorporated within the nacelle cowl and being driven by a flow of air created by or through the engine, and an electrical power and cooling unit for supplying electrical power and cabin cooling air. The electrical power and cooling unit is pneumatically driven by engine bleed air.

Abstract: The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system.

Abstract: Systems and methods are disclosed for determining heat transfer in an environment. In one system, heat transfer is determined with a probe including at least one element, a power supply, an amplifier, a temperature monitor, a timing structure, and a system controller. In another system, heat transfer is determined with a temperature sampler. In yet another system, the heat transfer rate is controlled in at least a partially closed environment. The disclosed methods include a method for calculating heat transfer from a first predetermined temperature, a second predetermined temperature, measured time and temperature of the environment. In another method, heat transfer is calculated from a first determined temperature, a second measured temperature, a predetermined period of time, and temperature of the environment.

Abstract: An sensor for sensing buoyancy force within a liquid mixture stored within a storage tank and an interlock employing the sensor to prevent a respirable cryogenic mixture from being dispensed from the storage tank with an unsafe oxygen content. The sensor has a float adapted to be submerged in the liquid mixture, thereby to exert a buoyancy force referable to the density. The buoyancy force is sensed by a load cell connected to an elongated base element cantilevered from the outlet by a bracket. The mounting of such sensor ensures that the buoyancy force and therefore, the density of the liquid as dispensed will be measured as opposed to liquid density at some other location of the tank. Such sensor can serve in an interlock in which a controller responsive to the load cell and a temperature sensor, also located within the outlet, controls a valve to close the outlet when the mixture has an unsafe oxygen level.

Abstract: A sensor for sensing buoyancy force within a liquid mixture stored within a storage tank and an interlock employing the sensor to prevent a respirable cryogenic mixture from being dispensed from the storage tank with an unsafe oxygen content. The sensor has a float adapted to be submerged in the liquid mixture, thereby to exert a buoyancy force referable to the density. The buoyancy force is sensed by a load cell connected to an elongated base element cantilevered from the outlet by a bracket. The mounting of such sensor ensures that the buoyancy force and therefore, the density of the liquid as dispensed will be measured as opposed to liquid density at some other location of the tank. Such sensor can serve in an interlock in which a controller responsive to the load cell and a temperature sensor, also located within the outlet, controls a valve to close the outlet when the mixture has an unsafe oxygen level.

Abstract: A method of tempering an article is disclosed in which an article is heated so that the material making up the article is in an essentially stress-free state and the article thereafter is quenched and cooled. At the conclusion of the quenching, a stress pattern in initiated through the thickness of the article in which the midplane layer is in tension and the surface layers are in compression. This stress pattern is further developed during the cooling stage. The article is quenched by spraying the surfaces with a coolant, preferably comprising either liquid nitrogen or liquid air in the form of a two phase flow of liquid and vapor. The liquid is sprayed so that the surface tensile stress of the surface layers are not exceeded and the liquid does not accumulate on the surface layers as a film.

Abstract: An impingement freezer having a zoned freezing chamber in which the temperature of each zone is independently controllable so that the temperature profile within the impingement freezer is coldest at a zone adjacent the outlet and warmest at a zone adjacent the inlet for maximum thermodynamic usage of the refrigerant. Additionally, the velocity of each of the impingement jets is independently adjustable from zone to zone so that in the zone adjacent the entrance of the freezing chamber, the impingement jets can be adjusted to have maximum velocity to produce maximum heat transfer coefficients and thereby an acceptable rate of cooling within the impingement jet freezer. Impingement jets are formed within nozzles that are tapered in two orthogonal directions to prevent frost build-up. Circulation within the impingement jet freezer is produced by venturi-like devices driven by vaporization of incoming refrigerant.