Abstract: An emission treatment system includes a separation device having a vessel that includes an inlet for receiving an emission stream having entrained solid particles. A first outlet from the vessel discharges captured solid particles from the emission stream and a second outlet from the vessel discharges a clean stream having fewer entrained solid particles than the emission stream received into the separation device. A particle collector is fluidly connected with the separation device and includes a collection portion for capturing solid particles from the emission stream.

Abstract: An emission treatment system includes a separation device having a vessel that includes an inlet for receiving an emission stream having entrained solid particles. A first outlet from the vessel discharges captured solid particles from the emission stream and a second outlet from the vessel discharges a clean stream having fewer entrained solid particles than the emission stream received into the separation device. A particle collector is fluidly connected with the separation device and includes a collection portion for capturing solid particles from the emission stream.

Abstract: A method for designing gas turbine engine components using a coupled parametric analysis of part geometry and flow control is disclosed. Included are the steps of parametrically defining the geometry of the duct wall shape, parametrically defining one or more flow control actuators in the duct wall, measuring a plurality of performance parameters or metrics (e.g., flow characteristics) of the duct and comparing the results of the measurement with desired or target parameters, and selecting the optimal duct geometry and flow control for at least a portion of the duct, the selection process including evaluating the plurality of performance metrics in a pareto analysis. The use of this method in the design of inter-turbine transition ducts, serpentine ducts, inlets, diffusers, and similar components provides a design which reduces pressure losses and flow profile distortions.

Abstract: A device separates particulates from a gas stream flowing through the device. The device includes at least one high voltage electrode and a substantially cylindrical separator. The high voltage electrode applies a first voltage to the gas stream. The separator has an inlet for introducing the gas stream into the separator tangentially to an interior wall of the separator, a particulate outlet for expelling the particulates from the separator, and a gas stream outlet.

Abstract: A device separates particulates from a gas stream flowing through the device. The device includes at least one high voltage electrode and a substantially cylindrical separator. The high voltage electrode applies a first voltage to the gas stream. The separator has an inlet for introducing the gas stream into the separator tangentially to an interior wall of the separator, a particulate outlet for expelling the particulates from the separator, and a gas stream outlet.

Abstract: A cooling system for a gas turbine engine includes a fuel deoxygenator for increasing the cooling capacity of the fuel. The fuel deoxygenator removes dissolved gases from the fuel to prevent the formation of insoluble deposits. The prevention of insoluble deposits increases the usable cooling capacity of the fuel. The increased cooling capacity of the deoxygenated fuel provides a greater heat sink for cooling air used to protect engine components. The improved cooling capacity of the cooling air provides for increased engine operating temperatures that improves overall engine efficiency.

Abstract: A method for designing gas turbine engine components using a coupled parametric analysis of part geometry and flow control is disclosed. Included are the steps of parametrically defining the geometry of the duct wall shape, parametrically defining one or more flow control actuators in the duct wall, measuring a plurality of performance parameters or metrics (e.g., flow characteristics) of the duct and comparing the results of the measurement with desired or target parameters, and selecting the optimal duct geometry and flow control for at least a portion of the duct, the selection process including evaluating the plurality of performance metrics in a pareto analysis. The use of this method in the design of inter-turbine transition ducts, serpentine ducts, inlets, diffusers, and similar components provides a design which reduces pressure losses and flow profile distortions.

Abstract: A system for the management of thermal transfer in a gas turbine engine includes a heat generating sub-system in operable communication with the engine, a fuel source to supply a fuel, a fuel stabilization unit to receive the fuel from the fuel source and to provide the fuel to the engine, and a heat exchanger in thermal communication with the fuel to transfer 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. A system for the thermal management of an aircraft provides for powering the aircraft, supplying a fuel deoxygenating the fuel, and transferring heat between a heat generating sub-system of the aircraft and the fuel.

Abstract: A cooling system for a gas turbine engine includes a fuel deoxygenator for increasing the cooling capacity of the fuel. The fuel deoxygenator removes dissolved gases from the fuel to prevent the formation of insoluble deposits. The prevention of insoluble deposits increases the usable cooling capacity of the fuel. The increased cooling capacity of the deoxygenated fuel provides a greater heat sink for cooling air used to protect engine components. The improved cooling capacity of the cooling air provides for increased engine operating temperatures that improves overall engine efficiency.

Abstract: The present invention relates to A reduced bleed vapor compression cycle environmental control system for an aircraft. The environmental control system provides conditioned external ram air to compartments such as the cabin, the flight deck, avionics compartment, and other equipment compartments, where conditioned air is needed. The system includes a first compressor for compressing the external ram air to cabin pressure and an evaporator for cooling the external ram air to a desired temperature. The system further includes a low-pressure water separator for removing moisture from the ram air prior to the external ram air being delivered to the compartment(s). The ram air compressor as well as a compressor for a refrigerant loop are driven by a turbine that expands a minimal amount of bleed air from an engine.

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 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 a reduced bleed vapor compression cycle environmental control system for an aircraft. The environmental control system provides conditioned external ram air to compartments such as the cabin, the flight deck, avionics compartment, and other equipment compartments, where conditioned air is needed. The system includes a first compressor for compressing the external ram air to cabin pressure and an evaporator for cooling the external ram air to a desired temperature. The system further includes a low-pressure water separator for removing moisture from the ram air prior to the external ram air being delivered to the compartment(s). The ram air compressor as well as a compressor for a refrigerant loop are driven by a turbine that expands a minimal amount of bleed air from an engine.

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: The present invention relates to a reduced bleed vapor compression cycle environmental control system for an aircraft. The environmental control system provides conditioned external ram air to compartments such as the cabin, the flight deck, avionics compartment, and other equipment compartments, where conditioned air is needed. The system includes a first compressor for compressing the external ram air to cabin pressure and an evaporator for cooling the external ram air to a desired temperature. The system further includes a low-pressure water separator for removing moisture from the ram air prior to the external ram air being delivered to the compartment(s). The ram air compressor as well as a compressor for a refrigerant loop are driven by a turbine that expands a minimal amount of bleed air from an engine.