Abstract: A thermal management system for a pulse load on an aircraft. The thermal management system utilizing the reserve fuel from the aircraft to create thermal capacitance such that the instantaneous capacity of the cooling system to remove heat from the aircraft may be sized less than the rate of heat generated by the pulsed load (e.g. laser, radar, rail gun etc.) The reserve fuel is maintained at a temperature in a reservoir and cooled via a cooling system. Fuel from the reservoir is selectively mixed with fuel exiting the pulsed load heat exchanger to provide fuel to the inlet of the heat exchanger at a predetermined temperature, the temperature based at least upon the heat generated by the laser, flow rate of fuel and efficiency of the heat exchanger.

Abstract: In some examples, propulsion, electrical generation, and cooling system. The system comprises a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a first fluid, wherein a portion of the compressed first fluid is directed out of the bleed air outlet to define bleed air from the compressor. The system also includes a turbo-generator including a combustor, wherein the combustor is configured to receive the bleed air from the compressor and combust a fuel with the bleed air, wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor. The system also includes an air cycle cooling system configured to remove heat via an air cycle cooling process, wherein the air cycle cooling process is charged via the bleed air from the compressor. A compressor of the air cycle cooling system may be driven by a turbine of the turbo-generator or a turbine of the gas turbine engine.

Abstract: A thermal management system for a pulse load on an aircraft. The thermal management system utilizing the reserve fuel from the aircraft to create thermal capacitance such that the instantaneous capacity of the cooling system to remove heat from the aircraft may be sized less than the rate of heat generated by the pulsed load (e.g. laser, radar, rail gun etc.) The reserve fuel is maintained at a temperature in a reservoir and cooled via a cooling system. Fuel from the reservoir is selectively mixed with fuel exiting the pulsed load heat exchanger to provide fuel to the inlet of the heat exchanger at a predetermined temperature, the temperature based at least upon the heat generated by the laser, flow rate of fuel and efficiency of the heat exchanger.

Abstract: A gearbox rigidly coupled to a static structure; a driven component rigidly coupled to another static structure; a clutch assembly floating between and coupled to the gearbox and driven component. The clutch may have aligned output and input shafts, defining an engagement surface, a bearing, and a magnetic friction plate coupled and rotating with the input shaft. The plate may have a friction-engagement face, and a magnetic flux generator. The magnetic flux generator may be rigidly coupled to a static housing and partially surrounded in the radial direction by a structure configured to reduce leakage of a magnetic flux, by defining a plurality of voids, which direct multiple passes of the magnetic flux through the engagement surface of the output shaft. The magnetic flux generator may create the magnetic flux that creates a magnetic force between the engagement face and the magnetic friction plate that causes them to engage.

Abstract: In some examples, a propulsion and electrical generation system including a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a fluid, wherein a portion of the compressed fluid is directed out of the bleed air outlet to define bleed air from the compressor; and a turbo-generator including a combustor, wherein the combustor includes a fuel inlet and a bleed air inlet, wherein the bleed air inlet is in fluid communication with the bleed air outlet from the compressor, wherein the combustor is configured to receive the bleed air via the bleed air inlet from the bleed air outlet of the gas turbine engine and receive fuel via the fuel inlet, wherein the combustor is configured to combust the received fuel with the received bleed air, and wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor.

Abstract: An inlet assembly for a high-mach engine includes a gas turbine core, an inlet turbine, and a core-flow director. When in a closed position, the core-flow director forces air to interact with the inlet turbine before entering the gas turbine core.

Abstract: A system includes at least one compressor, at least two turbines, and at least two combustors, each fluidically coupled to a respective turbine of the at least two turbines and configured to receive compressed fluid from the at least one compressor. The system further includes at least two motor-generators, each operably coupled to a respective turbine of the at least two turbines and configured to convert electrical energy to mechanical energy to drive a respective propulsor to which the respective motor-generator is operably coupled and to convert mechanical energy from the respective turbine to electrical energy. The system further includes at least two propulsors, each operably coupled to a respective turbine of the at least two turbines and configured to be driven by the respective turbine, a respective motor-generator to which the respective propulsor is operably coupled via the respective turbine, or both the respective turbine and the respective motor-generator.

Abstract: A refrigeration system is described that includes a compression device configured to increase a pressure of a refrigerant. The refrigeration system further includes a first heat exchanger configured to reject heat from the refrigerant and reduce a temperature of the refrigerant. The refrigeration system further includes a storage device configured to store the refrigerant at a supercritical state. The refrigeration system further includes an expansion device configured to reduce the pressure of the refrigerant. The refrigeration system further includes a second heat exchanger configured to absorb heat into the refrigerant and increase the temperature of the refrigerant. The refrigeration system further includes a controller configured to release the refrigerant from the storage device to the expansion device to provide cooling capacity to the refrigeration system.

Abstract: A vehicle includes an engine, an oil circuit for providing oil to the engine, a fuel supply line, and an air-oil separating unit. The air-oil separating unit is configured to receive aerated oil from the engine via the oil circuit, flow the aerated oil in approximately a helical direction to de-aerate the oil, receive fuel from the fuel supply line, cool the aerated oil with the fuel while the aerated oil flows in the approximately helical direction, causing the fuel to heat, and pass the cooled and de-aerated oil and pass the heated fuel to the engine.

Abstract: A system includes at least one compressor, at least two turbines, and at least two combustors, each fluidically coupled to a respective turbine of the at least two turbines and configured to receive compressed fluid from the at least one compressor. The system further includes at least two motor-generators, each operably coupled to a respective turbine of the at least two turbines and configured to convert electrical energy to mechanical energy to drive a respective propulsor to which the respective motor-generator is operably coupled and to convert mechanical energy from the respective turbine to electrical energy. The system further includes at least two propulsors, each operably coupled to a respective turbine of the at least two turbines and configured to be driven by the respective turbine, a respective motor-generator to which the respective propulsor is operably coupled via the respective turbine, or both the respective turbine and the respective motor-generator.

Abstract: A gas turbine engine and methods of operation include a low pressure electric motor-generator arranged for selective operation in a generator mode to generate electrical power or a drive mode to assist rotation of a low pressure drive shaft of the engine.

Abstract: A gas turbine engine and methods of operation include a low pressure electric motor-generator having an electrical assembly for electrical connection.

Abstract: A gas turbine engine and methods of operation are disclosed including a low pressure motor-generator and flutter control system.

Abstract: A turbofan gas turbine engine includes low pressure (LP) motor-generator operable in either a generation mode or a drive mode, an high pressure (HP) motor-generator operable in a either a generation mode or a drive mode, and a power control module for selectively operating the LP and HP motor-generators according to operational conditions of the engine.

Abstract: A refrigeration system is described that includes a compression device configured to increase a pressure of a refrigerant. The refrigeration system further includes a first heat exchanger configured to reject heat from the refrigerant and reduce a temperature of the refrigerant. The refrigeration system further includes a storage device configured to store the refrigerant at a supercritical state. The refrigeration system further includes an expansion device configured to reduce the pressure of the refrigerant. The refrigeration system further includes a second heat exchanger configured to absorb heat into the refrigerant and increase the temperature of the refrigerant. The refrigeration system further includes a controller configured to release the refrigerant from the storage device to the expansion device to provide cooling capacity to the refrigeration system.

Abstract: A high-Mach engine includes a gas turbine core, an inlet assembly, and a transmission. The inlet assembly including an inlet turbine and the transmission configured to couple the inlet turbine and a core turbine of the gas turbine core cooperate to control air moving through the high-Mach engine.

Abstract: An inlet assembly for a high-mach engine includes a gas turbine core, an inlet turbine, and a core-flow director. When in a closed position, the core-flow director forces air to interact with the inlet turbine before entering the gas turbine core.

Abstract: An exemplary electrical system may include a power plant and a dual motor/generator assembly coupled to each other. The power plant may be a gas turbine engine, and may be operable to provide motive power. The dual motor/generator assembly may include a first motor/generator and a second motor/generator operatively coupled to a common gear shaft, and a gear box configured to couple the first motor/generator and the second motor/generator to the power plant. The first motor/generator and the second motor/generator may be operable to selectively provide power to or extract power from the power plant. The dual motor/generator assembly may be configured such that the first motor/generator and the second motor/generator may operate together at part loads, or individually as a main and a redundant, backup to the other.

Abstract: A turbine engine includes an electrical system having at least two generator circuits, one coupled to a high pressure portion of a gas turbine engine and the other coupled to a low pressure portion of the gas turbine engine. The electrical system actively cools an electrical generator during operation in order to ensure proper operation as well as extend the lifespan of the generator.

Abstract: An exemplary electrical system may include a power plant operable to provide motive power, and a first and a second motor/generator operatively coupled to a common gear shaft, and to the power plant via a gearbox and drive shaft. The exemplary electrical system may further include a system controller configured to selectively operate at least one of the first motor/generator and the second motor/generator in one of a motor operating mode and a generator operating mode based on at least one parameter. The at least one parameter may be, but is not limited to, vibration and torque. In the motor operating mode, the first and/or second motor/generator provides power to the power plant. In the generator operating mode, the first and/or the second motor/generator extracts power from the power plant.