Abstract: A cooling assembly for a gas turbine engine including a heat source at a first temperature, a heat sink at a second temperature, and a heat pump coupled to the first heat source and the first heat sink. The heat pump is configured to convey a quantity of heat from the heat source through the heat pump and to the heat sink.

Abstract: An air vehicle power and thermal management system includes an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system and an electrically powered load. The controller is configured to direct the power to create a first duration cooling power to the cooling system to cool the engine fuel cooling medium over a first power time period. The controller is configured to shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period. By operation of the controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period.

Abstract: Fuel injection assemblies for a gas turbine engine includes a fuel injector and heat exchanger in communication via a fuel line cavity to provide heated fuel for combustion.

Abstract: A fan module for a gas turbine engine is disclosed herein. The fan module includes a fan, a plurality of outlet guide vanes, and a fluid cooling system. The fan is adapted to rotate about a central axis to pass air at least in part aftward along the central axis and around an engine core of the gas turbine engine. The outlet guide vanes are spaced aft of the fan along the central axis and configured to receive the air passed aftward along the central axis by the fan. The fluid cooling system is configured to transfer heat from a fluid to the air from the fan to cool the fluid.

Abstract: A cooling system is provided in a hybrid electric propulsion gas turbine engine for cooling electrical components therein. The cooling system includes an electrical component disposed in proximity to a power generation component in the hybrid electric propulsion gas turbine engine. The cooling system further includes a vapor chamber having an evaporator portion and a condenser portion, wherein the evaporator portion is disposed adjacent to and in thermal communication with the electrical component to transfer heat away from the electrical component. The vapor chamber includes biphasic working fluid therein that transitions between liquid and gaseous states as the working fluid flows proximal to the condenser portion and the evaporator portion respectively.

Abstract: A cooling system in a hybrid electric propulsion gas turbine engine is provided for cooling electrical components therein. The cooling system includes an electrical component disposed in proximity to an aircraft power generation component in the hybrid electric propulsion gas turbine engine such that the electrical component is thermally heated by the aircraft power generation component. A loop heat pipe structure is in thermal communication with the electrical component to transfer heat away from the electrical component. Wherein the loop heat pipe includes an evaporator portion, a condenser portion, a first pipe to supply a biphasic working fluid in a liquid state to the evaporator portion, and a second pipe to return the biphasic working fluid in a gaseous state to the condenser portion.

Abstract: A gas turbine engine includes an electrical device and a microchannel cooling system in communication with the electrical device to remove heat.

Abstract: An air vehicle power and thermal management system includes an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system and an electrically powered load. The controller is configured to direct the power to create a first duration cooling power to the cooling system to cool the engine fuel cooling medium over a first power time period. The controller is configured to shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period. By operation of the controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period.

Abstract: Fuel-air heat exchange system and methods thereof for use in a gas turbine engine. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine.

Abstract: An air vehicle power and thermal management system includes an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system and an electrically powered load. The controller is configured to direct the power to create a first duration cooling power to the cooling system to cool the engine fuel cooling medium over a first power time period. The controller is configured to shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period. By operation of the controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period.

Abstract: A propulsion system including a gas turbine engine is disclosed herein. The propulsion system further includes a heat exchanger arranged outside the gas turbine engine and adapted to cool fluid from the gas turbine engine.

Abstract: An aircraft capable of operating at a variety of speeds includes a power plant and an auxiliary turbine. The auxiliary turbine can be a ram air turbine used to expand and cool an airflow and provide work. The cooled airflow from the auxiliary turbine can be used in a heat exchange device such as, but not limited to, a fuel/air heat exchanger. In one embodiment the cooled airflow can be used to exchange heat with a compressor airflow being routed to cool a turbine. Work developed from the auxiliary turbine can be used to power a heating device and rotate a device to add work to a shaft of the aircraft power plant. In one form the aircraft power plant is a gas turbine engine and the work developed from the auxiliary turbine is used to heat a combustor flow or to drive a shaft that couples a turbine and a compressor.

Abstract: An aircraft capable of operating at a variety of speeds includes a power plant and an auxiliary turbine. The auxiliary turbine can be a ram air turbine used to expand and cool an airflow and provide work. The cooled airflow from the auxiliary turbine can be used in a heat exchange device such as, but not limited to, a fuel/air heat exchanger. In one embodiment the cooled airflow can be used to exchange heat with a compressor airflow being routed to cool a turbine. Work developed from the auxiliary turbine can be used to power a heating device and rotate a device to add work to a shaft of the aircraft power plant. In one form the aircraft power plant is a gas turbine engine and the work developed from the auxiliary turbine is used to heat a combustor flow or to drive a shaft that couples a turbine and a compressor.

Abstract: An integrated aircraft cooling system comprising a turbine engine and a plurality of secondary cooling streams, wherein the turbine engine core exhaust stream drives the plurality of secondary cooling streams. A core exhaust stream outlet has a periphery and a composite secondary outlet positioned around the periphery of the core exhaust stream outlet, and the composite secondary outlet is segregated between the plurality of secondary streams. Each of the secondary flows are in fluid isolation from each other upstream of the composite secondary outlet.

Abstract: An aircraft may have a heat generating component and an engine, at least one of which generates a heat load, and a thermal management system to cool the heat load. The engine may have a duct and an engine fan configured to draw an inlet air stream into an inlet portion of the duct, where at least a portion of the inlet air stream may be used as an engine air stream. The thermal management system may include a cooling circuit configured to circulate a fluid through the heat load such that at least a portion of it may be transferred to the fluid, a heat exchanger configured to enable heat transfer between the fluid and a cooling air stream, and a pumping device. The pumping device may be configured to draw the cooling air stream through the heat exchanger and into a portion of the engine air stream.

Abstract: A gas turbine engine flow duct comprising a flow duct disposed along an engine centerline of the gas turbine engine and defining a stream flow passage, and first and second rows of heat exchangers disposed along the engine centerline of the gas turbine engine and integrated in the flow duct in fluid communication with the stream flow passage of the flow duct.

Abstract: A fan module for a gas turbine engine is disclosed herein. The fan module includes a fan, a plurality of outlet guide vanes, and a fluid cooling system. The fan is adapted to rotate about a central axis to pass air at least in part aftward along the central axis and around an engine core of the gas turbine engine. The outlet guide vanes are spaced aft of the fan along the central axis and configured to receive the air passed aftward along the central axis by the fan. The fluid cooling system is configured to transfer heat from a fluid to the air from the fan to cool the fluid.

Abstract: A cooling air system for use in a gas turbine engine includes a microchannel fuel-air heat exchanger. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine.

Abstract: A cooling air system for use in a gas turbine engine includes a fuel-air heat exchanger. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine.

Abstract: A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft.