Abstract: A base plate for cooling a power electronics device is provided, the base plate comprising cooling fins, the base plate configured to receive the power electronics device directly above the cooling fins, the cooling fins integral to the base plate, the base plate configured to conduct a liquid coolant past the cooling fins

Abstract: A gas turbine engine system includes a gas turbine engine having a fan bypass duct, a heat exchanger system, and a flow transfer unit configured to selectively allow or preclude flow between the fan bypass duct and the heat exchanger system. A controller is coupled to and configured to vary the state of one or more of a fan exit nozzle, a heat exchanger exit nozzle, and a flow control valve controlling flow between the fan bypass duct and the heat exchanger system.

Abstract: Systems and methods for cooling electrical components disposed in a jet engine. An example system includes an evaporation chamber configured to contain the electrical components in contact with a coolant liquid. The coolant vapor formed during the heat transfer from the electrical components to the coolant liquid flows to a condenser assembly having a fuel-cooled condenser and an air-cooled condenser. The air-cooled condenser cools the coolant vapor to condensation using either fan stream air or engine bleed air from the intermediate pressure compressor or the high pressure compressor. An air cycle machine cools the engine bleed air. A controller may be used to select a coolant source for condensing the coolant vapor based on operating conditions of the aircraft. Spent air from the air-cooled condenser may be recycled back to the engine for engine cooling, added thrust, oil sump buffering, oil or fuel cooling, or blade tip clearance control.

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: An example thermal management system may include a first heat exchanger including a bleed air inlet configured to receive input bleed air from a gas turbine engine and a bleed air outlet configured to output cooled bleed air. A turbine including a turbine inlet may be fluidically coupled to the bleed air outlet. The turbine may be configured to drive a shaft mechanically coupled to the turbine in response to expansion of the cooled bleed air through the turbine. A second heat exchanger may include an expanded bleed air inlet fluidically coupled to a turbine outlet of the turbine. The second heat exchanger may be configured to extract heat from at least one heat source using the expanded bleed air.

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 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: 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 two-phase pump loop (TPPL) for dissipating a thermal load during operation of an apparatus includes a coolant, a vapor/liquid receiver, a pump, an evaporator, a condenser, a valve (V1) configured to regulate a pressure at an outlet of the condenser; a valve (V2) having a control set point set equivalent to a low pressure (PL) measured in the vapor/liquid receiver; and a controller configured to control the set points of V1 and V2. The TPPL is configured to cool the thermal load with tight control of the temperature of the coolant that is cooling the apparatus. The TPPL may be combined with a vapor cycle system (VCS) to provide a thermal management system with the VCS being configured to use the same or different coolant than the TPPL.

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: A thermal management system for regulating dissipation of multiple thermal loads during operation of an apparatus includes a two-phase pump loop (TPPL), a vapor cycle system (VCS), and a liquid thermal energy storage (TES) system integrated together to maintain the apparatus at a constant temperature. The TPPL is configured to remove heat from the apparatus; the TES system is configured to provide thermal energy storage and temperature regulation; and the VCS is configured to transfer heat to the environment. The multiple thermal loads include a primary thermal load in the form of heat from the apparatus and a secondary thermal load in the form of at least one of a housekeeping thermal load or a power electronics thermal load. The primary and secondary loads are at different temperatures with each being independently selected to be transient or steady state.

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: 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: A cooling assembly for a gas turbine engine may include a heat source, a heat sink, and a heat pump coupled to the heat source and the heat sink, wherein the heat pump may be configured to convey a quantity of heat from the heat source to the heat sink. The heat pump may be mounted to an inner surface of an inner fan casing, and the heat sink may be mounted to an outer surface of the inner fan casing such that heat may convey from the heat sink to a bypass air stream passing over the inner fan casing through or past the heat sink.

Abstract: Systems and methods for cooling electrical components disposed in a jet engine. An example system includes an evaporation chamber configured to contain the electrical components in contact with a coolant liquid. The coolant vapor formed during the heat transfer from the electrical components to the coolant liquid flows to a condenser assembly having a fuel-cooled condenser and an air-cooled condenser. The air-cooled condenser cools the coolant vapor to condensation using either fan stream air or engine bleed air from the intermediate pressure compressor or the high pressure compressor. An air cycle machine cools the engine bleed air. A controller may be used to select a coolant source for condensing the coolant vapor based on operating conditions of the aircraft. Spent air from the air-cooled condenser may be recycled back to the engine for engine cooling, added thrust, oil sump buffering, oil or fuel cooling, or blade tip clearance control.

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: A thermal management system for regulating dissipation of multiple thermal loads during operation of an apparatus includes a two-phase pump loop (TPPL), a vapor cycle system (VCS), and a liquid thermal energy storage (TES) system integrated together to maintain the apparatus at a constant temperature. The TPPL is configured to remove heat from the apparatus; the TES system is configured to provide thermal energy storage and temperature regulation; and the VCS is configured to transfer heat to the environment. The multiple thermal loads include a primary thermal load in the form of heat from the apparatus and a secondary thermal load in the form of at least one of a housekeeping thermal load or a power electronics thermal load. The primary and secondary loads are at different temperatures with each being independently selected to be transient or steady state.

Abstract: A two-phase pump loop (TPPL) for dissipating a thermal load during operation of an apparatus includes a coolant, a vapor/liquid receiver, a pump, an evaporator, a condenser, a valve (V1) configured to regulate a pressure at an outlet of the condenser; a valve (V2) having a control set point set equivalent to a low pressure (PL) measured in the vapor/liquid receiver; and a controller configured to control the set points of V1 and V2. The TPPL is configured to cool the thermal load with tight control of the temperature of the coolant that is cooling the apparatus. The TPPL may be combined with a vapor cycle system (VCS) to provide a thermal management system with the VCS being configured to use the same or different coolant than the TPPL.

Abstract: A cooling system is provided including a two-phase pump loop and a vapor compression system. The two-phase pump loop cools a thermal load with a first coolant. The vapor compression system is configured to circulate a second coolant. The vapor compression system includes a liquid vapor separator which separates the second coolant into a liquid portion and a gaseous portion. The liquid vapor separator is a thermal energy storage for the two-phase pump loop. A condenser of the two-phase pump loop transfers heat from the first coolant to the liquid portion of the second coolant in the liquid-vapor separator.