Abstract: An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that is expanded through a turbine section for powering a primary propulsor. The aircraft propulsion system further includes a tap that is at a location upstream of the combustor section where a bleed airflow is drawn, a heat exchanger where the bleed airflow is heated by the gas flow, a power turbine through which heated bleed airflow is expanded to generate a work output, and a secondary propulsor that is driven by the work output that is generated by the power turbine.

Abstract: A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger, and expanded through a power turbine that is coupled to drive the auxiliary compressor section.

Abstract: A gas turbine engine assembly including a tap that is at a location up stream of the combustor section for drawing a bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow and communicate the heated bleed airflow into the turbine section where it is expanded to drive the turbine section.

Abstract: A gas turbine engine assembly includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate an exhaust gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section through an engine drive shaft. A tap is at a location up stream of the combustor section for drawing a bleed airflow. A bleed air heat exchanger places the bleed airflow in thermal communication with an auxiliary flow for heating the bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow.

Abstract: A heat exchanger includes a first end opposite a second end, a first side opposite a second side, a first layer, and a second layer. The first side and the second side extend from the first end to the second end. The first layer includes an inlet at the first end and an outlet at the second end of the heat exchanger. The second layer includes a first passage at the first end of the heat exchanger and extending from the first side to the second side and a second passage adjacent to the first passage. The second passage extends from the first side to the second side. The second layer further includes a third passage extending from the second end toward the second passage. The first passage is fluidically connected to the third passage proximate the second end and the third passage is fluidically connected to the second passage.

Abstract: An environmental control system of a vehicle includes an inlet configured to receive a medium, a compression device fluidly connected to the inlet, and at least one heat exchanger fluidly connected to the compression device. A secondary fluid system is thermally coupled to the environmental control system. The secondary fluid system has a closed loop configuration through which a secondary fluid circulates. The secondary fluid system includes an evaporator and a condenser. The evaporator has an evaporator outlet fluidly connected to and configured to receive the medium output from an outlet of the heat exchanger outlet and the condenser is connected to the evaporator outlet. The condenser is fluidly connected to and receives the medium output from the evaporator.

Abstract: An environmental control system of a vehicle includes an inlet configured to receive a medium, a heat exchanger fluidly connected to the inlet to receive the medium, and a ram air circuit including another inlet configured to receive ram air and including a ram air heat exchanger. A closed secondary fluid loop is operably coupled to the heat exchanger and to the ram air heat exchanger. The secondary fluid loop has a secondary fluid circulating therein that removes heat from the medium in the heat exchanger and that discharges heat to the ram air in the ram air heat exchanger.

Abstract: A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger and expanded through a power turbine that is coupled to drive the auxiliary compressor section.

Abstract: A gas turbine engine assembly includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section, a first tap at a location up stream of the combustor section for communicating a portion of the core airflow as a bleed airflow downstream of the combustor section, a heat exchanger that places the bleed airflow that is communicated from the first tap in thermal communication with the high energy combusted gas flow downstream of the combustor section, and a power turbine that is configured to generate shaft power from expansion of the heated bleed airflow, the power turbine includes an inlet that is configured to receive the heated bleed airflow from the heat exchanger.

Abstract: A heat exchanger includes a first side opposite a second side and a third side opposite a fourth side and a cold layer with an inlet at the first side of the heat exchanger, an outlet at the second side of the heat exchanger, and a cold passage extending from the inlet to the outlet. The heat exchanger also includes a hot layer with an inlet manifold at the third side of the heat exchanger extending between the first side and the second side, an outlet manifold at the fourth side of the heat exchanger opposite the inlet manifold and extending between the first side and the second side, a hot passage extending from the inlet manifold to the outlet manifold, and a tube on the first side of the heat exchanger extending from the third side to the fourth side.

Abstract: A heat exchanger with increased heat transfer capability includes first and second end plates, tubes extending between the first and second end plates and fins disposed between the tubes. The heat exchanger is disposable within and differs in shape from a space defined between first and second walls such that corners of the first end plate abut the first wall and a point of the second end plate abuts the second wall, the first wall diverges from the corners of the first end plate to define a first open region and the second wall diverges from the point of the second end plate to define second open regions. At least one of the first end plate and the second end plates includes enhancements fluidly communicative with the at least one corresponding one of the first open region and the second open regions.

Abstract: An air cycle machine includes a compressor in fluid communication with a load cooling heat exchanger, a first valve and a first turbine connecting the compressor to the load cooling heat exchanger, and a second valve and a second turbine. The second valve and the second turbine connect the compressor to the load cooling heat exchanger and connected in parallel with the first valve and the first turbine between the compressor and the load cooling heat exchanger. Air cycle machine systems and methods of controlling air flow through air cycle machines are also described.

Abstract: A system includes a first fluid flow path configured to condition a pressurized medium and deliver the pressurized medium to one or more loads. The first fluid flow path including an air cycle machine. A second fluid flow path is configured to circulate a working fluid. The second fluid flow path includes a heat exchanger thermally coupled to the first fluid flow path. Within the heat exchanger, heat extracted from the pressurized medium is transferred to the working fluid. The second fluid flow path additionally includes a turbine operably coupled to the air cycle machine, a condenser, and a pump operable to circulate the working fluid through at least a portion of the second fluid flow path. The turbine is rotationally driven by expanding the working fluid across the turbine.

Abstract: Disclosed is an air cycle machine (ACM) having: a turbine; a compressor; a compressor shaft connected to the compressor and configured to receive rotational energy from a gearbox; and a turbine shaft connected to the turbine and configured to provide rotational energy to the gearbox; wherein the turbine shaft and the compressor shaft operate at different rotational speeds.

Abstract: A system includes a primary heat exchanger with a first passage connected to a hot fluid source, a second passage connected to the first passage, and a third passage connected to the second passage and an outlet line. A compressor inlet is connected to the outlet line. A secondary heat exchanger is connected to a compressor outlet. First and second turbines are connected to an outlet of the secondary heat exchanger. A first load heat exchanger is connected to the first turbine. A second load heat exchanger is between the second turbine and a system outlet. A first valve connects the hot fluid source to the second and third passages. A second valve connects the first and second passages with the outlet line. A third valve is between the secondary heat exchanger and the second turbine. A fourth valve is between the first load heat exchanger and the system outlet.

Abstract: A system includes a primary heat exchanger with a first passage connected to a hot fluid source, a second passage connected to the first passage, and a third passage connected to the second passage and an outlet line. A compressor inlet is connected to the outlet line. A secondary heat exchanger is connected to a compressor outlet. First and second turbines are connected to an outlet of the secondary heat exchanger. A first load heat exchanger is connected to the first turbine. A second load heat exchanger is between the second turbine and a system outlet. A first valve connects the hot fluid source to the second and third passages. A second valve connects the first and second passages with the outlet line. A third valve is between the secondary heat exchanger and the second turbine. A fourth valve is between the first load heat exchanger and the system outlet.

Abstract: A heat exchanger includes a first side opposite a second side and a third side opposite a fourth side and a cold layer with an inlet at the first side of the heat exchanger, an outlet at the second side of the heat exchanger, and a cold passage extending from the inlet to the outlet. The heat exchanger also includes a hot layer with an inlet manifold at the third side of the heat exchanger extending between the first side and the second side, an outlet manifold at the fourth side of the heat exchanger opposite the inlet manifold and extending between the first side and the second side, a hot passage extending from the inlet manifold to the outlet manifold, and a tube on the first side of the heat exchanger extending from the third side to the fourth side.

Abstract: A thermal management system for one or more aircraft components includes a bleed airflow source at a gas turbine engine of the aircraft, one or more turbines configured to expand the bleed airflow, thus lowering a temperature of the bleed airflow, the bleed airflow driving rotation of the one or more turbines. One or more heat exchangers are in fluid communication with the one or more turbines. The one or more heat exchangers are configured to exchange thermal energy between the bleed airflow and a thermal load. One or more electrical generators are operably connected to the one or more turbines. The one or more electrical generators are configured to convert rotational energy of the one or more turbines to electrical energy.

Abstract: A heat exchanger for managing thermal energy between a flow of a first fluid and a flow of a second fluid includes first and second parting sheets and a closure bar extending between the first and second parting sheets. The closure bar includes an elongate body, a shield positioned upstream from the body relative to a direction of the flow of the first fluid, and a support connecting the shield to the closure bar.

Abstract: A heat exchanger includes a body that includes an at least two opposing surfaces and the at least two opposing surfaces are a trapezoidal. The body of the heat exchanger also includes, an area of cross sectional flow channels through the body. The area of cross-sectional flow channels in a direction perpendicular to the bases of the trapezoid increase or decrease between the two bases.