Abstract: A cold layer adapted for use in a cross counter flow heat exchanger core includes a hot inlet tent for receiving hot flow and a hot outlet tent for discharging hot flow. The cold layer is configured to receive a cold inlet flow and discharge a cold outlet flow defining a main cold flow direction. The cold layer includes a first and second cold main closure bar, each parallel to the main cold flow direction and located near the respective hot inlet or outlet tent, cold main fins perpendicular to the direction of the hot inlet flow, and cold inlet corner fins near the hot inlet tent, configured to receive a portion of the cold inlet flow in a direction that forms an angle with the main cold flow that is greater than 5 degrees.

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: A heat exchanger with increased heat transfer capability is provided. The heat exchanger 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 end 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 end 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 environmental control system includes a cross-flow heat exchanger, a first valve, and a second valve. The heat exchanger includes three cores each with their own respective inlet, outlet, and cold air passage. The first inlet is fluidly connected with a hot air source. The second outlet is fluidly connected to the first outlet. The third inlet is fluidly connected to the second inlet and to a hot air destination. The first valve is fluidly connected with the hot air source, the second inlet, and the third inlet. The first valve is positioned in-line between the hot air source and the second and third inlets. The second valve is fluidly connected to the hot air destination, to the first outlet, and to the second outlet. The second valve is positioned in-line between the hot air destination and the first and second outlets.

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: An air cycle machine includes a compressor in fluid communication with an output conduit, a first turbine operably connected to the compressor and fluidly coupling the compressor with the output conduit, a second turbine operably connected to the compressor and fluidly coupling the compressor with the output conduit, and a valve. The valve couples the compressor with the output conduit and has an open position and a closed position. In the open position the first turbine and the second turbine are fluidly connected in parallel between the compressor and the output conduit. In the closed position the first turbine is fluidly connected in series with the second turbine between the compressor and the output conduit. Air cycle machine systems and methods of controlling flow in air cycle machines are also described.

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: 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: An environmental control system (ECS) for an aircraft includes at least one cooling turbine, and a turbine bypass valve disposed fluidly upstream of the at least one cooling turbine. The turbine bypass valve is configured to direct a first portion of an ECS output airflow to a first air load at a first pressure via a first outlet passage, and direct a second portion of the ECS output airflow across a cooling turbine of the at least one cooling turbine and to a second air load at a second pressure lower than the first pressure for cooling thereof.

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.

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: An environmental control system includes a cross-flow heat exchanger, a first valve, and a second valve. The heat exchanger includes three cores each with their own respective inlet, outlet, and cold air passage. The first inlet is fluidly connected with a hot air source. The second outlet is fluidly connected to the first outlet. The third inlet is fluidly connected to the second inlet and to a hot air destination. The first valve is fluidly connected with the hot air source, the second inlet, and the third inlet. The first valve is positioned in-line between the hot air source and the second and third inlets. The second valve is fluidly connected to the hot air destination, to the first outlet, and to the second outlet. The second valve is positioned in-line between the hot air destination and the first and second outlets.

Abstract: A heat exchanger includes first and second parting sheets, a cold fin extending between the first and second parting sheets, and a closure bar extending between the first and second parting sheets. The closure bar includes first, second, third, and fourth surfaces, a body, first and second ends, an inlet, and an outlet. The body forms an opening that extends from the first end to the second end of the body. The first surface faces the cold fin. The second surface is an opposite side of the body from the first surface. The third surface is in contact with the first parting sheet. The fourth surface is in contact with the second parting sheet. The inlet is disposed at the first end of the closure bar and is fluidly connected to the outlet via the opening. The outlet is disposed at the second end of the closure bar.

Abstract: A cold layer adapted for use in a cross counter flow heat exchanger core includes a hot inlet tent for receiving hot flow and a hot outlet tent for discharging hot flow. The cold layer is configured to receive a cold inlet flow and discharge a cold outlet flow defining a main cold flow direction. The cold layer includes a first and second cold main closure bar, each parallel to the main cold flow direction and located near the respective hot inlet or outlet tent, cold main fins perpendicular to the direction of the hot inlet flow, and cold inlet corner fins near the hot inlet tent, configured to receive a portion of the cold inlet flow in a direction that forms an angle with the main cold flow that is greater than 5 degrees.

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 hot layer adapted for use in an asymmetric cross counter flow heat exchanger core that includes a number of alternating hot and cold layers, a hot inlet tent configured to receive a hot inlet flow and defining a hot inlet tent width, and a hot outlet tent configured to discharge a hot outlet flow and defining a hot outlet tent width. A hot inlet closure bar is located adjacent to the hot inlet tent, a hot outlet closure bar is located adjacent to the hot outlet tent, and two hot side closure bars are each located adjacent to respective corresponding inlet and outlet hot fins. An angle between the inlet fin direction and the middle fin direction ranges from 5-175 degrees, and the hot inlet tent width is less than the hot outlet tent width.

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: An environmental control system of an aircraft includes at least one heat exchanger and a compression device arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component and a second component coupled by a shaft. A first bleed port is arranged in fluid communication with the first component and a second bleed port, distinct from the first bleed port, is arranged in fluid communication with the second component.

Abstract: An environmental control system for an aircraft according to an example of the present disclosure includes a first turbine coupled to an engine and a second turbine coupled to a compressor. One or more ducts are configured to provide bleed air from the engine to the first and second turbines and the compressor such that the first and second turbines and the compressor condition the bleed air. A method of conditioning air is also disclosed.

Abstract: A heat exchanger with increased heat transfer capability is provided. The heat exchanger 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 end 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 end 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.