Abstract: A heat exchanger including a plurality of tubes, a header, and a plurality of flow voids. The plurality of tubes extends in a first direction through which a first fluid is configured to flow. Each of the plurality of tubes have waves that repeat at regular intervals along the first flow direction and are spaced from one another vertically and laterally in the second direction. The header extends in the first direction and is attached to each of the plurality of tubes. The header is configured to convey the first fluid to each of the plurality of tubes. The plurality of flow voids are formed between the plurality of tubes. The plurality of flow voids extend in a second direction through which a second fluid is configured to flow such that the second fluid is in thermal contact with the plurality of tubes.

Abstract: A heat exchanger system includes an additively manufactured inlet header upstream of, and in fluid communication with, the heat exchanger core and an additively manufactured exit header downstream of, and in fluid communication with, the heat exchanger core. A method of manufacturing a header for a ducted heat exchanger system for a gas turbine engine includes additively manufacturing a header with respect to a desired airflow therethrough.

Abstract: A heat exchanger includes a core section defining a plurality of first fluid channels and a plurality of second fluid channels. The heat exchanger also includes a header section defining a plurality of first fluid layers and a plurality of second fluid layers. The heat exchanger further includes a transition region located between the header section and the core section, the transition region fluidly coupling the plurality of first fluid layers to the first fluid channels, each of the first fluid layers routing a first fluid to a respective group of first fluid channels.

Abstract: A fuel system for a gas turbine engine includes an accessory gearbox driven by a mechanical link to the gas turbine engine, a primary fuel pump providing a first fuel flow during engine operation, and a secondary fuel pump providing a second fuel flow. The primary fuel pump and the secondary fuel pump are driven by an output of the accessory gearbox.

Abstract: A gas turbine engine includes a main compressor section and a main turbine section. A cooling air supply system cools a location in at least one of the main compressor section and the main turbine section. The cooling air supply system includes a tap for tapping cooling air compressed by the main compressor section, connected for passing the cooling air through a heat exchanger and to a boost compressor, and then to the cooling location in the at least one of the main compressor section and the main turbine section. A fuel supply system has a fuel tank for delivering fuel to a fuel pump. At least one valve for selectively returning fuel downstream of the main pump back to an upstream location. At least one return turbine drives at least one fluid moving device in the air cooling system.

Abstract: A heat exchanger including a plurality of tubes, a header, and a plurality of flow voids. The plurality of tubes extends in a first direction through which a first fluid is configured to flow. Each of the plurality of tubes have waves that repeat at regular intervals along the first flow direction and are spaced from one another vertically and laterally in the second direction. The header extends in the first direction and is attached to each of the plurality of tubes. The header is configured to convey the first fluid to each of the plurality of tubes. The plurality of flow voids are formed between the plurality of tubes. The plurality of flow voids extend in a second direction through which a second fluid is configured to flow such that the second fluid is in thermal contact with the plurality of tubes.

Abstract: A fuel system for an engine can include a fuel circuit and a primary fuel pump in fluid communication with the fuel circuit and configured to pump fuel to the engine as a function of engine speed. The primary fuel pump is configured to pump insufficient fuel flow to the engine during at least one engine speed or speed range. The system also includes a supplemental fuel pump in fluid communication with the fuel circuit configured to selectively pump fuel to the engine at least during the at least one engine speed or speed range to supplement fuel flow from the primary fuel pump to provide sufficient total fuel flow to the engine during all engine speeds.

Abstract: A heat exchanger is disclosed herein that includes three walls that are each shaped in a wave pattern with the waves that extend in both a first lateral direction and a second lateral direction. A second wall is adjacent to and in contact with a first wall with the waves of the second wall being offset from the waves of the first wall by one-half wavelength in the first direction. The third wall is adjacent to and in contact with the second wall with the waves of the third wall being offset from the waves to the second wall by one-half wavelength in the second direction. The first wall and second wall form a first plurality of flow paths extending in the second direction, and the second wall and the third wall for a second plurality of flow paths extending in the first direction.

Abstract: A heat exchanger includes a core section defining a plurality of first fluid channels and a plurality of second fluid channels. The heat exchanger also includes a header section defining a plurality of first fluid layers and a plurality of second fluid layers. The heat exchanger further includes a transition region located between the header section and the core section, the transition region fluidly coupling the plurality of first fluid layers to the first fluid channels, each of the first fluid layers routing a first fluid to a respective group of first fluid channels.

Abstract: A method of cooling a component with a heat exchange device includes pulling air into a central airway in a heat exchange device using a blower; directing the air from the blower through a diffuser and across a heat sink base, wherein a first component positioned underneath the heat sink base is cooled when the air passes over the heat sink base; and directing the air out from the diffuser and across a second component to cool the second component.

Abstract: A counter-flow heat exchanger including: a primary flow passageway comprising a primary flow inlet, a primary flow outlet, and a plurality of primary flow subset passageways therebetween; a secondary flow passageway comprising a secondary flow inlet, a secondary flow outlet, and a plurality of secondary flow subset passageways therebetween; and a heat exchanger core comprising portions of the plurality of primary flow subset passageways and the plurality of secondary flow subset passageways, the secondary flow passageway being in thermal communication with the primary flow passageway in the heat exchanger core, wherein the primary flow subset passageways in the heat exchanger core and the secondary flow subset passageways in the heat exchanger core are oriented such that primary fluid flow through the primary flow subset passageways flows opposite secondary fluid flow through the secondary flow subset passageways.

Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a turbine section, with both the main compressor section and the turbine section housing rotatable components. A first tap taps air compressed by the main compressor section at an upstream location upstream of the downstream most location. The first tap passes through a heat exchanger, and to a cooling compressor. Air downstream of the cooling compressor is selectively connected to reach at least one of the rotatable components. The cooling compressor is connected to rotate at a speed proportional to a rotational speed in one of the main compressor section and the turbine section. A valve system includes a check valve for selectively blocking flow downstream of the cooling compressor from reaching the at least one rotatable component. A dump valve selectively dumps air downstream of the cooling compressor. A method is also disclosed.

Abstract: A heat exchanger header includes a plurality of first flow channels and second flow channels, each flow channel including a fluid circuit opening for fluid communication with a fluid circuit of a heat source and a core opening for communication with a heat exchanger core, wherein at least the first flow channels include a lobe section defining a non-uniform cross-sectional flow area that changes along a flow direction.

Abstract: Fuel tank inerting systems are provided. The systems include a fuel tank, an air source arranged to supply air into a reactive flow path, a catalytic reactor having a plurality of sub-reactors along the flow path, and a heat exchanger. The sub-reactors are arranged relative to the heat exchanger such that the flow path passes through at least a portion of the heat exchanger between two sub-reactors along the flow path. At least one fuel injector is arranged relative to at least one sub-reactor. The fuel injector is configured to inject fuel into the flow path at at least one of upstream of and in the respective at least one sub-reactor to generate a fuel-air mixture. A fuel tank ullage supply line fluidly connects the flow path to the fuel tank to supply an inert gas to a ullage of the fuel tank.

Abstract: A method of cooling a component with a heat exchange device includes pulling air into a central airway in a heat exchange device using a blower; directing the air from the blower through a diffuser and across a heat sink base, wherein a first component positioned underneath the heat sink base is cooled when the air passes over the heat sink base; and directing the air out from the diffuser and across a second component to cool the second component.

Abstract: Disclosed is a heat exchanger for a thermal management system of an aircraft assembly, the heat exchanger including: a core including a first side with a first core inlet, a second side opposing the first side and includes a first core outlet, the first core inlet is in fluid communication with the first core outlet, a third side having a second core inlet and a fourth side opposing the third side and includes a second core outlet, the second core inlet is in fluid communication with the second core outlet, and a screen wrapped around the core, the screen covering the first core inlet and the first core outlet, and a plurality of rollers disposed between the core and the screen for movably securing the screen to the core, the rollers engaging the screen and movement of at least one of the rollers moves the screen about the core.

Abstract: A counter-flow heat exchanger comprising a heat exchanger core including an inner wall and an outer wall radially outward and spaced apart from the inner wall. A first flow path is defined within the inner wall and a second flow path is defined between the inner wall and the outer wall. The heat exchanger core includes a primary flow inlet, a primary flow outlet and a middle portion therebetween. The inner and outer walls are concentric at the primary flow inlet of the heat exchanger core. The inner wall defines a first set of channels extending axially from the primary flow inlet to the middle portion of the heat exchanger core diverging away from a radial center of the heat exchanger core. The inner wall and the outer wall define a second set of channels extending axially from the primary flow inlet to the middle portion of the heat exchanger core converging toward the radial center of the heat exchanger core.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a heat exchanger positioned therein and a dehumidification system arranged in fluid communication with the ram air circuit. A plurality of expansion devices is arranged in fluid communication with the ram air circuit and the dehumidification system. At least one of the expansion devices is a simple cycle expansion device.

Abstract: A counter-flow heat exchanger comprising a heat exchanger core including an inner wall and an outer wall radially outward and spaced apart from the inner wall. A first flow path is defined within the inner wall and a second flow path is defined between the inner wall and the outer wall. The heat exchanger core includes a primary flow inlet, a primary flow outlet and a middle portion therebetween. The inner and outer walls are concentric at the primary flow inlet of the heat exchanger core. The inner wall defines a first set of channels extending axially from the primary flow inlet to the middle portion of the heat exchanger core diverging away from a radial center of the heat exchanger core. The inner wall and the outer wall define a second set of channels extending axially from the primary flow inlet to the middle portion of the heat exchanger core converging toward the radial center of the heat exchanger core.

Abstract: A heat exchanger header includes a plurality of first flow channels and second flow channels, each flow channel including a fluid circuit opening for fluid communication with a fluid circuit of a heat source and a core opening for communication with a heat exchanger core, wherein at least the first flow channels include a lobe section defining a non-uniform cross-sectional flow area that changes along a flow direction.