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 header for a high-pressure heat exchanger includes a first high-pressure transition section with inlets for multiple first high-pressure flow channels that are spaced from one another in a radial direction and collectively arranged in a substantially circular shape. The inlets for the multiple first high-pressure flow channels on a radially outer edge of the first high-pressure transition section are spaced further apart in a circumferential direction from adjacent inlets of the multiple first high-pressure flow channels than radially inward inlets are spaced from adjacent radially inward inlets of the multiple first high-pressure flow channels. The header also includes multiple first high-pressure flow channels extending from the first high-pressure transition section to a second-high pressure transition section that is configured to divide each of the multiple first high-pressure flow channels into at least two first high-pressure sub-flow channels.

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 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 includes a body, a plurality of first flow channels defined in the body; and a plurality of second flow channels defined in the body. The second flow channels are fluidly isolated from the first flow channels. The first flow channels and second flow channels are arranged in a checkerboard pattern.

Abstract: A counter-flow heat exchanger core includes a first wall defining a longitudinal axis. The first flow path is defined within the first wall. The first flow path includes a primary flow inlet and a primary flow outlet downstream from the primary flow inlet. The heat exchanger core includes at least two hollow vanes circumferentially spaced apart and extending in a radially inward direction from the first wall. Each of the at least two hollow vanes includes a first vane wall and a second vane wall. The heat exchanger core includes a second flow path defined within the at least two hollow vanes between the first vane wall and second vane wall of each of the at least two hollow vanes. The heat exchanger core includes at least one fin extending between two of the at least two circumferentially spaced apart vanes.

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 includes a body, a plurality of first flow channels defined in the body; and a plurality of second flow channels defined in the body. The second flow channels are fluidly isolated from the first flow channels. The first flow channels and second flow channels are arranged in a checkerboard pattern.

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 includes a heat exchanger body having a first end and a second end opposed to the first end along a flow axis. A plurality of flow channels is defined in the heat exchanger body extending axially with respect to the flow axis. A first set of the flow channels forms a first flow circuit and a second set of the flow channels forms a second flow circuit that is in fluid isolation from the first flow circuit. Each flow channel is fluidly isolated from the other flow channels. The flow channels all conform to a curvilinear profile.

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: 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 heat exchanger includes a heat exchanger body having a first end and a second end opposed to the first end along a flow axis. A plurality of flow channels is defined in the heat exchanger body extending axially with respect to the flow axis. A first set of the flow channels forms a first flow circuit and a second set of the flow channels forms a second flow circuit that is in fluid isolation from the first flow circuit. Each flow channel is fluidly isolated from the other flow channels. The flow channels all conform to a curvilinear profile.

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 core includes a first wall defining a longitudinal axis. The first flow path is defined within the first wall. The first flow path includes a primary flow inlet and a primary flow outlet downstream from the primary flow inlet. The heat exchanger core includes at least two hollow vanes circumferentially spaced apart and extending in a radially inward direction from the first wall. Each of the at least two hollow vanes includes a first vane wall and a second vane wall. The heat exchanger core includes a second flow path defined within the at least two hollow vanes between the first vane wall and second vane wall of each of the at least two hollow vanes. The heat exchanger core includes at least one fin extending between two of the at least two circumferentially spaced apart vanes.

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 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 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 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 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.