Abstract: A liquid-dissolved gas separator includes a metallic separator. The separator has a plurality of open pores that connect a liquid-facing surface of the separator with an opposed vacuum-facing surface of the separator for separating dissolved gases from a liquid traversing the liquid-facing surface of the separator body.

Abstract: An additively manufactured component is provided. The additively manufactured component includes an additively manufactured first part defining a first trench, an additively manufactured second part defining a second trench and a fiber optic sensor. The additively manufactured first and second parts are additively manufactured together with the first and second trenches corresponding in position such that the additively manufactured first and second parts form an assembled part with a fiber channel cooperatively defined by the first and second trenches. The fiber optic sensor includes a first sensor part embedded in the fiber channel and a second sensor part operably coupled to the first sensor part and extendible at an exterior of the assembled part.

Abstract: A heat exchanger includes a heat exchanger body having a first face, a second face disposed opposite the first face, a first wall, and a second wall disposed opposite the first wall. The first wall and the second wall each extend between the first face and the second face. The heat exchanger body defines a first transducer passageway and a second transducer passageway. The first transducer passageway extends from the first face towards the first wall. The second transducer passageway extends from the second face towards the first wall.

Abstract: A multi-stage gear pump includes a first pump stage, a second pump stage, and a variable speed gearbox including an input and an output, wherein the input is rotationally coupled to the first pump stage and the input rotates at a first rotational speed, and the output is rotationally coupled to the second pump stage and rotates at a second rotational speed, wherein a variable gear ratio determines the second rotational speed relative to the first rotational speed.

Abstract: A liquid-dissolved gas separator includes a metallic separator. The separator has a plurality of open pores that connect a liquid-facing surface of the separator with an opposed vacuum-facing surface of the separator for separating dissolved gases from a liquid traversing the liquid-facing surface of the separator body.

Abstract: A heat exchange system for an aircraft includes an aircraft controller for controlling an operation of an aircraft, a thermoelectric device having a low temperature side and a high temperature side. Heat is transferred away from the inlet line to the outlet line through the thermoelectric device when a predetermined condition is met.

Abstract: A heat exchanger includes a first half defining a first inlet portion and a first outlet portion, a second half defining a second inlet portion and a second outlet portion. The first half and the second half are configured to mate and form an inlet chamber and an outlet chamber. At least one of the first half or the second half includes one or more inlet transfer holes defined through a thickness of at least one of the first inlet portion and/or the second inlet portion. At least one of the first half or the second half includes one or more outlet transfer holes defined through a thickness of at least one of the first outlet portion or the second outlet portion.

Abstract: A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel stabilization unit. The fuel-air heat exchanger places deoxygenized fuel in a heat exchange relationship with compressor bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine is operationally connected to the engine compressor and receives cooled bleed air from the fuel-air heat exchanger.

Abstract: A turbomachine blade clearance system includes an actuator including an actuating portion that can be fixed to an interior surface of a turbomachine housing and a shaft for actuating movement relative to the turbomachine housing, a turbomachine blade seal operatively connected to the shaft of the actuator and configured to move relative to the turbomachine housing to adjust a distance from a turbomachine blade of a turbomachine to maintain a predetermined gap clearance between the blade seal and the blade, a waveguide disposed within the shaft, and at least one antenna disposed in electromagnetic communication with the waveguide such that a signal from the antenna can be directed by the waveguide.

Abstract: A heat exchange system for an aircraft includes an aircraft controller for controlling an operation of an aircraft, a thermoelectric device having a low temperature side and a high temperature side. Heat is transferred away from the inlet line to the outlet line through the thermoelectric device when a predetermined condition is met.

Abstract: A heat exchange system for an aircraft includes an aircraft controller for controlling an operation of an aircraft, a thermoelectric device having a low temperature side and a high temperature side, an inlet line that carries fluid through the low temperature side of the thermoelectric device and to the aircraft controller; and an outlet line that carrier the fluid away from the and aircraft controller through the high temperature side of the thermoelectric device. Heat is transferred away from the inlet line to the outlet line through the thermoelectric device when a predetermined condition is met.

Abstract: In one aspect, a turbine engine is provided. The engine includes a fan, a core engine case configured to receive a core airflow, and an inner fan case. An inner air bypass is defined between the core engine case and the inner fan case, and the engine further includes an outer fan case, an outer air bypass defined between the inner fan case and the outer fan case, a first heat exchanger arranged in the core engine case, the first heat exchanger providing heat exchange between the liquid and the core airflow to cool the core airflow, and a second heat exchanger arranged in the outer air bypass. The second heat exchanger is fluidly coupled to the first heat exchanger to receive the cooled core airflow. The second heat exchanger provides heat exchange between cooled core airflow and the second portion of airflow to further cool the cooled core airflow.

Abstract: An actuation system for a gas turbine engine oriented about a centerline includes a translating ring, at least one hydraulic actuator, and at least one electric actuator. The translating ring is oriented about the centerline and configured to move axially along the centerline. The at least one hydraulic actuator is configured to provide a first mechanical force to move the translating ring along the centerline. The at least one electric actuator is configured to provide a second mechanical force to move the translating ring in the axial direction. The at least one electric actuator is controlled to provide the second mechanical force upon determination of an operating condition.

Abstract: In one aspect, a turbine engine is provided. The engine includes a fan, a core engine case configured to receive a core airflow, and an inner fan case. An inner air bypass is defined between the core engine case and the inner fan case, and the engine further includes an outer fan case, an outer air bypass defined between the inner fan case and the outer fan case, a first heat exchanger arranged in the core engine case, the first heat exchanger providing heat exchange between the liquid and the core airflow to cool the core airflow, and a second heat exchanger arranged in the outer air bypass. The second heat exchanger is fluidly coupled to the first heat exchanger to receive the cooled core airflow. The second heat exchanger provides heat exchange between cooled core airflow and the second portion of airflow to further cool the cooled core airflow.

Abstract: A turbomachine blade clearance system includes an actuator including an actuating portion that can be fixed to an interior surface of a turbomachine housing and a shaft for actuating movement relative to the turbomachine housing, a turbomachine blade seal operatively connected to the shaft of the actuator and configured to move relative to the turbomachine housing to adjust a distance from a turbomachine blade of a turbomachine to maintain a predetermined gap clearance between the blade seal and the blade, a waveguide disposed within the shaft, and at least one antenna disposed in electromagnetic communication with the waveguide such that a signal from the antenna can be directed by the waveguide.

Abstract: An example fuel system includes a fuel sensor configured to sense at least one characteristic of a fuel provided to an engine. The fuel is selected from a plurality of different fuel types. The fuel system also includes a controller that is configured to meter the fuel in response to the at least one characteristic of the fuel.

Abstract: A gas turbine engine section has a rotor carrying a plurality of blades. The blades have airfoils which define a radially outer tip. A blade outer air seal is positioned radially outwardly of the tips of the blades. The blade outer air seal is provided by at least a plurality of circumferentially spaced segments, which slide circumferentially relative to each other to adjust an inner diameter of an inner surface of the blade outer air seal segments. An actuator actuates the blade outer air seal segments to slide towards each other to control a clearance between the inner periphery of the blade outer air seal segments and the radially outer tip of the blade airfoils. A gas turbine engine is also disclosed.

Abstract: A heat exchanger for disposition within a duct having a curved surface is provided and includes a frame formed to define an inlet, an outlet and an interior by which the inlet and outlet are fluidly communicative, the frame including first and second surfaces having curvatures similar to that of the curved surface on either side of the interior and a heat exchanger fin disposed in the interior, the fin having corrugations and being formed to define slots transverse to the corrugations such that the fin is bendable along the curvatures of the first and second surfaces.

Abstract: A heat pipe system and methods of arranging a heat pipe system are provided. The heat pipe system includes a plurality of heat pipes, with each of the plurality of heat pipes including a hot end thermally coupled to a heat source and a cold end thermally coupled to a heat sink The plurality of heat pipes include a first pair of heat pipes. When the plurality of heat pipes are secured to a rotatable body, the first pair of heat pipes are aligned with and oriented in opposing directions along a first axis of rotation of the rotatable body.

Abstract: A turbomachine includes a fan having a housing and a plurality of vanes rotatable within the housing. Each of the plurality of vanes includes a pressure side and a suction side. A pressure sensing system includes at least one pressure sensor mounted to one of the pressure side and the suction side of one or more of the plurality of vanes, and a pressure sensor receiver mounted to the housing. The at least one pressure sensor is configured and disposed to communicate pressure data to the pressure sensor receiver.