Abstract: A heat exchanger includes a first side of a heat exchanger layer with a first flow path, wherein the first flow path flows through a heat soak region and a flow region, and a second side of the heat exchanger layer with a second flow path in thermal communication with the first flow path, wherein an inlet of the first flow path and an inlet of the second flow path are proximate in the heat soak region.

Abstract: A fuel ecology system includes a fuel ecology reservoir having a reservoir volume, includes a moveable barrier disposed within the reservoir volume, the movable barrier defining a first volume and a second volume within the reservoir volume, a fuel inlet port in fluid communication with the first volume, a fuel outlet port in fluid communication with the first volume, and a vent port in fluid communication with the second volume.

Abstract: A filter assembly for a fluid flow system includes a filter housing, a housing inlet to allow the fluid flow into the filter housing and a housing outlet to allow the fluid flow to exit the filter housing. A filter element is located in the filter housing to collect contaminants from the fluid flow. A pressure sensor is located to measure a pressure drop across the filter element. The pressure sensor includes at least one sense line extending into an interior volume of the filter housing. A method of monitoring a filter assembly for a fluid flow system includes positioning a pressure sensor at a filter assembly, extending at least one sense line from the pressure sensor into an internal volume of a filter housing of the filter assembly, and measuring a pressure drop across a filter element of the filter assembly via the pressure sensor.

Abstract: An embodiment of a gear pump arrangement includes a first gear defining a first set of teeth; and a second gear defining a second set of teeth, the first set of teeth and the second set of teeth being in meshed communication such that fluid is pumped in response to rotation of the first gear and the second gear, at least one of the first set of teeth and the second set of teeth having at least one gear tooth passageway through each tooth thereby fluidically connecting opposing faces of the tooth.

Abstract: An engine fuel system is disclosed for managing drainage of fuel in response to an engine shut-down condition. For normal operation, a piston of a piston assembly is maintained in a first position by pressurized fuel in a volume on a first side of the piston. In response to engine shut-down, pressure is removed from the first side of the piston and fuel in the volume on the first side of the piston is drained into a return conduit that is part of the fuel system's thermal management system. Displacement of the piston in response to removal of pressure on the first side of the piston creates a volume on a second side of the piston for drainage of fuel from a fuel manifold.

Abstract: A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.

Abstract: A pump includes first and second gears coupled to one-another for rotation about respective axis. The first gear may include a concentrically disposed first hub portion and a plurality of first teeth radially projecting and circumferentially spaced about the first hub portion. A plurality of first recesses are defined by the first hub portion, communicate radially outward, and are circumferentially distributed about the first hub portion between adjacent teeth of the plurality of first teeth.

Abstract: A gear pump includes a drive gear with drive gear teeth and a driven gear with driven gear teeth. The drive gear is rotatably disposed about a drive gear axis. The driven gear is rotatably disposed about a driven gear axis and is intermeshed with the drive gear such that a plurality of driven gear teeth are in sliding contact with a plurality of the driven gear teeth. One or more of the drive gear teeth or the driven gear teeth define within the tooth interior a cavity. The cavity is in fluid communication through an orifice with an inter-tooth volume defined between the contacting drive gear teeth and driven gear teeth such that fluid flows through the orifice to reduce cavitation within fluid confined within the inter-tooth volume.

Abstract: A disclosed aircraft propulsion system includes a gas turbine engine supported within an aircraft fuselage, a main drive driven by the gas turbine engine and an open rotor propeller system supported outside of the aircraft fuselage separately from the gas turbine engine. A secondary drive that is driven by the main drive drives the open rotor propeller system.

Abstract: A shut-off valve includes a float and a negative G control component. The float is configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G. The negative G control component is operatively connected to the float to limit fluid, e.g. liquid or gas, communication between a tank outlet and an ejector pump during negative G events. An ecology fuel return system includes a tank, an ejector pump, a float, and a negative G control component, as described above. The tank has an inlet and an outlet. The inlet is configured to be in fluid communication with components of an engine. The ejector pump is in fluid communication with the tank outlet and is configured to pump fuel from the tank to a fuel pump inlet of an engine.

Abstract: An ecology system includes an ecology tank, a check valve, a shutoff valve, and an ejector pump. The check valve is fluidly connected to the ecology tank and is configured to allow flow from the ecology tank. The shutoff valve is fluidly connected to the check valve, and the ejector pump is fluidly connected to the shutoff valve. The ejector pump is configured to draw fuel from the ecology tank when the shutoff valve is in an open configuration.

Abstract: A seal device that may be for a variable area fan nozzle (VAFN) assembly of a turbofan engine is positioned between first and second surfaces configured to move between close and distant positions. The seal device includes a first electrode engaged to the first surface and a second electrode spaced between the first and second surfaces and spaced from the first electrode. A resilient first element of the device is disposed between and engages to the first and second electrodes, and is configured to move between contracted and expanded states when the electrodes are energized. A resilient second element of the device opposes the second surface and is engaged to the second electrode. The second element is configured to move between a compressed mode when the first and second surfaces are in the close position and an extended mode when the first and second surfaces are in the distant position.

Abstract: A heat exchanger is disclosed including an array of interlaced conduits. The conduit array includes a first plurality of conduits connected to a first inlet header at one end of the first plurality of conduits and to a first outlet header at an opposite end of the first plurality of conduits. This first plurality of conduits provides a first fluid flow path from the first inlet header through the first plurality of conduits to the first outlet header. The conduit array also includes a second plurality of conduits crossing and interlaced with the first plurality of conduits. First and second fluid flow paths are provided through the first and second pluralities of conduits, and a third fluid flow path is through open spaces between the crossed interlaced first and second pluralities of conduits.

Abstract: An aircraft propeller de-icing system comprises at least one propeller blade coupled to a rotatable prop assembly. The prop assembly is configured to rotate in response to rotatably driving a propeller shaft. At least one resistive-inductive heating unit is coupled to the at least one propeller blade. The resistive-inductive heating unit is configured to generate eddy currents that induce inductive heat in response to an electric current. A contactless power transfer system generates the electrical current in response to transferring power across an air gap separating the propeller shaft from the contactless power transfer system.

Abstract: A shut-off valve includes a float and a negative G control component. The float is configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G. The negative G control component is operatively connected to the float to limit fluid, e.g. liquid or gas, communication between a tank outlet and an ejector pump during negative G events. An ecology fuel return system includes a tank, an ejector pump, a float, and a negative G control component, as described above. The tank has an inlet and an outlet. The inlet is configured to be in fluid communication with components of an engine. The ejector pump is in fluid communication with the tank outlet and is configured to pump fuel from the tank to a fuel pump inlet of an engine.

Abstract: A bypass valve includes a housing for directing fluid flow through the bypass valve. A disc is positioned within the flow path having an inner perimeter and an outer perimeter. The bypass valve further includes at least one strain gauge disposed on the disc. One of the inner and outer perimeters of the disc is fixed to the bypass valve housing and one of the inner and outer perimeter of the disc is free to deflect from the bypass valve housing in response to fluid flow through the bypass valve such that a measurement of deflection of the disc induces strain on the strain gauge.

Abstract: A pendulum-type electromagnetic actuator is provided. The actuator includes a curved stationary member comprising a stationary core and a winding wound about the stationary core. A first moving member includes a first moving core and a first plurality of permanent magnets attached to the first moving core, the first moving member is curved and positioned on a first side of the stationary member. A second moving member includes a second moving core and a second plurality of permanent magnets attached to the second moving core, the second moving member is curved and position on a second side of the stationary member, the second side opposite the first side. The actuator further includes a pivot and a pivot connector connecting at least one of the first moving member and the second moving member to the pivot such that the curved moving member rotates about the pivot.

Abstract: A fuel management system may include a first fuel tank and a second fuel tank. The fuel management system may also include an intelligent crossfeed valve positioned between the first fuel tank and the second fuel tank and configured to allow fuel to flow between the first fuel tank and the second fuel tank. The fuel management system may also include a sensor configured to detect an amount to which the intelligent crossfeed valve is open. The fuel management system may also include an engine controller connected to the sensor and configured to cause the intelligent crossfeed valve to close in response to the intelligent crossfeed valve being open a third predetermined amount.

Abstract: An anti-icing system for annular turbofan engine housings what include a substantially closed annular housing at a leading edge of the turbofan engine housing, the annular housing containing a quantity of air and a conduit extending from a source of high pressure hot gas to the annular housing. The system also includes an injector connected to the end of the conduit and extending into the annular housing; one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing while the turbofan engine is operating. The nozzles have an entrance in fluid contact with the injector and an exit, wherein a cross-sectional area of the entrance is less than a cross-sectional area of the exit such that gas leaving the nozzles is travelling slower than gas entering the nozzles.

Abstract: An anti-icing system for annular gas turbine engine inlet housings includes a substantially closed annular housing at a leading edge of the gas turbine engine inlet housing, the annular housing containing a quantity of air and a conduit extending from a source of high-pressure hot bleed air to the annular housing. The system also includes an injector connected to the end of the conduit and extending into the annular housing and one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing. The system may include one or both of an airfoil on an upstream side of the injector and an air direction element disposed one the injector that causes the quantity of air to be directed toward an outlet of the one or more nozzles.