Abstract: An electric system and method includes a flux regulated permanent magnet generator configured to provide power for an accessory electric system. The accessory electric system includes an engine accessory and a voltage regulator. The engine accessory includes an induction motor that receives power from the flux regulated permanent magnet generator. The voltage regulator is configured to control an output of the flux regulated permanent magnet generator to maintain a constant voltage-to-frequency ratio.

Abstract: A pump comprises a housing partially defining a cavity, an impeller arranged in cavity, the impeller including a first disk, and a vane arranged on the first disk, the impeller operative to rotate about a rotational axis, a first stator core arranged on the housing, windings arranged on the first stator core, and a first inlet defined by the housing, wherein the first inlet, the impeller, and the housing partially define a fluid flow path.

Abstract: A fitting has a threaded insert to be tightened within a housing bore. A first lock ring has an anti-rotation structure on an outer peripheral surface to interfit with anti-rotation structure in a housing. The first lock ring has a face extending generally perpendicular to an axis of the insert, with anti-rotation structure included on the first face. A second lock ring has anti-rotation structure on a face which extends perpendicular to an axis of the threaded insert. The anti-rotation structure on the faces of the first and second lock ring interfit to resist relative rotation of the two. An assembly is also disclosed.

Abstract: A method of aircraft fuel distribution includes selecting a longitudinal center of gravity and predicting a rate of change of the center of gravity during flight. Fuel is located in a tail fin tank of a vertical tail fin of the aircraft, and is transferred from the tail fin tank forward at a predetermined transfer rate to counteract the predicted rate of change thereby maintaining the selected center of gravity. An aircraft fuel distribution system includes a center main fuel tank, a tail fin tank and a tail fin fuel pump to pump fuel between the tail fin tank and the center main fuel tank. An electronic controller operates the tail fin fuel pump such that fuel is flowed between the tail fin tank and the center main fuel tank at a predetermined transfer rate to maintain automatically an optimal position of a longitudinal center of gravity of the aircraft.

Abstract: A fuel system for a gas turbine engine comprises an injector disposed to inject fuel and air into a combustor of the gas turbine engine. In a first embodiment, the fuel system further comprises an air separation module configured to supply oxygen-enriched air into the combustor via the injector for combustion. In a second embodiment, the fuel system further comprises a barbotage system and a heating element. The barbotage system is configured to feed hydrogen to the injector, and the heating element is configured to pre-heat the fuel.

Abstract: A fuel supplying system includes a primary circuit for delivering fuel from a fuel tank to a primary circuit outlet. The system also includes a first supply circuit connected to the primary circuit outlet, the first supply circuit comprising a first supply circuit pump configured to pump fuel from the primary circuit outlet to engine fuel nozzles. The system further includes a second supply circuit also connected to the primary circuit outlet. The second supply circuit includes at least one actuating device configured to receive power from hydraulic pressure of the fuel. The second supply circuit also includes a second supply circuit pump configured to pump fuel from the primary circuit outlet to an actuating device, wherein the second supply circuit pump is independent from the first supply circuit pump.

Abstract: A shut-off valve system includes a tank having an inlet and an outlet with a flow path defined therebetween. A float within the tank occludes the tank outlet at a first fluid level under positive G forces and unoccludes the tank outlet at a second fluid level under positive G forces. A flow restricting orifice and/or a hydraulic fuse is downstream of float and tank outlet to restrict fluid communication between tank outlet and an ejector pump. A method for restricting flow in an ecology fuel return system includes recovering fuel from engine components, communicating the fuel to an inlet of a fuel tank, pumping the fuel from an outlet of fuel tank to an inlet of an engine when a float within tank unoccludes the outlet of the fuel tank, and restricting fluid flow from tank outlet to an ejector pump with a flow restricting orifice and/or a hydraulic fuse.

Abstract: A heat exchanger has a first flow path communicating fluid into a turning flow path at a first mitered interface. The turning flow path has a second mitered interface for communicating fluid from the turning flow path into a return flow path. The first flow path extends in a nominal direction toward the turning flow path. First flow passages within the first flow path and return flow passages in the return flow path are provided by walls having alternating sections which extend in opposed angular directions relative to nominal directions. Sizes of a portion of passages at the interfaces are different such that some passages are larger than other openings into other passages.

Abstract: A system configured for detection of corrosion of a metal substrate is disclosed. The article includes a first layer disposed over the metal substrate comprising a first electrically conductive polymer, and a first electrical conductivity sensor in sensing contact with the first layer.

Abstract: In accordance with at least one aspect of this disclosure, a turbomachine cooling system includes a first low pressure port disposed in a low pressure portion of a turbomachine and a first high pressure port disposed in a high pressure portion of the turbomachine and in selective fluid communication with the first low pressure port via a cooling channel. The high pressure portion of the turbomachine is configured for a higher compression than the low pressure portion of the turbomachine where the first low pressure port is disposed. The cooling system can include a heat exchanger system disposed in the cooling channel such that a flow traveling from the first high pressure port to the first low pressure port is cooled by the heat exchanger system before traveling through the first low pressure port into the low pressure portion of the turbomachine.

Abstract: A turbomachine blade clearance system can include an actuator having an anchor portion for fixation to an interior surface of a turbomachine housing and an actuating portion for actuating movement relative to the anchor portion. A turbomachine blade seal can be operatively connected to the actuating portion 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.

Abstract: In at least one aspect of this disclosure, a shut off valve for an ecology fuel return system can include an inlet for receiving a fluid, an outlet for effusing the fluid, and a valve member configured to move between an open position such that the valve member allows fluid to effuse from the outlet and a closed position such that the valve member prevents fluid from effusing from the outlet. The valve member can include a pressure deflector configured to prevent fluid flow from biasing the valve member toward the closed position.

Abstract: An isolated power management system includes at least one electronic power generator with a stationary side and a rotational side. The stationary side has an exciter field stator winding, a main field stator winding, and an isolator stator winding. The rotational side rotates with respect to the stationary side and includes a rotor power converting unit. At least one digital engine microcontroller generates a first electrical excitation current and excites the exciter field stator winding to generate a first electromagnetic field. The rotor power converting unit generates a second electromagnetic field in response to being energized by the first electromagnetic field. The main field stator winding and the isolator stator winding output first and second power signals, respectively, in response to being energized by the second electromagnetic field, where the second power signal is independent and isolated from the first power signal.

Abstract: Embodiments of the disclosure include a de-icing system for an aircraft. The de-icing system includes a plurality of resistive-inductive heating elements inserted adjacent to a flight control surface and a controller configured to provide a supply current to each of the plurality of resistive-inductive heating elements. Each of the plurality of resistive-inductive heating elements produces an electromagnetic field normal to the flight control surfaces and resistive heat in response to the supply current. The electromagnetic field induces an eddy current in the flight control surface.

Abstract: An electromagnetic device for overspeed control of a propeller driven by an engine shaft comprises a clutch, an eddy-current coupler, and an electromagnetic brake. The clutch is disposed to mechanically decouple the propeller from the engine shaft. The eddy current coupler is disposed to electromagnetically couple the propeller to the engine shaft when the clutch mechanically decouples the propeller from the engine shaft. The electronic brake is disposed to artificially load the engine shaft when the propeller load on the engine shaft is reduced by mechanically decoupling the propeller from the engine shaft.

Abstract: A compact heat exchanger is provided and includes a first manifold defining an inlet for receiving from a component a fluid to be cooled and an outlet for returning the cooled fluid to the component to cool the component. A second manifold is disposed spaced from the first manifold. A core extends between and fluidly communicates with the manifolds and includes hexagonal channels. Each channel is formed by mini-tubes defining respective triangular passages. A cross-section of the core defines an irregular-cross structure. The fluid enters the inlet of the first manifold, makes a first pass through the mini-tubes to the second manifold, makes a second pass through the mini-tubes to the first manifold such that the fluid is cooled across the mini-tubes, exits the first manifold through the outlet, and returns to the component to cool the component. A method of manufacturing the heat exchanger is provided also.

Abstract: Aspects of the disclosure are directed to a thrust reverser of an aircraft, comprising: a wall having a first surface that partially forms a flow channel associated with an air flow, a blocker door having a second surface that partially forms the flow channel, and a dielectric elastomeric device that is configured to selectively expand and contract within a cavity formed between the wall and the blocker door where the cavity is substantially radially adjacent to the flow channel when the thrust reverser is in a stowed state.

Abstract: A device is disclosed for separating nitrogen and oxygen. The device includes an inlet in fluid communication with a source of a gas comprising oxygen and nitrogen, a membrane having a greater permeability to oxygen than to nitrogen. One side of the membrane is in fluid communication with the inlet, and the other side of the membrane is in fluid communication with an outlet for nitrogen-enriched gas. An outlet for oxygen-enriched gas is also in fluid communication with the first side of the membrane. A porous metal foam is disposed between the inlet and the membrane.

Abstract: A bearing carrier has a bearing body including a first material. The bearing body has an exterior surface defining a bridge land with a finger cut and rotatably supports a first and second gear. The first and second gears intermesh with one another for pressurizing fluid traversing the gears between a fluid inlet and a fluid outlet defined in a housing enveloping the bearing carrier. The bridge land is defined in a second material integral with the first material.

Abstract: A heat exchanger has a plurality of cells. A first subset of the cells extends for a lesser distance along an axis of the cells and a second subset of the cells extends for a greater axial distance. The second subset of cells extends through separator plates which are positioned beyond axial ends of the first subset of cells. A method is also disclosed.