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: A kinetic energy storage system is provided. The kinetic energy storage system comprising: a vacuum container enclosing a vacuum chamber; and a flywheel located within the vacuum chamber, the flywheel being configured to convert electrical energy into kinetic energy, wherein the flywheel comprises: a rotor assembly and a stator assembly located within the rotor assembly.

Abstract: A brake system may comprise a hydraulic brake system or a hybrid brake system. The hydraulic brake system may include an inner axle disposed in an inner axle housing. The inner axle housing may include a working fluid therein. The inner axle may comprise a plurality of paddles extending radially from the inner axle. The working fluid may be pressurized and/or create friction with the plurality of paddles. The pressurized working fluid may impede a free rotation of the plurality of paddles.

Abstract: A multi-disk brake system comprises an electrical generator disposed therein. The electrical generator is configured to convert mechanical energy to electrical energy. The mechanical energy may be generated during a braking event of the multi-disk brake system. The electric generator may power various electrical components on the aircraft or store the electrical energy in a capacitor bank. The electric generator may also act as a motor and/or power a landing gear in a motor configuration.

Abstract: A rotary actuator including: an electric motor including: a left shaft projecting out towards a left-hand side; a left motor operably connected to the left shaft; a right shaft projecting out towards a right-hand side; and a right motor operably connected to the right shaft; an actuator housing operably connected to the right shaft; a left outer actuator shaft operably connected to the actuator housing; a left inner actuator shaft operably connected to the left shaft; and an output gearbox including: a ring gear rigidly connected to the left outer actuator shaft; a center gear located within the ring gear, the center gear being operably connected to the left inner actuator shaft; a planetary gear interposed between the ring gear and center gear, the planetary gear meshing with the ring gear and center gear; and an actuator stub operably connected to the planetary gear.

Abstract: An integrated flywheel energy storage device includes an inner stator having an interior support component and multiple stator cores connected to the interior support component, each with an associated stator coil arranged in multiple electrical phases. An outer rotor housing supports multiple active rotor poles which each face inward toward the stator cores, the active rotor poles being permanent magnets, copper relining, an induction squirrel cage, or variable reluctance poles. A vacuum containment housing surrounds the outer rotor housing. The outer rotor housing has a rotational moment of inertia that stores kinetic energy as a kinetic battery, allowing the device to deliver multi-phase electrical power when required. High power density is achieved by integrating the flywheel into the outer rotor housing. The device additionally functions as a gyroscope for stabilizing an exterior structure, or as a gyroscopic reference for navigational purposes when supported on a gimballed platform.

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: Apparatus and associated methods relate to equalizing wearing of a plurality of electrical power generators of an aircraft. Such equalization is achieved by logging operating conditions of at least a powered subset of the electrical power generators and then comparing of the logged operating conditions of each of the plurality of electrical power generators. Based on the comparison of the logged operating conditions, one of the plurality of electrical power generators for use the aircraft is recommended. A signal indicative of the recommended one of the electrical power generators determined is then generated.

Abstract: A fluid flow arrangement includes a manifold defining a fluid passage. A pressure sensor system is in fluid communication with the fluid passage. The pressure sensor system has a first sensor arranged along a first sense line and a second sensor arranged along a second sense line. The first and second sense lines are in fluid communication with the fluid passage. The first sense line has a first resonant frequency and the second sense line has a second resonant frequency. The second resonant frequency is different than the first resonant frequency.

Abstract: A gas turbine engine/generator arrangement including a generator, a low-pressure spool operably connected to the generator, a high-pressure spool operably connected to the low-pressure spool, and an electric motor. The electric motor is mechanically connected to the high-pressure spool and is electrically connected to the generator to communicate mechanical rotation between the electric motor and the high-pressure spool. Auxiliary power units and methods of generating electric power are also described.

Abstract: A bearing carrier is provided. The bearing carrier including: a bearing body of a first material having a shaft-receiving aperture and a bridge land with a finger cut to channel fluid pressurized by intermeshing of gears rotatably supported by the bearing carrier into an outlet defined by a housing enveloping the bearing carrier, wherein the bearing body includes a bearing face configured to be in a facing spaced relationship with the gears, wherein the bearing face includes a second material integral with the first material, wherein at least one of the first material and the second material define a portion of the bearing face of the bearing body extending about the shaft-receiving aperture, the portion of the bearing face excluding the bridgeland.

Abstract: A starter-generator module for a gas turbine engine includes an inner stator portion with an armature defining a rotation axis and an outer rotor portion disposed about the rotation axis. The outer rotor portion includes a permanent magnet and a gear teeth member. The permanent magnet is disposed about the rotation axis and the gear teeth member is defined on the outer rotor portion such that the gear teeth member transmits rotational energy to an accessory gearbox in a start mode and receives rotational energy from the accessory gearbox in a generate mode.

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: An adaptive thermal management system for a gas turbine engine includes a heat exchanger transferring heat into a coolant, a temperature sensor measuring a temperature of the coolant, and a sensor assembly that measures a parameter of the coolant during operation of the gas turbine engine. The parameter measured by the sensor assembly is indicative of a capacity of the coolant to accept heat from the hot flow. A control valve governs a flow of coolant into the heat exchanger. A controller adjusts the control valve to communicate coolant to the heat exchanger based on a determined capacity of the coolant to accept heat in view of the measured temperature of the coolant and that the measured parameter of the coolant is within a predefined range.

Abstract: An integrated fire suppression system receives inert gas from onboard gas generators and water effluent from onboard water generators. The inert gas and water effluent are mixed in a gas-water mixer to generate an inert aerosol. The inert aerosol is provided to a fire suppressant distribution network and sprayed into areas of the aircraft requiring fire suppression to provide cooling and to prevent reignition.

Abstract: An electro-mechanical system has a solenoid with a plunger received in a housing chamber. A plunger portion extends outwardly of the housing. There is at least one coil, and a control for the at least one coil. The control selectively applies a first higher level current to the coil to move the plunger to an actuated position relative to the housing. The control is operable to stop the supply of first high level current to the at least one coil and allow the plunger to move to an un-actuated position. The control is operable to supply a partial power current to the at least one coil when in said un-actuated position to resist movement of the plunger. A method is also disclosed.

Abstract: An outlet tube arrangement for an aircraft nacelle may comprise a vent tube defining a vent tube outlet, the vent tube outlet configured to be flush with an outer surface of the aircraft nacelle, and an inner tube disposed within the vent tube, the inner tube configured to increase momentum of fluid flowing through the inner tube to urge the fluid to separate from the inner tube without wetting the aircraft nacelle upon exiting from the vent tube, wherein the inner tube comprises an inner tube inlet comprising an inlet cross-sectional area and an inner tube outlet comprising an outlet cross-sectional area, the inlet cross-sectional area being less than a cross-sectional area of the vent tube at the inner tube inlet, the inlet cross-sectional area being greater than the outlet cross-sectional area, and the inner tube outlet being flush with the vent tube outlet.

Abstract: A fuel delivery system for a gas turbine engine is disclosed which includes a continuously variable drive assembly having a driving portion operatively associated with a gearbox of the gas turbine and a driven portion operatively associated with a fuel pump of the gas turbine, and a governor for controlling a drive ratio of the drive assembly to vary fuel pump flow performance over a range of engine operating conditions.

Abstract: A fuel-based thermal management system may comprise a heat exchanger configured to thermally couple a fluid and a fuel. A controller may be configured to modulate a flow of the fluid to the heat exchanger. A tangible, non-transitory memory may be configured to communicate with the controller. The controller may determine a temperature of the fluid, estimate a dissolved oxygen concentration in the fuel using a first fuel temperature, a flight cycle time, and at least one of an altitude measurement or a ambient pressure measurement, and modulate the flow of the fluid to the heat exchanger based on the dissolved oxygen concentration.

Abstract: A thermal management system for a gas turbine engine includes a primary vapor compression system including a primary evaporator defining thermal communication between a primary refrigerant and a flow of fuel to cool the fuel. A boost vapor compression system includes a boost heat exchanger defining thermal communication between the primary refrigerant. A boost refrigerant cools the primary refrigerant and a boost condenser in thermal communication with an air stream cools the boost refrigerant.