Abstract: A pressure sensor for fluid control system for an aircraft includes an enclosure, a piston assembly, and a bellows. The enclosure has a body that extends between a first end and a second end. A first fluid line extends to the first end. The piston assembly has a piston head that is movably disposed within the enclosure and a piston rod that extends from the piston head and through the second end. The bellows is disposed within the body that extends between and is operatively connected to the piston head and the first end.

Abstract: A system and method for detection of coking in a fuel. The system including a fuel system for delivery of fuel, a fuel contamination sensor having a contamination detection sensor with input and output transducers immersed in the fuel, a controller in operable communication with the fuel contamination sensor, the controller configured to execute a method for detection of coking in fuel. The method including generating an excitation signal for the contamination detection sensor, receiving at a controller operably connected to the contamination detection sensor, a sensor output signal from the output transducer, comparing the sensor output signal with the excitation signal, diagnosing a condition of the fuel based on a the comparing, and indicating a condition of coking based on the diagnosing. The system also includes an enunciator to indicate the detection of coking in the fuel.

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 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: An objective-driven system for blade tip clearance control may comprise a BOAS and a controller in operable communication with the BOAS. A tangible, non-transitory memory may be configured to communicate with the controller, the tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving an operating objective definition, and modulating a location of the BOAS using an optimization loop comprising the operating objective definition, input vector variables, and output vector variables driven by the input vector variables.

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: 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: 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: Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring a blade clearance of a first secondary BOAS that is circumferentially adjacent the first primary BOAS based on a position of the first primary BOAS when the blade clearance of the first primary BOAS is at the first predetermined blade clearance, determining if the measured blade clearance of the first secondary BOAS is at a value corresponding to the first predetermined blade clearance, and adjusting the position of the first secondary BOAS when the blade clearance of the first secondary BOAS is not at the first predetermined blade clearance with an actuator operably connected to the first secondary BOAS.

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 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: 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.

Abstract: A fuel pump system for a turbomachine engine can include a boost pump driven by an electric motor and configured to be in fluid communication with a fuel tank, a primary pump configured to be driven by a shaft connected to the turbomachine engine, wherein the primary pump is in fluid communication with the boost pump downstream of the boost pump by a boost branch, a bypass flow branch that connects the boost branch to a downstream branch that is downstream of the primary pump, the downstream branch is in fluid communication with one or more metering valves and/or one or more fuel nozzles, and a bypass valve disposed in the bypass flow branch and/or the downstream branch and configured to selectively directly fluidly communicate the boost branch and the downstream branch.

Abstract: A motor-generator includes a double-sided stator having a first stator pole wound with a first stator winding of a first channel and a second stator pole wound with a second stator winding of a second channel. The first stator pole and the second stator pole are axially aligned with respect to a centerline of the motor-generator and radially offset between a radially inner side and a radially outer side of the double-sided stator. The motor-generator also includes at least one rotor radially disposed from the double-sided stator with respect to the centerline of the motor-generator.

Abstract: A tubular heat exchanger includes a first flow path to receive a first fluid flow, wherein the first flow path is defined by a conduit, and a support structure with a plurality of support structure openings, wherein the support structure supports the first flow path, the plurality of support structure openings define a second flow path to receive a second fluid flow, and the first flow path is in thermal communication with the second flow path.

Abstract: A strut assembly for a bearing compartment of a gas turbine engine includes an inner case, an outer case, and a first plurality of struts. The inner case is disposed within the bearing compartment and includes a first axis. The outer case defines an exterior of the bearing compartment and includes a second axis disposed co-axially with the first axis. The inner and outer cases define a flowpath between the inner and outer cases. Each strut of the first plurality of struts extends between and is connected to the inner and outer cases. The first plurality of struts is configured to maintain concentric positioning between the inner and outer cases and to allow relative changes in size between the inner and outer cases without deforming the inner case.

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: 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 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: 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.