Abstract: A compressor assembly includes an impeller rotatable about a central axis and a seal assembly. The seal assembly includes a labyrinth seal defining a seal interface with a sealing element of the impeller and a seal support ring into which the labyrinth seal is installed. The seal support includes a deflector ramp fluidly downstream of the seal interface. The deflector ramp is configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis. A plurality of tortuous pathways are formed in a downstream surface of the seal support ring and are configured to diffuse a tangential component of the airflow.

Abstract: A compressor assembly includes an impeller rotatable about a central axis and a seal assembly. The seal assembly includes a labyrinth seal defining a seal interface with a sealing element of the impeller and a seal support ring into which the labyrinth seal is installed. The seal support includes a deflector ramp fluidly downstream of the seal interface. The deflector ramp is configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis. A plurality of tortuous pathways are formed in a downstream surface of the seal support ring and are configured to diffuse a tangential component of the airflow.

Abstract: A turbine pump system includes a turbine pump assembly including a housing, a pump located in the housing, a turbine located in the housing and operably connected to the pump, and a heat exchanger located between the pump and a hydraulic fluid load. The heat exchanger is configured to reduce a temperature of a hydraulic fluid flow output by the pump and directed to the hydraulic fluid load. The heat exchanger is operably connected to a turbine gas flow and utilizes the turbine gas flow to cool the hydraulic fluid flow at the heat exchanger.

Abstract: A rotor assembly of an electric machine includes a rotor body and a shaft assembly positioned at a central axis of the rotor assembly, and operably connected thereto. The shaft assembly includes a main rotor shaft operably connected to the rotor body, a center drive shaft located inside of the main rotor shaft, and a hydraulic damper sleeve located radially between the main rotor shaft and the center drive shaft. The hydraulic damper sleeve defines a plurality of cavities between the hydraulic damper sleeve and the center drive shaft. The hydraulic damper sleeve is configured to urge a fluid into and out of the plurality of cavities thereby damping relative circumferential motion between the main rotor shaft and the center drive shaft. A plurality of flow restrictors are configured to easily allow fluid into the plurality of cavities, while restricting flow of fluid out of the plurality of cavities.

Abstract: A power module includes a turbine arranged along a rotation axis, an interconnect shaft fixed in rotation relative to the turbine, and a compressor with a regenerative compressor wheel. The regenerative compressor wheel is fixed in rotation relative to the interconnect shaft supported for rotation with the turbine about the rotation axis. Generator arrangements, unmanned aerial vehicles, and methods of generating electrical power are also described.

Abstract: A rotor assembly of an electric machine includes a rotor body and a shaft assembly located at a central axis of the rotor assembly, and operably connected to the rotor body. The shaft assembly includes a main rotor shaft operably connected to the rotor body, a center drive shaft located inside of the main rotor shaft, and a hydraulic damper sleeve located radially between the main rotor shaft, defining a plurality of cavities between the hydraulic damper sleeve and the center drive shaft. The hydraulic damper sleeve is configured to urge a fluid into and out of the plurality of cavities thereby damping relative circumferential motion between the main rotor shaft and the center drive shaft.

Abstract: A compressor assembly includes an impeller rotatable about a central axis, and a seal assembly. The seal assembly includes a labyrinth seal defining a seal interface with a sealing element of the impeller, and a seal support ring into which the labyrinth seal is installed. The seal support includes a deflector ramp fluidly downstream of the seal interface. The deflector ramp is configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis.

Abstract: A distributed fuel module includes a fuel pressure vessel with a gas port and a fuel port, a hydraulic circuit breaker connected to the fuel port, and a gaseous circuit breaker. The gaseous circuit breaker is connected to the gas port, is fluidly coupled to the hydraulic circuit breaker through the fuel pressure vessel, and is cooperatively associated with the gaseous circuit breaker to isolate the fuel pressure vessel from a compressed gas header and a fuel header according to pressure differential within the hydraulic circuit breaker and pressure differential within the gaseous circuit breaker. Power modules and methods of controlling fuel flow in fuel modules are also described.

Abstract: A turbine pump assembly has a turbine, a centrifugal pump, a passive electrical speed control system, and a pneumatic circuit breaker. The pneumatic circuit breaker has a plurality of elements that are configured to move to a position blocking an outlet duct of the turbine when a flow velocity exceeds a predetermined threshold. A rocket thrust vector control system is also disclosed.

Abstract: A turbine pump system includes a turbine pump assembly including a housing, a pump located in the housing, a turbine located in the housing and operably connected to the pump, and a heat exchanger located between the pump and a hydraulic fluid load. The heat exchanger is configured to reduce a temperature of a hydraulic fluid flow output by the pump and directed to the hydraulic fluid load. The heat exchanger is operably connected to a turbine gas flow and utilizes the turbine gas flow to cool the hydraulic fluid flow at the heat exchanger.

Abstract: Disclosed is a sump cover for a sump basin of a generator of an aircraft, the sump cover having: a sump cover shell shaped as an inverted bowl, a front portion of the sump cover shell including a first plurality of fastener features, each configured to fasten to one of a second plurality of fastener features in the sump basin; and a sump cover support extending outwardly from the sump cover shell, past a perimeter edge of the sump cover shell, configured to fit through a sump port and against a sump tube of the sump basin, wherein the sump cover support and the first plurality of fastener features define a multi-point mounting configuration between the sump cover and the sump basin.

Abstract: A system includes a turbo pump that converts a compressed gas into power, and a storage tank configured to store the compressed gas. The system also includes a fire suppression control valve configured to be coupled between the storage tank and a cargo compartment of the aircraft and having a closed position in which the compressed gas fails to flow to the cargo compartment and an open position in which the compressed gas flows to the cargo compartment to suppress a fire. The system also includes a pump control valve configured to be coupled between the turbo pump and the storage tank and having a closed position in which the compressed gas fails to flow to the turbo pump and an open position in which the compressed gas flows to the turbo pump to cause the turbo pump to convert the compressed gas into the power.

Abstract: Disclosed is a hybrid electric torpedo that includes an igniter having a resistance, a current source, and a contactor. The torpedo includes a controller having input channels operable to receive a battery state of charge and the resistance and output channels configured to operate the contactor to control the current source of the igniter. The controller includes stored memory instructions operable upon execution to operate the contactor to conduct current through the igniter such that a temperature of the igniter increases. The contactor is operated responsive to the battery state of charge being less than a predetermined state of charge threshold and the resistance being less than a predetermined open circuit threshold.

Abstract: A landing gear assembly is also provided. The landing gear assembly may include a thin-skin support member defining a cavity and a cylindrical cavity. A cylinder may extend from the cylindrical cavity with an axle extending from the cylinder. A torsion link may be coupled to the axle and a torsion interface of the thin-skin support member.

Abstract: A system includes a turbo pump that converts a compressed gas into power, and a storage tank configured to store the compressed gas. The system also includes a fire suppression control valve configured to be coupled between the storage tank and a cargo compartment of the aircraft and having a closed position in which the compressed gas is prevented from flowing to the cargo compartment and an open position in which the compressed gas flows to the cargo compartment to suppress a fire. The system also includes a pump control valve configured to be coupled between the turbo pump and the storage tank and having a closed position in which the compressed gas is prevented from flowing to the turbo pump and an open position in which the compressed gas flows to the turbo pump to cause the turbo pump to convert the compressed gas into the power.

Abstract: A propulsion system for an unmanned underwater vehicle includes a turbine engine, a generator mechanically coupled to an output shaft of the turbine engine, an electrical motor mechanically decoupled from the turbine engine and electrically coupled to the generator via a power bus architecture, and a propulsor mechanically coupled to a rotational output of the electrical motor. The power bus architecture includes a pair of AC buses and a DC bus.

Abstract: According to an aspect, a method of providing internal shaft lubrication includes drip feeding a lubricant to a feed tube within a central bore of a shaft body. The lubricant is urged along a lubrication flow path including at least one rifling groove on an inner wall of the shaft body formed by the central bore and a plurality of lubrication holes axially distributed along the shaft body that fluidically connects the inner wall with an outer wall of the shaft body. The lubricant is sprayed out of the lubrication holes responsive to rotation of the shaft body.

Abstract: Disclosed is a sump cover for a sump basin of a generator of an aircraft, the sump cover having: a sump cover shell shaped as an inverted bowl, a front portion of the sump cover shell including a first plurality of fastener features, each configured to fasten to one of a second plurality of fastener features in the sump basin; and a sump cover support extending outwardly from the sump cover shell, past a perimeter edge of the sump cover shell, configured to fit through a sump port and against a sump tube of the sump basin, wherein the sump cover support and the first plurality of fastener features define a multi-point mounting configuration between the sump cover and the sump basin.

Abstract: A thin-skin support member is provided. The thin-skin support member may include a semi-circular edge and a flat edge that define a hollow cavity. A cylindrical cavity may be adjacent the hollow cavity and at least partially defined by the semi-circular edge. The cylindrical cavity may be configured to retain a strut assembly. A mounting interface may be coupled to the semi-circular edge and the flat edge. A torsion interface may be disposed adjacent the cylindrical cavity and configured to receive a torsion link. The thin-skin support member may be made using additive manufacturing and thus may have a grain structure grown in the direction of material being added.

Abstract: Disclosed is a multiple start torpedo including an aft body having an exhaust conduit defining a turbine end and a seawater end having an orifice. The multiple start torpedo includes an exhaust valve associated with the exhaust conduit including. The exhaust valve includes a fore section having a head and a valve stem. The exhaust valve includes an aft section tapered from the turbine end to the seawater end and defining a receptacle sized to receive the valve stem. The exhaust valve includes a biasing member disposed to bias the head in an extended position spaced apart from the aft section and abut the orifice in the extended position.