A dual pump unit having a pair of pumps that provide parallel hydraulic paths, and are configured to operate concurrently in opposite rotational directions. The dual pump unit has a sealed casing which includes a suction flange, two volutes in hydraulically parallel configuration, and a discharge flange. The pair of pumps are located within a respective volute of the casing and, in an example, are radially inline and horizontally inline. The casing may include a flattened bottom. Each pump may include a touchscreen for configuration of the respective pump. The pumps are controllable to circulate a circulating medium to collectively provide output to source a load.

An assembly for an aircraft propulsion system is provided, the assembly having an axial centerline. The assembly comprises a fixed structure, a first thrust reverser door, and a second thrust reverser door. The first thrust reverser door being pivotally attached to the fixed structure along a first pivot axis, and the second thrust reverser door being pivotally attached to the fixed structure along a second pivot axis. The first pivot axis and the second pivot axis are both radially located at a first distance from the assembly axial centerline. The first pivot axis is located at a first axial position, and the second pivot axis is located at a second axial position. The second axial position is displaced from the first axial position.

A turbine engine is described that includes a drive shaft and an electric generator comprising a first rotating element comprising a magnet array, wherein the first rotating element is configured to rotate in a first direction based on a rotation of the drive shaft. The turbine engine further includes a second rotating element comprising a coil array, wherein the second rotating element is configured to rotate in a second direction based on the rotation of the drive shaft, wherein the second direction is opposite to the first direction.

A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.

An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.

An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.

A dual pump unit having a pair of pumps that provide parallel hydraulic paths, and are configured to operate concurrently in opposite rotational directions. The dual pump unit has a sealed casing which includes a suction flange, two volutes in hydraulically parallel configuration, and a discharge flange. The pair of pumps are located within a respective volute of the casing and, in an example, are radially inline and horizontally inline. The casing may include a flattened bottom. Each pump may include a touchscreen for configuration of the respective pump. The pumps are controllable to circulate a circulating medium to collectively provide output to source a load.

A counter-rotating shaft assembly of a gas turbine engine includes an outer shaft rotatable in a first direction about a virtual rotational axis, an inner shaft counter-rotatable about the virtual rotational axis in a second direction that is opposite to the first direction, a differential bearing rotatably connecting the two shafts, a centering spring connecting the inner shaft to the differential bearing, and a squeeze film damper between the differential bearing and the inner shaft.

The present disclosure is directed to an outer drum rotor assembly for a gas turbine engine including a first outer drum and a second outer drum. Each outer drum defines a radially extended flange adjacent to one another. A plurality of outer drum airfoils is extended inward along the radial direction from between the first outer drum and the second outer drum at the flange.

The present disclosure is directed to a gas turbine engine including a torque frame. The torque frame includes an inner shroud defined circumferentially around the axial centerline, an outer shroud surrounding the inner shroud and defined circumferentially around the axial centerline, and a structural member extended along the radial direction and coupled to the inner shroud and the outer shroud. The torque frame is configured to rotate around the axial centerline.