What is described is a system for pumping lubricant to a component of a gas turbine engine. The system includes a fan gear coupled to a fan shaft of the gas turbine engine and configured to rotate in a forward direction and in a reverse direction based at least partially on a direction of wind relative to a fan of the gas turbine engine. The system also includes a first pump coupled to the fan gear and configured to pump lubricant to the component in response to the fan rotating in the forward direction. The system also includes a second pump coupled to the fan gear and configured to pump lubricant to the component in response to the fan rotating in the reverse direction.

A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades. The gas turbine engine also includes an outer nacelle surrounding the plurality of fan blades and defining an nacelle inlet, the outer nacelle including an inner wall defining a plurality of openings located aft of the nacelle inlet and forward of the plurality of fan blades of the fan along an axial direction for providing a swirl airflow upstream of the plurality of fan blades of the fan at a swirl angle greater than zero relative to a radial direction.

A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

A unique low cost and efficient submersible, hermetically sealed, variable speed system intended to drive submersible boosting units. The system includes a unique combination of a liquid filled electrical motor connected to a hydraulic coupling and a magnetic coupling driver section, in a hermetically sealed container, with a magnetic coupling follower driving a booster unit. The system further includes integrated cooling, lubrication and control functionality. The drive unit has an actuating system connected to internal guide vanes which controls the liquid flow between the pump impeller and turbine wheel of the hydrodynamic coupling and hence the torque and speed. The combined system is a sealed seal-less and topside-less submersible drive unit that can operate in harsh subsea environments. The drive unit opens up for use of thin walled pressure casings and low pressure electrical penetrators.

An airplane is provided. The airplane includes a first medium at a first pressure, a second medium at a second pressure, a third medium at a third pressure; and an air conditioning system. The air conditioning system includes a compressor, a first heat exchanger configured to transfer heat from the first medium to the third medium, a second heat exchanger configured to reject heat from the first medium, a third heat exchanger configured to reject heat from the second medium, a first turbine configured to receive the first medium, and a second turbine configured to receive the second medium.

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

A transport refrigeration system (20) is provided. The transport refrigeration system includes: a natural gas engine (26), a compressed natural gas storage tank (60), an artificial aspiration device (70) providing decompressed natural gas and compressed air to the natural gas engine, an electric generation device (24) powered by the natural gas engine and providing an electric output, and a refrigeration unit (22) electrically powered by the electric output of the electric generation device.

A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface defining a diffuser chamber radially outwardly of the combustor, and a cooling air chamber wall positioned outwardly of the diffuser chamber and the combustor, and radially inwardly of a second wall to define a cooling air chamber. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor and is passed through a heat exchanger. Air downstream of the heat exchanger passes into the cooling chamber, and then to the blade outer air seal.

An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, a turbine coupled to the compressor via the shaft; and a heat exchanger. The compressor receives and compresses a first medium in accordance with power provided by the turbine via the shaft. The turbine receives and expands a second medium to provide the power to the compressor via the shaft. The heat exchanger is configured to cool the first medium.

An airplane is provided. The airplane includes a motor-driven compressor assembly. The motor-driven compressor assembly includes a shaft, a motor, a compressor, and a turbine coupled to the compressor via the shaft. The motor provides a first power to the compressor via the shaft. The turbine receives and expands a second medium to provide a second power to the compressor via the shaft. The compressor receives and compresses a first medium in accordance with the first power provided by the turbine and the second power provided by the motor.