A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The compressor section includes a compressor electric motor that is electrically coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to a geared architecture to supplement power driving the fan section. A turbine generator driven by a portion of the turbine section provides electric power to the turbine electric motor.

The present invention relates to an aircraft including a fuselage and a thruster downstream of the fuselage. The thruster includes a power turbine, located inside a main flow jet, and at least one fan, located inside a secondary flow jet and mechanically driven by the power turbine. The main flow jet of the power turbine and the secondary flow jet of the fan are concentric. The power turbine is supplied with gases from two gas turbine gas generators via two supply channels. The gas turbine gas generators have axes parallel to that of the fuselage. The air inlet sleeve is spaced apart from the fuselage, and the supply channels each have a hatch for controlling the flow between a position for guiding the gas flow to the power turbine and a position for ejecting the gases into the atmosphere while bypassing the power turbine.

The present invention relates to an aircraft including a fuselage and a thruster downstream of the fuselage. The thruster includes a power turbine, located inside a main flow jet, and at least one fan, located inside a secondary flow jet and mechanically driven by the power turbine. The main flow jet of the power turbine and the secondary flow jet of the fan are concentric. The power turbine is supplied with gases from two gas turbine gas generators via two supply channels. The gas turbine gas generators have axes parallel to that of the fuselage. The air inlet sleeve is spaced apart from the fuselage, and the supply channels each have a hatch for controlling the flow between a position for guiding the gas flow to the power turbine and a position for ejecting the gases into the atmosphere while bypassing the power turbine.

A boundary layer ingestion engine includes a gas generator and a turbine fluidly connected to the gas generator. A fan is mechanically linked to the turbine via a shaft such that rotation of the turbine is translated to the fan. A boundary layer ingestion inlet is aligned with an expected boundary layer, such that the boundary layer ingestion inlet is configured to ingest fluid from a boundary layer during operation of the boundary layer ingestion engine.

A boundary layer ingestion engine includes a gas generator and a turbine fluidly connected to the gas generator. A fan is mechanically linked to the turbine via a shaft such that rotation of the turbine is translated to the fan. A boundary layer ingestion inlet is aligned with an expected boundary layer, such that the boundary layer ingestion inlet is configured to ingest fluid from a boundary layer during operation of the boundary layer ingestion engine.

A propulsion system for an aircraft having an aft end is provided herein. The propulsion system can include an electric propulsion engine defining a central axis. The electric propulsion engine can include an electric motor, a fan rotatable about the central axis of the electric propulsion engine by the electric motor, a bearing supporting rotation of the fan, and a thermal management system. The thermal management system can include a lubrication oil circulation assembly for providing the bearing with lubrication oil. The lubrication oil circulation assembly can be driven independently of a shaft of the electric propulsion engine.

A propulsion system for an aircraft having an aft end is provided herein. The propulsion system can include an electric propulsion engine defining a central axis. The electric propulsion engine can include an electric motor, a fan rotatable about the central axis of the electric propulsion engine by the electric motor, a bearing supporting rotation of the fan, and a thermal management system. The thermal management system can include a lubrication oil circulation assembly for providing the bearing with lubrication oil. The lubrication oil circulation assembly can be driven independently of a shaft of the electric propulsion engine.

A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.

A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.