Hybrid propulsion system for aircraft
OwnerJay Bhattinventor
Life of this patent
Estimating the term…
Abstract
Hybrid propulsion integral systems for a fixed wing aircraft, and a V/STOL aircraft. A core of the jet engine rotates an integral generator, that provides current to charge batteries located in various locations on an aircraft. The batteries and generator are selectively used to power electric motor(s) that provide the sole source of torque (power) to fans, propellers, or rotors that propel the aircraft, along with a fuel operated gas turbine. In addition, for a V/STOL air vehicle, a hybrid propulsion system fixed to a wing or split between wing and empennage, with moving integral submodules, such as a multifunctional thrust vectoring exhaust nozzle and electrically operated tiltable propeller(s). These differ from the prior configurations by provisioning integrated architectures as delineated.
Claims23
A hybrid propulsion system for a fixed wing aircraft comprising:
- a nacelle which houses a jet engine core comprises a fan cowl and a core cowl;
- a fan case is present within and is spaced apart from the fan cowl, thereby defining a battery space, wherein the fan case houses a fan operatively independent of the jet engine core;
- wherein the jet engine core includes a low-pressure compressor section, a high-pressure compressor section, a combustion chamber, a high-pressure turbine section, and a low-pressure turbine section;
- an electric motor disposed within the fan case, upstream of the jet engine core, wherein operation of the electric motor is mechanically independent from the jet engine core, and the fan is rotatably connected to the electric motor to be driven by the electric motor;
- a generator rotatably coupled to the jet engine core;
- a battery is disposed on an exterior surface of the fan case in the battery space, the battery is operatively connected to the fan to provide power thereto, is operatively connected to the generator to receive current therefrom, and is operatively connected to the electric motor to provide power thereto;
- and
- an electronic engine controller is operatively connected to the electric motor, the electronic controller configured to operate the system selectively to provide power from the battery and/or the generator to the electric motor to drive the fan.
A hybrid propulsion system for a fixed wing aircraft comprising:
- a nacelle which houses a gas turbine having a shaft connected to a low pressure compressor;
- a fan case within the nacelle, wherein the fan case houses a fan;
- an electric motor disposed within the fan case, upstream of the gas turbine, wherein operation of the electric motor is mechanically independent of the gas turbine, and the fan is rotatably connected to the electric motor;
- a generator is rotatably coupled to the shaft of the gas turbine and is disposed in the fan case upstream of the gas turbine;
- a battery is disposed on the fan case in a space defined between a fan cowl and the fan case and is operatively connected to receive current from the generator and operatively connected to the electric motor to provide power thereto;
- a controller is operatively connected to the electric motor to selectively provide current to the electric motor from one or more of the battery and the generator and operatively control a speed at which the fan rotates;
- and
- a flexible joint between the shaft of the gas turbine and the generator, wherein the flexible joint is configured to absorb vibration and mitigate differential displacement from the gas turbine.
A hybrid propulsion system for a fixed wing aircraft comprising:
- a nacelle which houses a gas turbine having a shaft connected to a low-pressure compressor;
- a fan case within the nacelle, wherein the fan case houses a fan;
- an electric motor disposed within the fan case, upstream of the gas turbine, wherein operation of the electric motor is mechanically independent of the gas turbine, and the fan is rotatably connected to the electric motor;
- wherein the electric motor is disposed concentrically around the generator;
- a battery is disposed on the fan case in a space defined between a fan cowl and the fan case and is operatively connected to receive current from the generator and operatively connected to the electric motor to provide power thereto;
- a generator is rotatably coupled to the shaft of the gas turbine and is disposed in the fan case upstream of the gas turbine;
- a controller operatively connected to the electric motor to selectively provide current to the electric motor from one or more of the battery and/or the generator to selectively operate the fan;
- and
- a backup battery disposed in a fuselage or in a dry bay of a wing of the fixed wing aircraft and operatively connected to the battery disposed on the fan case or to the electric motor.
Dependencies are inferred from the claim text.