Hybrid propulsion systems
AssigneeHamilton Sundstrand Corporation
InventorsLeo J. Veilleux, Jr., Lubomir A. Ribarov
Life of this patent
Estimating the term…
Abstract
A hybrid propulsion system can include a turbomachine having a compressor, a combustion chamber, and a compressor turbine. The compressor can be connected to the compressor turbine via a first shaft. The system can include a hybrid drive assembly which can include a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is disconnected from the first shaft. The hybrid drive assembly can also include an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft.
Claims19
A hybrid propulsion system, comprising:
- a turbomachine disposed within a fuselage, the turbomachine comprising:
- a compressor;
- a combustion chamber;
- and
- a compressor turbine, wherein the compressor is connected to the compressor turbine via a first shaft;
- a hybrid drive assembly, comprising:
- a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is mechanically disconnected from the first shaft continuously during operation of the hybrid propulsion system;
- an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft;
- and
- an electrical starter motor, wherein the electrical starter motor is connected to the compressor on the first shaft, wherein the electrical starter motor is electrically connected to the electrical machine to receive energy from the electrical machine to drive the electrical starter motor,
- wherein the second shaft connects to a propulsor at an aft end of the fuselage to drive the propulsor.
An aircraft, comprising:
- a hybrid propulsion system, comprising:
- a turbomachine disposed within a fuselage, the turbomachine comprising:
- a compressor;
- a combustion chamber;
- and
- a compressor turbine, wherein the compressor is connected to the compressor turbine via a first shaft;
- a hybrid drive assembly, comprising:
- a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is mechanically disconnected from the first shaft continuously during operation of the hybrid propulsion system;
- an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft;
- and
- an electrical starter motor, wherein the electrical starter motor is connected to the compressor on the first shaft, wherein the electrical starter motor is electrically connected to the electrical machine to receive energy from the electrical machine to drive the electrical starter motor,
- wherein the second shaft connects to a propulsor at an aft end of the aircraft to drive the propulsor.
A hybrid propulsion system for use in an aircraft fuselage, comprising:
- a turbomachine disposed within the aircraft fuselage, the turbomachine comprising:
- a compressor;
- a combustion chamber;
- and
- a compressor turbine, wherein the compressor is connected to the compressor turbine via a first shaft;
- a hybrid drive assembly, comprising:
- a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is mechanically disconnected from the first shaft continuously during operation of the hybrid propulsion system;
- an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft;
- an electrical starter motor, wherein the electrical starter motor is connected to the compressor on the first shaft, wherein the electrical starter motor is directly electrically connected to the electrical machine to receive energy from the electrical machine to drive the electrical starter motor;
- a planetary gear box connected to the electrical machine on the second shaft;
- and
- two coaxial shafts, directly connected to the planetary gear box and connected to respective propulsors, to drive the respective propulsors at an aft end of the aircraft fuselage.
Dependencies are inferred from the claim text.