Propulsion System for an Aircraft

Patent metadata

Field	Value
Publication number	US-2020324906-A1
Application number	US-202016914635-A
Country	US
Kind code	A1
Filing date	Jun 29, 2020
Priority date	Apr 21, 2017
Publication date	Oct 15, 2020
Grant date	—

Abstract

A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

First claim

What is claimed is:

1 . A propulsion system for an aircraft comprising:
an electric power source; an electric propulsion assembly comprising an electric motor and a propulsor, the propulsor powered by the electric motor; an electric power bus electrically connecting the electric power source to the electric propulsion assembly, the electric power source configured to provide electrical power to the electric power bus; and an inverter converter controller positioned along the electric power bus and electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

2 . The propulsion system of claim 1 , wherein the electric power bus is configured to transfer the electric power to the electric propulsion assembly at a voltage between 800 and 20,000 volts.

3 . The propulsion system of claim 1 , wherein the inverter converter controller is configured to increase a voltage of the electric power received from the power source.

4 . The propulsion system of claim 1 , wherein the inverter converter controller is configured to decrease the voltage of the electric power received from the power source.

5 . The propulsion system of claim 2 , wherein the second inverter controller is configured to transfer the electric power to the electric propulsion assembly to operate the electric propulsion assembly at a voltage between 800 and 20,000 volts.

6 . The propulsion system of claim 1 , wherein the electric power bus is configured to transfer the electric power to the electric propulsion assembly to operate the electric propulsion assembly at an electrical current between about 30 amps and about 1,200 amps.

7 . The propulsion system of claim 1 , wherein the electric power source comprises a combustion engine and an electric generator.

8 . The propulsion system of claim 7 , wherein the combustion engine is at least one of a turboprop engine or a turbofan engine.

9 . A propulsion system for an aircraft comprising:
an electric power source; an electric propulsion assembly comprising an electric motor and a propulsor, the propulsor powered by the electric motor; an electric power bus electrically connecting the electric power source to the electric propulsion assembly, the electric power source configured to provide electrical power to the electric power bus; and an inverter converter controller positioned along the electric power bus and electrically connected to the electric power source, wherein the inverter converter controller is configured to alter a voltage of the electric power received from the power source prior to powering the electric motor.

10 . The propulsion system of claim 9 , wherein the inverter converter controller increases the voltage to a voltage between 800 and 20,000 volts.

11 . The propulsion system of claim 9 , wherein the inverter converter controller is configured to increase the voltage of the electric power received from the electric power source by at least 20%.

12 . The propulsion system of claim 9 , wherein the power bus includes a cable, the cable comprising:
a conductor defining a central portion of the cable; a semi-conductive conductor screen enclosing the conductor; an insulation layer enclosing the conductor screen; and a semi-conductive insulator screen enclosing the insulation layer.

13 . The propulsion system of claim 9 , wherein the electric propulsion assembly further comprises a plurality of electric motors and a plurality of propulsors, each propulsor powered by a respective one of the electric motors.

14 . The propulsion system of claim 9 , wherein the power bus further comprises a coolant system having a cooling line, wherein at least a portion of high voltage cable extends coaxially with the cooling line.

15 . A method for operating a propulsion system for an aircraft comprising:
generating electric power with an electric power source; transferring the electric power generated with the electric power source to an electric propulsion assembly through an electric power bus, wherein the electric power bus is configured to transfer the electric power to the electric propulsion assembly at an output voltage between 800 and 20,000 volts; and generating thrust for the aircraft with the electric propulsion assembly, the electric propulsion assembly being powered by the electric power transferred through the electric power bus.

17 . The method of claim 16 , wherein transferring the electric power generated with the electric power source to the electric propulsion assembly through the electric power bus comprises transferring the electric power through an inverter converter controller positioned along the electric power bus at a location downstream of the electric power source and upstream of the electric propulsion assembly.

18 . The method of claim 17 , wherein transferring the electric power through an inverter converter includes converting electrical power from an alternating current electric power configuration to a direct current electric power.

19 . The method of claim 17 , wherein transferring the electric power through an inverter converter includes increasing the voltage from the electric power received from the electric power source.

20 . The method of claim 17 , wherein transferring the electric power through an inverter converter includes decreasing the voltage from the electric power received from the electric power source.

Assignees

• Gen Electric

Inventors

• Vondrell Randy M
• Bouvette Anthony Austin
• Crabtree Glenn David

Classifications

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title

• B64D27/32

  within, or attached to, fuselages · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B60L50/10 Primary

  using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title