Propulsion system for an aircraft

Patent metadata

Field	Value
Publication number	US-2025353382-A1
Application number	US-202519282273-A
Country	US
Kind code	A1
Filing date	Jul 28, 2025
Priority date	Apr 21, 2017
Publication date	Nov 20, 2025
Grant date	—

Abstract

A propulsion system for an aircraft can include an electric power source and an propulsion assembly having a propulsor. An electric power bus can electrically connect the electric power source to the 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; a propulsion assembly comprising a propulsor, the propulsor powered by the electric power source; an electric power bus electrically connecting the electric power source to the propulsion assembly; and an inverter converter controller positioned along the electric power bus, the inverter converter controller configured to convert an electric power from the electric power source to a voltage between 800 and 20,000 volts.

2 . The propulsion system of claim 1 , wherein the inverter converter controller is electrically connected to the electric power source at a location downstream of the electric power source and upstream of the propulsion assembly.

3 . The propulsion system of claim 1 , wherein the electric power bus includes a cable comprising a conductor and a conductor screen enclosing the conductor, wherein the conductor screen has a volume resistivity between about 1 ohm-meter and 1,000,000 ohm-meters.

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

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

6 . The propulsion system of claim 1 , wherein the electric power bus is configured to transfer the electric power to the propulsion assembly to operate the 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 generator.

8 . The propulsion system of claim 1 , wherein the electric power source further comprises at least one energy storage device.

9 . A propulsion system for an aircraft comprising:
an electric power source; a propulsion assembly comprising:
a first propulsor assembly connected to a first electric motor;
a second propulsor assembly connected to a second electric motor;
an electric power bus electrically connecting the electric power source to the propulsion assembly; 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 an electric power received from the electric power source by at least 100%.

10 . The propulsion system of claim 9 , wherein the inverter controller is a first inverter controller, wherein the propulsion system further comprises:
a second inverter 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 an electric power received from the electric power source by at least 100%.

11 . The propulsion system of claim 9 , wherein the electric power source is configured as one or more energy storage devices configured to provide to the electric power bus or receive power from the electric power bus.

12 . The propulsion system of claim 9 , wherein the electric power bus includes a cable, the cable further comprising:
an insulation layer enclosing a conductor screen; a semi-conductive insulator screen enclosing the insulation layer; and an outer sheath on an opposing side of the conductor screen from the conductor screen.

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

14 . The propulsion system of claim 9 , wherein the electric power bus further comprises:
a coolant system having a cooling line, wherein at least a portion of a 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 through an inverter converter that increases a voltage from the electric power source to an output voltage between 800 and 20,000 volts; transferring the electric power generated with the electric power source to a propulsion assembly through an electric power bus; and generating thrust for the aircraft with the propulsion assembly, the propulsion assembly being powered by the electric power transferred through the electric power bus.

16 . The method of claim 15 , wherein the electric power bus comprises a cable, and wherein the cable includes a conductor, a conductor screen enclosing the conductor, an insulation layer enclosing the conductor screen, an insulator screen enclosing the conductor, and a metallic shield enclosing the insulator screen.

17 . The method of claim 15 , wherein transferring the electric power generated with the electric power source to the 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 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

• H02K7/1823

  structurally associated with turbines or similar engines · CPC title

• H02G5/10

  Cooling · CPC title

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F02C6/206

  the vehicles being airscrew driven · CPC title

• B64D27/18

  within, or attached to, wings · CPC title