Propulsion System for an Aircraft

Patent metadata

Field	Value
Publication number	US-2024092494-A1
Application number	US-202318513916-A
Country	US
Kind code	A1
Filing date	Nov 20, 2023
Priority date	Apr 21, 2017
Publication date	Mar 21, 2024
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

1 - 20 . (canceled)

21 . A propulsion system for an aircraft comprising:
a propulsor assembly operably coupled with an electric machine; a propulsion assembly comprising an electric motor and a propulsor, the propulsor powered by the electric motor; an electric power bus electrically connecting the electric machine 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 machine to a voltage between 800 and 20,000 volts.

22 . The propulsion system of claim 21 , wherein the inverter converter controller is electrically connected to the electric machine at a location downstream of the electric machine and upstream of the propulsion assembly.

23 . The propulsion system of claim 21 , 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.

24 . The propulsion system of claim 21 , wherein the inverter converter controller is configured to increase a voltage of the electric power received from the electric machine.

25 . The propulsion system of claim 21 , wherein the inverter converter controller is configured to decrease the voltage of the electric power received from the electric machine.

26 . The propulsion system of claim 21 , 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.

27 . The propulsion system of claim 21 , wherein the propulsor assembly further comprises a combustion engine.

28 . The propulsion system of claim 27 , wherein the combustion engine is at least one of a turboprop engine or a turbofan engine.

29 . A propulsion system for an aircraft comprising:
a propulsor assembly, comprising:
a first aircraft engine comprising a first electric machine; and
a second aircraft engine comprising a second electric machine;
an electric power bus electrically connecting the first electric machine and the second electric machine; and an inverter converter controller positioned along the electric power bus and electrically connected to the first electric machine and the second electric machine, wherein the inverter converter controller is configured to alter a voltage of an electric power received from the first electric machine or the second electric machine by at least 100%.

30 . The propulsion system of claim 29 , further comprising:
a propulsion assembly comprising an electric motor and a propulsor, the propulsor powered by the electric motor, wherein the propulsion assembly is electrically connected to the electric power bus.

31 . The propulsion system of claim 29 , further comprising:
one or more energy storage devices electrically connected to the electric power bus and configured to provide to the electric power bus or receive power from the electric power bus.

32 . The propulsion system of claim 29 , 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.

33 . The propulsion system of claim 29 , wherein the inverter converter controller increases the voltage to a voltage between 800 and 20,000 volts.

34 . The propulsion system of claim 29 , 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.

35 . A method for operating a propulsion system for an aircraft comprising:
generating electric power with a propulsor assembly operably coupled with an electric machine; transferring the electric power through an inverter converter that increases a voltage from the electric machine to an output voltage between 800 and 20,000 volts; transferring the electric power generated with the electric machine 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.

36 . The method of claim 35 , 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.

37 . The method of claim 35 , wherein transferring the electric power generated with the propulsor assembly 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 machine and upstream of the propulsion assembly.

38 . The method of claim 37 , 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.

39 . The method of claim 37 , wherein transferring the electric power through an inverter converter includes increasing the voltage from the electric power received from the electric machine.

40 . The method of claim 37 , wherein transferring the electric power through an inverter converter includes decreasing the voltage from the electric power received from the electric machine.

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