In-flight hybrid electric engine shutdown

Patent metadata

Field	Value
Publication number	US-2022063826-A1
Application number	US-202117168725-A
Country	US
Kind code	A1
Filing date	Feb 5, 2021
Priority date	Aug 31, 2020
Publication date	Mar 3, 2022
Grant date	—

Abstract

A method for operating a hybrid-electric propulsion system of an aircraft is provided. The hybrid-electric propulsion system includes a gas turbine engine having a high pressure system, a low pressure system, and an electric machine coupled to one of the high pressure system or low pressure system. The method includes receiving data indicative of an actual or anticipated in-flight shutdown of the gas turbine engine; and adding power to the gas turbine engine through the electric machine in response to receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine.

First claim

1 . A method for operating a hybrid-electric propulsion system of an aircraft, the hybrid-electric propulsion system comprising a gas turbine engine having a high pressure system, a low pressure system, and an electric machine coupled to one of the high pressure system or low pressure system, the method comprising:
receiving data indicative of an actual or anticipated in-flight shutdown of the gas turbine engine; and adding power to the gas turbine engine through the electric machine in response to receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine.

2 . The method of claim 1 , wherein receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine comprises receiving data indicative of an actual in-flight shutdown of the gas turbine engine.

3 . The method of claim 2 , wherein adding power to the gas turbine engine includes adding power to the gas turbine engine immediately after receiving data indicative of the actual in-flight shutdown of the gas turbine engine.

4 . The method of claim 2 , further including
initiating a re-start of the engine after an amount of time after receiving data indicative of the actual in-flight shutdown of a gas turbine engine, wherein adding power to the gas turbine engine includes adding power to the gas turbine engine substantially continuously at least until the re-start process is initiated, adding power to the gas turbine engine substantially continuously until the engine is re-ignited, or both.

5 . The method of claim 4 , wherein the amount of time is at least 10 seconds.

6 . The method of claim 1 , wherein receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine comprises determining an anticipated in-flight shutdown of the gas turbine engine.

7 . The method of claim 1 , wherein adding power to the gas turbine engine includes adding power to the low pressure system of the gas turbine engine using the electric machine, adding power to the high pressure system of the gas turbine engine using the electric machine, or both.

8 . The method of claim 1 , wherein adding power to the gas turbine engine includes adding power to the low pressure system of the gas turbine engine using the electric machine.

9 . The method of claim 1 , wherein adding power to the gas turbine engine includes adding power to the low pressure system of the gas turbine engine using the electric machine to maintain a rotation speed of the low pressure system within about 75% of a pre-shutdown speed.

10 . The method of claim 1 , wherein adding power to the gas turbine engine includes adding power to the low pressure system of the gas turbine engine using the electric machine to maintain a rotation speed of the low pressure system above 25% of a maximum corrected speed.

11 . The method of claim 1 , wherein the electric machine is a first electric machine, wherein adding power to the gas turbine engine includes adding power to the low pressure system of the gas turbine engine using the first electric machine and adding power to the high pressure system of the gas turbine engine using a second electric machine.

12 . The method of claim 1 , wherein adding power to the gas turbine engine includes providing electrical power to the electric machine from an external source.

13 . The method of claim 1 , wherein the electric machine is a first electric machine, wherein the gas turbine engine is a first gas turbine engine, wherein adding power to the gas turbine engine includes providing electrical power to the electric machine from a second electric machine driven by a second gas turbine engine.

14 . The method of claim 1 , wherein adding power to the gas turbine engine includes providing electrical power to the electric machine from one or more electric energy storage units, from an auxiliary power unit, or both.

15 . The method of claim 1 , wherein adding power to the gas turbine engine includes adding at least 10 horsepower.

16 . The method of claim 1 , wherein adding power to the gas turbine engine includes adding at least 50 horsepower.

17 . A hybrid-electric system comprising:
a gas turbine engine having a high pressure system, a low pressure system, an electric machine coupled to one of the high pressure system or low pressure system, and a controller, the controller including memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the system to perform one or more functions, the functions including
receiving data indicative of an actual or anticipated in-flight shutdown of the gas turbine engine; and
adding power to the gas turbine engine through the electric machine in response to receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine.

18 . The hybrid-electric system of claim 17 , wherein receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine comprises receiving data indicative of an actual in-flight shutdown of the gas turbine engine.

19 . The hybrid-electric system of claim 17 , wherein receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine comprises receiving data indicative of an actual in-flight shutdown of the gas turbine engine.

20 . The hybrid-electric system of claim 19 , wherein adding power to the gas turbine engine includes adding power to the gas turbine engine immediately after receiving data indicative of the actual in-flight shutdown of the gas turbine engine.

Assignees

• Gen Electric

Inventors

• Hiett David Alexander
• Cafaro Stefan Joseph
• Ostdiek David Marion
• Mcquiston Robert Jon
• Gemin Paul Robert
• Rambo Jeffrey Douglas

Classifications

• F02C7/262

  Restarting after flame-out · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F02C9/00

  Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants (controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05) · CPC title

• F01D21/00 Primary

  Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for · CPC title