Propulsion system for an aircraft

Patent metadata

Field	Value
Publication number	US-2018372003-A1
Application number	US-201715631094-A
Country	US
Kind code	A1
Filing date	Jun 23, 2017
Priority date	Jun 23, 2017
Publication date	Dec 27, 2018
Grant date	—

Abstract

A hybrid-electric propulsion system includes an electric machine coupled to a rotating system of the turbomachine and an electric energy storage unit, the electric machine electrically coupled to an electric power source. A method for operating the turbomachine of a hybrid-electric propulsion system includes providing electrical power from the electric machine to the electric energy storage unit during a flight operation mode of the turbomachine, the turbomachine rotating the electric machine to generate electrical power during the flight operating mode; determining the turbomachine is in a post flight operation mode or in a pre-flight operation mode; and providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine to prevent or correct a bowed rotor condition.

First claim

What is claimed is:

1 . A method for operating a turbomachine of a hybrid-electric propulsion system of an aircraft, the hybrid-electric propulsion system comprising an electric machine coupled to a rotating system of the turbomachine, the electric machine electrically coupled to an electric power source, the method comprising:
rotating the electric machine with the turbomachine to generate electrical power during a flight operation mode of the turbomachine; rotating a propulsor of the hybrid electric propulsion system utilizing at least in part the electrical power generated from the rotating of the electric machine with the turbomachine to provide a propulsive benefit for the aircraft during the flight operation mode of the turbomachine; determining the turbomachine is in a post flight operation mode or in a pre-flight operation mode; and providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine to prevent or correct a bowed rotor condition.

2 . The method of claim 1 , wherein determining the turbomachine is in the post flight operation mode or in the pre-flight operation mode comprises determining the turbomachine is in the pre-flight operation mode, and wherein providing electrical power from the electric power source to the electric machine comprises providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine to correct a bowed rotor condition.

3 . The method of claim 2 , wherein providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine comprises rotating the rotating system at a constant rotational speed for an amount of time.

4 . The method of claim 2 , wherein providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine comprises rotating the rotating system at an increasing rotational speed for an amount of time.

5 . The method of claim 2 , wherein providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine comprises rotating the rotating system at a rotational speed between ten percent of a maximum core speed and forty percent of a maximum core speed.

6 . The method of claim 2 , wherein providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine comprises rotating the rotating system of the turbomachine to correct the bowed rotor condition prior to igniting a combustion section of the turbomachine.

7 . The method of claim 2 , wherein providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine comprises rotating the rotating system for at least about twenty seconds.

8 . The method of claim 1 , wherein determining the engine is in the post flight operation mode or in the pre-flight operation mode comprises determining the turbomachine is in the post flight operation mode, and wherein providing electrical power from the electric power source to the electric machine comprises rotating the rotating system of the turbomachine for an amount of time to prevent a bowed rotor condition.

9 . The method of claim 8 , wherein determining the turbomachine is in the post flight operation mode comprises determining the turbomachine is shut down.

10 . The method of claim 8 , wherein rotating the rotating system of the turbomachine for the amount of time to prevent the bowed rotor condition comprises rotating the rotating system of the turbomachine at a rotational speed less than about ten percent of a maximum core speed of the turbomachine.

11 . The method of claim 8 , wherein rotating the rotating system of the turbomachine for the amount of time to prevent the bowed rotor condition comprises rotating the rotating system of the turbomachine at a constant rotational speed for the amount of time.

12 . The method of claim 8 , wherein rotating the rotating system of the turbomachine for the amount of time to prevent the bowed rotor condition comprises rotating the rotating system of the turbomachine at a varying rotational speed for the amount of time.

13 . The method of claim 8 , wherein the amount of time is a predetermined amount of time between about twenty minutes and about eight hours.

14 . The method of claim 1 , wherein providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine comprises rotating the rotating system of the turbomachine solely with the electric machine.

15 . The method of claim 1 , wherein rotating the propulsor of the hybrid electric propulsion system utilizing at least in part the electrical power generated from the rotating of the electric machine with the turbomachine comprises providing electrical power from the electric machine to an electric propulsor assembly of the hybrid electric propulsion system during the flight operation mode of the turbomachine.

16 . The method of claim 1 , wherein the rotating system of the turbomachine is a high pressure system of the turbomachine, and wherein the electric power source is an electric energy storage unit of the hybrid-electric propulsion system.

17 . A hybrid-electric propulsion system comprising:
a turbomachine comprising a high pressure system, the high pressure system including a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool; an electric machine coupled to the high pressure system; an electric energy storage unit electrically connectable to the electric machine; and a controller configured to electrically connect the electric energy storage unit and the electric machine to provide electrical power from the electric machine to the electric energy storage unit during a flight operation mode of the turbomachine and further configured to provide electrical power from the electric energy storage unit to the electric machine to drive the electric machine and prevent or correct a bowed rotor condition during a post flight operation mode or a pre-flight operation mode of the turbomachine.

18 . The hybrid-electric propulsion system of claim 16 , further comprising:
an electric propulsor assembly electrically connectable to the electric machine, wherein the controller is further configured to provide the electric propulsor assembly with electrical power from one or both of the electric machine and the electric energy storage unit during the flight operation mode of the turbomachine.

19 . The hybrid-electric propulsion system of claim 16 , wherein the controller is further configured to provide electrical power from the electric energy storage unit to the electric machine to drive the electric machine and correct a bowed rotor condition during the pre-flight operation mode.

20 . The hybrid-electric propulsion system of claim 16 , wherein in providing electrical power from the electric energy storage unit to the electric machine to drive the electric machine and prevent or correct a bowed rotor condition, the controller is configured to rotate the high pressure system of the turboma

Assignees

• Gen Electric

Inventors

• Hon Robert Charles
• Gansler Michael Thomas

Classifications

• F02C7/268 Primary

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• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• B64D27/16

  of jet type · CPC title

• B64D2027/026

  Operations & Transport · mapped topic

• B64D27/35

  Arrangements for on-board electric energy production, distribution, recovery or storage · CPC title