Hybrid electric multiple shaft core

Patent metadata

Field	Value
Publication number	US-12480450-B2
Application number	US-202117359891-A
Country	US
Kind code	B2
Filing date	Jun 28, 2021
Priority date	Jun 28, 2021
Publication date	Nov 25, 2025
Grant date	Nov 25, 2025

Abstract

A hybrid electric engine of an aircraft includes a compressor, a turbine operably connected to the compressor via a variable gear ratio gearbox and a combustor configured to drive the turbine via a flow of combustion products. An electric motor is operably connected to the variable gear ratio rear box and configured to input rotational energy into the gearbox. The input of rotational energy into the gearbox from the electric motor changes a rotational speed of one of the compressor or the turbine relative to the other of the compressor or the turbine.

First claim

What is claimed is:

1 . A hybrid electric engine of an aircraft, comprising:
a high pressure compressor located at and rotatable about an engine central longitudinal axis; a high pressure turbine located at and rotatable about the engine central longitudinal axis, the high pressure turbine operably connected to the high pressure compressor via a variable gear ratio gearbox; a combustor configured to drive the high pressure turbine via a flow of combustion products; and an electric motor operably connected to the variable gear ratio gearbox and configured to input rotational energy into the variable gear ratio gearbox; wherein the rotational energy inputted into the variable gear ratio gearbox from the electric motor changes a rotational speed of one of the high pressure compressor or the high pressure turbine relative to the other of the high pressure compressor or the high pressure turbine; wherein the variable gear ratio gearbox is located axially between the high pressure compressor and the high pressure turbine; wherein:
the variable gear ratio gearbox is operably connected to the high pressure turbine via a first tower shaft operably connected to a turbine shaft at a first axial end of the high pressure compressor; and
the variable gear ratio gearbox is operably connected to the high pressure compressor via a second tower shaft operably connected to a compressor shaft at a second axial end of the high pressure compressor opposite the first axial end;
wherein the compressor shaft is located radially outboard of the turbine shaft and axially overlaps the turbine shaft.

2 . The hybrid electric engine of claim 1 , wherein the rotational energy accelerates the high pressure compressor relative to the high pressure turbine.

3 . The hybrid electric engine of claim 1 , wherein the rotational energy decelerates the high pressure compressor relative to the high pressure turbine.

4 . The hybrid electric engine of claim 1 , wherein in the variable gear ratio gearbox includes a planetary gear arrangement.

5 . The hybrid electric engine of claim 1 , wherein the electric motor is a variable speed electric motor.

6 . The hybrid electric engine of claim 1 , further comprising:
a compressor speed sensor configured to detect a compressor shaft speed; and a turbine speed sensor configured to detect a turbine shaft speed; wherein operation of the electric motor is selectably changed as a result of the detected compressor shaft speed and the detected turbine shaft speed.

7 . The hybrid electric engine of claim 1 , wherein the electric motor includes a brake mechanism to stop rotation of the electric motor.

8 . A method of operating a hybrid electric engine, comprising:
combusting a fuel at a combustor; driving a high pressure turbine about an engine central longitudinal axis via products of combusting the fuel at the combustor; driving a high pressure compressor about the engine central longitudinal axis via driving of the high pressure turbine, the high pressure turbine and the high pressure compressor operably connected to a variable gear ratio gearbox; inputting rotational energy from an electric motor into the variable gear ratio gearbox; changing a rotational speed of the high pressure compressor relative to the high pressure turbine via inputting the rotational energy into the variable gear ratio gearbox; wherein the variable gear ratio gearbox is located remotely from the engine central longitudinal axis; wherein the variable gear ratio gearbox is located axially between the high pressure compressor and the high pressure turbine; wherein:
the variable gear ratio gearbox is operably connected to the high pressure turbine via a first tower shaft operably connected to a turbine shaft at a first axial end of the high pressure compressor; and
the variable gear ratio gearbox is operably connected to the high pressure compressor via a second tower shaft operably connected to a compressor shaft at a second axial end of the high pressure compressor opposite the first axial end;
wherein the compressor shaft is located radially outboard of the turbine shaft and axially overlaps the turbine shaft.

9 . The method of claim 8 , further comprising accelerating the high pressure compressor relative to the high pressure turbine by inputting the rotational energy.

10 . The method of claim 9 , wherein the rotational speed of the high pressure compressor is increased by up to about 30% relative to a rotational speed of the high pressure turbine.

11 . The method of claim 8 , further comprising decelerating the high pressure compressor relative to the high pressure turbine by inputting the rotational energy.

12 . The method of claim 8 , wherein a default speed ratio of the high pressure compressor to the high pressure turbine without inputting the rotational energy from the electric motor is other than 1:1.

13 . The method of claim 8 , further comprising varying a speed of the electric motor.

14 . The method of claim 8 , further comprising:
detecting a compressor shaft speed via a compressor speed sensor; detecting a turbine shaft speed via a turbine speed sensor; and selectably changing operation of the electric motor as a result of the detected compressor shaft speed and the detected turbine shaft speed.

Assignees

• Rtx Corp

Inventors

• Greenberg Michael D
• Smith Lance L
• Cronin Dennis P
• Poisson Nancy
• Ramsey Christopher D
• Terwilliger Neil

Classifications

• F05D2220/76

  an electrical generator · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02K5/00

  Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2260/76

  the adjusting mechanism using auxiliary power sources · CPC title