Embedded electric machine

Patent metadata

Field	Value
Publication number	US-11247779-B2
Application number	US-201916366453-A
Country	US
Kind code	B2
Filing date	Mar 27, 2019
Priority date	Aug 22, 2016
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.

First claim

What is claimed is:

1. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;
a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;
a lubrication assembly;
an electric machine coupled to the rotary component at least partially inward of a portion of the core air flowpath defined by the turbine section along the radial direction;
an electric machine sump in fluid communication with the lubrication assembly for receiving a flow of lubrication fluid from the lubrication assembly; and
a sealed cavity assembly comprising one or more fluid seals at least partially defining a sealed cavity and configured to prevent the lubrication fluid from the electric machine sump from entering the sealed cavity, wherein the electric machine is enclosed within the sealed cavity.

2. The gas turbine engine of claim 1 , wherein the sealed cavity assembly is enclosed at least partially within the electric machine sump.

3. The gas turbine engine of claim 1 , wherein the sealed cavity assembly is formed in part by a rotor connection member and a stator connection member, and wherein the one or more fluid seals are positioned between the rotor connection member and the stator connection member.

4. The gas turbine engine of claim 3 , wherein the one or more fluid seals includes a first fluid seal positioned between the rotor connection member and the stator connection member at a location forward of the electric machine and a second fluid seal positioned between the rotor connection member and the stator connection member at a location aft of the electric machine.

5. The gas turbine engine of claim 3 , wherein a first bearing is positioned between the rotor connection member and the stator connection member, and wherein the one or more fluid seals comprises a first fluid seal positioned between the first bearing and the sealed cavity.

6. The gas turbine engine of claim 5 , wherein a second bearing is also positioned between the rotor connection member and the stator connection member, and wherein the one or more fluid seals comprises a second fluid seal positioned between the second bearing and the sealed cavity.

7. The gas turbine engine of claim 6 , wherein the first fluid seal and first bearing are each positioned between the rotor connection member and the stator connection member at a location forward of the electric machine, and wherein the second fluid seal and second bearing are each positioned between the rotor connection member and the stator connection member at a location aft of the electric machine.

8. The gas turbine engine of claim 1 , wherein the electric machine is an electric generator.

9. The gas turbine engine of claim 8 , wherein the electric generator is a permanent magnet electric generator comprising a plurality of permanent magnets.

10. The gas turbine engine of claim 9 , further comprising:
a cooling system operable with the buffer cavity, wherein the plurality of permanent magnets each define a Curie temperature limit, and wherein the cooling system maintains a temperature of each of the permanent magnets below the Curie temperature limit.

11. The gas turbine engine of claim 10 , wherein the cooling system maintains a temperature of the permanent magnets below at least about a 50° F. limit of the Curie temperature limit.

12. The gas turbine engine of claim 1 , wherein the electric machine is mounted coaxially with the rotary component.

13. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;
a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;
an electric machine coupled to the rotary component at least partially inward of a portion of the core air flowpath defined by the turbine section along the radial direction; and
a cavity assembly comprising one or more labyrinth seals at least partially defining a pressurized cavity, wherein the electric machine is enclosed within the sealed cavity.

14. The gas turbine engine of claim 13 , wherein the cavity assembly is enclosed at least partially within an electric machine sump.

15. The gas turbine engine of claim 13 , wherein cavity assembly is formed in part by a rotor connection member and a stator connection member, and wherein the one or more labyrinth seals are positioned between the rotor connection member and the stator connection member.

16. The gas turbine engine of claim 15 , wherein the one or more labyrinth seals includes a first labyrinth seal positioned between the rotor connection member and the stator connection member at a location forward of the electric machine and a second labyrinth seal positioned between the rotor connection member and the stator connection member at a location aft of the electric machine.

17. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;
a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;
an electric machine disposed at least partially inward of a portion of the core air flowpath defined by the turbine section along the radial direction;
a cavity assembly comprising a rotor connection member coupled to the rotary component, a stator connection member, and one or more seals, the rotor connection member, the stator connection member, and the one or more seals together at least partially defining a sealed cavity, wherein the electric machine is positioned within the sealed cavity and is coupled to the rotor connection member and the stator connection member; and
a cooling system comprising an electrical juncture box coupled to the rotor connection member or the stator connection member, wherein the electrical juncture box is thermally connected to the sealed cavity for cooling the sealed cavity.

18. The gas turbine engine of claim 17 , wherein the cooling system is configured to provide a cooling fluid to the electrical juncture box.

19. The gas turbine engine of claim 1 , wherein at least one bearing and the electric machine are mounted co-axially on an upper surface of a common structure.

20. The gas turbine engine of claim 1 ,
wherein the electric machine comprises a rotor and a stator, and
wherein the rotor is positioned on an outer side of the stator in the radial direction.

Assignees

• Gen Electric

Inventors

• Kupiszewski Thomas
• Miller Brandon Wayne
• Niergarth Daniel Alan
• Vondrell Randy M

Classifications

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title

• Y02T50/60

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

• F04D25/06

  the pump being electrically driven (F04D25/08 takes precedence) · CPC title

• H02K1/27

  Rotor cores with permanent magnets · CPC title

• F01D25/183

  Sealing means · CPC title