Embedded electric machine

Patent metadata

Field	Value
Publication number	US-10308366-B2
Application number	US-201615242789-A
Country	US
Kind code	B2
Filing date	Aug 22, 2016
Priority date	Aug 22, 2016
Publication date	Jun 4, 2019
Grant date	Jun 4, 2019

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 fan positioned at a forward end of the gas turbine engine;
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 the core air flowpath along the radial direction;
a cavity wall defining at least in part a buffer cavity and an electric machine sump, the electric machine sump positioned opposite the buffer cavity and extending at least partially around the electric machine, the buffer cavity surrounding at least a portion of the electric machine and the electric machine sump to thermally insulate the electric machine; and
a cooling duct in airflow communication with the buffer cavity for providing a cooling airflow to the buffer cavity, wherein the cooling duct is additionally in airflow communication with at least one of the fan or the compressor section.

2. The gas turbine engine of claim 1 , wherein the buffer cavity extends from a location forward of the electric machine to a location aft of the electric machine.

3. The gas turbine engine of claim 1 , wherein the buffer cavity is positioned at least partially between the electric machine and the core air flowpath.

4. The gas turbine engine of claim 1 , wherein the electric machine is mounted at least partially within or aft of the turbine section along the axial direction.

5. The gas turbine engine of claim 1 , further comprising:
an electric machine lubrication system, wherein the electric machine lubrication system is in fluid communication with the electric machine sump for providing a thermal fluid to the electric machine sump.

6. The gas turbine engine of claim 5 , further comprising:
an engine lubrication system, wherein the engine lubrication system operates independently of the electric machine lubrication system.

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

8. The gas turbine engine of claim 7 , wherein the electric generator is a permanent magnet electric generator comprising a plurality of permanent magnets.

9. The gas turbine engine of claim 8 , 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.

10. The gas turbine engine of claim 9 , wherein the cooling system maintains a temperature of the permanent magnets below at least about a 50° F. limit of the Curie temperature limit.

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

12. The gas turbine engine of claim 1 , wherein the cavity wall includes insulation.

13. The gas turbine engine of claim 1 , wherein the buffer cavity substantially completely surrounds the electric machine.

14. A propulsion system for an aeronautical device comprising:
an electric propulsor; and
a gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising
a fan positioned at a forward end of the gas turbine engine;
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 the core air flowpath along the radial direction, the electric machine electrically connected to the electric propulsor;
a cavity wall defining at least in part a buffer cavity and an electric machine sump, the electric machine sump positioned opposite the buffer cavity and extending at least partially around the electric machine, the buffer cavity surrounding at least a portion of the electric machine and the electric machine sump to thermally insulate the electric machine; and
a cooling duct in airflow communication with the buffer cavity for providing a cooling airflow to the buffer cavity, wherein the cooling duct is additionally in airflow communication with at least one of the fan or the compressor section.

15. The propulsion system of claim 14 , wherein the buffer cavity extends from a location forward of the electric machine to a location aft of the electric machine.

16. The propulsion system of claim 14 , wherein the buffer cavity is positioned at least partially between the electric machine and the core air flowpath.

17. The propulsion system of claim 14 , further comprising:
an electric machine lubrication system, wherein the electric machine lubrication system is in fluid communication with the electric machine sump for providing a thermal fluid to the electric machine sump.

Assignees

• Gen Electric

Inventors

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

Classifications

• B64D27/12

  within, or attached to, wings · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• B64D27/24 Primary

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

• B64D2027/026

  Operations & Transport · mapped topic

• H02K1/27

  Rotor cores with permanent magnets · CPC title