Embedded electric machine

• US 10,308,366 B2
• Filed: 08/22/2016
• Issued: 06/04/2019
• Est. Priority Date: 08/22/2016
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Kupiszewski, Thomas, Miller, Brandon Wayne, Niergarth, Daniel Alan, Vondrell, Randy M.
• Primary Examiner(s): Gugger, Sean
• Application Number:
  US15/242,789
• Publication Number:
  US 20180050806A1
• Time in Patent Office: 1,016 Days
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/12 within, or attached to, wings
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• CPC Class Codes: F01D 25/183 Sealing means
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F02C 7/24 Heat or noise insulation air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F02K 5/00 Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
• CPC Class Codes: F04D 19/02 Multi-stage pumps
• CPC Class Codes: F04D 25/06 the pump being electrically driven F04D25/08 takes precedence
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2220/768 equipped with permanent magnets
• CPC Class Codes: F05D 2260/98 Lubrication
• CPC Class Codes: H02K 1/27 Rotor cores with permanent magnets
• CPC Class Codes: H02K 7/1823 structurally associated with turbines or similar engines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

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.