Sump arrangement for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-12044169-B2
Application number	US-202217871146-A
Country	US
Kind code	B2
Filing date	Jul 22, 2022
Priority date	Jul 22, 2022
Publication date	Jul 23, 2024
Grant date	Jul 23, 2024

Abstract

A gas turbine engine including a compressor section including a compressor and a turbine section located downstream of the compressor section. The turbine section including a high pressure turbine, a low pressure turbine, a sump positioned between the high pressure turbine and the low pressure turbine, and a rotating cross flow arrangement defining a plurality of guiding passages fluidly coupling the compressor to the sump.

First claim

What is claimed:

1. A gas turbine engine comprising:
a compressor section comprising a compressor; and
a turbine section located downstream of the compressor section, the turbine section comprising:
a high pressure turbine;
a low pressure turbine;
a sump positioned between the high pressure turbine and the low pressure turbine, and
a rotating cross flow arrangement defining a plurality of guiding passages fluidly coupling the compressor to the sump.

2. The gas turbine engine of claim 1 , wherein the rotating cross flow arrangement crosses a compressed air flow with a purge air flow through the plurality of guiding passages.

3. The gas turbine engine of claim 2 , wherein the plurality of guiding passages providing for the compressed air flow are in flow communication with the sump for pressurizing the sump.

4. The gas turbine engine of claim 2 , wherein the plurality of guiding passages seals the compressed air flow from the purge air flow.

5. The gas turbine engine of claim 2 , wherein the compressed air flow is a low pressure center vent flow.

6. The gas turbine engine of claim 5 , wherein the plurality of guiding passages providing for the low pressure center vent flow are in flow communication with the compressor.

7. The gas turbine engine of claim 2 , wherein the purge air flow is a forward bore cooling flow.

8. The gas turbine engine of claim 1 , wherein the rotating cross flow arrangement is rotatable with the low pressure turbine.

9. The gas turbine engine of claim 8 , wherein the low pressure turbine comprises a torque cone, and wherein the rotating cross flow arrangement is coupled to or formed integrally with the torque cone.

10. The gas turbine engine of claim 9 , wherein the plurality of guiding passages provide an air flow path for a compressed air flow across the torque cone.

11. A method of operating a gas turbine engine, wherein the gas turbine engine comprises a compressor section and a turbine section, the turbine section comprising a high pressure turbine, a low pressure turbine, and a sump, the sump is positioned between the high pressure turbine and the low pressure turbine, the method comprising:
providing a compressed air flow from the compressor section to the sump during an operating condition of the gas turbine engine, wherein providing the compressed air flow comprises providing the compressed air flow through a rotating cross flow arrangement rotatable with the low pressure turbine at a location within the turbine section.

12. The method of claim 11 , wherein providing the compressed air flow through the rotating cross flow arrangement comprises crossing the compressed air flow with a purge air flow of the high pressure turbine.

13. The method of claim 12 , wherein the purge air flow is a forward bore cooling flow.

14. The method of claim 11 , wherein the method of operating the gas turbine engine further comprises:
pressurizing the sump with the compressed air flow, wherein the sump comprises a forward seal and an aft seal, and wherein pressurizing the sump comprises pressurizing the forward seal and the aft seal.

15. The method of claim 11 , wherein the rotating cross flow arrangement comprises a plurality of guiding passages, and wherein the plurality of guiding passages separately seals the compressed air flow and a purge air flow.

16. The method of claim 11 , wherein the compressed air flow is a low pressure center vent flow.

17. The method of claim 11 , wherein the rotating cross flow arrangement is formed integrally with a torque cone of the low pressure turbine.

18. A gas turbine engine comprising:
a sump;
a rotor being rotatable during operation of the gas turbine engine; and
a rotating cross flow arrangement rotatable with the rotor and defining a plurality of guiding passages fluidly configured to cross a first flow path and a second flow path, wherein the first flow path is fluidly coupled to the sump.

19. The gas turbine engine of claim 18 , wherein the plurality of guiding passages seals the first air flow from the second air flow path.

Assignees

• Gen Electric

Inventors

• Raghuvaran Vaishnav
• Saha Atanu
• Kumar Rajesh
• Schimmels Scott Alan

Classifications

• F16N7/30

  the oil being fed or carried along by another fluid (in internal- combustion engines F02F) · CPC title

• F05D2260/606

  Bypassing the fluid · CPC title

• F05D2260/98

  Lubrication · CPC title

• F16N2210/02

  Turbines · CPC title

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title