Stator temperature control system for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11035251-B2
Application number	US-201916583781-A
Country	US
Kind code	B2
Filing date	Sep 26, 2019
Priority date	Sep 26, 2019
Publication date	Jun 15, 2021
Grant date	Jun 15, 2021

Abstract

A stator temperature control system for a gas turbine engine is provided. The stator temperature control system includes a casing circumferentially surrounding a stator assembly, the casing having a top portion and a bottom portion; an air source having an inlet and an outlet; and a supply line in fluid communication with the outlet of the air source and the bottom portion of the casing, wherein the bottom portion of the casing receives a flow of air from the air source via the supply line to increase a temperature of the bottom portion of the casing.

First claim

What is claimed is:

1. A stator temperature control system for a gas turbine engine, the stator temperature control system comprising:
a casing circumferentially surrounding a stator assembly, the casing having a top portion and a bottom portion;
an air source having an inlet and an outlet; and
a supply line in fluid communication with the outlet of the air source and the bottom portion of the casing,
wherein the bottom portion of the casing receives a flow of air from the air source via the supply line to increase a temperature of the bottom portion of the casing.

2. The system of claim 1 , further comprising:
a heat shield at least partially surrounding a part of the bottom portion of the casing,
wherein the supply line is in fluid communication with the outlet of the air source and the heat shield, wherein the heat shield receives the flow of air from the air source via the supply line, and wherein the heat shield directs the flow of air to the bottom portion of the casing.

3. The system of claim 2 , wherein the heat shield comprises:
a heat shield inlet portion in fluid communication with the supply line;
a plurality of flow channels in fluid communication with the heat shield inlet portion; and
a plurality of flow apertures spaced around the heat shield and in communication with the plurality of flow channels, respectively,
wherein the plurality of flow channels of the heat shield receive the flow of air from the air source via the supply line and the heat shield inlet portion, and wherein the plurality of flow apertures of the heat shield direct the flow of air to the bottom portion of the casing.

4. The system of claim 2 , further comprising:
a control valve between the outlet of the air source and the supply line, the control valve transitionable between an open position in which the supply line is in fluid communication with the outlet of the air source and the heat shield receives the flow of air from the outlet of the air source via the supply line, and a closed position in which the supply line is not in fluid communication with the outlet of the air source.

5. The system of claim 4 , further comprising:
a controller operable to transition the control valve between the open position and the closed position.

6. The system of claim 4 , wherein the control valve is in the open position with the gas turbine engine in a ground idle pre-shutdown condition.

7. The system of claim 4 , wherein the control valve is in the closed position with the gas turbine engine in a shutdown condition.

8. The system of claim 1 , further comprising:
a temperature control flange disposed in the bottom portion of the casing.

9. The system of claim 1 , wherein the inlet of the air source receives bleed air from a portion of the gas turbine engine.

10. The system of claim 1 , wherein the air source comprises an air supply precooler and the supply line comprises a bypass supply line.

11. A stator temperature control system for a gas turbine engine, the stator temperature control system comprising:
a casing circumferentially surrounding a stator assembly, the casing having a top portion and a bottom portion;
a heat shield at least partially surrounding a part of the bottom portion of the casing;
an air source having an inlet and an outlet; and
a supply line in fluid communication with the outlet of the air source and the heat shield,
wherein the heat shield receives a flow of air from the air source via the supply line, and wherein the heat shield directs the flow of air to the bottom portion of the casing to increase a temperature of the bottom portion of the casing.

12. The system of claim 11 , wherein the heat shield comprises:
a heat shield inlet portion in fluid communication with the supply line;
a plurality of flow channels in fluid communication with the heat shield inlet portion; and
a plurality of flow apertures spaced around the heat shield and in communication with the plurality of flow channels, respectively,
wherein the plurality of flow channels of the heat shield receive the flow of air from the air source via the supply line and the heat shield inlet portion, and wherein the plurality of flow apertures of the heat shield direct the flow of air to the bottom portion of the casing.

13. The system of claim 11 , further comprising:
a control valve between the outlet of the air source and the supply line, the control valve transitionable between an open position in which the supply line is in fluid communication with the outlet of the air source and the heat shield receives the flow of air from the outlet of the air source via the supply line, and a closed position in which the supply line is not in fluid communication with the outlet of the air source.

14. A method of controlling a temperature of a stator assembly for a gas turbine engine, the method comprising:
providing a casing circumferentially surrounding the stator assembly, the casing having a top portion and a bottom portion;
providing an air source having an inlet and an outlet within the gas turbine engine; and
directing a flow of air from the outlet of the air source to the bottom portion of the casing to increase a temperature of the bottom portion of the casing.

15. The method of claim 14 , wherein directing the flow of air from the outlet of the air source to the bottom portion of the casing comprises providing a supply line in fluid communication with the outlet of the air source and the bottom portion of the casing, wherein the bottom portion of the casing receives the flow of air from the outlet of the air source via the supply line.

16. The method of claim 15 , further comprising:
providing a heat shield at least partially surrounding a part of the bottom portion of the casing, wherein the supply line is in fluid communication with the outlet of the air source and the heat shield.

17. The method of claim 16 , wherein directing the flow of air from the outlet of the air source to the bottom portion of the casing comprises moving the flow of air through the supply line to the heat shield, and wherein the heat shield directs the flow of air to the bottom portion of the casing.

18. The method of claim 15 , wherein directing the flow of air from the outlet of the air source to the bottom portion of the casing occurs with the gas turbine engine in a ground idle pre-shutdown condition and before shutdown of the gas turbine engine.

19. The method of claim 18 , further comprising:
after the gas turbine engine is shutdown, directing a second flow of air from a second air source to the bottom portion of the casing via the supply line to increase the temperature of the bottom portion of the casing.

20. The method of claim 14 , wherein the inlet of the air source receives bleed air from a portion of the gas turbine engine.

Assignees

• Gen Electric

Inventors

• Shinde Kudum
• Sharma Tarun
• Bibler John David
• Verma Ajit Kumar
• Hamilpur Ravinder

Classifications

• Y02T50/60

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

• F01D25/145 Primary

  Thermally insulated casings · CPC title

• F01D25/10

  Heating, e.g. warming-up before starting · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title