Active clearance control for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10378374-B2
Application number	US-201514672561-A
Country	US
Kind code	B2
Filing date	Mar 30, 2015
Priority date	Apr 4, 2014
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

A gas turbine engine includes a fluid intake. A turbine section includes a turbine case. A firewall is located upstream of the turbine section. A conduit is configured to direct a fluid from the fluid intake to the turbine case. A valve is located on a first side of the firewall opposite from the turbine section and is configured to regulate a flow of the fluid through the conduit.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a fluid intake;
a turbine section including a turbine case;
a firewall located upstream of the turbine section;
a conduit configured to direct a fluid from the fluid intake to the turbine case; and
a valve located on a first side of the firewall opposite from the turbine section and configured to regulate a flow of the fluid through the conduit.

2. The gas turbine engine of claim 1 including a combustor section, wherein the combustor section is located on a second side of the firewall opposite the first side of the firewall.

3. The gas turbine engine of claim 1 including at least one fluid delivery manifold in fluid communication with the conduit for directing the fluid along the turbine case.

4. The gas turbine engine of claim 3 wherein the fluid delivery manifold surrounds the turbine case.

5. The gas turbine engine of claim 1 wherein the conduit is configured to direct the fluid from the first side of the firewall to a second side of the firewall opposite the first side of the firewall.

6. The gas turbine engine of claim 1 wherein the fluid intake protrudes through an inner nacelle and is in fluid communication with a bypass airflow path in a fan section.

7. The gas turbine engine of claim 1 wherein the fluid intake is elliptical.

8. The gas turbine engine of claim 1 wherein the fluid intake extends into a fan bypass flow path and is in fluid communication with the fluid intake.

9. The gas turbine engine of claim 1 wherein the firewall includes an ECS manifold and a nacelle ventilation manifold.

10. The gas turbine engine of claim 1 wherein the fluid intake is located on the first side of the firewall.

11. The gas turbine engine of claim 1 , wherein the turbine section includes a high pressure turbine and a low pressure turbine and the conduit is in fluid communication with a first manifold surrounding the high pressure turbine and a second manifold surrounding the low pressure turbine.

12. The gas turbine engine of claim 11 , wherein the first manifold is configured to direct the fluid at an outside surface of the high pressure turbine.

13. The gas turbine engine of claim 12 , wherein the second manifold is configured to direct the fluid at an outside surface of the low pressure turbine.

14. The gas turbine engine of claim 11 , wherein the conduit includes a first branch in fluid communication with the first manifold and a second branch in fluid communication with the second manifold.

15. The gas turbine engine of claim 14 , wherein the first branch is located axially upstream of the low pressure turbine.

16. The gas turbine engine of claim 1 , wherein the firewall includes side an ECS manifold located on a downstream side of the firewall and the ECS manifold is in fluid communication with an ESC module.

17. The gas turbine engine of claim 16 , wherein the firewall includes a nacelle ventilation manifold on a downstream side of the firewall and the nacelle ventilation manifold is in fluid communication with the nacelle.

18. The gas turbine engine of claim 1 , wherein the intake is directed radially outward relative to an axis of rotation of the gas turbine engine.

19. The gas turbine engine of claim 1 , wherein the conduit extends radially inward from the fluid intake relative to an axis of rotation of a gas turbine engine.

20. The gas turbine engine of claim 19 , wherein the conduit and the fluid intake are located radially outward and spaced from a compressor section of the gas turbine engine.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M
• Snape Nathan

Classifications

• F02C7/25

  Fire protection or prevention (in general A62) · CPC title

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F05D2260/231

  Preventing heat transfer · CPC title

• F02C5/12

  the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title