Gas turbine engine with igniter stack or borescope mount having noncollinear cooling passages

Patent metadata

Field	Value
Publication number	US-10995954-B2
Application number	US-201816170981-A
Country	US
Kind code	B2
Filing date	Oct 25, 2018
Priority date	Dec 15, 2015
Publication date	May 4, 2021
Grant date	May 4, 2021

Abstract

A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.

First claim

What is claimed is:

1. A combustor for a gas turbine engine comprising:
a combustor liner defining a combustion chamber, wherein the combustor liner has at least one opening;
a combustor liner mount received in the at least one opening of the combustor liner and having an igniter tower;
at least one continuous cooling passage defined solely within the igniter tower having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis; and
a combustor component received in the combustor liner mount, wherein the combustor component has an inward portion in register with the combustion chamber and near to the outlet;
whereby the combustor is configured to direct a flow of cooling air external of the combustor liner to the inlet, through the at least one cooling passage, and out of the outlet to cool at least one of the combustor liner mount and the combustor component.

2. The combustor of claim 1 wherein the combustor component comprises an igniter or a borescope plug and the combustor liner mount comprises an igniter stack or borescope plug mount.

3. The combustor of claim 1 wherein the at least one cooling passage comprises an arcuate portion disposed between the inlet and the outlet thereof.

4. The combustor of claim 1 wherein the at least one cooling passage comprises an angled portion disposed between the inlet and the outlet thereof.

5. The combustor of claim 1 wherein the at least one cooling passage includes a change in direction between the inlet and outlet thereof.

6. The combustor of claim 1 wherein the at least one cooling passage has a plurality of inner dimensions between the inlet and outlet thereof.

7. The combustor of claim 1 wherein the at least one cooling passage includes at least one of a narrowing taper extending into the at least one cooling passage from the inlet thereof, and a widening taper extending into the at least one cooling passage from the outlet thereof.

8. The combustor of claim 1 wherein the at least one cooling passage includes a manifold which distributes air passing through the at least one cooling passage to a plurality of outlets of the at least one cooling passage fluidly connected to the manifold.

9. The combustor of claim 1 wherein the outlet of the at least one cooling passage comprises an opening adjacent a base of the combustor liner mount positioned adjacent to the combustor component.

10. The combustor of claim 1 wherein the igniter tower is unitary with the combustor liner.

11. A combustor for a gas turbine engine comprising:
a combustor liner defining a combustion chamber, wherein the combustor liner has a wall defining an inner surface and an outer surface, and with at least one opening extending from the outer surface;
a combustor liner mount received in the at least one opening of the combustor liner and having an igniter tower;
at least one continuous cooling passage defined solely within the igniter tower having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis, and the outlet is above the inner surface of the outer wall; and
a combustor component received in the combustor liner mount, wherein the combustor component has an inward portion in register with the combustion chamber and near to the outlet;
whereby the combustor is configured to direct a flow of cooling air external of the combustor liner to the inlet, through the at least one cooling passage, and out of the outlet to cool at least one of the combustor liner mount and the combustor component.

12. The combustor of claim 11 wherein the combustor component comprises an igniter or a borescope plug and the combustor liner mount comprises an igniter stack or borescope plug mount.

13. The combustor of claim 11 wherein the at least one cooling passage comprises an arcuate portion disposed between the inlet and the outlet thereof.

14. The combustor of claim 11 wherein the at least one cooling passage comprises an angled portion disposed between the inlet and the outlet thereof.

15. The combustor of claim 11 wherein the at least one cooling passage includes a change in direction between the inlet and outlet thereof.

16. The combustor of claim 11 wherein the at least one cooling passage has a plurality of inner dimensions between the inlet and outlet thereof.

17. The combustor of claim 11 wherein the at least one cooling passage includes at least one of a narrowing taper extending into the at least one cooling passage from the inlet thereof, and a widening taper extending into the at least one cooling passage from the outlet thereof.

18. The combustor of claim 11 wherein the at least one cooling passage includes a manifold which distributes air passing through the at least one cooling passage to a plurality of outlets of the at least one cooling passage fluidly connected to the manifold.

19. The combustor of claim 11 wherein the outlet of the at least one cooling passage comprises an opening adjacent a base of the combustor liner mount positioned adjacent to the combustor component.

20. The combustor of claim 11 wherein the igniter tower is unitary with the combustor liner.

Assignees

• Gen Electric

Inventors

• Gonyou Craig Alan
• Bennett William Thomas

Classifications

• F23R3/283 Primary

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• Y02T50/60

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

• F23R3/16

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title