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

Patent metadata

Field	Value
Publication number	US-10145559-B2
Application number	US-201514969372-A
Country	US
Kind code	B2
Filing date	Dec 15, 2015
Priority date	Dec 15, 2015
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

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, the combustor liner mount comprising:
an igniter tower,
a ferrule,
a tower cap, and
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 adjacent 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 igniter tower, the tower cap, and the ferrule are axially aligned in a stacked relationship disposed around the at least one opening of the combustor liner.

4. The combustor of claim 3 wherein the igniter tower, is unitary.

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

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

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

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

9. 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.

10. 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.

11. 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.

12. A combustor liner mount for a gas turbine engine received in an at least one opening of a combustor liner, the combustor liner mount including an igniter tower, a ferrule, and a tower cap, and having at least one cooling passage defined solely within the igniter tower, the at least one cooling passage having an inlet defining an inlet axis at an exterior portion of the combustor liner mount and an outlet defining an outlet axis at an interior portion of the combustor liner, wherein the at least one cooling passage has non-collinear portion between the inlet and outlet of the at least one cooling passage thereof.

13. The combustor liner mount of claim 12 wherein the at least one cooling passage comprises an arcuate portion disposed between the inlet and the outlet.

14. The combustor liner mount of claim 12 wherein the at least one cooling passage comprises an angled portion disposed between the inlet and the outlet.

15. The combustor liner mount of claim 12 wherein the at least one cooling passage comprises a change in direction between the inlet and outlet.

16. The combustor liner mount of claim 12 wherein the at least one cooling passage comprises a plurality of inner dimensions between the inlet and outlet.

17. The combustor liner mount of claim 12 wherein the at least one cooling passage comprises at least one of a narrowing taper extending into the at least one cooling passage from the inlet, and a widening taper extending into the at least one cooling passage from the outlet.

18. 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, comprising:
a tower,
a tower cap,
a ferrule, and
at least one cooling passage defined solely within the tower wherein the at least one cooling passage has a non-collinear portion between inlet and outlet ends thereof; and

a combustor component received in the combustor liner mount;
wherein the tower, tower cap, and ferrule are axially aligned in a stacked relationship disposed around the at least one opening of the combustor liner, wherein the combustor component has an inward portion in register with the combustion chamber and adjacent to the outlet;

whereby the combustor is configured to direct a flow of cooling air adjacent to the combustor liner in part to the inlet end, through the at least one cooling passage, and out of the outlet end to provide cooling to at least one of the combustor liner mount and the combustor component.

19. The combustor of claim 18 wherein the flow of cooling air further cools the inward portion of the combustor component.

20. The combustor of claim 18 wherein the combustor component comprises an igniter or a borescope plug and the combustor liner mount comprises an igniter stack or borescope plug mount.

21. The combustor of claim 18 wherein the at least one cooling passage of the combustor liner mount is defined within at least one of the tower, tower cap and ferrule, or an outer liner impingement baffle.

Assignees

• Gen Electric

Inventors

• Gonyou Craig Alan
• Bennett William Thomas

Classifications

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R3/283 Primary

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

• F23R3/002 Primary

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

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title