Insert adjacent to a heat shield element for a gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-9534783-B2
Application number	US-201113188442-A
Country	US
Kind code	B2
Filing date	Jul 21, 2011
Priority date	Jul 21, 2011
Publication date	Jan 3, 2017
Grant date	Jan 3, 2017

Abstract

A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert at least partially between opposed surfaces of the support shell and the heat shield panel, the insert exposed to a combustion chamber, and the insert being flush with a hot side of the heat shield.

First claim

What is claimed is:

1. A combustor of a gas turbine engine comprising:
a support shell;
a heat shield panel mounted to said support shell;
an insert including a central area and at least one flange extending from said central area, said at least one flange at least partially sandwiched between opposed surfaces of said support shell and said heat shield panel, said central area of said insert exposed to a combustion chamber, and said central area of said insert extending from said at least one flange in a direction toward said combustion chamber such that said central area is flush with a hot side surface of said heat shield panels;
wherein said heat shield panel includes a heat shield dilution hole and said support shell includes a support shell dilution hole along a common dilution axis, said insert offset from said dilution axis; and
wherein said central area is at least partially received in one of said heat shield dilution hole and said support shell dilution hole.

2. The combustor as recited in claim 1 , wherein said insert is located at a combustor hot spot.

3. The combustor as recited in claim 1 , wherein said heat shield panel includes at least one film cooling hole.

4. The combustor as recited in claim 1 , wherein said support shell includes at least one impingement cooling hole.

5. The combustor as recited in claim 1 , wherein said insert extends at least partially between said heat shield panel and said support shell.

6. The combustor as recited in claim 1 , wherein said insert is arcuate in shape relative to a reference plane perpendicular to said common dilution axis.

7. The combustor as recited in claim 1 , comprising at least one fastener fixedly securing said insert between said support shell and said heat shield panel.

8. The combustor as recited in claim 1 , wherein said insert is made of a first material, and said heat shield panel is made of a second, different material, and said first material is configured to have a relatively higher thermal resistance than said second material.

9. The combustor as recited in claim 8 , wherein a thermal barrier coating is disposed on surfaces of said insert contacting said support shell.

10. A combustor of a gas turbine engine comprising:
a support shell;
a heat shield panel mounted to said support shell;
an insert at least partially between opposed surfaces of said support shell and said heat shield panel, said insert exposed to a combustion chamber, and said insert being flush with a hot side of said heat shield;
wherein said heat shield panel includes a heat shield dilution hole and said support shell includes a support shell dilution hole along a common dilution axis, said insert offset from said dilution axis; and
wherein said insert is located between said heat shield panel and said support shell, and a portion of said insert is placed within and partially around a perimeter of at least one of said heat shield dilution hole and said support shell dilution hole.

11. The combustor as recited in claim 10 , wherein said insert includes a main body and a flange extending at least partially along a perimeter of said main body, said main body being crescent shaped, and said flange being arcuate shaped.

12. The combustor as recited in claim 11 , wherein each of said main body and said flange partially follows the contour of said at least one of said heat shield dilution hole and said support shell dilution hole.

13. The combustor as recited in claim 11 , wherein said main body is flush with said hot side of said heat shield panel, and said flange is between said opposed surfaces of said support shell and said heat shield panel.

14. The combustor as recited in claim 13 , wherein said flange is at least partially sandwiched between said support shell and said heat shield panel.

15. The combustor as recited in claim 10 , wherein said insert is made of a first material, and said heat shield panel is made of a second, different material, and said first material is configured to have a relatively higher thermal resistance than said second material.

16. The combustor as recited in claim 15 , wherein said insert is manufactured of ceramic matrix composite.

17. A combustor of a gas turbine engine comprising:
a support shell;
a heat shield panel mounted to said support shell; and
an insert including a central area and at least one flange extending from said central area, said central area being crescent shaped and said at least one flange being arcuate shaped, said at least one flange at least partially sandwiched between opposed surfaces of said support shell and said heat shield panel, said central area of said insert exposed to a combustion chamber, and said central area of said insert extending from said at least one flange in a direction toward said combustion chamber such that said central area is flush with a hot side surface of said heat shield panel.

18. The combustor as recited in claim 17 , wherein said insert is located at a combustor hot spot.

19. The combustor as recited in claim 17 , wherein said insert is made of a first material, and said heat shield panel is made of a second, different material, and said first material is configured to have a relatively higher thermal resistance than said second material.

20. The combustor as recited in claim 19 , wherein said insert is manufactured of ceramic matrix composite.

21. The combustor as recited in claim 17 , wherein said heat shield panel includes at least one film cooling hole, and said support shell includes at least one impingement cooling hole.

22. The combustor as recited in claim 17 , wherein said heat shield panel includes a heat shield dilution hole and said support shell includes a support shell dilution hole along a common dilution axis, and said central area is at least partially received in one of said heat shield dilution hole and said support shell dilution hole such that said insert is offset from said common dilution axis.

23. The combustor as recited in claim 22 , wherein said insert extends at least partially between said heat shield panel and said support shell.

24. The combustor as recited in claim 23 , wherein said insert is arcuate in shape relative to a reference plane perpendicular to said common dilution axis.

25. The combustor as recited in claim 24 , wherein a cross-sectional profile of said central area and said at least one flange defines a step relationship.

Assignees

• Dierberger James A
• Hongoh Masamichi
• Sullivan Dennis J
• United Technologies Corp

Inventors

• Dierberger James A
• Hongoh Masamichi
• Sullivan Dennis J

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F23R3/002 Primary

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

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic