Combustor

• US 8,015,829 B2
• Filed: 02/26/2008
• Issued: 09/13/2011
• Est. Priority Date: 10/23/2003
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Goetschius, Alan J., Coughlan, Joseph D. III, Pacheco-Tougas, Monica, Hoke, James B.
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US12/037,128
• Publication Number:
  US 20090293488A1
• Time in Patent Office: 1,295 Days
• Field of Search: 608/02, 607/55, 607/56, 607/57, 608/05, 608/04
• US Class Current: 60/804
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/42 characterised by the arrangement or form of the flame tubes or combustion chambers
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. The shell has a plurality of holes for directing air to a space between the shell and heat shield and adapted for preferentially directing said air toward leading edge portions of first stage vanes of a turbine section.

Claims

1. A gas turbine engine combustor comprising:

an inboard wall;

an outboard wall; and

a forward bulkhead extending the inboard and outboard walls and cooperating therewith to define a combustor interior volume,

wherein, at least a first wall of said inboard and outboard walls comprises;

an exterior shell; and

an interior heat shield comprising a plurality of panels having;

an interior surface;

an exterior surface;

a perimeter having leading and trailing edges and first and second lateral edges; and

a plurality of pins protruding from the exterior surface toward the shell wherein the shell has a plurality of holes for directing air to a space between the shell and heat shield and adapted for preferentially directing said air toward leading edge portions of first stage vanes of a turbine section, the plurality of holes comprising a plurality of first groups and a plurality of second groups, the holes of the first groups being smaller and more closely spaced than the holes of the second groups.

2. The combustor of claim 1 wherein the plurality of holes comprises a plurality of alternating first and second groups of holes having at least partial differences in at least one of size and distribution.

3. The combustor of claim 1 wherein the plurality of holes comprises a plurality of alternating first and second groups of holes having at least partial differences in both size and distribution.

4. The combustor of claim 1 wherein:

the first groups have a circumferential span between 60% and 150% of a circumferential span of the second groups.

5. The combustor of claim 1 wherein the first wall is the inboard wall and the outboard wall comprises:

an exterior shell; and

an interior heat shield comprising a plurality of panels having;

an interior surface;

an exterior surface;

a perimeter having leading and trailing edges and first and second lateral edges; and

a plurality of pins protruding from the exterior surface toward the shell wherein the outboard wall shell has a plurality of holes for directing air to a space between the outboard wall shell and outboard wall heat shield and adapted for preferentially directing said air toward leading edge portions of said first stage vanes of said turbine section.

6. The combustor of claim 5 wherein:

the outboard wall holes comprise a plurality of first groups and a plurality of second groups, the holes of the first groups being smaller and more closely spaced than the holes of the second groups.

7. The combustor of claim 6 wherein:

the outboard wall hole first groups have a circumferential span between 60% and 150% of a circumferential span of the outboard wall hole second groups; and

the inboard wall hole first groups have a circumferential span between 60% and 150% of a circumferential span of the inboard wall hole second groups

8. The combustor of claim 1 wherein the plurality of pins contacts the shell.

9. The combustor of claim 1 wherein the plurality of pins is a continuous uninterrupted array.

10. The combustor of claim 1 wherein the plurality of pins a plurality of circumferential rows of pins, each row being out of phase with any adjacent row.

11. The combustor of claim 1 wherein the first wall is the outboard wall.

12. A gas turbine engine combustor comprising:

an inboard wall;

an outboard wall; and

a forward bulkhead extending the inboard and outboard walls and cooperating therewith to define a combustor interior volume, wherein, at least a first wall of said inboard and outboard walls comprises;

an exterior shell;

an interior heat shield comprising a plurality of panels having;

an interior surface;

an exterior surface;

a perimeter having leading and trailing edges and first and second lateral edges; and

a plurality of pins protruding from the exterior surface toward the shell; and

means for directing air to a space between the shell and heat shield preferentially toward leading edge portions of first stage vanes of a turbine section, the means comprising a plurality of holes for directing air to a space between the shell and heat shield, the plurality of holes comprising a plurality of first groups and a plurality of second groups, the holes of the first groups being smaller and more closely spaced than the holes of the second groups.

13. The combustor of claim 12 wherein the first wall is the inboard wall and the outboard wall comprises:

an exterior shell; and

an interior heat shield comprising a plurality of panels having;

an interior surface;

an exterior surface;

a perimeter having leading and trailing edges and first and second lateral edges; and

a plurality of pins protruding from the exterior surface toward the shell; and

means for directing air to a space between the shell and heat shield preferentially toward leading edge portions of said first stage vanes of said turbine section.

14. The combustor of claim 13 wherein the means of the outboard wall comprises a plurality of alternating first and second groups of holes having at least partial differences in at least one of size and distribution.

15. The combustor of claim 13 wherein the means of the outboard wall comprises a plurality of alternating first and second groups of holes having at least partial differences both size and distribution.

16. The combustor of claim 12 wherein the plurality of pins contacts the shell.

17. The combustor of claim 12 wherein the plurality of pins is a continuous uninterrupted array.

18. The combustor of claim 12 wherein the plurality of pins a plurality of circumferential rows of pins, each row being out of phase with any adjacent row.

19. The combustor of claim 12 wherein the first wall is the outboard wall.