Wall elements for gas turbine engine combustors

• US 6,408,628 B1
• Filed: 11/02/2000
• Issued: 06/25/2002
• Est. Priority Date: 11/06/1999
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Pidcock, Anthony, Spooner, Michael P., Close, Desmond
• Primary Examiner(s): Freay, Charles C.
• Assistant Examiner(s): LIU, HAN L
• Application Number:
  US09/703,666
• Time in Patent Office: 600 Days
• Field of Search: 607/52, 607/55, 607/57, 607/58
• US Class Current: 60/752
• 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

Abstract

A wall element (29A, 29B) for a combustor (20) of a gas turbine engine (10). The wall element (29A, 29B) defines an axis. In use, the axis is arranged generally parallel to the principal axis of the engine (10). In one aspect, the length of the wall element (29B) along the axis is at least substantially 20% of the length of the wall element (29B) transverse to the axis. In another aspect, the wall element (29A, 29B) has a first pair of opposite edges extending transverse to the axis and a second pair of opposite edges (48, 50) extending transverse to the first pair, at least one of the second pair of edges (48, 50) being angled relative to the axis of the wall element (29A, 29B).

Claims

1. A wall element for a wall structure of a gas turbine engine combustor with the engine having a principal axis, the wall element comprising a base portion having an axis which in use, extends generally parallel to the principal axis of the engine, wherein the dimension of said wall element parallel to said axis thereof is greater then substantially 20% of the dimension of the wall element transverse to said axis of the wall element, and the base portion includes a plurality of rows of mixing ports to allow gas to enter the combustor in use.

2. A wall element according to claim 1 wherein the dimension of the wall element parallel to said axis thereof is greater than substantially 40% of its dimension transverse to said axis of the wall element.

3. A wall element according to claim 1 wherein the dimension of the wall element parallel to said axis thereof is substantially equal to its dimension transverse to said axis of the wall element.

4. A wall element according to claim 1 wherein the dimension of the wall element parallel to said axis thereof is greater than substantially 40 mm.

5. A wall element according to claim 1 wherein the dimension of the wall element parallel to said axis thereof is between substantially 40 mm and substantially 80 mm.

6. A wall element according to claim 1 wherein the dimension of the wall element parallel to said axis thereof is greater than substantially 80 mm.

7. A wall element according to claim 1 wherein the dimension of the wall element parallel to said axis thereof is substantially 250 mm.

8. A wall element according to claim 1 wherein the base portion has two of said rows, each row extending substantially transverse to said axis of the wall element.

9. A wall element according to claim 1 wherein the base portion defines a plurality of apertures for the passage of a cooling fluid to cool a surface of the base portion which, in use, faces, inwardly of the combustor.

10. A wall element according to claim 1 wherein said base portion has edge regions and further including a plurality of apertures at or adjacent the edge regions of the base portion for the passage of the cooling fluid therethrough in use.

11. A wall element according to claim 10, the base portion being provided with upstream and downstream edge regions, wherein said apertures are located adjacent the downstream edge region.

12. A wall element according to claim 11 wherein the apertures are spaced from upstream and downstream edge regions of the base portion, and are spaced along a line extending substantially centrally of the base portion and transverse to said axis.

13. A wall element according to claim 11 wherein said combustor has an outer wall and at least the downstream edge of the base portion is provided with an outwardly directed flange adapted, in use, to engage the outer wall of the combustor, said flange including a lip portion adapted to engage an adjacent downstream wall element, an outwardly directed flange being provided on the upstream edge of the base portion.

14. A wall element according to claim 11 wherein said combustor has an outer wall and the upstream and downstream edges of the base portion are spaced from the outer wall to provide an opening to allow cooling fluid to flow over the respective edges.

15. A wall element according to claim 11 wherein said combustor has an outer wall and the downstream edge of the base portion is open to allow cooling fluid to flow over said downstream edge, and wherein the upstream edge is adapted to engage the outer wall substantially to prevent cooling fluid flow over said upstream edge.

16. A wall element according to claim 9 wherein the apertures are in the form of effusion holes adapted to direct a film of cooling fluid along said surface of the base portion.

17. A wall element according to claim 1 further including a barrier member extending at least part way across the base portion, the barrier member serving to control flow of cooling fluid across said base portion in use.

23. A wall structure for a gas turbine engine combustor comprising an inner wall and an outer wall, wherein the inner wall comprises a plurality of all elements as claimed in claim 1.

24. A gas turbine engine combustor having a wall structure as claimed in claim 23.

25. A gas turbine engine incorporating a combustor as claimed in claim 24.

18. A wall element for a combustor of a gas turbine engine with the engine having a principal axis, the wall element comprising a base portion having an axis which, in use, extends generally parallel to the principal axis of the engine, and the base portion having a first pair of opposite edges extending transverse to said axis of the base portion and a second pair of opposite edges extending transverse to said first pair of edges wherein at least one of said second pair of edges is angled relative to said axis of the base portion to extend obliquely relative to said axis of said base portion, said base portion including at least one row of mixing ports extending between the second pair of edges to allow gas to enter the combustor in use.

19. A wall element according to claim 18 wherein both of the edges of said second pair of edges are angled as aforesaid relative to the axis of the base portion and extend substantially parallel to each other.

20. A wall element according to claim 18 wherein the or each edge of said second pair of edges is angled relative to the axis of the base portion at an angle of between substantially 10°

and substantially 40°

.

21. A wall element according to claim 20 wherein the or each edge of said second pair of edges is angled relative to the axis of the base portion at an angle of between substantially 20°

and substantially 30°

.

22. A wall element according to claim 20 wherein the or each edge of said second pair of edges is angled relative to the axis of the base portion at an angle of substantially 30°

.

31. A wall element according to claim 18 wherein a plurality of rows of mixing ports extend between the second pair of edges.

26. A wall element for a wall structure of a gas turbine engine combustor with the engine having a principal axis, the wall element comprising a base portion having an axis which in use, extends generally parallel to the principal axis of the engine, wherein the dimension of said wall element parallel to said axis thereof is greater then substantially 20% of the dimension of the wall element transverse to said axis of the wall element, and the base portion includes a plurality of rows of mixing ports to allow gas to enter the combustor in use, the dimension of the wall element parallel to said axis of said base portion being greater than substantially 40 mm.

27. A wall element for a wall structure of a gas turbine engine combustor with the engine having a principal axis, the wall element comprising a base portion having an axis which in use, extends generally parallel to the principal axis of the engine, wherein the dimension of said wall element parallel to said axis thereof is greater then substantially 20% of the dimension of the wall element transverse to said axis of the wall element, and the base portion includes a plurality of rows of mixing ports to allow gas to enter the combustor in use, the dimension of the wall element parallel to said axis of said base portion being between substantially 40 mm and substantially 80 mm.

28. A wall element for a wall structure of a gas turbine engine combustor with the engine having a principal axis, the wall element comprising a base portion having an axis which in use, extends generally parallel to the principal axis of the engine, wherein the dimension of said wall element parallel to said axis thereof is greater then substantially 20% of the dimension of the wall element transverse to said axis of the wall element, and the base portion includes a plurality of rows of mixing ports to allow gas to enter the combustor in use, the dimension of the wall element parallel to said axis of said base portion being greater than substantially 80 mm.

29. A wall element for a wall structure of a gas turbine engine combustor with the engine having a principal axis, the wall element comprising a base portion having an axis which in use, extends generally parallel to the principal axis of the engine, wherein the dimension of said wall element parallel to said axis thereof is greater then substantially 20% of the dimension of the wall element transverse to said axis of the wall element, and the base portion includes a plurality of rows of mixing ports to allow gas to enter the combustor in use, the dimension of the wall element parallel to said axis of said base portion being substantially 250 mm.

30. A wall element for a wall structure of a gas turbine engine combustor with the engine having a principal axis, the wall element comprising a base portion having an axis which in use, extends generally parallel to the principal axis of the engine, wherein the dimension of said wall element parallel to said axis thereof is greater then substantially 20% of the dimension of the wall element transverse to said axis of the wall element, and the base portion includes a plurality of rows of mixing ports to allow gas to enter the combustor in use, said wall element further including a plurality of barrier members extending at least part way across the base portion, the barrier members serving to control flow of cooling fluid across said base portion in use, said barrier members defining a boundary of regions for flow of the cooling fluid isolated from the remainder of the wall element for producing an increase or decrease in pressure of said cooling fluid in said regions relative to the remainder of said wall element.