LOW LUMP MASS COMBUSTOR WALL WITH QUENCH APERTURE(S)

• US 20160123594A1
• Filed: 11/04/2015
• Published: 05/05/2016
• Est. Priority Date: 11/04/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Cunha, Frank J., Kostka, Stanislav
• Granted Patent: US 10,451,281 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube

Abstract

An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a first layer vertically connected with a second layer. A first portion of the first layer overlaps and is vertically spaced from the second layer by a cavity. A second portion of the first layer is substantially vertically inline with an adjacent portion of the second layer. The second portion of the first layer at least partially forms a quench aperture vertically through the combustor wall.

Claims

1. An assembly for a turbine engine, comprising:

a combustor wall including a first layer vertically connected with a second layer;

a first portion of the first layer overlapping and vertically spaced from the second layer by a cavity; and

a second portion of the first layer substantially vertically inline with an adjacent portion of the second layer, and at least partially forming a quench aperture vertically through the combustor wall.

2. The assembly of claim 1, wherein the second portion substantially completely defines the quench aperture vertically through the combustor wall.

3. The assembly of claim 1, wherein a thickness of the first portion is substantially equal to a thickness of the second portion.

4. The assembly of claim 1, wherein the second portion extends at least partially vertically into an aperture in the second layer.

5. The assembly of claim 1, wherein the second portion forms a vertical indentation in the first layer.

6. The assembly of claim 1, wherein at least the second portion of the first layer and the second layer are configured to form a side periphery of a combustion chamber.

7. The assembly of claim 6, wherein at least a portion of the first layer at the side periphery is coated with a thermal barrier coating and/or at least a portion of the second layer at the side periphery is coated with a thermal barrier coating.

8. The assembly of claim 1, wherein the second portion has a curved geometry.

9. The assembly of claim 1, wherein the second portion includes one or more cooling holes.

10. The assembly of claim 1, wherein the second portion includes one or more stiffening features.

11. The assembly of claim 1, wherein the second portion includes one or more protrusions.

12. The assembly of claim 1, wherein the first layer comprises a shell and the second layer comprises a heat shield.

13. The assembly of claim 1, wherein the combustor wall extends circumferentially about and axially along a centerline, and the first portion is located axially forward of the second portion.

14. The assembly of claim 1, wherein the combustor wall extends circumferentially about and axially along a centerline, and the first portion is located axially aft of the second portion.

15. The assembly of claim 1, wherein a third portion of the first layer overlaps and is vertically spaced from the second layer by the cavity or another cavity, and the second portion is between the first and the third portions.

16. A combustor wall for a turbine engine, comprising:

a first layer vertically attached with a second layer;

wherein a first portion of the first layer overlaps and is vertically offset from the second layer; and

wherein a second portion of the first layer extends vertically at least partially into an aperture in the second layer, and at least partially forms a quench aperture vertically through the combustor wall.

17. The combustor wall of claim 16, wherein the first layer substantially completely defines the quench aperture vertically through the combustor wall.

18. The combustor wall of claim 16, wherein the second layer has a substantially uniform thickness.

19. A combustor wall for a turbine engine, comprising:

a first layer vertically connected with a second layer;

wherein a cooling cavity extends vertically between the first layer and the second layer; and

wherein the first layer substantially completely defines a quench aperture vertically through the combustor wall, and the first layer has a substantially uniform thickness.

20. The combustor wall of claim 19, wherein the first layer comprises a shell and the second layer comprises a heat shield.