COMBUSTORS WITH HYBRID WALLED LINERS

• US 20140190171A1
• Filed: 01/10/2013
• Published: 07/10/2014
• Est. Priority Date: 01/10/2013
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Critchley, Ian, Guerra, Eduardo, Kujala, Stony
• Application Number:
  US13/738,619
• Publication Number:
  US 20140190171A1
• Time in Patent Office: Days
• US Class Current: 60/755
• CPC Class Codes: F23R 2900/00012 Details of sealing devices
• 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 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: F23R 3/045 using pipes
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A combustor for a turbine engine includes a first liner and a second liner forming a combustion chamber with the first liner. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and has a longitudinal axis that defines axial, radial and circumferential directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall. The combustor further includes a primary air admission hole defined in the first hot wall and a first fixed liner seal between the first hot wall and the first cold wall proximate to the primary air admission hole.

Claims

1. A combustor for a turbine engine, comprising:

a first liner;

a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial, radial and circumferential directions,

the first liner being a first dual walled liner comprising a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends; and

a primary air admission hole defined in the first hot wall; and

a first fixed liner seal between the first hot wall and the first cold wall proximate to the primary air admission hole.

2. The combustor of claim 1, wherein the first fixed liner seal has a first portion proximate to and upstream of the primary air admission hole.

3. The combustor of claim 2, wherein the first fixed liner seal has a second portion proximate to and downstream of the primary air admission hole.

4. The combustor of claim 1, wherein the first fixed liner seal extends in the circumferential direction about the longitudinal axis.

5. The combustor of claim 1, wherein the first fixed liner seal circumscribes the primary air admission hole.

6. The combustor of claim 1, wherein the first fixed liner seal at least partially forms the primary air admission hole.

7. The combustor of claim 6, wherein the primary air admission hole is a first primary air admission hole and wherein the combustor further comprises a second primary air admission hole defined in the first cold wall, the first fixed liner seal circumscribing the second primary air admission hole.

8. The combustor of claim 7, wherein the first fixed liner seal at least partially forms the first primary air admission hole and the second primary air admission hole.

9. The combustor of claim 1, wherein the first liner seal is formed by brazing the first hot wall to the first cold wall.

10. The combustor of claim 1, further comprising a first sliding liner seal configured to seal the first end of the first liner cavity to accommodate relative movement of the first hot wall and the first cold wall.

11. The combustor of claim 10, wherein the first sliding liner seal is configured to accommodate relative movement of the first hot wall and the first cold wall in the axial and radial direction.

12. The combustor of claim 10, further comprising a second sliding liner seal configured to seal the second end of the first liner cavity to accommodate relative to movement of the first hot wall and the first cold wall.

13. The combustor of claim 10, wherein the first hot wall includes radially extending first and second hot wall flanges that define a first hot wall groove, and wherein the first sliding liner seal includes a radially extending liner seal flange positioned within the first hot wall groove,

wherein the liner seal flange is movable within the first hot wall groove relative to the first and second hot wall flanges generally in the radial direction and is generally retained by the first and second hot wall flanges in the axial direction, wherein the first liner seal and the first hot wall define a first axial cavity, and wherein one end of the first cold wall is positioned within the first axial cavity, wherein the cold wall is movable within the first axial cavity relative to the hot wall and first liner seal generally in the axial direction and is generally retained by the hot wall and first liner seal in the radial direction.

14. The combustor of claim 10, wherein the first hot wall includes radially extending first hot wall flange, and wherein the first liner seal comprises first and second portions, the first portion having a first inner flange and a second inner flange that define an inner groove, the first hot wall flange being positioned within the inner groove, wherein the first hot wall flange is movable within the inner groove relative to the first and second outer flanges generally in the radial direction and is generally retained by the first and second outer flanges in the axial direction, wherein the first portion of the first liner seal further includes a first outer flange and a second outer flange that define an outer groove, wherein the first liner seal further includes a second portion with a first leg and a second leg extending perpendicularly to the first leg, and wherein the first leg of the second portion is positioned within the outer groove such that the second portion is movable within the outer groove generally in the radial direction and is generally retained by the first and second outer flanges in the axial direction, wherein first portion further includes an axial flange extending from the first outer flange, the second leg of the second portion and the axial flange of the first portion defining an axial cavity for receiving one end of the cold wall, and

wherein the cold wall is movable within the axial cavity relative to the axial flange of the first portion and the second leg of the second portion generally in the axial direction and is generally retained by the axial flange of the first portion and the second leg of the second portion in the radial direction.

15. A combustor for a turbine engine, comprising:

a first liner;

a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial, radial and circumferential directions,

the first liner being a first dual walled liner comprising a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends; and

a first primary air admission hole defined in the first hot wall; and

a first fixed liner seal between the first hot wall and the first cold wall proximate to the primary air admission hole; and

a first sliding liner seal between the first hot wall and the first cold wall on the first end of the first liner cavity.

16. The combustor of claim 15, further comprising a second primary air admission hole downstream of the first primary air admission hole, the first fixed liner seal extending from upstream of the first primary air admission hole to downstream of the second primary air admission hole.

17. The combustor of claim 15, wherein the first fixed liner seal circumscribes the primary air admission hole.

18. The combustor of claim 15, wherein the first fixed liner seal at least partially forms the primary air admission hole, and wherein the combustor further comprises a second primary air admission hole defined in the first cold wall, the first fixed liner seal circumscribing the second primary air admission hole.

19. The combustor of claim 15, wherein the first sliding liner seal is configured to accommodate movement in the axial and radial directions.

20. The combustor of claim 15, further comprising a dome assembly and a retention ring at a forward end of the combustion chamber, and wherein the first sliding seal is formed between the dome assembly and the retention ring.