Liner retaining feature for a combustor

Patent metadata

Field	Value
Publication number	US-9696037-B2
Application number	US-201414515661-A
Country	US
Kind code	B2
Filing date	Oct 16, 2014
Priority date	Oct 16, 2014
Publication date	Jul 4, 2017
Grant date	Jul 4, 2017

Abstract

The present application provides a combustor for use with a gas turbine engine. The combustor may include a liner and a flow sleeve surrounding the liner with the liner and the flow sleeve defining a flow path therebetween. A liner retaining feature extends into the flow path to retain the liner within the flow sleeve. The liner retaining feature may include a bolt therein.

First claim

We claim:

1. A combustor for use with a gas turbine engine, comprising:
a liner comprising a liner lug;
a flow sleeve surrounding the liner and comprising a flow sleeve boss, the flow sleeve boss comprising a channel extending from an upstream end of the flow sleeve boss, with respect to combustion flow through the combustor, to a downstream face of the flow sleeve boss, with respect to combustion flow through the combustor; and
a bolt securing the liner lug to the flow sleeve boss;
wherein the liner lug and the bolt are positioned within the channel; and
wherein the bolt comprises a longitudinal axis extending in an axial direction of the combustor along a flow path defined between the liner and the flow sleeve.

2. The combustor of claim 1 , further comprising a casing surrounding the flow sleeve in whole or in part.

3. The combustor of claim 1 , wherein the liner and the flow sleeve each comprise one or more apertures defined therethrough.

4. The combustor of claim 1 , wherein the bolt comprises an upstream end and a downstream end, and wherein the bolt secures the liner lug between the downstream end of the bolt and the downstream face of the flow sleeve boss.

5. The combustor of claim 1 , further comprising a lock tab positioned about the bolt to secure the bolt relative to the liner lug, wherein the lock tab comprises a plurality of flanges surrounding a head of the bolt.

6. The combustor of claim 1 , wherein the flow sleeve boss extends radially inward into the flow path toward the liner, and wherein the liner lug extends radially outward into the flow path toward the flow sleeve.

7. A combustor for use with a gas turbine engine, comprising:
a liner;
a flow sleeve surrounding the liner;
the liner and the flow sleeve defining a flow path therebetween; and
a liner retaining feature extending into the flow path to retain the liner within the flow sleeve, the liner retaining feature comprising:
a flow sleeve boss attached to the flow sleeve and comprising a channel defined therein, the channel extending from an upstream end of the flow sleeve boss, with respect to combustion flow through the combustor, to a downstream face of the flow sleeve boss, with respect to combustion flow through the combustor;
a liner lug attached to the liner and positioned within the channel; and
a bolt positioned within the channel to secure the liner lug therein, the bolt comprising a longitudinal axis extending in an axial direction of the combustor.

8. The combustor of claim 7 , further comprising a casing surrounding the flow sleeve in whole or in part.

9. The combustor of claim 7 , further comprising a plurality of liner retaining features extending into the flow path to retain the liner within the flow sleeve.

10. The combustor of claim 7 , wherein the flow path is configured to direct a flow of air from a compressor.

11. The combustor of claim 7 , wherein the liner and the flow sleeve each comprise one or more apertures defined therethrough.

12. The combustor of claim 7 , wherein the flow sleeve boss comprises a downstream wall defining the downstream face and defining a downstream end of the flow sleeve boss.

13. The combustor of claim 7 , wherein the bolt comprises an upstream end and a downstream end, and wherein the bolt secures the liner lug between the downstream end of the bolt and the downstream face of the flow sleeve boss.

14. The combustor of claim 7 , wherein the flow sleeve boss extends from the flow sleeve radially inward into the flow path toward the liner.

15. The combustor of claim 7 , wherein the liner lug comprises an upstream end and a downstream end, wherein the bolt engages the upstream end of the liner lug, and wherein the flow sleeve boss engages the downstream end of the liner lug.

16. The combustor of claim 7 , wherein the liner lug extends from the liner radially outward into the flow path toward the flow sleeve.

17. The combustor of claim 7 , wherein the liner retaining feature further comprises a lock tab positioned about the bolt to secure the bolt relative to the liner lug.

18. The combustor of claim 17 , wherein the lock tab comprises a plurality of flanges surrounding a head of the bolt.

19. The combustor of claim 7 , wherein the combustor is a dry low nitrogen oxide combustor.

20. The combustor of claim 7 , wherein the liner surrounds a combustion zone of the combustor.

Assignees

• Gen Electric

Inventors

• Kidder Kyle Lee
• Davis Iii Charles Lewis
• Bataille Steven

Classifications

• F23R3/44

  Combustion chambers comprising a {single} tubular flame tube within a tubular casing (reverse-flow combustion chambers F23R3/54) · CPC title

• F23R3/54

  Reverse-flow combustion chambers · CPC title

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title