Swirler mount interface for gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-10101031-B2
Application number	US-201414911205-A
Country	US
Kind code	B2
Filing date	Jun 30, 2014
Priority date	Aug 30, 2013
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.

First claim

What is claimed is:

1. A forward assembly for a combustor of a gas turbine engine, the forward assembly comprising:
a bulkhead support shell;
a swirler mounted to said bulkhead support shell through a snap-fit interface; and
a cowl mounted to said bulkhead support shell,
wherein said cowl includes a circumferentially distributed hood port to extend into contact with said swirler to apply an axial load to said swirler, and said snap-fit interface is located along a frustro-conical surface of said swirler.

2. The forward assembly as recited in claim 1 , wherein said swirler includes a male snap component.

3. The forward assembly as recited in claim 2 , wherein said bulkhead support shell includes a female snap component around a swirler central longitudinal axis.

4. The forward assembly as recited in claim 3 , wherein said male snap component extends radially outward with respect to the swirler central longitudinal axis.

5. The forward assembly as recited in claim 1 , wherein said snap-fit interface is located along a swirler outer body.

6. The forward assembly as recited in claim 5 , further comprising a swirler inner body mounted within said swirler outer body along a swirler central longitudinal axis.

7. The forward assembly as recited in claim 6 , further comprising a guide housing mounted to said swirler inner body.

8. The forward assembly as recited in claim 7 , further comprising a capture plate mounted to said guide housing to retain a nozzle guide such that said nozzle guide is movable with respect to said guide housing.

9. The forward assembly as recited in claim 1 , wherein said frustro-conical surface of said swirler is defined along a swirler outer body.

10. The forward assembly as recited in claim 9 , further comprising a guide housing mounted to a swirler inner body mounted at least partially within said swirler outer body, and a capture plate mounted to said guide housing to retain a nozzle guide such that said nozzle guide is movable with respect to said guide housing.

11. A method of assembling a swirler into a bulkhead support shell of a gas turbine engine, the method comprising:
snap fitting at a snap-fit interface the swirler into the bulkhead support shell along a swirler axis; and
mounting a cowl to said bulkhead support shell,
wherein said cowl includes a circumferentially distributed hood port that extends into contact with the swirler to apply an axial load to the swirler, and the snap-fit interface is located along a frustro-conical surface of the swirler.

12. A forward assembly for a combustor of a gas turbine engine, the forward assembly comprising:
a bulkhead support shell;
a swirler mounted to said bulkhead support shell through a snap-fit interface located along a frustro-conical surface of said swirler.

Assignees

• United Technologies Corp

Inventors

• Williams Alexander W
• Max Seth A
• Lyons Christopher B

Classifications

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R3/60

  Support structures; Attaching or mounting means · CPC title