Dual anti surge and anti rotation feature on first vane support

Patent metadata

Field	Value
Publication number	US-10337354-B2
Application number	US-201414915755-A
Country	US
Kind code	B2
Filing date	Sep 3, 2014
Priority date	Sep 10, 2013
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

A gas turbine engine includes a vane and a combustor housing that are supported relative to an engine static structure. A retaining assembly clamps the combustor housing and the vane to one another in an axial direction. A circumferential load transfer assembly circumferentially affixes the vane relative to the engine static structure. The retaining assembly is secured to the circumferential load transfer assembly.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a vane and a combustor housing supported relative to an engine static structure;
a retaining assembly clamping the combustor housing and the vane to one another in an axial direction; and
a circumferential load transfer assembly circumferentially affixing the vane relative to the engine static structure, the retaining assembly secured to the circumferential load transfer assembly, wherein the engine static structure includes a vane support, the vane support including one of a tab and a fork, and the vane including the other of the tab and the fork, the tab received in the fork, and the tab and the fork providing the circumferential load transfer assembly, wherein the retainer assembly includes a retainer secured to the tab, and the combustor housing arranged axially between the retainer and the vane.

2. The gas turbine engine according to claim 1 , comprising a seal ring engaged between the combustor housing and the vane.

3. The gas turbine engine according to claim 2 , wherein the retainer includes a finger, the combustor housing includes an annular protrusion extending radially outward from the combustor housing, the finger engaging the annular protrusion.

4. The gas turbine engine according to claim 3 , wherein the combustor housing includes an edge engaging the seal ring.

5. The gas turbine engine according to claim 1 , wherein the retainer and tab include holes, and a fastener extends through the holes to secure the retainer to the vane support.

6. The gas turbine engine according to claim 5 , comprising a circumferential array of a number of vanes, each vane including a fork, and a number of tabs with holes, the number of tabs being less than the number of vanes.

7. The gas turbine engine according to claim 1 , wherein the retaining assembly is provided by discrete retainers circumferentially spaced from one another.

8. The gas turbine engine according to claim 1 , wherein the retaining assembly is provided by an annular ring secured to multiple tabs.

9. The gas turbine engine according to claim 8 , wherein the annular ring includes lightening holes.

10. The gas turbine engine according to claim 1 , comprising discrete retainers circumferentially spaced from one another.

11. The gas turbine engine according to claim 1 , wherein the retainer is provided by an annular ring secured to multiple tabs.

12. A gas turbine engine comprising:
an engine static structure including a vane support having a tab;
a vane including a fork having a notch receiving the tab to circumferentially affix the vane to the engine static structure; and
a retainer secured to the tab and mounting a combustor housing to the vane in an axial direction, wherein the retainer includes a finger, the combustor housing includes an annular protrusion extending radially outward from the combustor housing, the finger engaging the annular protrusion.

13. The gas turbine engine according to claim 12 , comprising a seal ring engaged between the combustor housing and the vane, wherein the combustor housing includes an edge engaging the seal ring.

14. A gas turbine engine comprising:
an engine static structure including a vane support having a tab;
a vane including a fork having a notch receiving the tab to circumferentially affix the vane to the engine static structure; and
a retainer secured to the tab and mounting a combustor housing to the vane in an axial direction, wherein the retainer and tab include holes, and a fastener extends through the holes to secure the retainer to the vane support.

15. The gas turbine engine according to claim 14 , comprising a circumferential array of a number of vanes, each vane including a fork, and a number of tabs with holes, the number of tabs being less than the number of vanes.

Assignees

• United Technologies Corp

Inventors

• Drake Christopher

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F01D11/003

  by packing rings; Mechanical seals · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title