Seals for a circumferential stop ring in a turbine exhaust case

Patent metadata

Field	Value
Publication number	US-9771818-B2
Application number	US-201213730899-A
Country	US
Kind code	B2
Filing date	Dec 29, 2012
Priority date	Dec 29, 2012
Publication date	Sep 26, 2017
Grant date	Sep 26, 2017

Abstract

A turbine seal system comprises an annular structural frame, a circumferential ring, a fairing and a seal. The circumferential ring is joined to the annular structural frame. The fairing is disposed within the annular structural frame and is engaged with the circumferential ring to limit circumferential rotation of the fairing with respect to the annular structural frame. The seal extends between the fairing and the circumferential ring. In one embodiment, the structural component comprises a ring-strut-ring turbine exhaust case.

First claim

The invention claimed is:

1. A turbine seal system comprising:
an annular structural frame;
a circumferential ring joined to the annular structural frame, the circumferential ring comprising:
an annular ring body engaged with the annular structural frame;
a circumferential stop comprising slots projecting radially inward from the annular ring body; and
a seal land projecting axially from the annular ring body;

a fairing disposed within the annular structural frame and engaged with the circumferential stop to limit circumferential rotation of the fairing with respect to the annular structural frame, wherein the fairing includes lugs extending axially so as to be interposed with the slots; and
a seal extending between the fairing and the circumferential ring to engage the seal land.

2. The turbine seal system of claim 1 and further comprising:
a backing plate extending radially from the annular ring body; and
a plurality of bolt holes extending through the backing plate.

3. The turbine seal system of claim 1 wherein the seal land projects axially aftward from an inner diameter of the annular ring body.

4. The turbine seal system of claim 1 wherein the seal land projects axially aftward from an outer diameter of the annular ring body.

5. The turbine seal system of claim 1 wherein the seal comprises:
a first end coupled to the fairing; and
a second end biased against the seal land.

6. The turbine seal system of claim 5 and further comprising:
a second seal comprising:
a first end coupled to the annular ring body; and
a second end extending aftward so as to be configured to engage a structural component joined to the annular structural frame.

7. The turbine seal system of claim 1 wherein the seal comprises:
a first end coupled to the fairing; and
a second end secured between the seal land and the annular structural frame.

8. The turbine seal system of claim 7 and further comprising:
a coupling flange extending from the fairing; and
an attachment ring joined to the coupling flange;
wherein the first end of the seal is secured between the coupling flange and the attachment ring.

9. The turbine seal system of claim 1 and further comprising means for inhibiting circumferential rotation of the fairing within the frame.

10. A circumferential stop ring for a gas turbine engine structural member and fairing, the circumferential stop ring comprising:
an annular ring body for joining to the structural member;
a plurality of circumferential stop lugs projecting radially inward from the annular ring body for engaging the fairing; and
a seal land projecting axially aftward from the annular ring body to provide a seal surface; and
a plurality of bolt holes extending through the annular ring body, wherein the seal land is positioned radially outward of the plurality of bolt holes.

11. A gas turbine engine structural system comprising:
a frame comprising:
an outer ring;
an inner ring; and
a plurality of struts joining the outer ring and the inner ring;

a fairing coupled to the plurality of struts between the outer ring and the inner ring;
a circumferential stop ring joined to the outer ring at a bolted connection and engaged with the fairing, the circumferential stop ring including a seal land that projects axially aftward from the circumferential stop ring radially outward of the bolted connection; and
a seal extending between the fairing and the seal land.

12. The turbine seal system of claim 11 wherein the seal comprises:
a first end coupled to the fairing; and
a second end secured between the seal land and the outer ring.

13. A turbine seal system comprising:
an annular structural frame;
a circumferential ring joined to the annular structural frame, the circumferential ring comprising:
an annular ring body engaged with the annular structural frame;
a circumferential stop projecting radially from the annular ring body; and
a seal land projecting axially from the annular ring body;

a fairing disposed within the annular structural frame and engaged with the circumferential stop to limit circumferential rotation of the fairing with respect to the annular structural frame; and
a first seal extending between the fairing and the circumferential ring to engage the seal land, the first seal comprising:
a first end coupled to the fairing; and
a second end biased against the seal land; and

a second seal comprising:
a first end coupled to the annular ring body; and
a second end extending aftward so as to be configured to engage a structural component joined to the annular structural frame.

14. The turbine seal system of claim 13 , wherein the circumferential stop ring is joined to the outer ring at a bolted connection.

15. The gas turbine engine structural system of claim 14 wherein the seal land projects axially aftward from the circumferential stop ring radially inward of the bolted connection.

Assignees

• United Technologies Corp

Inventors

• Budnick Matthew
• Chuong Conway
• Scott Jonathan A

Classifications

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D25/162

  Bearing supports · CPC title