Combustor seal mistake-proofing for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10190504-B2
Application number	US-201314432339-A
Country	US
Kind code	B2
Filing date	Oct 1, 2013
Priority date	Oct 1, 2012
Publication date	Jan 29, 2019
Grant date	Jan 29, 2019

Abstract

A combustor seal for use between a downstream end of a combustor and a turbine vane includes a seal body and a plurality of seal alignment features. The plurality of seal alignment features projects from the seal body. The seal alignment features are arranged such that there is only one alignment of the combustor seal with the turbine vane.

First claim

The invention claimed is:

1. A combustor seal for use between a downstream end of a combustor and a turbine vane assembly having a plurality of circumferentially spaced vane alignment features, the combustor seal comprising:
a seal body; and
a plurality of circumferentially spaced seal alignment features projecting from the seal body, each seal alignment feature being positioned and configured to mate with a corresponding vane alignment feature, wherein one of the seal alignment features is a different size from the rest of the seal alignment features such that there is only one alignment position of the combustor seal with respect to the turbine vane assembly in which the differently sized seal alignment feature engages and mates with a correspondingly sized vane alignment feature that is a second different size from the rest of the vane alignment features, wherein the plurality of seal alignment features includes:
a first fork including a first prong and a second prong, wherein the first prong and the second prong are separated in a circumferential direction by a first width, wherein the first fork is shaped to receive a first vane alignment feature; and
a second fork including a third prong and a fourth prong, wherein the third prong and the fourth prong are separated in the circumferential direction by a second width, and wherein the second fork is circumferentially spaced from the first fork, wherein the second fork is shaped to receive a second vane alignment feature;
wherein the first width is greater than the second width.

2. The seal of claim 1 , wherein the plurality of seal alignment features project radially outward from the seal body.

3. The seal of claim 1 , wherein the plurality of seal alignment features are spaced along the seal body at equal intervals in the circumferential direction.

4. The seal of claim 1 , wherein each of the plurality of seal alignment features comprises a fork, wherein the plurality of seal alignment features includes at least two seal alignment features differentiated by size.

5. A method of installing the combustor seal of claim 1 into a gas turbine engine, the method comprising:
inserting the combustor seal into the gas turbine engine axially adjacent a vane support;
rotating the combustor seal about an engine center axis to align the combustor seal relative to the vane support; and
engaging the combustor seal with the vane support.

6. The method of claim 5 , wherein the plurality of seal alignment features project radially outward from a centerline of the gas turbine engine and are operatively associated with the vane support.

7. The method of claim 6 , further including engaging the plurality of seal alignment features with the plurality of vane alignment features such that all of the plurality of seal alignment features engage all of the plurality of vane alignment features.

8. The method of claim 7 , wherein the first fork cannot engage the second vane alignment feature.

9. A gas turbine engine comprising:
an outer casing;
a combustor within the outer casing;
a plurality of vane alignment features within and connected to the outer casing, wherein the plurality of vane alignment features includes: a first lug including a first width in a circumferential direction; and a second lug including a third width in the circumferential direction;
a turbine vane downstream of the combustor, the turbine vane including: an outer platform surface facing in an upstream axial direction; and
an alignment feature for engaging with the plurality of vane alignment features to align the turbine vane to the outer casing; and
a combustor seal in contact with the platform surface and a downstream end of the combustor configured to seal a gap defined between the combustor and the outer platform surface of the turbine vane, the combustor seal including: a seal body, and
a plurality of seal alignment features projecting from the seal body configured to engage the plurality of vane alignment features for aligning the combustor seal relative to the turbine vane, wherein one of the seal alignment features is a different size from the rest of the seal alignment features such that there is only one alignment position of the combustor seal with respect to a turbine vane assembly in which the differently sized seal alignment feature engages and mates with a correspondingly sized vane alignment feature that is a second different size from the rest of the vane alignment features, wherein the plurality of seal alignment features includes:
a first fork including a first prong and a second prong, wherein the first prong and the second prong are separated in the circumferential direction by a second width, the second width greater than the first width such that the first fork can engage the first lug; and
a second fork including a third prong and a fourth prong, wherein the third prong and the fourth prong are separated in the circumferential direction by a fourth width, the fourth width greater than the third width such that the second fork can engage the second lug, and wherein the second fork is circumferentially spaced from the first fork;
wherein the first width is greater than the fourth width such that the second fork cannot engage the first lug.

10. The engine of claim 9 , wherein the vane alignment features are integral with the outer casing.

11. The engine of claim 9 , wherein the plurality vane alignment features project radially inward from the outer casing, and the plurality of seal alignment features project radially outward from the seal body.

12. The engine of claim 9 , wherein the seal alignment features are spaced along the seal body at equal intervals in the circumferential direction.

13. The engine of claim 9 , wherein the plurality of seal alignment features includes at least two seal alignment features differentiated by size; and the plurality of vane alignment features includes at least two vane alignment features differentiated by size.

Assignees

• United Technologies Corp

Inventors

• Low Kevin Joseph
• Wong Joey

Classifications

• F01D11/003

  by packing rings; Mechanical seals · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• Y10T29/4932

  Turbomachine making · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title

• F01D11/00

  Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) · CPC title