Tapered gas turbine segment seals

Patent metadata

Field	Value
Publication number	US-9863323-B2
Application number	US-201514623570-A
Country	US
Kind code	B2
Filing date	Feb 17, 2015
Priority date	Feb 17, 2015
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

Abstract

The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a gas turbine segment seal assembly may include a first tapered segment seal with a first tapered portion having a first tapered surface and a first taper angle. The gas turbine segment seal assembly may include a second tapered segment seal with a second tapered portion having a second tapered surface and a second taper angle. The gas turbine segment seal assembly may include a seal pin positioned in between the first tapered segment seal and the second segment seal and adjacent to the first tapered surface and the second tapered surface.

First claim

We claim:

1. A gas turbine segment seal assembly, comprising:
a first tapered segment seal comprising a first tapered portion with a first tapered surface having a first taper angle, the first tapered segment seal being received in a first segment seal slot;
a second tapered segment seal comprising a second tapered portion with a second tapered surface having a second taper angle, the second tapered segment seal being received in a second segment seal slot; and
a substantially cylindrical seal pin positioned in between the first tapered segment seal and the second tapered segment seal, such that the seal pin is in contact with the first tapered surface and the second tapered surface and occludes a leakage path between the first tapered segment seal and the second tapered segment seal,
wherein the first tapered seal segment extends primarily in a first direction, the second tapered seal segment extends primarily in a second direction, and the first direction is angled with respect to the second direction.

2. The gas turbine segment seal assembly of claim 1 , wherein the first taper angle is different than the second taper angle.

3. The gas turbine segment seal assembly of claim 1 , wherein the first tapered segment seal is positioned substantially perpendicular to the second tapered segment seal.

4. The gas turbine segment seal assembly of claim 1 , wherein the seal pin is retained by an axle positioned in opposite ends of the seal pin that slide in a slot groove.

5. The gas turbine segment seal assembly of claim 1 , wherein the seal pin comprises a ceramic metal composite.

6. The gas turbine segment seal assembly of claim 1 , wherein the first tapered segment seal loads under a pressure differential independent of the second tapered segment seal.

7. The gas turbine segment seal assembly of claim 1 , wherein the first tapered segment seal loads under a pressure differential independent of the seal pin.

8. The gas turbine segment seal assembly of claim 1 , wherein an opposite seal end of the first tapered segment seal is loaded by the seal pin.

9. The gas turbine segment seal assembly of claim 1 , wherein the second tapered segment seal loads under a pressure differential independent of the seal pin.

10. The gas turbine segment seal assembly of claim 1 , wherein each of the first tapered segment seal, the second tapered segment seal, and the seal pin load under a pressure differential independent of each other.

11. A method of reducing leakage flow in a gas turbine component, the method comprising:
positioning a first tapered segment seal comprising a first tapered portion with a first tapered surface having a first taper angle in a first segment slot;
positioning a second tapered segment seal with a second tapered surface having a second taper angle in a second segment slot;
positioning a substantially cylindrical seal pin in between the first tapered segment seal and the second segment seal such that the seal pin is in contact with the first tapered surface and the second tapered surface; and
loading the seal pin with a pressure differential independent of the first tapered segment seal and the second tapered segment seal such that a leakage path between the first tapered segment seal and the second tapered segment seal is occluded,
wherein the first tapered seal segment is substantially flat and extends primarily in a first direction, the second tapered seal segment is substantially flat and extends primarily in a second direction, and the first direction is angled with respect to the second direction.

Assignees

• Gen Electric

Inventors

• Kirtley Kevin Richard
• Morgan Victor John

Classifications

• F05D2240/55

  Seals · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title