Apparatus and methods for sealing components in gas turbine engines

Patent metadata

Field	Value
Publication number	US-2016245108-A1
Application number	US-201615049747-A
Country	US
Kind code	A1
Filing date	Feb 22, 2016
Priority date	Feb 20, 2015
Publication date	Aug 25, 2016
Grant date	—

Abstract

An apparatus adapted for use in a gas turbine engine includes a first circumferential member and a second circumferential member. The first circumferential member includes an end portion that defines a recess and includes a first seal surface. The second circumferential member includes an end portion that includes a second seal surface. The end portion of the second circumferential member is configured to be at least partially disposed in the recess of the first circumferential member to collectively form at least a portion of a circumferential assembly of a gas turbine. The first seal surface of the first circumferential member is forms a first seal with a seal member and the second seal surface of the second circumferential member is forms a second seal with the seal member when the end portion of the second circumferential member is disposed in the recess of the first circumferential member.

First claim

What is claimed is:

1 . An apparatus adapted for use in a gas turbine engine, the apparatus comprising
a first circumferential member, an end portion of the first circumferential member defining a recess and including a first seal surface; and a second circumferential member, an end portion of the second circumferential member configured to be at least partially disposed within the recess of the first circumferential member, the end portion of the second circumferential member including a second seal surface, the first circumferential member and the second circumferential forming at least a portion of a circumferential assembly of a gas turbine when the end portion of the second circumferential member is at least partially disposed within the recess of the first circumferential member, the first seal surface configured to form a first seal with a seal member and the second seal surface configured to form a second seal with the seal member when the end portion of the second circumferential member is at least partially disposed within the recess of the first circumferential member.

2 . The apparatus of claim 1 , wherein a line normal to the first seal surface intersects the second seal surface.

3 . The apparatus of claim 1 , wherein the first seal surface and the second seal surface define an acute angle.

4 . The apparatus of claim 1 , wherein the end portion of the first circumferential member includes a protrusion including the first seal surface; and
the end portion of the second circumferential member defines a recess, the protrusion configured to be disposed within the recess of the second circumferential member when the end portion of the second circumferential member is at least partially disposed within the recess of the first circumferential member.

5 . The apparatus of claim 1 , wherein the circumferential assembly is any one of a blade track assembly, a vane assembly, a support assembly, or an end wall assembly.

6 . The apparatus of claim 1 , wherein the seal member has a circular cross-sectional area.

7 . The apparatus of claim 1 , wherein the first circumferential member is formed from a ceramic matrix composite (CMC) material.

8 . The apparatus of claim 1 , wherein the end portion of the first circumferential member is a first end portion;
the seal member is a first seal member; and the first circumferential member includes a second end portion configured to be at least partially disposed within a recess of a third circumferential member, the second end portion of the first circumferential member including a third seal surface configured to form a seal with a second seal member.

9 . The apparatus of claim 1 , wherein the end portion of the first circumferential member defines the recess having a first portion and a second portion, the first portion of the recess including the first seal surface, the second portion of the recess configured to receive a tab extending from the end portion of the second circumferential member when the end portion of the second circumferential member is at least partially disposed within the recess of the first circumferential member.

10 . An apparatus adapted for use in a gas turbine engine, the apparatus comprising
a first circumferential member, an end portion of the first circumferential member including a first seal surface; and a second circumferential member, an end portion of the second circumferential member including a second seal surface, the end portion of the second circumferential member configured to be disposed adjacent to the end portion of the first circumferential member such that a line normal to the second seal surface intersects the first seal surface, the first seal surface configured to form a first seal with a seal member and the second seal surface configured to form a second seal with the seal member when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member, the first circumferential member, the second circumferential member, and the seal member configured to collectively form at least a portion of a circumferential assembly of a gas turbine when the seal member forms the first seal and the second seal.

11 . The apparatus of claim 10 , wherein the first seal surface and the second seal surface define an acute angle.

12 . The apparatus of claim 10 , wherein the end portion of the first circumferential member defines a recess including the first seal surface; and
the end portion of the second circumferential member configured to be disposed within the recess of the first circumferential member when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member.

13 . The apparatus of claim 10 , wherein the first circumferential member includes an inner surface, the end portion of the first circumferential member defines a recess including the first seal surface, the first seal surface being substantially parallel to the inner surface of the first circumferential member; and
the second circumferential member includes an inner surface, the second seal surface being non-parallel to the inner surface of the second circumferential member, the end portion of the second circumferential member configured to be disposed within the recess of the first circumferential member when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member, the inner surface of the first circumferential member and the inner surface of the second circumferential member having a substantially similar radius of curvature such that when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member, at least the portion of the circumferential assembly has a substantially constant inner diameter.

14 . The apparatus of claim 10 , wherein the seal member is formed from a ceramic matrix composite (CMC) material.

15 . The apparatus of claim 10 , wherein the end portion of the first circumferential member is a first end portion;
the seal member is a first seal member; and the first circumferential member includes a second end portion opposite the first end portion, the second end portion including a third seal surface, the second end portion configured to be disposed adjacent to an end portion of a third circumferential member such that a line normal to the second seal surface intersects a fourth sealing surface, the fourth sealing surface included in the end portion of the third circumferential member, the third seal surface configured to form a seal with a second seal member and the fourth seal surface configured to form a seal with the second seal member when the second end portion of the first circumferential member is disposed adjacent to the end portion of the third circumferential member.

16 . The apparatus of claim 10 , wherein the end portion of the first circumferential member defines a recess and includes a protrusion, at least one of the recess of the first circumferential member or the protrusion of the first circumferential member including the first seal surface;
the end portion of the second circumferential member defines a recess and includes a protrusion, at least one of the recess of the second circumferential member or the protrusion of the second circumferential member including the second seal surface; and the protrusion of the first circumferential member configured to be disposed within the recess of the second circumferential member and

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Sippel Aaron D
• Freeman Ted J

Classifications

• F05D2240/55

  Seals · CPC title

• F16J15/44 Primary

  Free-space packings · CPC title

• F16J15/062

  characterised by the geometry of the seat · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D11/02 Primary

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title