Seal member assembly structure and assembly method, seal member, and gas turbine

Patent metadata

Field	Value
Publication number	US-10961859-B2
Application number	US-201615757745-A
Country	US
Kind code	B2
Filing date	Sep 1, 2016
Priority date	Sep 8, 2015
Publication date	Mar 30, 2021
Grant date	Mar 30, 2021

Abstract

A seal member assembly structure and assembly method, a seal member, and a gas turbine, wherein, in a state where first flange parts provided on a combustor transition piece are fitted into first fitting parts provided in seal members, protruding parts provided on the first flange parts are inserted into recessed parts provided in the first fitting parts.

First claim

The invention claimed is:

1. A gas turbine comprising an assembly structure of a seal member provided along a circumferential direction of the gas turbine between a combustor pipe and a turbine shroud, wherein:
a first flange part provided on the combustor pipe is positioned within a first fitting part provided in the seal member;
a linking pin penetrates the first flange part and the first fitting part to link the seal member to the combustor pipe;
a protruding part is provided on one of the first flange part or the first fitting part;
a recessed part is provided in the other of the first flange part or the first fitting part;
the protruding part is positioned within the recessed part;
the protruding part and the recessed part are configured to prevent the first fitting part from moving with respect to the first flange part along the circumferential direction of the gas turbine;
the first fitting part is provided on an upstream end of the seal member and includes a first fitting wall, a second fitting wall, and a third fitting wall, the first fitting wall being upstream from the second fitting wall and the third fitting wall; and either:
the protruding part protrudes from a radial end face of the first fitting wall; or
the recessed part is recessed into the radial end face of the first fitting wall.

2. The gas turbine according to claim 1 , wherein the protruding part protrudes in a radial direction of the gas turbine, and the recessed part is recessed in the radial direction of the gas turbine.

3. The gas turbine according to claim 2 , wherein:
the recessed part is defined by a notch in a block body protruding upstream from a flat part of the first flange part.

4. The gas turbine according to claim 1 , wherein the protruding part and the recessed part are positioned with a gap between the protruding part and the recessed part along the circumferential direction of the gas turbine.

5. The gas turbine according to claim 1 , wherein a surface of the protruding part and a surface of the recessed part face each other and are curved.

6. The gas turbine according to claim 1 , wherein the first flange part fits into the first fitting part such that neither the first flange part nor the first fitting part is capable of relative movement in an axial direction of the gas turbine, and the linking pin penetrates the first flange part and the first fitting part such that neither the first flange part nor the first fitting part is capable of relative movement in the circumferential direction of the gas turbine.

7. The gas turbine according to claim 1 , wherein the seal member is provided with a second fitting part, and a second flange part provided on the turbine shroud fits into the second fitting part such that neither the second flange part nor the second fitting part is capable of relative movement in a radial direction of the gas turbine.

8. A gas turbine assembly method, wherein the gas turbine comprises:
an assembly structure of a seal member provided along a circumferential direction of the gas turbine between a combustor pipe and a turbine shroud, wherein:
a first flange part provided on the combustor pipe is positioned within a first fitting part provided in the seal member;
a linking pin penetrates the first flange part and the first fitting part to link the seal member to the combustor pipe;
a protruding part is provided on one of the first flange part or the first fitting part;
a recessed part is provided in the other of the first flange part or the first fitting part;
the protruding part is positioned within the recessed part;
the protruding part and the recessed part are configured to prevent the first fitting part from moving with respect to the first flange part along the circumferential direction of the gas turbine;
the first fitting part is provided on an upstream end of the seal member and includes a first fitting wall, a second fitting wall, and a third fitting wall, the first fitting wall being upstream from the second fitting wall and the third fitting wall; and either:
the protruding part protrudes from a radial end face of the first fitting wall; or
the recessed part is recessed into the radial end face of the first fitting wall;

the assembly method comprising:
fitting the first flange part into the first fitting part;
inserting the protruding part into the recessed part; and
securing the first flange part and the first fitting part by the linking pin.

Assignees

• Mitsubishi Hitachi Power Sys
• Mitsubishi Power Ltd

Inventors

• Kishida Hiroaki
• Nagai Norihiko

Classifications

• F16J15/04

  without packing between the surfaces, e.g. with ground surfaces, with cutting edge · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D25/00

  Component parts, details, or accessories, not provided for in, or of interest apart from, other groups · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title