Static seal arrangement and turbomachine

Patent metadata

Field	Value
Publication number	US-2020200030-A1
Application number	US-201916704881-A
Country	US
Kind code	A1
Filing date	Dec 5, 2019
Priority date	Dec 21, 2018
Publication date	Jun 25, 2020
Grant date	—

Abstract

Disclosed is a static seal arrangement for sealing a gap between a first static component and a second static component of a turbomachine such as an aircraft engine or a static gas turbine, having a brush seal held distant from a hot gas, this brush seal being arranged standing or vertical with its clamping section that can be surrounded by cooling air in a radially outer clamping space relative to the gap, and forming a radial sealing site with the first component and an axial sealing site with the second component; also disclosed is a turbomachine.

First claim

What is claimed is:

1 . A static seal arrangement for sealing a gap between a first static component and a second static component of a turbomachine, comprising:
a brush seal that is arranged standing or vertical with its head in a radially outer clamping space relative to the gap and that forms a radial sealing site with the first component and an axial sealing site with the second component.

2 . The seal arrangement according to claim 1 , wherein the first static component and the second static component have two axially overlapping cylinder sections and the brush seal forms the radial sealing site with the cylinder section of the first static component and forms the axial sealing site with the cylinder section of the second static component.

3 . The seal arrangement according to claim 1 , wherein the clamping space of the brush seal is open to a sealing air space.

4 . The seal arrangement according to claim 1 , wherein the clamping space is arranged on the end side of a radial projection of a support housing, which accommodates the first static component and the second static component.

5 . The seal arrangement according to claim 2 , wherein an annular gap is formed between the cylinder section of the second static component and the radial projection.

6 . The seal arrangement according to claim 4 , wherein the support housing is divided axially into a first housing module for the uptake of the first static component and into a second housing module for the uptake of the second static component ( 8 ).

7 . The seal arrangement according to claim 4 , wherein the radial projection is assigned to the second housing module and the second static component is joined to the radial projection.

8 . The seal arrangement according to claim 1 , wherein, in the peripheral direction, the second static component is divided into segments, which are distanced from each other in the peripheral direction by way of a segment gap in each case, and bristles of the brush seal are aligned in a radial direction, so that each bristle is supported axially at one of the segments.

9 . The seal arrangement according to claim 8 , wherein the segment gaps are positioned in the radial direction between adjacent segments.

10 . The seal arrangement according to claim 1 , wherein the brush seal stands with a maximum absolute inclination of 30° to the radial direction.

11 . The seal arrangement according to claim 1 , wherein the seal arrangement is configured and arranged in a turbomachine.

Assignees

• MTU Aero Engines AG

Inventors

• Feldmann Manfred
• Schmalfuss Simon

Classifications

• F16J15/0812

  with a braided or knitted body · CPC title

• F16J15/3216

  supported in a direction parallel to the surfaces · CPC title

• F16J15/3288

  Filamentary structures, e.g. brush seals · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F05D2220/32

  in gas turbines · CPC title