Brush seal

Patent metadata

Field	Value
Publication number	US-9920838-B2
Application number	US-201514790663-A
Country	US
Kind code	B2
Filing date	Jul 2, 2015
Priority date	Jul 4, 2014
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.

First claim

What is claimed is:

1. A brush seal for a gas turbine, comprising:
a support ring, wherein the support ring is comprised of a mounting plate and a support element, wherein a radial inner end of the mounting plate is integral with or integrally molded onto a radial outer end of the support element and wherein the support element has a support plate and a support structure, wherein the support structure is arranged downstream in a direction of flow with respect to the support plate and wherein a clearance is defined between the support structure and the support plate; and
bristles which are arranged upstream in the direction of flow with respect to the support ring and wherein ends of the bristles protrude radially inward beyond the support plate.

2. The brush seal according to claim 1 , wherein the support structure runs parallel to the support plate.

3. The brush seal according to claim 1 , wherein the support structure has ribs disposed in a plane running radially and wherein the ribs are inclined in at least a section by an angle (β) to a radial direction, wherein the angle (β) is between 10° and 40°.

4. The brush seal according to claim 3 , wherein the bristles form an angle (γ) of 40° to 60° to the radial direction.

5. The brush seal according to claim 3 , wherein at least one of the ribs is a spring and/or at least one of the ribs runs in a straight line.

6. The brush seal according to claim 3 , wherein an inner cover band is integrally molded on a radially directed inward end of at least one of the ribs.

7. The brush seal according to claim 1 , wherein the support plate and/or the support structure is disposed with an axial offset relative to the mounting plate.

Assignees

• MTU Aero Engines AG

Inventors

• Klaen Stephan
• Weber Julian
• Stiehler Frank
• Cernay Christoph
• Hess Thomas

Classifications

• F05D2250/294

  grooved · CPC title

• F05D2250/283

  honeycomb · CPC title

• F05D2250/22

  parallelepipedal · CPC title

• F05D2250/132

  hexagonal · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title