# US 5,704,760 A · Method and apparatus for improving the airsealing effectiveness in a turbine engine

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- Number: US 5,704,760 A
- Document ID: US5704760A
- Status: Granted
- Kind: A
- Application number: 08/770,312
- Filed: 1996-12-20
- Granted: 1998-01-06
- Earliest claimed: 1996-03-26
- Assignees: United Technologies Corporation
- Inventors: Joseph P. Bouchard; Merrell W. Long
- Web page: https://patentgrep.com/patent/US5704760A

## CPC

- F01D 11/02: by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08)
- F01D 11/001: {for sealing space between stator blade and rotor}
- F01D 11/12: using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F16J 15/3288: Filamentary structures, e.g. brush seals
- F05D 2230/60: Assembly methods
- F05D 2230/70: Disassembly methods
- F05D 2230/80: Repairing, retrofitting or upgrading methods
- F05D 2240/56: Brush seals
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F16J: PISTONS {(specially adapted for dampers F16F9/32)}; CYLINDERS; SEALINGS
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A gas turbine engine having coannular components 22, 30 includes means for receiving and retaining a replaceable brush seal 60 so that the seal bristles impede the leakage of air through an intercomponent gap 41. In the preferred embodiment one of the components is a hollow, cylindrical barrel 30 comprising upper and lower barrel segments and the receiving and retaining means includes a retainer 52. The retainer cooperates with the barrel to define a groove 56 within which the brush seal is trapped radially and axially. The brush seal slides circumferentially within the groove to facilitate seal installation and removal.

## Claims

### Claim 1

A gas turbine engine component, characterized by:
a hollow substantially cylindrical barrel comprising upper and lower barrel segments separably secured together and having means for radially retaining and axially trapping a brush seal;
a brush seal comprising at least two brush seal segments, the brush seal segments being radially retained and axially trapped by the retaining and trapping means;
wherein the brush seal segments are slidably installable and removable upon separation of the upper barrel segment from the lower barrel segment.

### Claim 2 (depends on 1)

The gas turbine engine component of claim 1, characterized in that each barrel segment has a seal seat and a face and said retaining and trapping means comprises a retainer attached to the barrel segments and cooperating with the seal seat and the face to define a circumferentially extending groove, the groove being oversized with respect to the brush seal so that the brush seal segments are slidably installable in and removeable from the groove upon separation of the upper barrel segment from the lower barrel segment.

### Claim 3 (depends on 2)

The gas turbine component of claim 2 characterized in that the brush seal is a multilayered brush seal.