Brush seal assembly and method

Patent metadata

Field	Value
Publication number	US-10844741-B2
Application number	US-201615357158-A
Country	US
Kind code	B2
Filing date	Nov 21, 2016
Priority date	Nov 21, 2016
Publication date	Nov 24, 2020
Grant date	Nov 24, 2020

Abstract

A brush seal assembly is adapted to be operatively mounted between a stator and a rotor of a gas turbine engine. The brush seal assembly comprises a housing and a seal operatively coupled to the housing. The seal comprises at least two annular brushes each having a plurality of bristles extending away from the housing. The at least two annular brushes and the housing defines a cavity therebetween. The housing defines at least one circumferential surface within the cavity. The housing comprises at least one discontinuity defined in the at least one circumferential surface. The at least one discontinuity disrupts a continuity of annularity of the circumferential surface.

First claim

The invention claimed is:

1. A brush seal assembly adapted to be operatively mounted between a stator and a rotor of a component of a gas turbine engine, the brush seal assembly comprising a housing and a seal operatively coupled to the housing, the seal comprising at least two annular brushes spaced-apart by a spacer of the housing, at least one cavity between the at least two annular brushes, the at least one cavity having an annular cavity portion axially extending from one of the at least two annular brushes to a face defined by the spacer, the spacer defining at least one circumferential surface within the annular cavity portion, the at least one circumferential surface having at least one discontinuity extending therefrom and disrupting a continuity of annularity of the at least one circumferential surface, the at least one circumferential surface being axisymmetric but for the at least one discontinuity.

2. The brush seal assembly of claim 1 , wherein the housing comprises at least three annular spacers, the at least two annular brushes being sandwiched between the at least three annular spacers.

3. The brush seal assembly of claim 1 , wherein the at least one discontinuity is a bump defined by the at least one circumferential surface and disposed at a given circumferential position.

4. The brush seal assembly of claim 1 , comprising a plurality of discontinuities disposed along the at least one circumferential surface, wherein a volume of the plurality of discontinuities is up to 20% of a volume of the at least one cavity without the plurality of discontinuities.

5. The brush seal assembly of claim 4 , wherein the housing is configured to be mounted to the stator, an inertial center of the brush seal assembly being offset from an axis of rotation of the rotor.

6. The brush seal assembly of claim 2 , wherein the at least three annular spacers and the at least two annular brushes define at least two cavities therebetween.

7. The brush seal assembly of claim 6 , wherein the at least two cavities are annular cavities each defined between one of the at least two annular brushes and one of the at least three annular spacers.

8. The brush seal assembly of claim 1 , wherein the at least one discontinuity is a hollow portion defined in the housing.

9. A component of a gas turbine engine comprising a stator, a rotor, and a brush seal assembly operatively mounted therebetween, the brush seal assembly comprising a housing and a seal operatively coupled to the housing, the seal comprising at least two annular brushes spaced-apart from one another by a spacer, at least one cavity located between the at least two annular brushes, the at least one cavity having an annular cavity portion axially extending from one of the at least two annular brushes to a face of the spacer, the spacer defining at least one circumferential surface within the annular cavity portion, the at least one cavity extending circumferentially around an axis of rotation of the rotor and being non-axisymmetric, the housing comprising at least one discontinuity defined in the at least one circumferential surface between the at least two annular brushes, the at least one circumferential surface being axisymmetric other than for the at least one discontinuity.

10. The brush seal assembly of claim 9 , wherein the housing comprises at least three annular spacers, the at least two annular brushes being sandwiched between the at least three annular spacers.

11. The brush seal assembly of claim 9 , wherein the at least one discontinuity is a bump defined by the at least one circumferential surface and disposed at a given circumferential position.

12. The brush seal assembly of claim 9 , comprising a plurality of discontinuities disposed along the at least one circumferential surface, wherein a volume of the plurality of discontinuities is up to 20% of a volume of the at least one cavity without the plurality of discontinuities.

13. The brush seal assembly of claim 12 , wherein the housing is configured to be mounted to the stator, an inertial center of the brush seal assembly being offset from the axis of rotation of the rotor.

14. The brush seal assembly of claim 10 , wherein the at least three annular spacers and the at least two annular brushes define at least two cavities therebetween.

15. The brush seal assembly of claim 14 , wherein the at least two cavities are annular cavities each defined between one of the at least two annular brushes and one of the at least three annular spacers.

16. A method for damping flutter of a rotor of a gas turbine engine, comprising:
creating a sealing engagement between the rotor and a stator using a housing and at least two annular brushes located between the rotor and the stator, at least one cavity between the at least two annular brushes, the at least one cavity having an annular cavity portion axially extending from one of the at least two annular brushes to a face defined by the spacer;
permitting a fluid to flow within the at least one cavity, the fluid creating acoustic waves inside the at least one cavity thereby inducing flutter of the rotor when said rotor is in rotation; and
disrupting a tangential acoustic mode of the at least one cavity using at least one discontinuity making the at least one cavity non-axisymmetric, the at least one discontinuity defined in at least one circumferential surface of the spacer and extending within the annular cavity portion thereby attenuating propagation of the acoustic waves inside the at least one cavity.

17. The method of claim 16 , wherein the step of disrupting a tangential acoustic mode further comprises decreasing a volume of the at least one cavity by up to 20% using a plurality of discontinuities defined in the at least one circumferential surface.

18. The method of claim 16 , wherein the at least one discontinuity is a bump defined by the at least one circumferential surface and disposed at a given circumferential position.

Assignees

• Pratt & Whitney Canada

Inventors

• Theratil Ignatius
• Coutu Daniel
• Houle Nicola

Classifications

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F04D29/164

  of an axial flow wheel · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D25/04 Primary

  Antivibration arrangements · CPC title

• F16J15/3288

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