Dual walled seal assembly

Patent metadata

Field	Value
Publication number	US-9850773-B2
Application number	US-201514724442-A
Country	US
Kind code	B2
Filing date	May 28, 2015
Priority date	May 30, 2014
Publication date	Dec 26, 2017
Grant date	Dec 26, 2017

Abstract

A seal assembly that may be for turbine engine includes a first wall defining in-part a first flowpath and a second wall defining in-part a second flowpath having a pressure that is greater than the first flowpath. The second wall has a plurality of metering apertures in fluid communication between the second flowpath and a cavity defined by and between the first and second walls. The walls may be convoluted and generally, resiliently compressed between two substantially opposing surfaces for providing a seal between the two flowpaths.

First claim

What is claimed:

1. A turbine engine seal assembly for a turbine section of an engine having a central longitudinal axis, comprising:
a shroud ring concentric to the axis;
a blade outer air seal ring concentric to the axis and spaced axially aft of the shroud ring with respect to the axis;
a circumferentially extending outer wall including a plurality of metering apertures spaced circumferentially from one-another, and the outer wall being in resilient sealing relationship between the shroud ring and the blade outer air seal ring;
a circumferentially extending inner wall spaced at least in part radially inward from the outer wall and resiliently compressed between the shroud ring and the blade outer air seal ring;
wherein a circumferentially extending cavity is defined between the outer and inner walls that is in fluid communication with the plurality of apertures,
wherein the outer and inner walls are generally W-shaped in cross section and each have a mid-bend located axially between upstream and downstream bend portions of each outer and inner wall, and
wherein a mid portion of the inner wall is in contact with a mid portion of the outer wall, and the cavity is an upstream cavity defined between the upstream bend portions, and a downstream cavity is defined between the downstream bend portions, and the plurality of apertures are in the upstream and downstream bend portions of the outer wall.

2. The turbine engine seal assembly set forth in claim 1 , wherein the outer wall is located generally between a secondary cooling flowpath and the cavity, and the inner wall is located between the cavity and an engine core flowpath.

3. The turbine engine seal assembly set forth in claim 1 , wherein the circumferentially extending inner wall has no apertures.

Assignees

• United Technologies Corp

Inventors

• Zelesky Mark F
• Davis Timothy M

Classifications

• F05D2240/55

  Seals · CPC title

• F16J15/0887

  the sealing effect being obtained by elastic deformation of the packing · CPC title

• F01D11/003

  by packing rings; Mechanical seals · CPC title

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title