Slider seal

Abstract

An assembly for a gas turbine engine includes a component, a seal element, and a seal cap. The component defines a pocket adapted to accept the seal element and the pocket allows for sliding movement of the component relative to the seal element. The seal cap overlying the pocket and the seal element.

1 . An assembly for a gas turbine engine, comprising:
 a seal element;   a component defining a pocket adapted to accept the seal element, wherein the pocket allows for sliding movement of the component relative to the seal element; and   a seal cap overlying the pocket and the seal element.   
     
     
         2 . The assembly of  claim 1 , wherein the component comprises a seal carrier, and the pocket is disposed in the seal carrier, and wherein the seal carrier separates a first cavity of the gas turbine engine from a second cavity of the gas turbine engine. 
     
     
         3 . The assembly of  claim 2 , wherein the second cavity comprises a main gas flow path for the gas turbine engine. 
     
     
         4 . The assembly of  claim 3 , further comprising:
 a casing;   a fairing disposed within the casing and connected to the seal carrier; and   a probe extending through the casing, the seal cap, the seal element, and the seal carrier into the second cavity.   
     
     
         5 . The assembly of  claim 2 , wherein a first surface of the seal element defines a portion of the first cavity, and wherein a second surface of the seal element defines a portion of the second cavity. 
     
     
         6 . The assembly of  claim 5 , wherein the second surface of the seal element contacts an inner surface of the component that defines the pocket. 
     
     
         7 . The assembly of  claim 6 , wherein the inner surface of the component abuts the seal element in a generally radial direction but is free to slide generally circumferentially or axially with respect to a centerline axis of the gas turbine engine. 
     
     
         8 . The assembly of  claim 1 , wherein the component includes a depression that forms a portion of the pocket. 
     
     
         9 . The assembly of  claim 1 , wherein the seal cap is adapted to be joined with the component and in part cover the pocket to capture the seal element within the pocket. 
     
     
         10 . An assembly for a gas turbine engine, comprising:
 a seal carrier including a pocket with an aperture therein;   a seal element disposed within the pocket and overlying the aperture, wherein the pocket allows the component to move relative to the seal element; and   a seal cap connected to the component and overlaying the pocket and seal element.   
     
     
         11 . The assembly of  claim 10 , wherein the seal carrier separates a first cavity of the gas turbine engine from a second cavity. 
     
     
         12 . The assembly of  claim 11 , wherein the seal carrier comprises a fairing and the second cavity comprises a main gas flow path for the gas turbine engine. 
     
     
         13 . The assembly of  claim 11 , wherein a first surface of the seal element defines a portion of the first cavity, and wherein a second surface of the seal element forms a portion of the second cavity. 
     
     
         14 . The assembly of  claim 13 , wherein the second surface of the seal element contacts an inner surface of the seal carrier. 
     
     
         15 . The assembly of  claim 14 , wherein the inner surface of the component abuts the seal element in a generally radial direction but is free to slide generally circumferentially or axially with respect to a centerline axis of the gas turbine engine. 
     
     
         16 . The assembly of  claim 10 , wherein the seal cap is adapted to be joined with the component and in part cover the pocket to capture the seal element within the pocket. 
     
     
         17 . The assembly of  claim 10 , wherein the seal carrier includes a depression that defines a portion of the pocket. 
     
     
         18 . A turbine section for a gas turbine engine, comprising:
 a casing extending along the turbine section;   a fairing disposed within the casing to form a main gas flow path, the fairing having a pocket and an aperture therein;   a probe mounted to the casing and extending through the casing and the fairing;   a seal element disposed within the pocket and overlying the aperture in the fairing, wherein the seal element defines an aperture that is adapted to receive the probe; and   a seal cap connected to the fairing and extending around the probe and overlaying the pocket and seal element.   
     
     
         19 . The turbine section of  claim 18 , wherein a first surface of the seal element defines a portion of the first cavity, and wherein a second surface of the seal element forms a portion of the second cavity. 
     
     
         20 . The turbine section of  claim 19 , wherein the second surface of the seal element contacts a surface of the pocket.