Solid seal with cooling pathways

Abstract

The present application provides a seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine. The seal may include a first surface facing the high pressure cooling air flow, a second surface with a second surface air plenum facing the hot gas path, and a number of cooling pathways extending from the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough.

We claim: 
     
         1 . A seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine, comprising:
 a first surface facing the high pressure cooling air flow;   a second surface facing the hot gas path;   the second surface comprising a second surface air plenum; and   a plurality of cooling pathways extending from the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough.   
     
     
         2 . The seal of  claim 1 , wherein the seal comprises a solid seal. 
     
     
         3 . The seal of  claim 1 , wherein the seal comprises a substantial “I” beam-like shape. 
     
     
         4 . The seal of  claim 1 , wherein the second surface comprises a second surface peripheral lip. 
     
     
         5 . The seal of  claim 1 , wherein the first surface comprises a first surface air plenum. 
     
     
         6 . The seal of  claim 1 , wherein the first surface comprises a first surface peripheral lip. 
     
     
         7 . The seal of  claim 1 , wherein the first surface comprises a top surface and wherein the second surface comprises a bottom surface. 
     
     
         8 . The seal of  claim 1 , further comprising a first blocked end and a second blocked end. 
     
     
         9 . The seal of  claim 1 , wherein the plurality of cooling holes comprises a straight configuration. 
     
     
         10 . The seal of  claim 1 , wherein the plurality of cooling holes comprises an angled configuration. 
     
     
         11 . The seal of  claim 1 , wherein the plurality of cooling holes comprises a plurality of impingement holes. 
     
     
         12 . The seal of  claim 1 , wherein the components comprise a first stator and a second stator 
     
     
         13 . The seal of  claim 1 , wherein the components define a seal slot and wherein the seal slot is cooled via the high pressure cooling air flow from the plurality of cooling pathways. 
     
     
         14 . A method of cooling a seal positioned between components in a gas turbine engine, comprising:
 flowing high pressure cooling air about a first surface of the seal;   drawing the high pressure cooling air through a plurality of cooling pathways in the seal; and   drawing the high pressure cooling air through an air plenum about a second surface of the seal towards a hot gas path.   
     
     
         15 . The method of  claim 14 , further comprising the step of cooling the components with the high pressure cooling air leaving the air plenum. 
     
     
         16 . A solid seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine, comprising:
 a first surface facing the high pressure cooling air flow;   the first surface comprising a first surface air plenum;   a second surface facing the hot gas path;   the second surface comprising a second surface air plenum; and   a plurality of cooling pathways extending from the first surface air plenum of the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough.   
     
     
         17 . The solid seal of  claim 16 , wherein the seal comprises a substantial “I” beam-like shape. 
     
     
         18 . The solid seal of  claim 16 , wherein the first surface comprises a first surface peripheral lip and wherein the second surface comprises a second surface peripheral lip. 
     
     
         19 . The solid seal of  claim 16 , further comprising a first blocked end and a second blocked end. 
     
     
         20 . The solid seal of  claim 16 , wherein the plurality of cooling holes comprises a plurality of impingement holes with a straight configuration and/or an angled configuration.