Gas turbine engine component platform cooling

Abstract

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least one of the leading edge portion and the trailing edge portion of the outer surface of the platform.

What is claimed is: 
     
         1 . A component for a gas turbine engine, comprising:
 a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion; and   at least one augmentation feature disposed on at least one of said leading edge portion and said trailing edge portion of said outer surface of said platform.   
     
     
         2 . The component as recited in  claim 1 , wherein said platform is an inner diameter platform. 
     
     
         3 . The component as recited in  claim 1 , wherein the component is a turbine vane. 
     
     
         4 . The component as recited in  claim 1 , wherein said outer surface is a non-gas path side of said platform and said inner surface is a gas path side of said platform. 
     
     
         5 . The component as recited in  claim 1 , comprising an airfoil that extends from said inner surface of said platform. 
     
     
         6 . The component as recited in  claim 1 , wherein said at least one augmentation feature includes a plurality of trip strips. 
     
     
         7 . The component as recited in  claim 6 , wherein said plurality of trip strips are disposed at said trailing edge portion of said platform. 
     
     
         8 . The component as recited in  claim 6 , wherein each of said plurality of trip strips are angled relative to opposing mate faces of said platform. 
     
     
         9 . The component as recited in  claim 6 , wherein each of said plurality of trip strips include a first portion and a second portion that is transverse to the first portion. 
     
     
         10 . The component as recited in  claim 9 , wherein said first portions are angled at a first angle relative to a mate face of said platform and said second portions are angled at a second angle different from said first angle relative to said mate face. 
     
     
         11 . The component as recited in  claim 1 , wherein said at least one augmentation feature is disposed at said leading edge portion of said platform. 
     
     
         12 . The component as recited in  claim 1 , wherein said at least one augmentation feature is disposed on a portion of said outer surface of said platform that axially overlaps a neighboring component of the gas turbine engine. 
     
     
         13 . A gas turbine engine, comprising:
 a compressor section;   a combustor section in fluid communication with said compressor section;   a turbine section in fluid communication with said combustor section; and   wherein at least one of said compressor section and said turbine section includes:
 a first component having a platform that includes an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion; 
 a second component mounted adjacent to said first component and including a platform; 
 wherein a portion of said platform of said first component axially overlaps a portion of said platform of said second component, and said portion of said first platform includes at least one augmentation feature disposed on said outer surface of said platform. 
   
     
     
         14 . The gas turbine engine as recited in  claim 13 , wherein said first component is a vane and said second component is a blade. 
     
     
         15 . The gas turbine engine as recited in  claim 13 , wherein said at least one augmentation feature includes a plurality of trip strips. 
     
     
         16 . The gas turbine engine as recited in  claim 13 , wherein said at least one augmentation feature is disposed on at least one of said leading edge portion and said trailing edge portion of said platform of said first component. 
     
     
         17 . The gas turbine engine as recited in  claim 13 , wherein said at least one augmentation feature is angled relative to a mate face of said platform. 
     
     
         18 . A method of cooling a component of a gas turbine engine, comprising the steps of:
 cooling a platform of the component with a leakage airflow that is communicated from a cavity positioned radially inwardly from the component by circulating the leakage airflow over at least one augmentation feature that is disposed on an outer surface of the platform.   
     
     
         19 . The method as recited in  claim 18 , wherein the leakage airflow is not a dedicated cooling airflow that is communicated inside of the component. 
     
     
         20 . The method as recited in  claim 18 , wherein the at least one augmentation feature is disposed on a trailing edge portion of the platform.