Gas turbine engine turbine vane rail seal

Abstract

A stator vane seal assembly for a gas turbine engine that includes a vane that has a rail with a scallop that extends axially through the rail. A scallop seal obstructs the scallop.

What is claimed is: 
     
         1 . A stator vane seal assembly for a gas turbine engine comprising:
 a vane having a rail with a scallop extending axially through the rail; and   a scallop seal obstructing the scallop.   
     
     
         2 . The stator vane seal assembly according  1 , wherein the rail is a turbine vane aft rail, and comprising a blade outer air seal supporting the aft rail relative to an outer case structure. 
     
     
         3 . The stator vane seal assembly according  2 , wherein the aft rail includes an annular groove, and the blade outer air seal includes a first flange received in the annular groove. 
     
     
         4 . The stator vane seal assembly according  3 , comprising an annular seal provided axially between and sealing against the blade outer air seal, the aft rail and the scallop seal. 
     
     
         5 . The stator vane seal assembly according  4 , wherein the annular seal includes undulations. 
     
     
         6 . The stator vane seal assembly according  1 , wherein the scallop extends radially to an outer periphery of the rail. 
     
     
         7 . The stator vane seal assembly according  6 , wherein the rail includes a radially extending recess receiving the scallop seal, the scallop seal flush with a surface of the rail. 
     
     
         8 . The stator vane seal assembly according  7 , comprising an annular seal engaging the scallop seal and the surface. 
     
     
         9 . The stator vane seal assembly according  7 , wherein the scallop seal is rectangular in shape. 
     
     
         10 . The stator vane seal assembly according  1 , comprising a blade outer air seal, and an annular seal provided axially between the blade outer air seal and the rail, a first cavity arranged on an outer side of a platform providing the rail, and the blade outer seal separating second and third cavities, the scallop seal and the annular seal configured to prevent fluid flow from the first cavity to both of the second and third cavities. 
     
     
         11 . The stator vane seal assembly according  10 , the scallop seal flush with a surface of the rail, the annular seal engaging the scallop seal and the surface. 
     
     
         12 . The stator vane seal assembly according  11 , wherein the scallop seal is rectangular in shape. 
     
     
         13 . The stator vane seal assembly according  11 , wherein the annular seal includes undulations. 
     
     
         14 . A gas turbine engine comprising:
 a compressor section;   a combustor in fluid communication with the compressor section; and   a turbine section in fluid communication with the combustor, the turbine section including a vane having a platform with a rail, and a blade outer air seal, the vane having a rail with a scallop extending axially through the rail, a scallop seal obstructing the scallop, and an annular seal in sealing engagement with the rail and the blade outer air seal.   
     
     
         15 . The gas turbine engine according to  claim 14 , wherein the turbine section includes a high pressure section arranged fluidly forward of a low pressure turbine section, the vane arranged in the low pressure turbine section. 
     
     
         16 . The gas turbine engine according to  claim 15 , wherein the rail is an aft rail. 
     
     
         17 . The gas turbine engine according to  claim 14 , wherein the scallop extends radially to an outer periphery of the rail. 
     
     
         18 . The gas turbine engine according to  claim 14 , wherein the rail includes a radially extending recess receiving the scallop seal, the scallop seal flush with a surface of the rail, and comprising an annular seal engaging the scallop seal and the surface. 
     
     
         19 . The gas turbine engine according to  claim 14 , comprising a cooling source configured to provide a cooling fluid to a first cavity arranged on an outer side of a platform providing the rail, and the blade outer seal separating second and third cavities, the scallop seal and the annular seal configured to prevent fluid flow from the first cavity to both of the second and third cavities. 
     
     
         20 . The gas turbine engine according to  claim 19 , wherein the cooling source is the compressor section.