Seal for a gas turbine engine

Abstract

A gas turbine engine assembly includes a shield that has a first portion and a second portion. The first portion extends radially from an axial end portion of the shield and includes a blade outer air seal contact surface. The second portion extends axially from a radially outer end of the first portion and includes a vane contact surface.

What is claimed is: 
     
       1. A gas turbine engine assembly comprising:
 a shield having a first portion and a second portion, the first portion extending radially from an axial end portion of the shield and includes a blade outer air seal contact surface and the second portion extends axially from a radially outer end of the first portion and includes a vane contact surface, wherein the blade outer air seal contact surface faces in an axial direction and the vane contact surfaces faces in a radial direction. 
 
     
     
       2. The gas turbine engine assembly of  claim 1 , wherein the shield forms a complete unitary circumferential hoop. 
     
     
       3. The gas turbine engine assembly of  claim 1 , wherein the shield forms a circumferential hoop with a single discontinuity. 
     
     
       4. The gas turbine engine assembly of  claim 1 , comprising
 a seal in contact with the shield. 
 
     
     
       5. The gas turbine engine assembly of  claim 4 , wherein the second portion of the shield is located radially outward from the seal and the first portion of the shield is located axially upstream from the seal. 
     
     
       6. The gas turbine engine assembly of  claim 4 , wherein the seal directly contacts a radially inner surface of the first portion of the shield and includes a “W” shaped cross section pointing radially outward. 
     
     
       7. The gas turbine engine assembly of  claim 4 , wherein the second portion of the shield is located radially outward from the seal and the first portion of the shield is located axially downstream from the seal. 
     
     
       8. The gas turbine engine assembly of  claim 1 , wherein the shield includes an “L” shaped cross section. 
     
     
       9. A gas turbine engine comprising:
 at least one vane; 
 at least one blade outer air seal adjacent the at least one vane; 
 a shield located axially between the at least one vane and the at least one blade outer air seal and the shield includes a first portion extending axially from an axial end of the shield having a blade outer air seal contact surface facing in an axial direction and a second portion extending axially from a radially outer end of the first portion having a vane contact surface facing in a radial direction; and 
 a seal located radially inward from the shield. 
 
     
     
       10. The gas turbine engine of  claim 9 , wherein the first portion extends in a radial direction from an axially upstream end of the shield. 
     
     
       11. The gas turbine engine of  claim 9 , wherein the first portion extends in a radial direction from an axially downstream end of the shield. 
     
     
       12. The gas turbine engine of  claim 9 , wherein the second portion of the shield is located radially outward from the seal and the first portion of the shield is located axially upstream from the seal. 
     
     
       13. The gas turbine engine of  claim 9 , wherein the at least one vane includes at least one anti-rotation tab. 
     
     
       14. The gas turbine engine of  claim 13 , wherein the at least one blade outer air seal includes a pair of tabs for engaging the at least one anti-rotation tab. 
     
     
       15. The gas turbine engine of  claim 13 , comprising an engine static structure with a plurality of anti-rotation protrusions and the at least one anti-rotation tab engages one of the plurality anti-rotation protrusions. 
     
     
       16. The gas turbine engine of  claim 15 , wherein the at least one blade outer air seal includes a pair of tabs for engaging the at least one of anti-rotation tab. 
     
     
       17. The gas turbine engine of  claim 9 , wherein the seal directly contacts a radially inner surface of the first portion of the shield and includes a “W” shaped cross section. 
     
     
       18. A method assembling a portion of a gas turbine engine comprising:
 positioning a shield in abutting contact with a blade outer air seal, wherein the shield includes a first portion extending axially from an axial end of the shield having a blade outer air seal contact surface facing in an axial direction and a second portion extending axially from a radially outer end of the first portion having a vane contact surface facing in a radial direction; 
 positioning a seal in abutting contact with the shield and the blade outer air seal; and 
 positioning a vane in abutting contact with the shield. 
 
     
     
       19. The method of  claim 18 , wherein the shield is located axially between the vane and the blade outer air seal and the seal is located radially inward from the shield. 
     
     
       20. The method of  claim 19 , wherein the shield comprises a first portion extending radially on an axially upstream end of the shield and a second portion extending axially from a radially outer end of the first portion.