Air seal interface with forward engagement features and active clearance control for a gas turbine engine
An interface assembly for a gas turbine engine. The interface a full-hoop vane ring around the engine axis, the full-hoop vane ring comprises an aft vane rail with a vane ring contact surface, the aft vane rail engaged with the anti-rotation case slot at a vane ring anti-rotation tab; and a multiple of BOAS segments around the engine axis, each of the multiple of BOAS segments comprise a BOAS forward engagement feature and a BOAS contact surface, the BOAS forward engagement feature engaged with the outer case, the BOAS contact surface abuts the vane ring contact surface.
1. An interface assembly for a gas turbine engine, comprising:
an outer case that defines an engine axis, the outer case comprises an anti-rotation case slot;
a full-hoop vane ring around the engine axis, the full-hoop vane ring comprises an aft vane rail with a vane ring contact surface, the aft vane rail engaged with the anti-rotation case slot at a vane ring anti-rotation tab; and
a multiple of BOAS segments around the engine axis, each of the multiple of BOAS segments comprise a BOAS forward engagement feature and a BOAS contact surface, the BOAS forward engagement feature engaged with the outer case, the BOAS contact surface abuts the vane ring contact surface.
2. The interface assembly as recited in claim 1 , wherein the vane ring contact surface loads against the BOAS contact surface in response to attachment of a second outer case to the engine case, the second case abuts with the full-hoop vane ring.
3. The interface assembly as recited in claim 2 , wherein the second outer case comprises a turbine exhaust case.
4. The interface assembly as recited in claim 2 , further comprising a full hoop seal arranged around the engine axis, the multiple of BOAS segments load against the full hoop seal.
5. The interface assembly as recited in claim 4 , wherein the full hoop seal is a dogbone seal.
6. The interface assembly as recited in claim 2 , wherein the forward engagement feature in each of the multiple of BOAS segments comprises at least one anti-rotation slot.
7. The interface assembly as recited in claim 1 , wherein each of the multiple of BOAS segments comprise a BOAS aft engagement feature engaged with the engine case, the BOAS aft engagement feature forms a forward facing hook.
8. The interface assembly as recited in claim 7 , wherein the BOAS aft engagement feature of each of the multiple of BOAS segments comprise a BOAS aft segment contact surface to abut a second vane ring contact surface of a second full-hoop vane ring aft of the multiple of BOAS segments.
9. The interface assembly as recited in claim 1 , further comprising a forward rail that extends from the full-hoop vane ring, the forward rail comprises a groove to receive a seal.
10. The interface assembly as recited in claim 1 , wherein each of the multiple of BOAS segments comprises a circumferential feather seal slot to seal between each of the multiple of BOAS segments.
11. The interface assembly as recited in claim 1 , wherein the BOAS contact surface is transverse to the forward engagement feature.
12. The interface assembly as recited in claim 11 , wherein the outer case comprises a case groove with an anti-rotation slot that receives the vane ring anti-rotation tab and the BOAS forward engagement feature.
13. The interface assembly as recited in claim 12 , wherein the BOAS forward engagement feature comprises a rail with a BOAS anti-rotation slot to receive the vane ring anti-rotation tab.
14. The interface assembly as recited in claim 13 , wherein the rail with the BOAS anti-rotation slot is transverse to the BOAS contact surface.
15. The interface assembly as recited in claim 14 , further comprising a BOAS aft engagement feature aft of the BOAS forward engagement feature, the BOAS aft engagement feature forms a hook.
16. The interface assembly as recited in claim 15 , wherein the hook extends toward the BOAS forward engagement feature.
17. A method of assembling a module for a gas turbine engine, comprising:
installing a full-hoop vane ring around an engine axis into a case groove with an anti-rotation slot in an engine case, the full-hoop vane ring comprises an aft vane rail with a vane ring contact surface and a vane ring anti-rotation tab received into the anti-rotation slot in an engine case; and
installing a multiple of BOAS segments around the engine axis, each of the multiple of BOAS segments comprise a BOAS segment forward engagement feature, a BOAS contact surface, and a BOAS segment anti-rotation slot, the BOAS segment forward engagement feature engaged with the case groove, the BOAS segment anti-rotation slot engaged with the vane ring anti-rotation tab such that the BOAS contact surface abuts the vane ring contact surface.
18. The method as recited in claim 17 , further comprising attaching a second outer case to seal the BOAS contact surface with the vane ring contact surface.
19. The method as recited in claim 18 , further comprising compressing a seal between the full-hoop vane ring and a second multiple of BOAS segments forward of the full-hoop vane ring.
20. The method as recited in claim 19 , further comprising installing the seal within a groove formed in the full-hoop vane ring.