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