CMC boas cooling air flow guide
A turbine section for a gas turbine engine includes a turbine blade that extends radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is mounted in a support structure and is arranged radially outward of the outer tip. A flow guide is arranged between the support structure and the blade outer air seal and defines a passage between the flow guide and the blade outer air seal. The passage is configured to communicate air in a generally axial direction.
1. A turbine section for a gas turbine engine, comprising:
a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation;
a blade outer air seal mounted in a support structure and arranged radially outward of the outer tip; and
a flow guide arranged between the support structure and the blade outer air seal, defining a passage between the flow guide and the blade outer air seal configured to communicate air in a generally axial direction.
2. The turbine section of claim 1 , wherein the blade outer air seal has a hook near a first axial side and a lip near a second axial side for engagement with the support structure, and the flow guide has a flow guide hook and flow guide lip that engage with the blade outer air seal.
3. The turbine section of claim 2 , wherein the flow guide hook is a radially outermost portion of the flow guide.
4. The turbine section of claim 2 , wherein the blade outer air seal has an air inlet in the hook and the flow guide has an air outlet near the second axial side of the blade outer air seal.
5. The turbine section of claim 4 , wherein the air inlet is configured to communicate cooling air radially inward to the passage.
6. The turbine section of claim 4 , wherein the air outlet is configured to communicate air to a chamber between the support structure and the blade outer air seal.
7. The turbine section of claim 1 , wherein a spacer is positioned between the flow guide and the blade outer air seal to maintain a gap between the flow guide and the blade outer air seal.
8. The turbine section of claim 7 , wherein the spacer is sized to force convection cooling on a radially outer surface of the blade outer air seal.
9. The turbine section of claim 7 , wherein the spacer is integrated with the flow guide.
10. The turbine section of claim 7 , wherein the spacer includes an inlet passage configured to communicate air radially inward to the passage.
11. The turbine section of claim 10 , wherein the blade outer air seal includes an inlet circumferentially aligned with the inlet passage.
12. The turbine section of claim 1 , wherein the flow guide has a blade out protection feature extending radially outward from the flow guide.
13. The turbine section of claim 1 , wherein the structure has a cooling air port configured to communicate the air from the passage to a turbine vane aft of the blade.
14. The turbine section of claim 1 , wherein the flow guide has a plurality of segments extending circumferentially about the axis.
15. The turbine section of claim 14 , wherein the blade outer air seal has a plurality of seal segments extending circumferentially about the axis, and the flow guide segments are offset from the seal segments.
16. The turbine section of claim 14 , wherein the blade outer air seal has a plurality of seal segments and there are the same number of flow guide segments and seal segments.
17. The turbine section of claim 1 , wherein the flow guide has a uniform thickness.
18. The turbine section of claim 1 , wherein the blade outer air seal is a ceramic matrix composite material.
19. The turbine section of claim 1 , wherein the flow guide is a cobalt alloy.
20. The turbine section of claim 1 , wherein the flow guide is formed from sheet metal.
21. The turbine section of claim 1 , wherein the blade outer air seal is a monolithic ceramic.
22. The turbine section of claim 1 , wherein the blade outer air seal and the flow guide are formed of different materials.