Air seal assembly

1. An air seal assembly for a gas turbine, the air seal assembly comprising:

a flow path platform;

a casing disposed radially outside the flow path platform; and

an annular finger seal mounted to the casing and disposed between the flow path platform and the casing, the annular finger seal comprising a first circumferential portion mounted to the casing, a second circumferential portion extending from the first circumferential portion, and a third circumferential portion extending from the second circumferential portion and contacting an outer surface of the flow path platform, the third circumferential portion comprising a plurality of air cooling holes configured to direct a cooling air stream onto the flow path platform;

wherein the annular finger seal further comprises a fillet disposed at an interface between the second circumferential portion and the third circumferential portion of the annular finger seal; and

wherein one or both of the fillet and the second circumferential portion contact a seal carrier disposed axially aft of the first circumferential portion.

2. The air seal assembly of claim 1 , wherein the second circumferential portion extends between the casing and the seal carrier.

3. The air seal assembly of claim 1 , wherein the plurality of air cooling holes is arranged in a circumferential row about the annular finger seal.

4. The air seal assembly of claim 3 , wherein each air cooling hole of the plurality of air cooling holes is directed towards the outer surface of the flow path platform.

5. The air seal assembly of claim 4 , wherein the third circumferential portion has a length extending between the fillet and a point of contact between the third circumferential portion and the outer surface of the flow path platform and wherein the circumferential row of the plurality of air cooling holes is disposed in a middle section of the third circumferential portion.

6. The air seal assembly of claim 5 , wherein the circumferential row of the plurality of air cooling holes is disposed in the third circumferential portion at a center of the length.

7. The air seal assembly of claim 4 , wherein the plurality of air cooling holes is configured to direct air from a first side of the annular finger seal to a second side of the annular finger seal so as to impinge on the outer surface of the flow path platform.

8. The air seal assembly of claim 4 , wherein the second circumferential portion of the annular finger seal is free of penetrations.

9. A gas turbine comprising:

a first turbine module comprising a flow path platform and a casing disposed radially outside the flow path platform;

a second turbine module mounted to the first turbine module and disposed axially aft of the first turbine module; and

an annular finger seal mounted to the casing and disposed between the flow path platform and the casing, the annular finger seal comprising a first circumferential portion mounted to the casing, a second circumferential portion extending from the first circumferential portion, and a third circumferential portion extending from the second circumferential portion and contacting an outer surface of the flow path platform, the third circumferential portion comprising a plurality of air cooling holes configured to direct a cooling air stream onto the flow path platform;

wherein the annular finger seal further comprises a fillet disposed at an interface between the second circumferential portion and the third circumferential portion of the annular finger seal; and

wherein the second turbine module further comprises a seal carrier mounted to the second casing and wherein one or both of the fillet and the second circumferential portion contact the seal carrier.

10. The gas turbine of claim 9 , wherein the first turbine module comprises a fairing assembly comprising a fairing outer platform defining the flow path platform and a fairing inner platform disposed radially inward of the fairing outer platform, the fairing outer platform and the fairing inner platform defining a portion of a main engine gas flow path therebetween.

11. The gas turbine of claim 10 , wherein the casing is a first casing and wherein the second turbine module comprises a second casing mounted to the first casing radially outside the annular finger seal.

12. The gas turbine of claim 9 , wherein the plurality of air cooling holes is arranged in a circumferential row about the annular finger seal and wherein the second circumferential portion of the annular finger seal is free of penetrations.

13. A method for cooling an air seal assembly, the method comprising:

providing an annular finger seal mounted to a casing and disposed between a flow path platform and the casing, the casing disposed radially outside the flow path platform, the annular finger seal comprising a first circumferential portion mounted to the casing, a second circumferential portion extending from the first circumferential portion, and a third circumferential portion extending from the second circumferential portion and contacting an outer surface of the flow path platform; and

directing a cooling air stream onto the flow path platform with a plurality of air cooling holes disposed in the third circumferential portion;

wherein the annular finger seal further comprises a fillet disposed at an interface between the second circumferential portion and the third circumferential portion of the annular finger seal; and

wherein one or both of the fillet and the second circumferential portion contact a seal carrier disposed axially aft of the first circumferential portion.

14. The method of claim 13 , wherein the plurality of air cooling holes is arranged in a circumferential row about the annular finger seal.

15. The method of claim 14 , wherein each air cooling hole of the plurality of air cooling holes is directed towards the outer surface of the flow path platform.

16. The method of claim 15 , wherein the second circumferential portion of the annular finger seal is free of penetrations.