Stator rim for a turbine engine
A stator rim structure for a gas turbine engine comprises a stator having an end wall and a discourager defining a channel therebetween. The end wall is adjacent to a hot gas flow and the discourager is adjacent to a purge flow. A rotor has an angel wing extending into the channel. At least one supply passage is disposed within the stator and extends through the discourager and at least one aperture fluidly couples the supply passage with the channel. A flow of cooling air is fed from the supply passage into the aperture and into the channel to form a fluidic dam discouraging ingestion of the hot gas flow.
1. A structure for a gas turbine engine, the structure comprising:
a stator having an end wall and a discourager defining a channel therebetween with the end wall adjacent to a hot gas flow and the discourager adjacent to a purge flow;
a rotor having an angel wing extending into the channel;
at least one supply passage disposed within the stator and extending through the discourager; and
at least one aperture fluidly coupling the at least one supply passage with the channel;
wherein a flow of cooling air fed from the at least one supply passage to the at least one supply aperture and into the channel forms a fluidic dam between the hot gas flow and the purge flow.
2. The structure of claim 1 wherein the cooling air is fed at an angle in a direction of rotation.
3. The structure of claim 2 wherein the cooling air is fed at an angle being both axial and in the direction of rotation.
4. The structure of claim 1 further comprising a minimum clearance region between the angel wing and the discourager.
5. The structure of claim 4 wherein the cooling air is fed into the minimum clearance region.
6. The structure of claim 1 further comprising a plurality of vanes mounted to the stator wherein a pair of adjacent vanes define a nozzle.
7. The structure of claim 6 having one supply passage of the at least one supply passage and one aperture of the at least one aperture complementary to each nozzle.
8. The structure of claim 1 wherein the cooling air is injected at an angle in the direction of rotation of the rotor.
9. The structure of claim 8 wherein the cooling air is injected at an angle being both axial and in the direction of rotation of the rotor.
10. The structure of claim 1 further comprising a minimum clearance region between the angel wing and the discourager.
11. The structure of claim 10 wherein the cooling air is injected into the minimum clearance region.
12. The structure of claim 1 further comprising a plurality of vanes mounted to the stator wherein a pair of adjacent vanes define a nozzle.
13. The structure of claim 12 having one supply passage of the at least one supply passage and one aperture of the at least one aperture disposed complementary to each nozzle.
14. A method of minimizing hot gas ingestion within a gas turbine engine, the engine comprising a stator having an end wall and a discourager, defining a channel therebetween, with the end wall adjacent to a hot gas flow and the discourager adjacent to a purge flow, with a rotor including an angel wing disposed in the channel, the method comprising:
injecting cooling air from at least one supply passage disposed within the stator and extending the discourager through at least one aperture in the discourager fluidly coupling the at least one supply passage with the channel;
wherein a flow of cooling air fed from the at least one supply passage to the at least one aperture and into the channel forms a fluidic dam between the hot gas flow and the purge flow.
15. The method of claim 14 wherein injecting the cooling air through the at least one supply aperture further comprises injecting the cooling air at an angle in a direction of rotation of the rotor.
16. The method of claim 15 wherein injecting the cooling air further comprising injecting the cooling air into a minimum clearance region between the discourager and the angel wing.