Thermal management system for a gas turbine engine
A thermal management system for a gas turbine engine includes a high pressure compressor rotor having a plurality of disks and a shaft; at least one forward cavity between a rim of at least one of the disks and the shaft and at least one aft cavity formed between a rim of at least one other of the disks and the shaft; a first flow of cooling air in the at least one forward cavity; and a second flow of cooling air in the at least one aft cavity.
1. A thermal management system for a gas turbine engine comprising:
means for delivering a first stream of cooling air to at least one forward cavity for controlling disk temperature and shaft temperature;
means for allowing said first stream of cooling air to exit said at least one forward cavity;
means for delivering a second stream of cooling air to at least one aft cavity for providing disk web cooling; and
means for mixing said first stream of cooling air exiting said at least one forward cavity with an intershaft flow of cooling air, wherein said at least one forward cavity comprises a plurality of forward cavities formed by a plurality of disks, hubs and an outer diameter of a shaft and said at least one aft cavity comprises a plurality of aft cavities formed by a plurality of disks and the outer diameter of said shaft.
2. The thermal management system of claim 1 , wherein said means for delivering a second stream of cooling air comprises means for bleeding air from a main gas path.
3. The thermal management system of claim 2 , wherein said means for bleeding air from said main gas path comprises at least one radial bleed slot located in a rim of a disk.
4. The thermal management system of claim 2 , wherein said main gas path is created between a casing surround a high pressure rotor and a rim of at least one disk.
5. The thermal management system of claim 1 , wherein said means for delivering a second stream of cooling air comprises means for minimizing pressure loss while maximizing said disk web cooling.
6. The thermal management system of claim 5 , wherein said means for minimizing pressure loss comprises at least one anti-vortex tube.
7. The thermal management system of claim 6 , wherein said at least one anti-vortex tube is connected to a wall of a disk.
8. The thermal management system of claim 5 wherein said at least one anti-vortex tube includes a first anti-vortex tube mounted to a wall of a first disk and a second anti-vortex tube mounted to a wall of a second disk.
9. The thermal management system of claim 8 , wherein a first one of said first and second anti-vortex tubes is shorter than a second one of said first and second anti-vortex tubes.
10. The thermal management system of claim 1 , further comprising means for isolating the at least one forward cavity from said at least one aft cavity.
11. The thermal management system of claim 10 , wherein said isolating means comprises a seal.
12. The thermal management system of claim 1 , further comprising means for exiting said cooling air from said at least one aft cavity.
13. The thermal management system of claim 12 , wherein said exiting means comprises at least one hole in a rear hub foot.
14. The thermal management system of claim 1 , further comprising means for cooling the first stream of cooling air.
15. The thermal management system of claim 14 , wherein said cooling means comprises a heat exchanger.
16. The thermal management system of claim 1 , further comprising a compressor rotor having a front hub and said front hub having at least one flow hole therein for delivering said first stream of cooling air to said at least one forward cavity.
17. The thermal management system of claim 16 , further comprising a tie shaft and said first stream of cooling air flowing through at least one bore in at least one disk and exiting through at least one flow hole in an outer diameter of said tie shaft.
18. The thermal management system of claim 17 , wherein said tie shaft is a hollow shaft which encases a second shaft and wherein intershaft cooling air flows between an inner diameter of said tie shaft and an outer diameter of said second shaft.
19. The thermal management system of claim 18 , wherein said second shaft is a low pressure shaft.