Title:
【発明の名称】ガスタービンエンジンの高圧タービンの冷却
Document Type and Number:
Japanese Patent JP2002543319
Kind Code:
A
Abstract:
A turbine engine having improved high pressure turbine cooling is disclosed. In the engine, relatively cool intermediate pressure (P2x) air is diverted from a region of a compressor section and over a high work turbine blade at a lower static pressure than the diverted air to cool the blade. Advantageously, as the diverted air is relatively cool, use of a conventional TOBI nozzle may be eliminated. Similarly, showerheads on the blade may be eliminated. As well, the diverted air may conveniently be used to seal a rear bearing compartment within the engine.
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Inventors:
Riu, Kioryu
Application Number:
JP2000613924A
Publication Date:
December 17, 2002
Filing Date:
April 26, 2000
Export Citation:
Assignee:
Pratt & Whitney Canada Corporation
International Classes:
F01D5/08; F01D25/12; F02C7/18; (IPC1-7): F01D5/08; F02C7/18
Attorney, Agent or Firm:
Fujiya Shiga (2 outside)