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RESEARCH PAPERS

Effect of New Blade Cooling System With Minimized Gas Temperature Dilution on Gas Turbine Performance

[+] Author and Article Information
K. Kawaike, N. Kobayashi, T. Ikeguchi

Mechanical Engineering Research Laboratory, Hitachi, Ltd., Saiwai-cho, Hitachi-shi, Japan

J. Eng. Gas Turbines Power 106(4), 756-764 (Oct 01, 1984) (9 pages) doi:10.1115/1.3239635 History: Received January 06, 1984; Online October 15, 2009

Abstract

Recent developments in high-performance and high-reliability gas turbine engines necessitate enforced cooling to maintain the blade temperature at reasonably low levels associated with increased turbine inlet temperature and compressor pressure ratio. However, the gas turbine performance is strongly penalized by the consumption of cooling flow, resulting in temperature dilution of hot mainstream, aerodynamic mixing loss, and pumping power loss. In this paper, a new practical blade cooling system using state-of-the-art engineering, which aims at minimizing the dilution effect, is presented. Trade-off studies between performance and reliability in terms of blade metal temperature are performed to evaluate cooling systems. Analytical comparison of different cooling systems demonstrates that the proposed cooling system provides significant improvements in performance gain and growth potential over conventional air cooling systems.

Copyright © 1984 by ASME
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