RESEARCH PAPERS: Gas Turbines: Heat Transfer

Study on the Turbine Vane and Blade for a 1500°C Class Industrial Gas Turbine

[+] Author and Article Information
S. Amagasa, K. Shimomura, M. Kadowaki

Tohoku Electric Power Co., Inc., Sendai, Japan

K. Takeishi, H. Kawai

Takasago R&D Center, Mitsubishi Heavy Industries, Ltd., Takasago, Japan

S. Aoki, K. Aoyama

Takasago Machinery Works, Mitsubishi Heavy Industries, Ltd., Takasago, Japan

J. Eng. Gas Turbines Power 116(3), 597-604 (Jul 01, 1994) (8 pages) doi:10.1115/1.2906861 History: Received March 01, 1993; Online April 24, 2008


This paper describes the summary of a three-year development program for the first-stage stationary vane and rotating blade for the next generation, 1500°C class, high-efficiency gas turbine. In such a high-temperature gas turbine, the first turbine vane and blade are the most important hot parts. Full-coverage film cooling (FCFC) is adopted for the cooling scheme, and directionally solidified (DS) nickel base superalloy and thermal barrier coating (TBC) will be used to prolong the creep and thermal fatigue life. The concept of the cooling configuration, fundamental cascade test results, and material test results will be presented.

Copyright © 1994 by The American Society of Mechanical Engineers
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