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

[+] Author Affiliations
S. Amagasa, K. Shimomura, M. Kadowaki

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

K. Takeishi, H. Kawai, S. Aoki, K. Aoyama

Mitsubishi Heavy Industries, Ltd., Takasago, Japan

Paper No. 93-GT-414, pp. V03CT17A075; 8 pages
doi:10.1115/93-GT-414
From:
  • ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3C: General
  • Cincinnati, Ohio, USA, May 24–27, 1993
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7892-7
  • Copyright © 1993 by ASME

abstract

This paper describes the summary of a three year development program for the 1st 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 1st 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 super-alloy 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 © 1993 by ASME
This article is only available in the PDF format.

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