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.
Study on the Turbine Vane and Blade for a 1500°C Class Industrial Gas Turbine
- Views Icon Views
- Share Icon Share
- Search Site
Amagasa, S., Shimomura, K., Kadowaki, M., Takeishi, K., Kawai, H., Aoki, S., and Aoyama, K. (July 1, 1994). "Study on the Turbine Vane and Blade for a 1500°C Class Industrial Gas Turbine." ASME. J. Eng. Gas Turbines Power. July 1994; 116(3): 597–604. https://doi.org/10.1115/1.2906861
Download citation file: