Study on the turbine vane and blade for a 1,500 C class industrial gas turbine

Journal Article · Fri Jul 01 00:00:00 EDT 1994 · Journal of Engineering for Gas Turbines and Power; (United States)

DOI:https://doi.org/10.1115/1.2906861· OSTI ID:7130419

Amagasa, S; Shimomura, K; Kadowaki, M ^[1]; Takeishi, K; Kawai, H; Aoki, S; Aoyama, K ^[2]

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1. Tohoku Electric Power Co., Inc., Sendai (Japan)
2. Mitsubishi Heavy Industries, Ltd., Takasago (Japan)

This paper describes the summary of a three year development program for the first stage stationary vane and rotating blade for the next generation, 1,500 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.

• OSTI ID: 7130419
• Journal Information: Journal of Engineering for Gas Turbines and Power; (United States), Vol. 116:3; ISSN 0742-4795
• Country of Publication: United States
• Language: English

Related Subjects

20 FOSSIL-FUELED POWER PLANTS
GAS TURBINES
TURBINE BLADES
VANES
FILM COOLING
MATERIALS TESTING
COOLING
EQUIPMENT
MACHINERY
TESTING
TURBINES
TURBOMACHINERY
200104* - Fossil-Fueled Power Plants- Components