IGTC-64 Development of a Thermal Barrier Coated Blade with a New Cooling Air Passage Scheme for High Cooling Effectiveness(Session B-6 BLADE COOLING I)
スポンサーリンク
概要
- 論文の詳細を見る
The final target of development of the advanced gas turbine sponsored by MITI of Japan is a thermal efficiency of over 55% for the combined plant, at an HPT inlet temperature of 1400℃. A thermal barrier coated blade has been developed as a part of the project in order to attain this target. This paper provides a summary of the blade design and describes the hot wind tunnel tests performed to verify the cooling characteristics of the blade.
- 公益社団法人日本ガスタービン学会の論文
著者
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Teshima K.
Engineering Research Association for Advanced Gas Turbines
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Koga A.
Engineering Research Association for Advanced Gas Turbines
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Hijikata T.
Engineering Research Association For Advanced Gas Turbines
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Okamoto Y.
Research and Development Center, Toshiba Corporation
関連論文
- IGTC-69 Design Study of Cooled Blades for the AGTJ-100B Using Pre-Cooling System(Session B-8 TURBINE COOLING (AGTJ-100))
- IGTC-64 Development of a Thermal Barrier Coated Blade with a New Cooling Air Passage Scheme for High Cooling Effectiveness(Session B-6 BLADE COOLING I)
- IGTC-68 Cooling Design and Heat Transfer Analysis of Gas Turbine Blades for AGTJ-100A(Session B-8 TURBINE COOLING (AGTJ-100))
- IGTC-116 AERODYNAMIC AND COOLING CHARACTERISTICS OF A FULL SCALE HIGH TEMPERATURE TURBINE
- IGTC-116 AERODYNAMIC AND COOLING CHARACTERISTICS OF A FULL SCALE HIGH TEMPERATURE TURBINE(Session C-10 Gas Turbine Development II)