C-7 CMC材を用いた冷却タービン翼モデルの冷却性能に関する研究(伝熱,一般講演)

概要

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From environmental and economical viewpoints it is strongly demanded to reduce fuel consumption and CO2 emission of aeroengines. To achieve this goal, reductions of amount of cooling air for hot parts as well as their weight are quite effective. In this sense, Ceramic Matrix Composite (CMC) can be a candidate material for hot-section components of next generation aeroengines because of its durability at the higher temperature and lower density compared with conventional nickel-based super alloys. Apart from the material itself, manufacturing vane and/or blade with cooling structure from CMC is a challenging task. This study first attempts to create an air-cooled turbine airfoil with film and impingement cooling from SiC/SiC-based CMC, then examines its aerodynamic and cooling performances through the cascade testing.
2011-07-06