C102 ガスタービン翼の水ミストを伴うフィルム冷却法に関する基礎研究(OS9 熱・流動(1))

抄録

Higher temperature of the combustion leads to efficiency in gas turbine engines Now by the cooling of gas turbine blade, the gas temperature of the first stage inlet is possible to exceed the heatproof temperature of the turbine blade material, film cooling is one of the cooling to turbine blade methods Gas temperature in the first stage entrance is in creased by this cooling technology, but on the other hand, the increase in amount of cooling air leads to the mainstream gas temperature drop Efficient cooling and less air flow rate is required the high gas temperature further In this study, in order to obtain a difficult data, at high temperature, pressure conditions were carried out numerical calculations using the STAR-CCM+