A-14 フィルム孔を有する閉鎖空間における斜め衝突噴流の伝熱特性(伝熱,一般講演)

概要

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One of the new cooling concepts of turbine nozzle and blade endwall for next generation 1700℃ class industrial gas turbines is an impingement cooling technology in a closed cavity. As the turbine inlet temperature increases the turbine aerodynamic load becomes high and the secondary flow generated by pressure difference between pressure and suction side of a vane becomes strong. Thereby, passage vortex glows strong and rolls up the film cooling air blowing through a film cooling hole in the endwall to cool the endwall. Therefore, not to penetrate the film cooling air into the passage vortex, film cooling air must remain in the boundary layer under the passage vortex. Cell cooling structure and swirling film cooling will solve these problems. In this paper heat transfer coefficients of inclined jet impingements in a closed cavity to make swirling motion were studied by using naphthalene sublimation method.
2009-10-21