2127 タービン静翼の非軸対称な流路壁面におけるフィルム冷却の数値的研究(J18-2 ガスタービンにおける熱流動問題(2),ジョイントセッション,21世紀地球環境革命の機械工学:人・マイクロナノ・エネルギー・環境)

概要

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This paper presents results of a computational study for the endwall film cooling of an annular nozzle cascade employing a circumferentially asymmetric contoured passage. The investigated geometrical parameters and the flow conditions are consistent with a generic modem HP-turbine nozzle. Rows of cylindrical film cooling holes on the contoured endwall are arranged with a design practice for the ordinary axisymmetric endwall. The solution domain, which includes the mainflow, cooling holes paths, and the coolant plenum, is discretized in the RANS equations with the realizable k-epsilon model. With the asymmetric endwall more uniform film coverage is achieved especially in the rear part of the passage and the laterally averaged effectiveness is also significantly improved in this region. The closer inspection of the calculated thermal field reveals that, with the asymmetric passage, the coolant ejected from the holes are less deflected, and it attaches better to the endwall in this rear part.
一般社団法人日本機械学会の論文
2008-08-02