軸方向に翼端隙間の変化するタービンシュラウド面上の熱伝達特性

概要

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This paper presents the result of experiments undertaken to investigate the heat transfer characteristics on a shroud wall with changing of tip-clearance to the axial direction. An axial-flow real turbine of single-stage was used to measure the local heat transfer coefficients and the static pressures on the surface. A11 heat transfer measurements were performed under uniform heat-flux conditions. It is shown that from the results the local heat transfer coefficients increased from near the middle of the wall opposite the rotor blade row and reached a peak value near the trailing-edge. The location of the peak value corresponded to that of the minimum value of static pressures. It is also indicated that the mean heat transfer coefficients in the region opposite the rotor blade were correlated with the blade-chord Reynolds number and were little affected by the blade tip-clearance and the incidence flow angle.
社団法人日本ガスタービン学会の論文
1995-12-10