ラジアルタービンのノズル性能に及ぼす翼先端すきまの影響
1987 年 53 巻 487 号 p. 933-939
詳細
1987 年 53 巻 487 号 p. 933-939
The turning angle of nozzle blades is smaller and the pressure loss is larger as the tip-clearance of turbine nozzle is increased. The mean flow angle at the nozzle exit was measured in four independent ways and the results agreed well with each other. Furthermore a simple flow model was proposed based on the measured pressure distribution on the nozzle blades, and the predicted exit mean flow angle and the pressure loss or the flow coefficient agreed well with the experimental data.
