关键词: 涡轮部件;叶片翼型;研究

Abstract: This paper is a further step of trial from the previous effort (Literature 1, 2) to obtain an even nearly constant degree of reaction turbine stage. The tension spline streamline curvature method applied to a nearly constant shroud diameter flowpath is similar as before. But the nozzle vanes leading edge positive lean angle is increased to 18°, and their reverse to conventional exit angle twist increased to 22. 5°.The variations of main gas dynamic parameters, total pressure loss coefficients and stage efficiencies along the blade height are shown together with the corresponding conventional stage of same flowpath for comparison. A reaction difference of only 0. 032 is achieved, yet owing to the stage exit pressure being highest at shroud, the nozzle exit pressure is still highest at shroud.It seems apparent that in order to minimize nozzle vane secondary flow and shroud clearance leakage losses, an optimum pressure gradient along nozzle vane exit is decisive in future study.

Key words: Turbine part;Blade airfoil;Research