涡轮叶片弦中区冲击冷却的模拟实验研究

EXPERIMENTAL SIMULATION OF IMPINGEMENT COOLING IN MIDCHORD REGION OF TURBINE BLADE

本文模拟某涡轮叶片弦中区的几何参数 ,对有初始横流、气膜孔按规定压比排气、和受冲击面带有弦向肋片的冲击冷却进行了实验研究。获得具体的流动和换热规律。同时 ,对于受冲击面为弧形、带有肋片及气膜孔排气对冲冷却的影响 ,作了对比实验。并通过液晶显示表明了射孔排列方式、孔靶间距对阵列射流换热的影响。

The simulating experiments have been completed to research the characteristics of impingement cooling in midchord region of turbine blade in the condiltons of given geometric para-meter of jet array,initial crossflow and pressure ratios of film cooling exhaust.Comparative experiments have been made between curvilinear and flate plate impinged surfaces,and impinged surfaces with and without chordwise fin.Moreover,the thermal patterns from liquid crystal indication show that the jet hole arrangement and distance between cooled surface and jet plate affect the heat transfer distributions for jet array impingement.Finally,the effects of the cooling air axially injected into guide tube on radial jets flow have also been determined by measurements.