摘要
在发动机典型雷诺数和压比状态下对一种放大导叶叶型进行了表面静压和换热测量.雷诺数对表面压力系数的影响较小,压比增大使压力系数减小,并且吸力面压力系数最低点后移.雷诺数增大时叶片表面传热系数增加,并且吸力面上边界层转捩位置提前.压比主要影响吸力面传热系数,小雷诺数时压比增大会推迟吸力面上边界层转捩点位置,大雷诺数且吸力面后半段为超声速流动时,增大压比使该区域传热系数降低.保持主流总温不变,叶片表面绝热壁温随叶栅压比增大而降低,相同压比下,叶片表面处于层流状态时绝热壁温比处于湍流状态时低.
Surface pressure and heat transfer measurements of an enlarged vane were conducted at engine’s typical Reynolds numbers and pressure ratios.The pressure coefficients decreased and the lowest point of the suction surface moved backward with an increasing pressure ratio,while the Reynolds number had small effect on the surface pressure coefficients.With increase of the Reynolds number,the surface heat transfer coefficients rose,and the transition occurred earlier at suction surface.The pressure ratio mainly affected the heat transfer of suction surface.The transition occurred later when the pressure ratio increased in small Reynolds number state.When supersonic flow appeared at the suction’s rear region in large Reynolds number state,the heat transfer coefficients at large pressure ratio were lower than those at small pressure ratio.The local adiabatic wall temperatures decreased with increase of pressure ratio.In the case of constant pressure ratio,the local adiabatic wall temperature of laminar flow was lower than that of turbulent flow.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2013年第4期819-824,共6页
Journal of Aerospace Power
关键词
短周期风洞
叶栅压比
表面压力系数
表面传热系数
绝热壁温
short duration wind tunnel
pressure ratio
surface static pressure coefficient
surface heat transfer coefficient
adiabatic wall temperature
