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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.
Under the condition of the typical Reynolds number and pressure ratio of the engine, the surface static pressure and heat transfer of an enlarged guide vane are measured.The Reynolds number has little influence on the surface pressure coefficient, the pressure ratio is increased and the pressure coefficient is decreased, and the suction When the Reynolds number is increased, the heat transfer coefficient of the blade surface increases and the position of the boundary layer on the suction surface advances. The pressure ratio mainly affects the heat transfer coefficient of the suction surface, and the increase of the pressure ratio at small Reynolds number will be delayed When the large Reynolds number and the second half of the suction surface are supersonic flow, the increase of the pressure ratio decreases the heat transfer coefficient in the region, while keeping the total temperature of the mainstream unchanged, the adiabatic wall temperature of the blade surface changes with the cascade pressure Lower than the increase, the same pressure ratio, the leaf surface laminar flow state when the adiabatic wall temperature is lower than in the turbulent state.