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利用短周期跨声速换热风洞测量非设计状态下攻角对涡轮叶片表面静压及换热的影响,研究攻角对涡轮叶栅压力分布及换热系数分布的影响规律。实验结果表明,攻角变化对吸力面压力分布影响较大,正攻角时在靠近吸力面前缘处产生很大的逆压梯度,随攻角增大吸力面后部压力逐渐增高,负攻角时压力面前缘产生较小的逆压梯度;正攻角主要影响吸力面换热系数,随攻角增大吸力面前缘局部区域换热显著加强,负攻角主要影响压力面换热分布,随攻角减小压力面换热加强,大雷诺数下换热系数分布规律与小雷诺数时基本一致。
The short-period transonic wind tunnel was used to measure the influence of the angle of attack on the static pressure and heat transfer of the turbine blade under non-designed conditions. The influence of the angle of attack on the pressure distribution and the heat transfer coefficient distribution of the turbine cascade was studied. The experimental results show that the change of angle of attack has a great influence on the pressure distribution on the suction surface. When the angle of attack is on the front of the suction surface, a great pressure gradient is generated. With the increase of the angle of attack, the pressure at the rear of the suction surface gradually increases, When the angle of attack (ATO) increases, the heat transfer in the local area at the leading edge of the suction surface is significantly enhanced, and the negative angle of attack mainly affects the distribution of pressure surface heat transfer Reducing the angle of attack heat exchange strengthened, the distribution law of the heat transfer coefficient under the large Reynolds number is basically the same with the small Reynolds number.