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为评估可调向心涡轮在脉冲进气条件下的性能,通过对脉冲进气条件下的涡轮内部流场进行数值模拟分析,得到了脉冲进口压力对导流叶片段泄漏流量和总压损失、导流叶片尾缘激波强度及转子叶片前缘载荷的影响规律。导流叶片段泄漏流量和总压损失及激波随脉冲进口压力提高而线性增大,进口压力每提高10k Pa,泄漏流量增加约2.9%,导流叶片段的总压损失增加约2.7%,激波增强约14%;转子叶片前缘载荷也随脉冲进口压力增加而线性上升,当脉冲进口压力提高50k Pa时,转子叶片叶根前缘的载荷峰值增加约12.7%,中间叶高前缘位置的载荷峰值增加约24.9%。
In order to evaluate the performance of adjustable radial turbine under pulsed air intake, the leakage flow and total pressure loss of the guide vane are obtained by numerical simulation of the flow field inside the turbine under pulsed air intake. Influence of shock wave intensity at the trailing edge of guide vane and load on leading edge of rotor blade. The leakage flow and the total pressure loss and the shock wave of the guide vane segment increased linearly with the increase of the impulse inlet pressure. The leakage pressure increased by about 2.9% and the total pressure loss of the guide vane segment increased by 2.7% The shock load increases about 14%. The load on the leading edge of the rotor blade also increases linearly with the increase of the pulse inlet pressure. When the inlet pressure increases by 50kPa, the peak value of the load on the leading edge of the rotor blade increases about 12.7% The location of the peak load increased by about 24.9%.