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已有的数值研究表明叶身/端壁融合设计能有效推迟、减弱或消除压气机角区分离,但实验数据缺乏。为了弥补这一不足,本文针对一42°折转角的NACA65扩压叶栅进行了吸力面叶身/端壁融合设计,并首次在低速平面叶栅风洞中进行了对比实验,证实了叶身/端壁融合扩压叶栅性能提升能力。基于实验结果,进一步校验了RNG-KE、SST等不同湍流模型的模拟精度,并基于SST模型结果揭示了叶身/端壁融合设计的作用机理。实验结果表明:叶身/端壁融合扩压叶栅能在设计攻角及正攻角下改进叶栅性能,提高总压损失系数7%~8%。数值结果表明:融合的加入重新组织了端区流场,避免了流体在叶栅后部吸力面角区内的过度堆积而发生的强三维分离,有效缓解了原型叶栅高损失流动。
The existing numerical studies show that the blade / end fusion design can effectively delay, weaken or eliminate the compressor corner separation, but the experimental data are lacking. In order to remedy this problem, this paper designs a suction blade leaf / end wall fusion design for a 42 ° turning angle NACA65 compressor cascade and compares it for the first time in a low-speed plane cascade wind tunnel. / Endwall diffuser cascades improve performance. Based on the experimental results, the simulation accuracy of different turbulence models, such as RNG-KE and SST, is further verified. Based on the SST model results, the mechanism of blade / end fusion design is revealed. The experimental results show that the blade / end fusion diffuser cascade can improve the cascade performance at the design attack angle and the positive attack angle, and increase the total pressure loss coefficient by 7% -8%. The numerical results show that the integration of the reorganization of the end-flow field, to avoid the fluid in the posterior gassing region of the suction surface over-accumulation of strong three-dimensional separation occurs, effectively alleviating the prototype cascade high loss flow.