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通过数值求解非定常三维可压缩Reynolds averaged Navier-Stokes(RANS)方程,模拟了跨音速压气机级Rotor35/Stator37内的流场。为了分析该压气机级的损失,推导了描述非定常流动损失的参数(不可逆性)及其对应的强度量参数。以此为基础,研究了损失和流动结构之间的关系,得到了不同流动结构在损失产生上的主次关系;并定量给出了主要区域损失的大小。发现在最高效率点附近,边界层产生最大的损失,然后是顶隙泄漏流动,尾迹,以及核心区流动。本文也对该级压气机进行了损失功分析,结果表明吸力面边界层以及顶隙泄漏流动对于损失产生贡献最大。
The flow field in the transonic compressor stage Rotor35 / Stator37 was simulated by solving the unsteady three-dimensional compressible Reynolds averaged Navier-Stokes (RANS) equation numerically. In order to analyze the compressor stage losses, the parameters describing the unsteady flow losses (irreversibilities) and their corresponding strength parameters were derived. Based on this, the relationship between loss and flow structure is studied, and the primary and secondary relationship between different flow structures in loss generation is obtained. The size of main area loss is given quantitatively. Near the highest efficiency point, it was found that the boundary layer produced the greatest loss, followed by the headspace leakage flow, the wake, and the core flow. The paper also analyzes the loss function of this stage compressor. The results show that the suction layer boundary layer and the headspace leakage flow contribute the most to the loss.