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本文通过调整叶型中线分布设计了几种不同的跨音转子,并采用数值模拟的方法研究了其对跨音转子流场性能的影响。研究结果表明,高来流马赫数下跨音转子流场对叶型中线分布比较敏感,中线分布应尽可能保证负荷的平稳加载和预期的气流折转;跨音转子叶根区域仅在前缘附近存在局部超音区,较大的叶型折转对流场影响不大;其叶尖区域主要依靠激波增压且易诱发边界层分离,在设计中该区域的叶型折转应尽可能小,且应将叶型的折转主要集中在通道激波后的扩张段;跨音转子设计中,其最大厚度点之后的中线折转比重采用由叶根沿展向逐渐增大的分布规律可有效地降低流动分离损失;通道激波后出现的局部加速区有助于压制激波诱导的边界层分离。
In this paper, we design several different transonic rotors by adjusting the midline distribution of the leaves. The numerical simulation is used to study the effect on the flow field of the transonic rotor. The results show that the transonic rotor flow field is sensitive to the leaf midline distribution at high Mach number, and the midline distribution should be as smooth as possible to ensure the steady loading and the expected airflow deflation. The transonic rotor root zone is only at the leading edge There is a local supersonic region nearby, and the larger folds have little effect on the flow field. The tip region mainly relies on the shock pressure and is easy to induce the boundary layer separation. In the design, May be small, and folds should be mainly concentrated in the channel after the expansion of the shock segment; transonic rotor design, the maximum thickness after the point of the midpoint of the proportion of the use of folds along the spread along the spread gradually increased distribution The regularity can effectively reduce the flow separation loss. The local acceleration zone appearing after the channel shock contributes to suppress shock wave induced boundary layer separation.