Experimental Investigation on the Aerodynamic Instability Process of a High-Speed Axial-Centrifugal Compressor

Jiaan Li, Baotong Wang, Xuedong Zheng, Zhiheng Wang, Xinqian Zheng
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Abstract

Aerodynamic instability plays an important role in compressor design and may cause performance degradation and fatigue damage. In this paper, an experimental study on the evolution of aerodynamic instability is carried out on a compressor that combines the performance benefits of an axial stage and centrifugal stage. The spatiotemporal characteristics of unsteady wall pressure were obtained using fast-responding pressure transducers over a range of operating conditions. The results show that the axial stage works on the positive slope of the performance characteristic curve from choke to stall at low-speed operating conditions, and mainly features rotating instability. Rotating stall is also observed in the impeller (IMP) and diffuser passages. At medium-speed operating conditions, the centrifugal stage suffers a high-frequency mild surge, alternating with rotating stall. With the increase in back pressure, the mild surge diminishes, and rotating stall persists. This behavior is similar to a two-regime-surge, which has been reported for centrifugal compressors. At high-speed operating conditions, the compressor directly reaches surge without other instabilities. Further analysis of the spatial pattern of the rotating stall revealed the existence of a high-pressure region near the volute tongue, resulting in obvious pressure distortion along the circumferential direction at the volute inlet. This induced the amplitude difference of stall cells in corresponding diffuser passages. The disturbance caused by stall cells propagates upstream through the blade passage, and the largest pressure disturbance induced by the stall cell propagation appears in a circumferential position 45 deg downstream of the volute tongue at the impeller inlet and the axial stage inlet.
高速轴向离心压缩机气动不稳定过程的实验研究
空气动力不稳定性在压缩机设计中起着重要作用,可能导致性能下降和疲劳损坏。本文对结合了轴向级和离心级性能优势的压缩机进行了空气动力不稳定性演变的实验研究。在一系列运行条件下,使用快速响应压力传感器获得了非稳定壁压的时空特征。结果表明,在低速运行条件下,轴向级工作在从阻塞到失速的性能特性曲线的正斜率上,主要表现为旋转不稳定性。在叶轮(IMP)和扩散器通道中也观察到了旋转失速现象。在中速运行条件下,离心级会出现高频率的轻微浪涌,与旋转失速交替出现。随着背压的增加,轻度浪涌减弱,而旋转失速持续存在。这种现象类似于离心式压缩机的双周期喘振。在高速运行条件下,压缩机直接达到浪涌,而没有其他不稳定性。对旋转失速空间模式的进一步分析表明,在涡舌附近存在一个高压区,导致涡舌入口处沿圆周方向出现明显的压力畸变。这诱发了相应扩散器通道中失速单元的振幅差。滞流单元引起的扰动通过叶片通道向上游传播,滞流单元传播引起的最大压力扰动出现在叶轮入口和轴向级入口涡舌下游 45 度的圆周位置。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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