压气机角区失速预测模型的改进与实验验证

Improvement of Criterion for Prediction of Axial CompressorCorner Stall and Its Experimental Verification

关键词:  角区分离  角区失速  角区失速预测模型  轴流压气机

摘要:

角区分离普遍存在于压气机中，随着负荷的提升，角区分离可能发展为角区失速，导致流动的堵塞与损失显著增大。前人基于二维叶栅，提出了预测叶片角区失速的模型，但这些模型并没有考虑到真实压气机环境中流动的强三维性。本文在现有模型基础上，一方面对其进行改进，以考虑压气机中流动具有强三维性的影响；另一方面，利用低速压气机实验台上获得的大量实验数据对现有模型和改进后的模型进行校验。结果表明：在真实压气机中，现有的准则不再可行；而基于改进后的模型，存在一个临界参数，能够准确判断静子根部角区分离和角区失速；另外，改进后的参数与静子根部端区流动影响范围内的堵塞和损失存在很强的关联。

Abstract:

Endwall corner separation is a typical secondary flow in axial compressor. With the increase of blade loading, the corner separation flow could develop into corner stall flow, which could cause serious flow blockage and loss in compressor blade passage and should be avoided during the compressor design procedure. In order to predict the corner stall flow in compressors, some criterions has been developed， which are mainly based on two-dimensional airfoil data. The endwall flow is strong three-dimensional in real compressor environment. A new criterion is developed accordingly in the present paper. The newly developed criterion was verified by experimental data obtained from low-speed compressor tests. The results showed that the existed criterions do not work well in real compressor environment and the newly developed criterion could accurately predict the stator hub corner stall in compressors with a critical value of. In addition, the newly developedD parameter shows related correlation to the flow loss and blockage in compressor stators.