轴流压气机性能预测及喘振/堵塞流量边界分析

Performance Prediction and Surge/Chock Boundary Analysis of Axial Compressor

轴流压气机一维分析在压气机设计及性能快速预测领域具有重要作用,本文基于广泛实验得到的冲角、落后角及各类总压损失模型,建立了逐叶片排计算的一维平均中径程序,利用NASA 2级压气机验证了程序计算精度。通过对四类失速边界模型和三种堵塞边界模型的预测结果对比,分析各类模型在不同转速下的适用性,对压气机流量边界的一维预测提供指导,同时基于速度比提出了一种堵塞边界预测方法,取得较好的效果。

One-dimensional analysis of axial compressor plays an important role in the field of compressor design and rapid performance prediction.Based on the incidence angle,deviation an-gle and a serial of total pressure loss models obtained by classical experiments,a one-dimensional meanline program is established in this paper.The accuracy of the program is verified with a NASA 2-stage compressor from public literature.By comparing the prediction results of four stall boundary models and three chock boundary models,the suitability of various models under different condition is analyzed,which provides guidance for one-dimensional prediction of compressor flow boundary.Meanwhile,a chock boundary prediction method based on velocity ratio is proposed with less error.