Performance Prediction and Surge/Chock Boundary Analysis of Axial Compressor
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.
axial compressorone-dimensional meanline methodperformance simulationpredic-tion of flow boundary
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