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

作　　者：孙伟文 王巍[1,2] 王晓放[1,2] SUN Weiwen;WANG Wei;WANG Xiaofang(School of Energy and Power Engineering,Dalian University of Technology,Dalian 116024,China;Key Laboratory of Ocean Energy Utilization and Energy Conservation,Ministry of Education,Dalian 116024,China)

机构地区：[1]大连理工大学能源与动力学院,大连116024 [2]大连理工大学海洋能源利用与节能教育部重点实验室,大连116024

出　　处：《工程热物理学报》2024年第3期733-740,共8页Journal of Engineering Thermophysics

基　　金：国家科技重大专项(No.J2019-I-0012-0012)。

摘　　要：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.

关 键 词：轴流压气机 一维平均中径法 特性仿真 流量边界预测 

分 类 号：TK14[动力工程及工程热物理—热能工程]