真实进气条件下发动机稳定裕度损失评估  

Assessment of Stability Margin Loss of Aeroengine under Actual Inlet Condition

作　　者：任丁丁 刘思余 王俊琦[1] 杜紫岩 REN Ding-ding;LIU Si-yu;WANG Jun-qi;DU Zi-yan(Chinese Flight Test Establishment,Aviation Industry Corporation of China,Xi’an 710089,China)

机构地区：[1]中国航空工业集团公司中国飞行试验研究院,陕西西安710089

出　　处：《推进技术》2023年第9期184-190,共7页Journal of Propulsion Technology

基　　金：航空工业试飞中心技术创新项目(YY-2121-FDJ)。

摘　　要：为了确定航空发动机压缩系统在进气总压畸变条件下的稳定裕度损失,开展了基于平行压气机模型的稳定裕度损失评估方法研究。通过对试飞中实测的总压畸变图谱进行等效转换,转换结果作为平行压气机模型的输入,得到畸变条件下压缩系统的稳定边界,再通过试飞数据确定压缩系统的流量,从而确定畸变时刻压缩系统的稳定裕度损失。对某型涡扇发动机进行计算,得到周向总压畸变强度为3.3%时风扇的稳定裕度损失为3.8%。通过对两种不同畸变强度的周向总压畸变的计算结果的对比,表明该方法可用于确定总压畸变条件下的稳定裕度损失。To determine the stability margin loss of the aeroengine compression system under the condition of inlet total pressure distortion,the stability margin loss evaluation method,which is based on the parallel com pressor model,was studied.Measured total pressure distortion contour maps in flight test were equivalently con verted.Conversion results were the inputs of the parallel compressor model,the stability boundary of compression system was determined under distorted flow.And the mass flow of compression system was determined through the flight test data,then,the stability margin loss of compression system can be calculated at distorted time.For a turbofan engine,the stability margin loss of the fan is 3.8%when the circumferential total pressure distortion in tensity is 3.3%.The comparison of the calculated results of different intensity of circumferential total pressure dis tortion shows that the method can be used to determine the stability margin loss under total pressure distortion.

关 键 词：航空发动机 试飞数据 稳定裕度损失 总压畸变 平行压气机模型 稳定边界 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]