轴流压气机非定常气动响应模型分析研究  

Unsteady Aerodynamic Response Model for Axial Compressor

作　　者：张韬[1,2] 乔渭阳 陈伟杰[3] 栾长春[3] ZHANG Tao;QIAO Wei-yang;CHEN Wei-jie;LUAN Chang-chun(Beijing Power Machinery Institute,Beijing 100074,China;School of Vehicle and Mobility,Tsinghua University,Beijing 100084,China;School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]北京动力机械研究所,北京100074 [2]清华大学车辆与运载学院,北京100084 [3]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2023年第2期83-93,共11页Journal of Propulsion Technology

基　　金：国家科技重大专项(2017-II-0008-0022);国家自然科学基金(51776174,51936010,52106056);中央高校基本科研业务费(3102021OQD706)。

摘　　要：压气机非定常气动响应模型是进行航空发动机气动稳定性分析的基础,本文基于经典的独立叶片动态失速模型,根据压气机基元级做功原理,建立了压气机非定常气动响应模型,推导了压气机非定常气动响应计算公式,并基于多台发动机进气畸变实验数据确定了非定常气动响应模型的时间常数,数值计算分析了多种形式稳态周向压力畸变对压气机动态响应特性的影响。计算结果表明,动态气动响应模型的二阶系统时间常数分别取τ_(1)=2.5,τ_(2)=2.0较为合适,在相同的进气畸变强度下,低压区范围越大,有效增压比就会越大;在同样低压区范围的情况下,低压区数目越多,有效增压比会越小;而在同样畸变度和低压区范围情况下,低压区向高压区的气流变化越平缓,则有效增压比会越小。本文给出的压气机非定常气动响应模型能准确捕捉到压气机气动响应基本规律。The unsteady aerodynamic response model of compressor is the basis for the analysis of aeroengine aerodynamic stability. Based on the classical isolated airfoil dynamic stall model and the work principle of compressor elementary stage, a general compressor unsteady aerodynamic response model which can be used to analyze the dynamic characteristics of compressor under any unsteady incoming flow condition is established, and the calculation formula of unsteady aerodynamic response model is described in detail. The analysis method of unsteady aerodynamic response model for any unsteady incoming flow is given, and the time constant of unsteady aerodynamic response model is determined based on the experimental data of engines inflow distortion.The effects of various forms of steady-state circumferential pressure distortion on the dynamic response characteristics of compressor are numerically analyzed. The calculation results show that the time constants for the secondorder dynamic aerodynamic response model taking respectively τ_(1)=2.5, τ_(2)=2.0 is more appropriate. Under the same inlet distortion intensity, the larger the range of low pressure zone, the greater the effective pressure ratio is. In the case of the same range of low pressure zones, the more the number of low pressure zones, the smaller the effective pressure ratio is. Under the same distortion intensity and low pressure range, the more gentle the change from low pressure to high pressure, the smaller the effective pressure ratio is. The results show that the unsteady aerodynamic response model given in this paper can accurately describe compressor aerodynamic response characteristics.

关 键 词：压气机 动态失速 气动响应模型 进气畸变 气动稳定性 非定常流 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]