摘要
利用基于彻体力模型建立的时间推进三维计算模型,获得了某单级跨声速压气机在周向总压进气畸变下的总体特性及流场分布,并与相关试验数据进行对比,以验证该模型的准确性及可靠性。随后利用该模型详细分析了进口分别存在周向总压进气畸变及对涡旋流畸变下某四级低速轴流压气机内部流场特征。单级跨声速压气机总体特性的计算结果与相关试验数据的相对误差不超过2%,且内部流场参数的分布特征也与试验结果相吻合。四级低速轴流压气机的计算结果反映周向总压进气畸变导致压气机气动性能及稳定性恶化,对涡旋流进气畸变则影响有限。同时揭示了不同形式的进气畸变在多级轴流压气机内部的传递过程,充分说明该模型在进气畸变这类工程问题中的广泛应用前景。
The time-marching three-dimensional computational model based on the body force model was used to obtain the general characteristics and flow field of a single-stage transonic compressor with circumferential total pressure inlet distortion.Comparison between calculated and related experimental results was made to verify the accuracy and reliability of the model.Then the internal flow field of a four-stage low speed axial compressor with circumferential total pressure inlet distortion and twin swirl inlet distortion were analyzed in detail respectively by this model.The relative error between the calculated results of the single-stage transonic compressor and the related experimental data was less than 2%,and the distribution of the internal flow field agreed with the experimental measuring data.The calculated results of the four-stage low speed axial compressor reflected that the circumferential total pressure inlet distortion worsened the aerodynamic performance and stability of the compressor while the twin swirl inlet distortion had limited impact.Meanwhile,the trav-elling process of inlet distortion with different forms in the multistage axial compressor was also revealed.The results fully prove that the model has bright prospects of application in the field of inlet distortion.
作者
郭晋
胡骏
屠宝锋
GUO Jin;HU Jun;TU Baofeng(Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2018年第9期2161-2169,共9页
Journal of Aerospace Power
基金
航空科学基金(2015ZB52018)
关键词
多级轴流压气机
彻体力模型
周向总压进气畸变
旋流进气畸变
气动性能
稳定性
multistage axial compressor
body force model
circumferential total pressure inlet distortion
swirl inlet distortion
aerodynamic performance
stability
