高亚声速大弯角轴流压气机平面叶栅损失模型研究

Investigation of Loss Model Applicable to Large Range of High Subsonic Cascades in Axial-Flow Compressor

关键词:  损失  平面叶栅  流场  附面层  工作范围  轴向密流比

Key words:  Loss  Cascade  Flow field  Boundary layer  Scope of work  Axial velocity density ratio

摘要:

基于亚声速叶栅设计点损失预估模型，结合无粘S1流场与附面层迭代计算发展了一套计算大弯角轴流压气机平面叶栅流场程序。增加弯度比分布及最大厚度修正得到设计点损失预估模型，采用马赫数修正后的叶栅有效工作范围得到一套大弯角叶栅全工况损失预估模型。分析了轴向密流比在实验中对叶栅损失系数的影响。结果表明，S1流场计算程序与修正后的损失预估模型均能准确地预估出大弯角叶栅设计点损失系数，误差分别小于0.006与0.004。非设计点损失模型能有效地预估得到叶栅有效工作范围内的损失随攻角的分布。初步验证了损失模型对高亚声速大弯角平面叶栅损失系数预估的准确性。

Abstract:

A set of procedure which was used to calculate large range of cascades’ S1 flow field in axial-flow compressor was developed，which based on the old estimated loss model of subsonic cascade and combined with the inviscid S1 field and boundary layer interactive calculation. The design point loss model was built by corrected camber ratio and maximum thickness. An overall working condition loss model of large range cascade was developed through cascade’s scope of work. The paper also analysed the influence of axial velocity ratio in cascade experiment. The results show that S1 flow field procedure and modified loss model are able to predict design point loss coefficient，error of loss are less than 0.006 and 0.004. Off-design point loss model estimates loss incidence characteristic effectively by the corrected scope of work. The accuracy of the loss model for predicting large range of high subsonic cascades’ loss coefficient is proved.