跨音压气机动叶落后角模型修正方法研究  

Investigation of Deviation Model Correction for Transonic Compressor Rotors

作　　者：王啸宸 任晓栋 李雪松[1] 顾春伟[1] 阙晓斌 周国宇 WANG Xiaochen;REN Xiaodong;LI Xuesong;GU Chunwei;QUE Xiaobin;ZHOU Guoyu(Department of Energy and Power Engineering,Tsinghua University,Beijing 100084,China;China United Gas Turbine Technology CO.LTD.,Beijing 102209,China)

机构地区：[1]清华大学能源与动力工程系,北京100084 [2]中国联合重型燃气轮机技术有限公司,北京102209

出　　处：《工程热物理学报》2024年第9期2605-2611,共7页Journal of Engineering Thermophysics

基　　金：国家科技重大专项(No.2017-II-0007-0021)。

摘　　要：本文基于S1流面平均流线曲率变化规律,提出了一种用于跨音动叶落后角修正的理论方法。经典亚音叶栅落后角模型与跨音修正方法缺乏激波结构参数的指导,在气流折转与做功能力预测方面误差范围较大。本文以经典的跨音修正思想为基础,将亚音与跨音条件下的落后角差异描述为S1流面波后横向压力梯度驱动下的平均流线曲率变化的结果,建立了设计点附近跨音流动落后角的理论模型以及经验公式。上述方法应用于自主开发的流线曲率法二维通流计算程序中,针对某多级轴流压气机开展第一级跨音动叶(R1)的落后角修正研究,获得了与试验数据及CFD计算结果吻合良好的预测效果。This paper proposes a theoretical analysis method of deviation angle correction in transonic rotors considering the changes in mean streamline curvatures of S1 stream surfaces.Classical deviation models for subsonic cascades and transonic correction lack the instruction of shock-structure parameters,and causes obvious prediction errors in flow turning and loading characteristics.Based on classical transonic correction method,this paper describes the transonic correction of deviation angle as the outcome of changes in mean streamline curvatures due to transverse pressure difference in the post-shock region of S1 stream surface.The analytical model and empirical correlations of transonic deviation angle are established near the design point.The model is employed to an in-house through-flow code of streamline curvature method,and the correction method is investigated in the first transonic rotor(R1)of a multi-stage axial compressor.The through-flow predictions agree well with experiment data and CFD results.

关 键 词：轴流压气机 跨音动叶 落后角模型 通流分析 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程]