跨音压气机等离子体激励扩稳的数值研究  

Numerical Simulation on Stall Margin Improvements With Plasma Actuation in a Transonic Axial Compressor

作　　者：李志远[1,2] 杜娟[1] 李帆[1,2] 王开[1] 李钢[3] 林峰[1] 

机构地区：[1]中国科学院工程热物理研究所先进能源与动力重点实验室,北京100190 [2]中国科学院大学,北京100190 [3]中国科学院工程热物理研究所燃气轮机实验室,北京100190

出　　处：《工程热物理学报》2015年第6期1191-1195,共5页Journal of Engineering Thermophysics

基　　金：国家青年自然科学基金(No.50906085);国家自然科学基金(No.51176188)

摘　　要：本文以跨音轴流单转子压气机为研究对象,对65%和98%额定转速下,不同等离子体激励强度的扩稳效果进行研究。结果表明,在一定转速下,等离子体激励强度越高,扩稳效果越好;相同等离子激励强度下,转速越高,扩稳效果越差。通过对该单转子机匣壁面轴向剪切应力的分析,发现等离子体激励的扩稳机制是将泄漏流与主流交界面位置推向叶片通道下游,抑制泄漏流在叶片前缘的溢出。在此基础上,本文提出了一种利用靠近失速的小流量工况下的泄漏流与主流交界面位置预判等离子体激励效果的方法。该方法由于不需要计算到失速边界,因此可以快速初判等离子激励的相对扩稳效果,为跨音环境下等离子扩稳方案的设计提供指导。A numerical investigation on the stall margin improvement by plasma actuations is presented for an transonic axial single-rotor compressor at 65%and 98%design speed.It is found that the stall margin improvement is increased when the plasma actuation is strengthened or the rotor rotating speed is reduced.Through anlyzing the axial shear stress on the shroud,it is demonstrated that the plasma actuation improves the stability by pushing the TLF/MF interface(interface between tip leakage flow and incoming main flow) location downstream towards the blade trailing edge,and thus suppressing the spillage of TLF/MF interface at the blade leading edge plane.A method to predict the stability enhancement ability of plasma actuations by comparing the TLF/MF interface location changed by the plasma actuation at a small flow rate point near stall is then proposed.Since there is no need to capture the stall limit accurately,this method can be used to quickly evaluate the relative stability enhancement ability of the plasma actuation,and thus guide the design of plasma actuations for the further experimental investigation in transonic compressors.

关 键 词：等离子 轴流压气机 扩稳 流动控制 跨音 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]