基于压气机三维彻体力模型的叶尖射流扩稳方法  

Compressor Stability Enhancement Using Tip Injection Based on Three-dimensional Bulk Body Force Model

作　　者：杨阳 郭政波 YANG Yang;GUO Zheng-bo(Engine Department of Chinese Flight Test Establishment,Xian 710089,China)

机构地区：[1]中国飞行试验研究院发动机所,西安710089

出　　处：《科学技术与工程》2024年第3期1268-1274,共7页Science Technology and Engineering

摘　　要：为了分析转子叶尖射流对多级轴流压气机的扩稳作用,研究了轴流式压气机三维黏性彻体力模型,通过对ANSYS CFX软件的二次开发,求解带动量源项和能量源项的N-S(Navier-Stokes)方程,实现无叶片条件下的压气机全通道数值模拟。基于模型计算的Stage 35单级压气机压比特性与实验值误差不大于0.8%,失稳点流量比实验值大1.2%,对端壁边界层流动能够准确模拟。基于模型计算了无射流和有射流条件下的多级压气机特性和失稳边界,并分析了叶尖射流扩稳机理。结果表明,模型能够模拟叶尖射流对多级压气机的扩稳作用,在100%设计转速下,设计点流量的4.6%的射流流量使稳定裕度增加了7.06%,射流能够消除叶尖区域的堵塞流动,从而扩大了压气机的稳定工作裕度。In order to analyze the effect of rotor tip jet on the stability enhancement of multistage axial flow compressor,a three-dimensional viscous bulk body force model of axial flow compressor was developed.Through the secondary development of ANSYS CFX software,the N-S equations of momentum and energy source terms were solved,and the full channel numerical simulation of compressor without blades was realized.The error between the pressure ratio characteristics of Stage 35 single-stage compressor calculated based on the model and the experimental data was not greater than 0.8%,and the flow rate at the instability point was 1.2%higher than the experimental value,which could accurately simulate the end wall boundary layer flow.Based on the model,the characteristics and instability boundary of multistage compressor without jet and with jet were calculated,and the mechanism of tip jet expansion was analyzed.The results show that the model can simulate the effect of tip jet on multistage compressor stability expansion.At 100%design rotor speed,the jet flow rate of 4.6%of the design point flow rate enhance the stability margin by 7.06%,and the jet can eliminate the choked flow in the tip area,thus enhancing the stability margin of the compressor.

关 键 词：轴流式压气机 三维黏性彻体力模型 气动稳定性 叶尖射流 

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]