摘要
通过流体振荡器特有结构产生双孔振荡射流,采用非定常数值模拟方法研究其抑制压气机叶栅大攻角下角区分离的控制机理。重点分析了射流位置、射流角度、射流流量和单个/阵列型射流对控制效果的影响。结果表明:在近端壁单个射流器方案下,最佳射流位置位于角区分离未充分发展处(54%叶片轴向弦长),最佳射流角度和射流流量比分别为10°和0.09%,并使总压损失系数降低6.48%,静压升系数增加2.39%。振荡射流通过向附面层内低能流体注入高流向动量,抑制了附面层的发展;其非定常激励将吸力面大尺度分离涡离散破碎成一系列小尺度涡,并且其锁频效应减小尾缘压力脉动幅值,最终减小损失。相比单个射流器方案,阵列型射流方案在全叶高范围内进行振荡射流,通过5倍流量的输入,使气动性能增益增加了约1倍。
Based on the unsteady numerical simulation method,the dual-hole oscillating jet was generated by the unique structure of the fluid oscillator,and its control mechanism to inhibit the compressor cascade corner separation at a high incidence angle was investigated.The effects of jet position,jet angle,jet flow rate,and sin-gle/array jet configurations on the control effect were carefully analyzed.The results indicate that for the single-jet configuration applied to the proximal endwall,the optimal jet position is located where the corner separation is not fully developed(54%blade axial chord length).The optimal jet angle and jet flow ratio are determined to be 10°and 0.09%,respectively,resulting in a reduction of 6.48%in the total pressure loss coefficient and an in-crease of 2.39%in the static pressure rise coefficient.The oscillating jet effectively inhibits boundary layer devel-opment by injecting high flow momentum into the low-energy fluid within the boundary layer.Furthermore,the unsteady excitation of the oscillating jet breaks down the large-scale separation vortices on the suction surface in-to a series of small-scale vortices,and the frequency-locking effect reduces trailing edge pressure pulsation am-plitude,ultimately leading to reduced loss.Compared to the single-jet configuration,the array-type jet configu-ration applies oscillating jet flow across the entire blade height,and the aerodynamic performance gain has dou-bled through inputting five times flow rate.
作者
杨宗豪
刘波
茅晓晨
张博涛
王何建
张瑞辰
YANG Zonghao;LIU Bo;MAO Xiaochen;ZHANG Botao;WANG Hejian;ZHANG Ruichen(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2024年第7期77-87,共11页
Journal of Propulsion Technology
基金
国家科技重大专项(2017-Ⅱ-0001-0013)
气动院流动显示与测量重点实验室基金(D5110220177)
高等学校学科创新引智计划(B17037)。
关键词
压气机叶栅
流体振荡器
振荡射流
角区分离
气动性能
Compressor cascade
Fluid oscillator
Oscillating jet
Corner separation
Aerodynamic performance
