无源微脉冲射流抑制叶栅气流分离的初步实验  

Preliminary experiment of suppressing flow separation in cascade by micro pulsed jet without external device

作　　者：朱剑锋[1] 黄国平[1] 傅鑫[1] 付勇[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016

出　　处：《航空动力学报》2014年第2期391-397,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(51176072);江苏省普通高校研究生科研创新基金(CXLX11_0216)

摘　　要：基于一种适用于高负荷压气机的无源微脉冲射流控制技术，在平面叶栅实验平台上开展了低马赫数实验研究，得到了无流动控制时叶栅通道内稳态及动态压力特性．对该分离流场（通道内分离涡主频为478Hz，对应的斯特劳哈尔数Sr约为0．2）进行了无源微脉冲射流控制通道内气流分离的实验研究，并针对148Hz到840Hz频率范围内的无源微脉冲射流控制分离流的效果进行了实验测量分析．实验结果表明：在分离涡主频0．85～1．20频率范围内，控制效果最为明显；相比于开缝吹气等定常射流控制方式，无源微脉冲射流控制方式引气流量小，大幅降低了引气对压力面流动特征及叶栅总体性能的影响．Based on a micro pulsed jet without external device control technology suit- able for high-load compressor, experimental investigation at low Mach number state was car- ried out on the cascade tunnel, and the steady and dynamic pressure characteristics in no-con- trol state were obtained. The characteristic frequency of the separated vortex was found to be about 478 Hz, and the corresponding Strouhal number was about 0.2. The experiment of controlling separation flow by micro pulsed jet was performed, with the frequency of the mi- cro pulsed jet from 148 Hz to 840 Hz. Results show that when the frequency of the micro pulsed jet ranges from 0.85 to 1.20 of characteristic frequency of the separated vortex, the control effect is more obvious. Compared with blade slot treatment in other steady control methods, the suction mass flow ratio of this micro pulsed control method is few, and the in- fluence of suction phenomena on the flow characteristics of pressure side and overall perform ance has been decreased significantly.

关 键 词：微脉冲射流 非定常 气流分离 平面叶栅 低马赫数 

分 类 号：V211.15[航空宇航科学与技术—航空宇航推进理论与工程] V231.1