离心叶轮背腔旋流抑制技术设计及验证  

Design and validate about swirl velocity restrain on cavity behind centrifugal impeller disk

作　　者：张远森 周志翔 郝旭生 赵尊盛 陈杜 吴楠 ZHANG Yuansen;ZHOU Zhixiang;HAO Xusheng;ZHAO Zunsheng;CHEN Du;WU Nan(Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2024年第11期152-159,共8页Journal of Aerospace Power

摘　　要：基于旋转盘腔径向外流科氏力作用理论,开展了叶轮背腔旋流抑制引气方案设计,并通过数值计算对设计方案进行了评估,结果表明:叶轮背腔径向外流引气方案由科氏力起主导作用,可抑制叶轮背腔旋转比,提高引气出口静压系数至0.88,较常规方案A增加16.6%,增大了叶轮背腔向前的轴向力,可起到调节发动机在慢车等低状态的转子轴向力轻载、反向的作用,但由于轮背旋转壁面与气流之间的速度差增大,导致轮盘消耗风阻功率增加,引气出口温度增加30 K,并在旋转换热实验台上对该技术进行了验证。Base on the theory about Coriolis force on rotate cavity,the project to restrain swirl ratio on the cavity behind centrifugal impeller disk was designed,and then analyzed by the numerical tool.The result showed that:the project about radial outer flow on the cavity behind centrifugal impeller disk was dominated by the Coriolis force,which can restrain the swirl ratio and increase the static pressure coefficient to 0.88 on the cavity exit,the static pressure coefficient increased by 16.6%compared to plan A,so it can increase the axial force on the cavity behind impeller disk and improve the light load of bearing and reverse the direction of axial force at small state.But due to the great velocity diversity between rotation wall and air,the power wasting on the cavity behind impeller disk increased,the temperature of air exit increased to 30 K.The result was validated on rotating heat exchange coefficient testing stand.

关 键 词：叶轮背腔 径向外流 旋转比 轴向力 功耗 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]