叶栅参数对反推力装置气动性能影响规律  

Numerical Study for the Effects of Cascade Geometry Parameters on Cascade-Type Thrust Reverser Performances

作　　者：单勇[1,2] 沈锡钢[2] 张靖周[1] 尚守堂[2] 邵万仁[2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]沈阳发动机设计研究所,沈阳110015

出　　处：《中国民航大学学报》2010年第3期10-14,共5页Journal of Civil Aviation University of China

基　　金：中国博士后科学基金项目(20080441049);江苏省博士后科研基金项目(0901034C)

摘　　要：针对某型叶栅式反推力装置,开展了气动性能数值预测的研究工作。采用本文提出的数值计算方法,在不同落压比下反推力预测值与实验值最大相差8.2%。流场速度等值线分布展示反推力装置叶栅内部流动特征,叶栅叶盆处的旋涡和叶背处的失速是导致气动性能下降的不利因素。大量数值计算结果揭示了叶片进入角、出流角、稠度等结构参数对轴向反推力、流量系数、总压恢复系数的影响规律。在本研究范围内,叶片进入角54°、出流角135°、稠度1.3的叶栅几何结构综合气动性能最优。Aiming at a cascade-type thrust reverser, some numerical studies were performed to forecast the aerodynamic performances. Compared with the experimental data, it is indicated that the maximum error between the computational and experimental result is below 8.2% under the different nozzle pressure ratio. The velocity contour shows the inner flow characters in the cascades. The vortex located at the concave and the stall located convex of the vane has a disadvantage to the aerodynamic performances. The effects of inlet angle, outlet angle, and solidity on the performances are revealed by a lot of numerical results. With inlet angle of 54°, outlet angle of 135° and solidity of 1.3, the cascade has the best integrated aerodynamic performances .

关 键 词：反推力装置 叶栅式 气动性能 数值模拟 

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] O354.1[理学—流体力学]