双推力复合式高速直升机悬停状态全机气动干扰特性计算研究  

Computational Investigation of the Dual-thrust Compound High-speed Helicopter Aerodynamic Interactions in Hover

作　　者：王许泉 江露生 孙会迅 樊枫[1] 李尚斌[1] WANG Xuquan;JIANG Lusheng;SUN Huixun;FAN Feng;LI Shangbin(National Key Laboratory of Helicopter Aeromechanics,China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所直升机动力学全国重点实验室,江西景德镇333001

出　　处：《直升机技术》2024年第4期15-21,共7页Helicopter Technique

摘　　要：对双推力复合式高速直升机开展了悬停状态全机气动干扰特性计算研究。采用基于动量源的CFD方法完成悬停状态全机配平和旋翼、螺旋桨、机身部件的全机组合与两两组合以及孤立状态的流场数值模拟;对计算结果进行性能对比和流场分析,得到各部件之间的干扰机理。结果表明:悬停状态下机身和机翼对旋翼下洗的阻塞作用使旋翼拉力增大,在两侧螺旋桨作用下旋翼拉力进一步增大4.2%,悬停效率提高4%;机身受到旋翼下洗产生的向下载荷,又由于右侧螺旋桨滑流作用,机身所受向下载荷进一步增大;两侧螺旋桨受旋翼下洗流作用,拉力明显增大,但由于机翼的干扰作用,全机下左侧螺旋桨拉力减少0.8%,右侧螺旋桨拉力提高45.6%。High speed is the development direction of future helicopters.The aerodynamic interaction characteristics of the dual-thrust compound high-speed helicopter in hovering state were computational investigated.The CFD method based on the actuator disk was used to the whole aircraft trim in hover and numerical simulation of the flow field of the rotor,propeller,fuselage in the combination of the whole aircraft and the combination of the two,the isolated state of the components and compared performance and flowfield to obtain the interaction relationship between the components.The results showed that the blocking effect of the fuselage and the wing on the rotor downwash under hovering caused the rotor thrust to increase,and the propellers on both sides also caused the rotor thrust to increase,and finally the rotor thrust increased by 4.2%,and the hovering efficiency increased by 4%.At the same time,the fuselage not only subjected to the downward load produced by the rotor downwash,but also further experienced an increased downward load due to slipstream of right propeller.The thrust of both propellers increased significantly after the rotor downwash flow.However,due to the interactions of wings,the thrust of left propeller decreased by 0.8%while the thrust of the right propeller increased by 45.6%.

关 键 词：气动干扰 悬停状态全机配平 数值模拟 性能变化 高速直升机 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]