直升机/粒子分离器一体化流场特性:第二部分桨盘载荷的影响

Integrated flow field characteristics of helicopter/particle separator: Part 2 influence of rotor disk load

采用等效盘模型与全三维黏性仿真相结合的方法,对旋翼下洗流干扰下直升机/粒子分离器的一体化流场特性进行了仿真研究.验证了ROBIN(rotor body interaction)模型,对类"阿帕奇"直升机/粒子分离器进行了大、小前进比时不同桨盘载荷下的一体化流场特性仿真,并对比了一体化条件、孤立条件下粒子分离器工作特性差异.结果表明:小前进比时下洗流对粒子分离器进口的分离流结构影响较大,且下洗流携带动能的叠加使得一体化条件下扫气流出口的总压损失反而比独立粒子分离器低;较大前进比状态下,下洗流干扰使得齿轮箱外罩鼓包后的分离区位置向两侧偏移,范围相比无桨盘载荷状态有所扩大,不过其对粒子分离器气动性能参数的影响并不明显.

Integrated flow field characteristics of helicopter/particle separator under the interference of rotor downwash flow were studied by combination of the actuator disk model combining three dimensional viscosity simulations.Firstly,the ROBIN（rotor body interaction）experiment model was used to check the validity of the numerical methods,then an Apache-like helicopter with different rotor disk loads under different advance ratios were investigated.Finally some comparisons between the integrated flow and the independent flow of particle separator were made.The results show that rotor downwash flow has much more influence on separated flow characteristics of particle separator at lower advance ratio and the total pressure loss of scavenge exit is reduced under the downwash flow environment.At higher advance ratio,compared to no disk load state,the separation section upstream the gear box moves to the sides and becomes bigger while the performance of particle separator changes little when the separator operated in the downwash environment.