高速直升机尾推螺旋桨气动设计研究

为了研究高速直升机的动力推进装置,基于螺旋桨片条理论和环量优化设计理论对高速直升机尾推螺旋桨进行了气动优化设计和气动性能计算.在设计过程中,以高速飞行工况(H=2 000 m,v=400 km/h)为设计点,完成了一款直径D=2.5 m高速直升机尾推螺旋桨的气动方案,给出了螺旋桨桨叶最优环量、弦长以及扭转角分布.基于采用片条理论计算了在不同工况下螺旋桨的气动性能,结果表明该螺旋桨在较宽的前进比范围内均能保持较高效率(η=0.80~0.85).同时采用CFD数值模拟方法完成了2个典型状态点(静止状态v=0 km/h、高速状态v=400 km/h)的气动性能分析,获取了螺旋桨气动性能参数和流场信息,其中数值计算的拉力系数与效率值与理论计算值相差1%~2%,从而验证了复合式高速直升机尾推螺旋桨气动设计方案可靠性.

Research on aerodynamic design of tail-thrust propeller of high-speed helicopter

In order to study the propulsion plant of high-speed helicopter, the aerodynamic optimization design and the aerodynamic performance calculation of tail-thrust propeller of high-speed helicopter have been investigated based on the theory of propeller standard strip analysis and the theory of the vortex optimization design theory of screw propellers. During the design process, taking the high speed flight condition of H=2 000 m, v=400 km/h as the design point, a propeller's aerodynamic shape with diameter of 2.5 m is determined, including the distribution of optimal circulant, chord length and angle of twist are given. Based on the strip theory, the aerodynamic performance of the propeller under different working conditions is calculated. The results show that the propeller can maintain high efficiency of η=0.80-0.85 in wide advance ratio range. The aerodynamic performance of static take off condition with v=0 km/h and high speed condition with v=400 km/h is calculated by CFD numerical simulation method. The aerodynamic performance parameters and flow field information of propeller are obtained. The difference of tension coefficient and efficiency between the numerical calculation and theoretical calculation is 1%-2%.Therefore, the reliability of aerodynamic design of high speed helicopter tail propeller is verified.