涵道尾桨的CFD模拟与验证

于子文; 曹义华

涵道尾桨的CFD模拟与验证

北京航空航天大学航空科学与工程学院, 北京 100083

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出版历程
- 收稿日期: 2004-12-27
- 修回日期: 2005-03-07
- 刊出日期: 2006-02-28

CFD Simulation and Validation of Ducted Tail Rotor

School of Aeronautical Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 采用CFD(计算流体力学)方法分析在悬停和侧飞时直升机涵道尾桨的流场与性能。在轴对称的圆柱坐标系中,用有限容积法和SIMPLE(压力耦合方程的半隐式法)算法求解定常不可压的湍流N-S方程。在分析中,旋转的螺桨被描绘成沿螺桨桨叶展向分布的、与本地流动参数相关的、时间平均的动量源项,通过在N-S方程中加入此动量源项来替代螺桨对流体的作用。计算方法还包括涵道壁的阶梯型近似,原始变量的交错网格,k-ε湍流模型和涵道壁上的壁面函数法等措施。涵道尾桨的流场分析和性能预测同实验测量数据的良好的一致性表明,这种CFD方法可以有效的分析涵道尾桨的具体设计问题。
- 航空、航天推进系统 /
- 涵道尾桨 /
- 湍流流动 /
- 数值模拟 /
- 动量源项 /
- 壁面函数
Abstract: The flow field and performance of a helicopter ducted tail rotor in hovering and sideward flight were analyzed using CFD(Computational Fluid Dynamic) technique.At first the general governing equations of turbulent flow around ducted tail rotors were set up,and then directly solved by finite volume approach and SIMPLE(Semi-Implicit Method for Pressure-Linked Equations) approach in an axisymmetric coordinate system.The spinning fan was represented as time-averaged momentum source terms distributed along the span of the fan with functional relationship to the local flow conditions in N-S equations.The calculation method also included a stair-step representation of the shroud,staggered grid system,the k-ε turbulence model and wall function method on the shroud.The calculated results of flow field and performance correlation show good agreement with the measured data.Therefore,it is concluded that the numerical simulation technique is proved to be feasible for analyzing design issues of ducted tail rotor.
- aerospace propulsion system /
- ducted tail rotor /
- turbulent flow /
- numerical simulation /
- momentum source term /
- wall function

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参考文献(8)

[1]	Clark D R.Aerodynamic Design Rational for the Fan-in-Fin on the S-76 Helicopter[R].Presented at the 31st Annual National Forum,American Helicopter Society,Preprint 904,Washington D.C.,May 1975.
[2]	陶文铨.数值传热学[M].西安;西安交通大学出版社,1988.
[3]	Wilhelm R.Development and Testing of an Actuator Disk Boundary Condition Based on the DLR FLOWer Code[R].DLR Technical Report IB 129-99/22,Braunschweig 1999.
[4]	Brezillon J.Simulation of Rotor Fuselage Interactions by Using an Actuator Disk[R].In;Proceedings of the 26th European Rotorcra f t Forum,The Hague,The Netherlands,2000.
[5]	F Le Chuiton.Actuator Disc Modeling for Helicopter Rotors[J].Aerospace Science and Technology,2004,8; 285 ～297.
[6]	Rajagopalan R G,Lim C K.Laminar Flow Analysis of a Rotor in Hover[J].Journal of the American Helicopter Society,1991,36(1);12～23.
[7]	Rajagopalan R G,Mathur S R.Three Dimensional Analysis of a Rotor in Forward Flight[J].Journal of the American Helicopter Society,1993,38(3); 14～25.
[8]	Rajagopalan R G,Keys C N.Detailed Aerodynamic Analysis of the RAH-66 Fantaihm Using CFD[J].Journal of the American Helicopter Society,1997; 310～ 320.