带输出轴的直升机进气道设计改进

汪明生; 黄国平; 傅鑫; 尤延铖

带输出轴的直升机进气道设计改进

南京航空航天大学能源与动力学院,南京 210016

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出版历程
- 收稿日期: 2009-11-13
- 修回日期: 2010-03-31
- 刊出日期: 2010-12-28

Study of modifying helicopter inlet containing output shaft

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

摘要

摘要: 利用自主软件NAPA对典型带输出轴的直升机进气道进行了三维流场数值分析,通过修正进气道输出轴迎风侧的管道曲率半径、在背风侧增添优化的尾锥,改进设计了原型进气道并进行了模拟.结果表明,原型进气道由于输出轴堵塞了流道,使输出轴背风侧存在很大的分离,同时迎风侧存在转弯损失,导致出口面流场畸变严重.改型进气道减小了输出轴背风侧的分离和迎风侧的转弯损失,使其既保持了高总压恢复系数,且畸变指数最大降低了74％.
- 进气道 /
- 直升机 /
- 改型设计 /
- 数值模拟 /
- 气动特性
Abstract: A typical helicopter inlet containing output shaft was studied by three-dimensional turbulent numerical calculation code NAPA in this paper.The inlet was redesigned by modifying the curvature of upwind side of the inlet and adding an optimal spike on the backward of output shaft,and then simulated using NAPA program.The results show that,as output shaft blocks the flow path in the original inlet,there is a large separation zone behind the shaft and a turn loss in upwind of the shaft,thus inducing a serious distortion in the inlet.By modification,the separation zone behind the shaft and turn loss at upwind side are reduced.Modifying inlet maintains high pressure recovery,and the distortion index is reduced by 74% at most.
- inlet /
- helicopter /
- modifying design /
- numerical simulation /

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参考文献(12)

[1]	倪先平.直升机手册[M].北京:航空工业出版社,2003.
[2]	Hamed A.Particle dynamics of inlet flow fields with swirling vanes .AIAA Paper 1981-0001,1981.
[3]	Hamed A,Jun A D,Yeuan J J.Particle dynamics simulations in inlet separator with an experimentally based bounce model .AIAA Paper 1993-2156,1993.
[4]	韩东,郭荣伟,万大为.带前输出轴直升机进气道侧滑特性[J].航空动力学报,2001,16(2):119-122. HAN Dong,GUO Rongwei,WAN Dawei.Characteristics of helicopter inlet with front output shaft at yawed flight[J].Journal of Aerospace Power,2001,16(2):119-122.(in Chinese)
[5]	韩东,郭荣伟,万大为.一种带前输出轴的直升机进气道性能试验研究[J].工程热物理学报,2001,22(6):697-699. HAN Dong,GUO Rongwei,WAN Dawei.An investigation of the flow in a helicopter intake with front output shaft[J].Journal of Engineeing Thermophysics,2001,22(6):697-699.(in Chinese)
[6]	杨永飞.某型直升机机身及进气道气动特性分析[J].直升机技术,2008,155(3):103-106. YANG Yongfei.Aerodynamic characteristic analysis about a fuselage/intake of some helicopter[J].Helicopter Technique,2008,155(3):103-106.(in Chinese)
[7]	Han D,Guo R W,Wan D W,et al.Characteristic flow in a partially dynamic helicopter inlet[J].Transactions of Nanjing University of Aeronautics and Astronautics,2001,18(２):151-156.
[8]	谢永奇,余建祖,高红霞,等.某型直升机进气舱流场数值仿真[J].航空动力学报,2007,22(5):728-732. XIE Yongqi,YU Jianzu,GAO Hongxia,et al.Numerical simulation of airflowfield of helicopter inlet cabin[J].Journal of Aerospace Power,2007,22(5):728-732.(in Chinese)
[9]	Baldwin B S,Lomax H.Thin layer approximation and algebraic model for separeted turbulent flows .AIAA Paper 1978-0257,1978.
[10]	Visbal M,Knight D.Evaluation of the Baldwin-Lomax turbulence model for two-dimensional shock wave boundary layer interactions .AIAA Paper 1983-1697,1983.
[11]	黄国平,梁德旺.一种改进的MUSCL格式[J].南京航空航天大学学报,1997,29(3):277-282. HUANG Guoping,LIANG Dewang.Improvement on MUSCL scheme[J].Journal of Nanjing University of Aeronautics and Astronautics,1997,29(3):277-282.(in Chinese)
[12]	梁德旺,黄国平,赵海峰.B/L湍流模型在强压力梯度流场计算中的应用[J].南京航空航天大学学报,1999,31(1):37-42. LIANG Dewang,HUANG Guoping,ZHAO Haifeng.Application of B/L turbulence model for calculating flow with strong adverse pressure gradient[J].Journal of Nanjing University of Aeronautics and Astronautics,1999,31(1):37-42.(in Chinese)