Low noise design of fan outlet guide vane, part Ⅰ: Method and optimization

被引：0
|
作者：
Jiang Y. [1 ]
Zheng W. [1 ]
Zhao H. [1 ]
Yang M. [1 ]
Wang Y. [1 ]
机构：
[1] Shenyang Engine Research Institute of AECC, Shenyang
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2019年 / 40卷 / 10期
关键词：
3D lifting surface theory; Aerodynamic and acoustic integrated design; Duct acoustic theory; High bypass ratio turbofan; Rotor/stator interaction noise;
D O I：
10.7527/S1000-6893.2019.22955
中图分类号：
学科分类号：
摘要：
As the first part of the "Low noise design of fan outlet guide vane" serial articles, this paper proposes an integrated aerodynamic and acoustic design method. The influence of axial sweep and circumferential lean of Outlet Guide Vane (OGV) on the rotor wake/stator interaction noise of a modern high-bypass ratio fan stage is investigated. To improve the evaluation efficiency in the design process, an analytic model for the rotor/stator interaction noise is employed based on the three dimensional lifting surface and duct acoustic theories. A rotor wake model whose parameters are obtained from throughflow calculation and blade design steps is also applied. The rotor/stator interaction noises of different combinations of sweep and lean angles are examined to obtain the effect graph, which is used to choose a prime combination of sweep and lean angles as the starting point of the following optimization. During the optimization, the chord length and blade tip meridian position are fixed, and a genetic algorithm is employed to obtain the final leading edge and stack line shape of OGV. The two obtained swept and leaned vanes can gain a promising reduction of interaction noise at least of 8 dB. © 2019, Press of Chinese Journal of Aeronautics. All right reserved.
引用
收藏
相关论文
共 21 条
  • [1] Lighthill M.J., On sound generated aerodynamically. II Turbulence as a source of sound, Proceeding of the Royal Society of London, Series A, 211, 1107, pp. 564-587, (1952)
  • [2] Rainer S., Investigation of the tonal acoustic field of a transonic fanstage by time-domain CFD-calculations with arbitrary blade counts: GT2004-54216, (2004)
  • [3] Kroger G., Schnell R., Humphreys N.D., Optimised aerodynamic design of an OGV with reduced blade count for low noise aircraft engines: GT2012-69459, (2012)
  • [4] Anil P., Dilip P., Unsteady aerodynamics and aeroacoustics of a high-bypass ratio fan stage: GT2004-53955, (2004)
  • [5] Cumpsty N.A., A critical review of turbomachinery noise, ASME Journal of Fluids Engineering, 99, pp. 278-293, (1977)
  • [6] Sun X.F., Zhou S., Aeroacoustics, pp. 94-95, (1993)
  • [7] Schnell R., Investigation of the tonal acoustic field of a transonic fanstage by time-domain CFD-calculations with arbitrary blade counts: GT2004-54216, (2004)
  • [8] Tyler J.M., Sofrin T.G., Axial flow compressor noise studies, SAE Trans, 70, pp. 309-332, (1962)
  • [9] Woodward R.P., Elliott D.M., Hughes C.E., Et al., Benefit of swept-and-leaned stators for fan noise reduction, Journal of Aircraft, 28, 6, pp. 1130-1138, (2001)
  • [10] Kazin S.B., Radially leaned outlet guide vanes for fan source noise reduction: CR-134486, (1973)
123