Volume 29 Issue 9
Sep.  2014
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PAN Cheng-xiong, ZHANG Jing-zhou, SHAN Yong. Pumping performance for double-stage lobe mixer/ejector[J]. Journal of Aerospace Power, 2014, 29(9): 2174-2180. doi: 10.13224/j.cnki.jasp.2014.09.022
Citation: PAN Cheng-xiong, ZHANG Jing-zhou, SHAN Yong. Pumping performance for double-stage lobe mixer/ejector[J]. Journal of Aerospace Power, 2014, 29(9): 2174-2180. doi: 10.13224/j.cnki.jasp.2014.09.022

Pumping performance for double-stage lobe mixer/ejector

doi: 10.13224/j.cnki.jasp.2014.09.022
  • Received Date: 2013-05-26
  • Publish Date: 2014-09-28
  • The pumping performances of double-stage lobe mixer/ejector were experimentally and numerically investigated. The aerodynamic characteristics difference of mixer/ejector between two inlet modes of mixing duct was illustrated and the effects of mixing duct area ratio and length-diameter ratio on the pumping performance of double-stage lobe mixer/ejector were preliminarily analyzed. The results show that the inlet mode of mixing duct has strong influence on pumping capacity. Under the present configuration parameters, the pumping capacity of single-stage lobe mixer/ejector is 10% superior to that of double-stage lobe mixer/ejector in the case of confined inlet. While in the case of open inlet, the pumping capacity is 35% superior to that of confined inlet at most. The pumping capacity of double-stage lobe mixer/ejector is stronger than that of single-stage lobe mixer/ejector. Especially for the mixing duct with bigger area ratio or less length-diameter ratio, the pumping performances of double-stage lobe mixer/ejector in the case of open inlet is superior to that of confined inlet.

     

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  • [1]
    Francois T.Internal aerodynamics of infrared suppressors for helicopter engines[J].Journal of the American Helicopter Society,1988,33(4):4-14.
    [2]
    Power G D,McClure M D,Vinh D.Advanced IR suppressor design using a combined CFD/test approach[R].AIAA 94-3215,1994.
    [3]
    Ponton T,Warnes G.Helicopter IRS engine integeration for the 'first' technology demonstrator programme[R].ASME Paper GT2007-27408,2007.
    [4]
    Presz W M,Morin B L,Gousy R G.Forced mixer lobes in ejector designs[J].Journal of Propulsion and Power,1988,4(4):350-355.
    [5]
    Skebe S,McCormick D,Presz W.Parameter effects on mixer-ejector pumping performance[R].AIAA 88-7018,1988.
    [6]
    张靖周,李立国,高潮,等.波瓣喷管红外抑制系统的实验研究[J].航空动力学报,1997,12(2):212-214. ZHANG Jingzhou,LI Liguo,GAO Chao,et al.An experimental study on a lobed nozzle of an infrared suppression system[J].Journal of Aerospace Power,1997,12(2):212-214.(in Chinese)
    [7]
    Liu Y H.Experimental and numerical investigation of circularly lobed nozzle with/without central plug[J].International Journal of Heat and Mass Transfer,2002,45(12):2577-2585.
    [8]
    Zhang J Z,Shan Y,Li L G.Computation and validation of parameter effects on lobed mixer-ejector performances[J].Chinese Journal of Aeronautics,2005,18(3):193-198.
    [9]
    张靖周,单勇,李立国.直升机排气系统用波瓣喷管引射混合式红外抑制器研究[J].航空学报,2007,28(1):32-36. ZHANG Jingzhou,SHAN Yong,LI Liguo.Investigation on lobed nozzle mixer-ejector infrared suppressor for helicopter exhaust system[J].Acta Aeronautica et Astronautica Sinica,2007,28(1):33-36.(in Chinese)
    [10]
    SHAN Yong,ZHANG Jingzhou.Numerical investigation of flow mixture enhancement and infrared radiation shield by lobed forced mixer[J].Applied Thermal Engineering,2009,29(17/18):3687-3695.
    [11]
    刘友宏,郭楠,李江宁,等.后缘切角对波瓣混合器性能影响[J].航空动力学报,2009,24(9):1917-1922. LIU Youhong,GUO Nan,LI Jiangning,et al.Effect of cut angles at trailing edge on the performance of a lobed mixer[J].Journal of Aerospace Power,2009,24(9):1917-1922.(in Chinese)
    [12]
    王先炜,黄勇,路玉霞.旋翼下洗气流对红外抑制器性能的影响研究[J].航空动力学报,2003,18(6):772-776. WANG Xianwei,HUANG Yong,LU Yuxia.Influences of the downwash flow from a helicopter rotor on the performances of an infrared suppressor[J].Journal of Aerospace Power,2003,18(6):772-776.(in Chinese)
    [13]
    唐正府,张靖周,单勇.波瓣喷管-狭长出口弯曲混合管引 射混合特性研究[J].航空动力学报,2005,20(6):978-982. TANG Zhengfu,ZHANG Jingzhou,SHAN Yong.Investigation on ejecting and mixing characteristics of lobed nozzle with curved mixing duct and slot exit[J].Journal of Aerospace Power,2005,20(6):978-982.(in Chinese)
    [14]
    唐正府,张靖周,王先炜,等.排气系统与尾机身一体化红外抑制器实验分析[J].航空动力学报,2007,22(2):233-237. TANG Zhengfu,ZHANG Jingzhou,WANG Xianwei,et al.Experimental research on infrared suppressor integrating the exhaust system with the tail part of a helicopter[J].Journal of Aerospace Power,2007,22(2):233-237.(in Chinese)
    [15]
    Bettini C,Cravero C,Cogliandro S.Multidisciplinary analysis of a complete infrared suppression system[R].ASME Paper GT2007-27721,2007.
    [16]
    王同辉,王先炜,张靖周,等.直升机红外抑制器遮挡罩间距对红外辐射特性的影响[J].航空动力学报,2009,24(7):1493-1499. WANG Tonghui,WANG Xianwei,ZHANG Jingzhou,et al.Effect of covering shelter on infrared radiation characteristics of helicopter infrared radiation suppressor[J].Journal of Aerospace Power,2009,24(7):1493-1499.(in Chinese)
    [17]
    潘丞雄,张靖周,单勇,等.引射/强迫式波瓣混合器开设通气狭缝的流动分离控制[J].航空动力学报,2013,28(2):331-337. PAN Chengxiong,ZHANG Jingzhou,SHAN Yong,et al.Flow separation control of lobed ejector/forced mixer by ventilation[J].Journal of Aerospace Power,2013,28(2):331-337.(in Chinese)
    [18]
    Presz W M,Werle M.Multi-stage mixer/ejector system[R].AIAA-2002-4064,2002.
    [19]
    鲁盼,黄勇,王方,等.面积比、波瓣张角对多级波瓣喷管性能的影响研究[J].航空发动机,2010,36(6):12-17. LU Pan,HUANG Yong,WANG Fang,et al.Area ration and lobe angle influence on the performance of multistage lobed nozzles[J].Aeroengine,2010,36(6):12-17.(in Chinese)
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