Volume 30 Issue 8
Aug.  2015
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ZHOU Li, XIAO Hua, WANG Zhan-xue, LIU Zeng-wen. Effects of passive cavity on high pressure ratio single expansion ramp nozzle[J]. Journal of Aerospace Power, 2015, 30(8): 1811-1817. doi: 10.13224/j.cnki.jasp.2015.08.003
Citation: ZHOU Li, XIAO Hua, WANG Zhan-xue, LIU Zeng-wen. Effects of passive cavity on high pressure ratio single expansion ramp nozzle[J]. Journal of Aerospace Power, 2015, 30(8): 1811-1817. doi: 10.13224/j.cnki.jasp.2015.08.003

Effects of passive cavity on high pressure ratio single expansion ramp nozzle

doi: 10.13224/j.cnki.jasp.2015.08.003
  • Received Date: 2014-01-23
  • Publish Date: 2015-08-28
  • The flow control method of single expansion ramp nozzle (SERN) was investigated based on passive cavity, and the effects of passive cavity on internal flow field and performance of SERN were numerically investigated under over-expanded condition by solving Reynolds average Navier-Stokes equations, with adoption of standard two-equation k-ε turbulent model. When the pressure ratio value equals 8, the results show that the passive cavity for SERN has evident effects on the flow field structure by encouraging stable separation and affecting pressure distribution on upper expansion ramp wall, thus improving by 1.75% of the axial thrust coefficient of SERN as compared with baseline SERN, meanwhile the nose-down pitching moment does not get worse. Within the range of 3 to 13 of pressure ratio, the passive cavity can enhance the separation of boundary layer near the passive cavity for SERN, and improve the performance of SERN by decreasing the number of shock train and increasing axial thrust coefficient of SERN and pressure peak value distribution on upper expansion ramp wall.

     

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  • [1]
    Christopher A S,Jaime J M.The design and performance estimates for the propulsion module for the booster of a TSTO vehicle[R].AIAA 91-3136,1991.
    [2]
    Kevin A S,Paul L M.Structural design and analysis of a Mach zero-to-five turbo-ramjet system[R].AIAA 93-1983,1993.
    [3]
    Lynn E S,Daric W E,Rich L D,et al.Turbine based combination cycle (TBCC) propulsion subsystem integration[R].AIAA-2004-3649,2004.
    [4]
    Karen A D,Scott C A.An experimental and computational investigation of a translating throat single-expansion-ramp nozzle[R].AIAA 96-2540,1996.
    [5]
    Lederer R.Testing the actively cooled fully variable hypersonic demonstrator nozzle[R].AIAA 96-4550,1996.
    [6]
    郝东兴,王占学.下斜板可调的单膨胀斜面喷管型面设计和流场模拟[J].机械设计与制造,2009(12):8-10. HAO Dongxing,WANG Zhanxue.The design and flow field simulation of single expansion ramp nozzle with variable flaps[J].Machinery Design and Manufacture,2009(12):8-10.(in Chinese)
    [7]
    Grarnland T,Berens T.Nozzle/afterbody integration for hypersonic vehicles by means of secondary air injection[R].AIAA 95-6050,1995.
    [8]
    Eric G,Dan H.Improving off-design nozzle performance using fluidic injection[R].AIAA-2004-1206,2004.
    [9]
    刘爱华,王占学.二次流喷射对喷管流场性能的影响[J].推进技术,2007,28(2):144-147. LIU Aihua,WANG Zhanxue.Effect of secondary flow injection on flow field and performance of nozzle[J].Journal of Propulsion Technology,2007,28(2):144-147.(in Chinese)
    [10]
    Yungster S,Trefny C J.Computational study of single-expansion-ramp nozzles with external burning[R].AIAA 94-0024,1994.
    [11]
    Berens T M.Experimental and numerical analysis of a two-duct nozzle/afterbody model at supersonic Mach numbers[R].AIAA 95-6085,1995.
    [12]
    Gronland T A,Gambier J L,Wallin S.Nozzle/afterbody performance for hypersonic airbreathing vehicles[R].AIAA 97-3166,1997.
    [13]
    张少丽,单勇,张勇,等.膨胀边开槽对单边膨胀喷管性能影响的数值研究[J].推进技术,2012,33(3):436-442. ZHANG Shaoli,SHAN Yong,ZHANG Yong,et al.Numerical studies on the performances of the single expansion ramp nozzle with slots on the ramp[J].Journal of Propulsion Technology,2012,33(3):436-442.(in Chinese)
    [14]
    Thiede P,Krogmann P,Stanewsky E.Active and passive shock/boundary layer interaction control on supercritical airfoils[R].AGARD CP-365,1984.
    [15]
    Asbury S C,Gunther C L,Hunter C A.A passive cavity concept for improving the off-design performance of fixed-geometry exhaust nozzles[R].AIAA 96-2541,1996.
    [16]
    Gräsel J,Beylich A E.Passive control for the off-design performance of a single expansion ramp nozzle[R].AIAA 98-1602,1998.
    [17]
    杨承宇.S弯通道单边膨胀喷管气动和红外特性数值研究[D].南京:南京航空航天大学,2009. YANG Chengyu.Numerical investigation on pneumatic performances and infrared radiation characteristics of an s-shaped tunnel single expansion ramp nozzle[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2009.(in Chinese)
    [18]
    王占学,刘爱华,蔡元虎.高超声速推进系统用单膨胀斜面喷管型面设计和流场模拟[J].燃气涡轮试验与研究,2007,20(1):8-12. WANG Zhanxue,LIU Aihua,CAI Yuanhu.Design method and flow field simulation of single expansion ramp nozzle[J].Gas Turbine Experiment and Research,2007,20(1):8-12.(in Chinese)
    [19]
    Francis J C,Richard J R,Bare E A.Parametric investigation of single-expansion-ramp nozzles at Mach number from 0.60 to 1.20[R].NASA Technical Paper 3240,1992.
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