首页|Experimental investigation and numerical analysis on high-efficiency shock vectoring control serpentine nozzles
Experimental investigation and numerical analysis on high-efficiency shock vectoring control serpentine nozzles
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The high-efficiency Shock Vectoring Control Serpentine Nozzle(SVCSN)takes into account both thrust vectoring and infrared stealth,and significantly improves the comprehensive performance of the aero-engines through an additional auxiliary duct.In this paper,the schlieren photographs at the exit of the high-efficiency SVCSN and the wall static pressure distributions were obtained by experiments,and the numerical results were used to enrich the thrust vectoring char-acteristics.The effects of the auxiliary injection were analyzed first to reveal the advantages of the high-efficiency SVCSN compared to the conventional SVCSN.Then,the aerodynamic param-eters and the structural parameters of the high-efficiency SVCSN were investigated,including the Nozzle Pressure Ratio(NPR),the Secondary flow Pressure Ratio(SPR),the secondary flow relative area and the secondary flow injection angle.Finally,the coupling performance of the high-efficiency SVCSN is studied by using the approximate modeling technology.Results show that the auxiliary injection increases the range between the two shock legs of the"λ"shock wave induced by the sec-ondary flow,then causes the separation zone and high-pressure boss of the down wall to expand upstream,and finally results in a prominent increase in the thrust vectoring performance.The thrust vectoring angle and Vectoring Efficiency(VE)of the high-efficiency SVCSN are about 61.6％and 75.7％,respectively,higher than those of the conventional SVCSN at NPR=6.The effects of the NPR and the SPR on the thrust vectoring performance of the high-efficiency SVCSN are coupled with each other.A larger NPR matched with a smaller SPR shows better thrust vectoring perfor-mance.The maximum fluctuations in thrust vectoring angle and VE caused by the NPR and SPR are about 22％and 64％.The VE decreases monotonously with the increase of the secondary flow relative area.Smaller secondary flow injection angle shows better thrust vector performance,and the thrust vectoring angle and VE of the secondary flow injection angle of 90° are about 20％higher than those of the secondary flow injection angle of 110° at NPR=6.Therefore,the secondary flow relative area of 0.06 and the secondary flow injection angle of 90° are recommended.
Shock vectoring controlSerpentine nozzleAuxiliary injectionThrust vectoring perfor-manceFlow control
Zhonghao HUI、Jingwei SHI、Wentao LIN、Li ZHOU、Zhanxue WANG、Yongquan LIU
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School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China
National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine,Xi'an 710129,China
Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China
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