激波管管长对阶跃压力波形的影响分析
|
摘要
激波管作为动态压力校准装置,其产生的阶跃压力幅值大小,以及平台时间是对阶跃压力进行测量校准的重要指标。基于理想情况下,选择管腔内气体介质为空气,通过理论分析得到了使得阶跃平台时间最长的高低压腔长度比优化设计方案。在考虑由实际激波管管腔内的黏性所导致的激波衰减情况时,通过仿真方式对理论结果进行误差分析,得到理想情况下与实际的偏差度。结果表明,在有黏情况下压力幅值随距离增加而逐渐减小,同时入射激波的马赫数在底端面附近呈线性衰减,衰减系数随马赫数增加而增大,而在入射激波马赫数相同时,低压腔越长,底端面附近位置处的衰减系数越小。同时利用仿真结论对实验测量计算马赫数结果进行修正,减小底端面位置处的真实值与实验计算值之间的误差。
A shock tube is taken as a dynamic pressure calibration device. Its produced step pressure amplitude and platform time are two important indexes for step pressure measurement and calibration. Here, based on the ideal case, air was chosen as gas medium in tub cavity of the shock tube, the design scheme for the optimization of the length ratio between high pressure tub cavity and low pressure one to produce the longest step platform time was obtained through theoretical analysis. Considering the shock wave attenuation case due to viscosity in the actual shock tube, the error analysis was done for the theoretical results through simulation to get the degree of deviation between the ideal case and the actual one. The simulation results showed that in viscous case, the pressure amplitude gradually decreases with increase in distance; at the same time, Mach number of incident shock wave reveals a linear attenuation near the bottom end surface, the attenuation coefficient increases with increase in Mach number; if with the same incident shock wave Mach number, the longer the low pressure tube cavity, the smaller the attenuation coefficient near the bottom end surface. The simulation results were used to modify Mach number obtained in test measurements to reduce the error between the actual value at the bottom end surface and the test calculated one.
A shock tube is taken as a dynamic pressure calibration device. Its produced step pressure amplitude and platform time are two important indexes for step pressure measurement and calibration. Here, based on the ideal case, air was chosen as gas medium in tub cavity of the shock tube, the design scheme for the optimization of the length ratio between high pressure tub cavity and low pressure one to produce the longest step platform time was obtained through theoretical analysis. Considering the shock wave attenuation case due to viscosity in the actual shock tube, the error analysis was done for the theoretical results through simulation to get the degree of deviation between the ideal case and the actual one. The simulation results showed that in viscous case, the pressure amplitude gradually decreases with increase in distance; at the same time, Mach number of incident shock wave reveals a linear attenuation near the bottom end surface, the attenuation coefficient increases with increase in Mach number; if with the same incident shock wave Mach number, the longer the low pressure tube cavity, the smaller the attenuation coefficient near the bottom end surface. The simulation results were used to modify Mach number obtained in test measurements to reduce the error between the actual value at the bottom end surface and the test calculated one.
引文
[1] 范毓润,韩惠霖,李玉麟.高动压激波管中的真实气体效应[J].计量学报,1990(1):37-41.FAN Yurun,HAN Huilin,LI Yulin.The real-gas effect in the high dynamical shock tube[J].Journal of Bionics Engineering,1990(1):37-41.
[2] 葛竹,马铁华,杜红棉,等.不同驱动气体对激波管校准系统特性的影响分析[J].中国测试,2017(43):125-128.GE Zhu,MA Tiehua,DU Hongmian,et al.Effects of different gases on the characteristics of shock tube calibration system[J].Chin Measurement & Test,2017(43):125-128.
[3] 黄芬.压力动态标准方法研究[D].南京:南京理工大学,2003.
[4] YU Hongru.Oxyhydrogen combustion and detonation driven shock tube[J].Mechanical Sinica (English Series),1999:97-107.
[5] 薛莉.双膜激波管技术在动压校准中的研究[D].太原:中北大学,2014.
[6] 杨军,李程,王维,等.双腔负压法用于激波管动态压力校准[J].计量学报,2012,33(3):240-243.YANG Jun,LI Cheng,WANG Wei,et al.Double-chamber negative pressure method in the dynamic pressure calibration of the shock tube[J].Journal of Measurement,2012,33(3):240-243.
[7] 全鹏程,易仕和,武宇,等.激波与层流湍流边界层相互作用实验研究[J].物理学报,2014,63:084703.QUAN Pengcheng,YI Shihe,WU Yu,et al.The experimental study of the interaction between the shock wave and boundary layers of laminar and turbulent[J].Journal of Physics,2014,63:084703.
[8] 袁俊先,蔡菁.激波管长度对阶跃压力恒定时间的影响[J].计测技术,2012(增刊1):78-80.YUAN Junxian,CAI Jing.The effect of the length of the shock tube on the constant time[J].Metrology & Measurement Technology,2012(Sup 1):78-80.
[9] HOLDER D W,SCHULTZ D L.On the flow in a reflected-shock tunnel[M].London,UK:HMSO,1962.
[10] TEICHTER J.Design of a shock tube[M].Boras,Sweden:SP Measurement Technology,2005.
[11] 陈强.激波管流动的理论和实验技术[M].合肥:中国科技大学,1979.
[12] BEAN V E,BOWERS W J,HURST,et al.Development of a primary standard for the measurement of dynamic pressure and temperature[J].Metrologia,2015,30(6):747-750.
[13] DOWNS S,KNOTT A,ROBINSON I.Towards a shock tube method for the dynamic calibration of pressure sensors[R].National Physical Laboratory,R.Soc.A 2014,372,20130299.
[14] 杨帆.大口径激波管动态校准系统设计[D].太原:中北大学,2016.
[15] GROGAN K P,IHME M.Regimes describing shock boundary layer interaction and ignition in shock tubes[J].Proceedings of the Combustion Institute,2017,36(2):2927-2935.
[2] 葛竹,马铁华,杜红棉,等.不同驱动气体对激波管校准系统特性的影响分析[J].中国测试,2017(43):125-128.GE Zhu,MA Tiehua,DU Hongmian,et al.Effects of different gases on the characteristics of shock tube calibration system[J].Chin Measurement & Test,2017(43):125-128.
[3] 黄芬.压力动态标准方法研究[D].南京:南京理工大学,2003.
[4] YU Hongru.Oxyhydrogen combustion and detonation driven shock tube[J].Mechanical Sinica (English Series),1999:97-107.
[5] 薛莉.双膜激波管技术在动压校准中的研究[D].太原:中北大学,2014.
[6] 杨军,李程,王维,等.双腔负压法用于激波管动态压力校准[J].计量学报,2012,33(3):240-243.YANG Jun,LI Cheng,WANG Wei,et al.Double-chamber negative pressure method in the dynamic pressure calibration of the shock tube[J].Journal of Measurement,2012,33(3):240-243.
[7] 全鹏程,易仕和,武宇,等.激波与层流湍流边界层相互作用实验研究[J].物理学报,2014,63:084703.QUAN Pengcheng,YI Shihe,WU Yu,et al.The experimental study of the interaction between the shock wave and boundary layers of laminar and turbulent[J].Journal of Physics,2014,63:084703.
[8] 袁俊先,蔡菁.激波管长度对阶跃压力恒定时间的影响[J].计测技术,2012(增刊1):78-80.YUAN Junxian,CAI Jing.The effect of the length of the shock tube on the constant time[J].Metrology & Measurement Technology,2012(Sup 1):78-80.
[9] HOLDER D W,SCHULTZ D L.On the flow in a reflected-shock tunnel[M].London,UK:HMSO,1962.
[10] TEICHTER J.Design of a shock tube[M].Boras,Sweden:SP Measurement Technology,2005.
[11] 陈强.激波管流动的理论和实验技术[M].合肥:中国科技大学,1979.
[12] BEAN V E,BOWERS W J,HURST,et al.Development of a primary standard for the measurement of dynamic pressure and temperature[J].Metrologia,2015,30(6):747-750.
[13] DOWNS S,KNOTT A,ROBINSON I.Towards a shock tube method for the dynamic calibration of pressure sensors[R].National Physical Laboratory,R.Soc.A 2014,372,20130299.
[14] 杨帆.大口径激波管动态校准系统设计[D].太原:中北大学,2016.
[15] GROGAN K P,IHME M.Regimes describing shock boundary layer interaction and ignition in shock tubes[J].Proceedings of the Combustion Institute,2017,36(2):2927-2935.