基于流场探测的发动机喘振控制仿真研究
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摘要
为使冲压发动机性能最优并始终工作在安全状态,需要使其工作的喘振裕度最小且在喘振边界内。在喘振边界安装一种能够准确分辨超声速或亚声速流场状态的流场探测装置,控制进气道结尾激波位置。针对一维变截面流动控制方程,研究了流场探测装置的安装位置,以及激波越过流场探测装置后控制系统的减油规律。仿真研究结果表明,用试验数据修正理论仿真的方法可以准确地捕捉进气道结尾激波,同时根据某型冲压发动机的设计临界喘振裕度,确定了流场探测装置安装位置位于距进气道锥尖的距离;进气道沿程压力跟随发动机燃油流量的变化而变化,压力波传播时间相对于燃油调节时间可以忽略;由于进气道内激波前后运动存在明显的压力滞环现象,当激波越过喘振边界时,进气道出口压力会进一步上升,发动机喘振危险加大,应使用加速电磁阀快速减小燃油流量,控制激波回到安全区域。
In order to make the ramjet performance optimization and always work in a security state,the ramjet's buzz margin should be keep in minimum and within the buzz boundary. A flow field detecting device that can distinguish the supersonic or subsonic flow field status is installed in the buzz boundary to control shock wave location at the intake terminal. Aiming at the one-dimensional variable cross-section flow control equations,the installation position of the flow field detecting device and the fuel reduction law of the control system after the shock wave goes through flow field detecting device are studied in this paper. The simulation result indicates that the method to use the test data to correct theoretical simulation data can accurately catch the shock wave at intake terminal,and according tothe critical buzz margin designed for a certain type ramjet,can determine the installation location of the shock exploring device. The pressure along intake changes with the variation of engine's fuel flow,pressure wave propagation time relative to the fuel regulating time can be ignored. As the existence of the pressure hysteresis phenomenon is obvious before and after the intake shock motion,when the shock goes through the buzz boundary,the pressure at intake exit will rise further,the engine buzz risk increases,and the acceleration electromagnetic valve should be adopted to quickly reduce fuel flow,so as to make the shock wave go back to a safe area.
In order to make the ramjet performance optimization and always work in a security state,the ramjet's buzz margin should be keep in minimum and within the buzz boundary. A flow field detecting device that can distinguish the supersonic or subsonic flow field status is installed in the buzz boundary to control shock wave location at the intake terminal. Aiming at the one-dimensional variable cross-section flow control equations,the installation position of the flow field detecting device and the fuel reduction law of the control system after the shock wave goes through flow field detecting device are studied in this paper. The simulation result indicates that the method to use the test data to correct theoretical simulation data can accurately catch the shock wave at intake terminal,and according tothe critical buzz margin designed for a certain type ramjet,can determine the installation location of the shock exploring device. The pressure along intake changes with the variation of engine's fuel flow,pressure wave propagation time relative to the fuel regulating time can be ignored. As the existence of the pressure hysteresis phenomenon is obvious before and after the intake shock motion,when the shock goes through the buzz boundary,the pressure at intake exit will rise further,the engine buzz risk increases,and the acceleration electromagnetic valve should be adopted to quickly reduce fuel flow,so as to make the shock wave go back to a safe area.
引文
[1]TRAPIERSimon,DECK Sébastien,DUVEAU Philippe,et al.Time-frequency analysis and detection of supersonic inlet buzz[J].AIAA journal,2007 45(9):7-13.
[2]STERBENTZ W,EVVARD J.Criterions for prediction and control of ramjet flow pulsations:NACA RM E51C27[R].USA:NACA,1951.
[3]NEWSOME R.Numerical simulation of near-critical and unsteady,subcritical inlet flow[J].AIAA journal,1984,22(10):1375-1379.
[4]LU P J,JAIN L T.Numerical investigation of inlet buzz flow[J].Journal of propulsion and power,1998,14(1):90-100.
[5]TRAPIER S,DECK S,DUVEAU P,et al.Delayed detached-eddy simulation of supersonic inlet buzz:AIAA2007-4353[R].USA:AIAA,2007.
[6]FERRI A,NUCCI L M.The origin of aerodynamic instability of supersonic inlets at subcritical conditions:NACA RM L50K30[R].USA:NACA,1951.
[7]DAILEY C L.Supersonic diffuser instability[D].Pasadena,CA:California Inst.of Technology,1954.
[8]TRIMPI R.A Theory for stability and buzz pulsation amplitude in ramjets and an experimental investigation including scale effects[R].USA:NACA Rept,1956.
[9]FISHER S A,NEALE M C,BROOKS A J.On the subcritical stability of variable ramp intakes at Mach numbers around 2:ARC-R/M-3711[R].England:National Gas Turbine Establishment,1970.
[10]NAGASHIMA T,OBOKATA T,ASANUMA T.Experiment of supersonic air intake buzz[R]Tokyo:Institute of Space and Aeronautical Science,1972.
[11]HONGPRAPAS Sorarat,KOZAK J D,MOSES Brooks,et al.A small scale experiment for investigating the stability of a supersonic inlet[J].AIAA journal,1997,27:1031-1037
[12]孙健国,黄金泉.发动机喘振裕度自适应控制[J].航空动力学报.1993.7(3):279-282.
[13]何中伟,张世英.轴对称超音速进气道喘振及其控制[J].航空学报.1983(2):73-82.
[14]OHSHIMA Takao,KANBE Katsuhiro.Control of the intake shock-position in the test rig for ramjet engine:AIAA 1977-2885[R].USA:AIAA,1977.
[15]STERBENTZ W H.,EVVARD J C.Criterions for prediction and control of ram-jet flow pulsations:NACA3506[R].USA:NACA,1955.
[16]CROWL R,DUNBAR W R,WENTWORTH C.Experimental investigation of marquard shock-positioning control unit on a 28-inch ramjet engine:NACA RM E56E09[R].USA:NACA,1967.
[17]HURRELLH G,VASU George,DUNBAR W R.Experimental study of shock-positioning method of ram-jet-engine control:NACA RM E55F21[R].USA:NACA,1955.
[2]STERBENTZ W,EVVARD J.Criterions for prediction and control of ramjet flow pulsations:NACA RM E51C27[R].USA:NACA,1951.
[3]NEWSOME R.Numerical simulation of near-critical and unsteady,subcritical inlet flow[J].AIAA journal,1984,22(10):1375-1379.
[4]LU P J,JAIN L T.Numerical investigation of inlet buzz flow[J].Journal of propulsion and power,1998,14(1):90-100.
[5]TRAPIER S,DECK S,DUVEAU P,et al.Delayed detached-eddy simulation of supersonic inlet buzz:AIAA2007-4353[R].USA:AIAA,2007.
[6]FERRI A,NUCCI L M.The origin of aerodynamic instability of supersonic inlets at subcritical conditions:NACA RM L50K30[R].USA:NACA,1951.
[7]DAILEY C L.Supersonic diffuser instability[D].Pasadena,CA:California Inst.of Technology,1954.
[8]TRIMPI R.A Theory for stability and buzz pulsation amplitude in ramjets and an experimental investigation including scale effects[R].USA:NACA Rept,1956.
[9]FISHER S A,NEALE M C,BROOKS A J.On the subcritical stability of variable ramp intakes at Mach numbers around 2:ARC-R/M-3711[R].England:National Gas Turbine Establishment,1970.
[10]NAGASHIMA T,OBOKATA T,ASANUMA T.Experiment of supersonic air intake buzz[R]Tokyo:Institute of Space and Aeronautical Science,1972.
[11]HONGPRAPAS Sorarat,KOZAK J D,MOSES Brooks,et al.A small scale experiment for investigating the stability of a supersonic inlet[J].AIAA journal,1997,27:1031-1037
[12]孙健国,黄金泉.发动机喘振裕度自适应控制[J].航空动力学报.1993.7(3):279-282.
[13]何中伟,张世英.轴对称超音速进气道喘振及其控制[J].航空学报.1983(2):73-82.
[14]OHSHIMA Takao,KANBE Katsuhiro.Control of the intake shock-position in the test rig for ramjet engine:AIAA 1977-2885[R].USA:AIAA,1977.
[15]STERBENTZ W H.,EVVARD J C.Criterions for prediction and control of ram-jet flow pulsations:NACA3506[R].USA:NACA,1955.
[16]CROWL R,DUNBAR W R,WENTWORTH C.Experimental investigation of marquard shock-positioning control unit on a 28-inch ramjet engine:NACA RM E56E09[R].USA:NACA,1967.
[17]HURRELLH G,VASU George,DUNBAR W R.Experimental study of shock-positioning method of ram-jet-engine control:NACA RM E55F21[R].USA:NACA,1955.