多喷嘴超声速引射器数值仿真与试验研究
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摘要
本文采用数值仿真和试验两种方法对多喷嘴超声速引射器进行了研究。
首先对二维构型的超声速引射器进行了数值计算,研究了零二次流和带二次流时的流场结构,同时对影响其启动性能和引射性能的因素如引射马赫数、混合室收缩角等进行了分析。其次对试验件的内流场进行了三维数值仿真,仿真结果与试验数据比较吻合。在此基础上,分析得到:在混合室前段多股超声速引射气流相互撞击所造成的能量损失是造成该型引射器启动困难的主要原因;采用多个引射喷嘴使一、二次流的混合面积大大增加,改善了引射器的引射性能。
试验方面则探讨了引射喷嘴的安装构型、混合室收缩比等因素对多喷嘴超声速引射器启动性能的影响,得到影响该型超声速引射器启动性能的一些结论;提出了利用二次流对一次流的“助推”作用来改善引射器启动性能的方法;分析了一次流总压和引射喷嘴安装构型对引射器引射能力的影响。结果表明:较低的一次流总压能够更好地满足更低总压的二次流的引射需要;合理的喷嘴安装构型意味着更高的引射性能。
The CFD and experimental methods were introduced to study the multi-nozzle supersonic ejector.
Firstly, the flow-field of a two dimensional ejector with and without induced flow was simulated, the key parameters affecting the starting performance and ejecting performance, such as the primary flow mach number, were analyzed. The 3-D numerical results approximately agreed with the experiment data. At the same time, the following conclusions could be drawn: the flow loss caused by the collision of multi-primary flow was the chief reason for difficulties in starting of the ejector; by increasing the mixing area, improved ejecting performance could be obtained by multi-nozzle.
The influences of ejecting-nozzle assembling configuration and the contraction ratio of mixing chamber on the starting performance were studied in detail, and some valuable conclusions could be drawn. It was found that the secondary-flow could act as a“booster”, which helped to improve starting performance of the multi-nozzle ejector. Moreover, it was discovered that the lower the primary flow total pressure, the better for the secondary flow with lower total pressure to be ejected; and a reasonable ejecting-nozzle assembling configuration meant good performance for multi-nozzle ejector.
首先对二维构型的超声速引射器进行了数值计算,研究了零二次流和带二次流时的流场结构,同时对影响其启动性能和引射性能的因素如引射马赫数、混合室收缩角等进行了分析。其次对试验件的内流场进行了三维数值仿真,仿真结果与试验数据比较吻合。在此基础上,分析得到:在混合室前段多股超声速引射气流相互撞击所造成的能量损失是造成该型引射器启动困难的主要原因;采用多个引射喷嘴使一、二次流的混合面积大大增加,改善了引射器的引射性能。
试验方面则探讨了引射喷嘴的安装构型、混合室收缩比等因素对多喷嘴超声速引射器启动性能的影响,得到影响该型超声速引射器启动性能的一些结论;提出了利用二次流对一次流的“助推”作用来改善引射器启动性能的方法;分析了一次流总压和引射喷嘴安装构型对引射器引射能力的影响。结果表明:较低的一次流总压能够更好地满足更低总压的二次流的引射需要;合理的喷嘴安装构型意味着更高的引射性能。
The CFD and experimental methods were introduced to study the multi-nozzle supersonic ejector.
Firstly, the flow-field of a two dimensional ejector with and without induced flow was simulated, the key parameters affecting the starting performance and ejecting performance, such as the primary flow mach number, were analyzed. The 3-D numerical results approximately agreed with the experiment data. At the same time, the following conclusions could be drawn: the flow loss caused by the collision of multi-primary flow was the chief reason for difficulties in starting of the ejector; by increasing the mixing area, improved ejecting performance could be obtained by multi-nozzle.
The influences of ejecting-nozzle assembling configuration and the contraction ratio of mixing chamber on the starting performance were studied in detail, and some valuable conclusions could be drawn. It was found that the secondary-flow could act as a“booster”, which helped to improve starting performance of the multi-nozzle ejector. Moreover, it was discovered that the lower the primary flow total pressure, the better for the secondary flow with lower total pressure to be ejected; and a reasonable ejecting-nozzle assembling configuration meant good performance for multi-nozzle ejector.
引文
[1] 庄琦等. 化学激光器 [M].
[2] 庄琦, 桑凤亭. 短波长化学激光器 [M]. 国防工业出版社, 1997
[3] R.W.F.格罗斯, J.L.博特. 化学激光手册 [M]
[4] K.L.科姆帕. 化学激光 [M]. 科学出版社, 1981
[5] 谈洪, 朱宗厚. 气动激光技术[M]. 国防工业出版社, 1977
[6] H.Schrelber. Multi-stage steam ejector methodology:model development and application to high energy lasers [C]. AIAA paper, 1985
[7] http://www.airborne.com
[8] http://www.trw.com
[9] Dr.Josel Shwartz, Tactical High Energy Laser [J]. SPIE Vol.4632,P.10-20,2002
[10] Fabri J,Siestrunck R. Supersonic Air Ejector [J]. Advances in Applied Mechanics, 1958
[11] Emanuel.G. Optimum Performance for A Single-Stage Gaseous Ejector [J]. AIAA Journal, 1976
[12] Dutton.J.C, Mikkelsen.C.D, et al. A Theoretical and Experimental Investigation of the Constant Area, Supersonic-Supersonic Ejector [J]. AIAA Journal, 1982
[13] Nagaraja.K.S, Hammond.D.L. One-Dimensional Compressible Ejector Flows [J], AIAA,1973
[14] Tillman.T.G, Paterson.R.W, et al. Supersonic Nozzle Mixer Ejector [J]. Journal of Propulsion and Power, 1992
[15] 沈坚, 胡国新. 引射器及引射系统在工程中的应用 [J] , 煤气与热力, 2005.1
[16] 冲压发动机技术 [M],约翰霍普金斯大学应用物理实验室
[17] 徐万武. 高性能、大压缩比化学激光器压力恢复系统研究 [D], 国防科学技术大学研究生院, 博士学位论文, 2003
[18] Barton.D.L, Taylor.D. An Investigation of Ejectors Without Induced Flow,Phase I [J]. AEDC-TN-59-145, 1959
[19] Taylor.D, Barton.D.L, Simmons.M. An Investigation of Cylindrical Ejectors Equipped With Truncated Conical Inlets, Phase II [J]. AEDC-TN-60-224, 1961
[20] German.R.C, Bauer.R.C. The Effect of Diffuser Length on the Performance of Ejectors Without Induced Flow [J]. AEDC-TN-61-89, 1961
[21] Bauer.R.C, German.R.C. Some Reynolds Number Effects on the Performance of Ejectors Without Induced Flow [J]. AEDC-TN-61-87, 1961
[22] Bauer.R.C, German.R.C. The Effect of Second Throat Geometry on thePerformance of Ejectors Without Induced Flow [J]. AEDC-TN-61-133, 1961
[23] James.W.Hale. Comparison of Diffuser-Ejector Performance With Five Different Driving Fluids [J]. AEDC-TDR-63-207, 1963
[24] 张靖周, 单勇. 二维引射-混合器内流场的数值分析 [J]. 航空动力学报, 1997, Vol.23, NO.5
[25] 徐万武, 谭建国, 王振国. 高空模拟试车台超声速引射器数值研究 [J]. 固体火箭技术, 2003, Vol.26, NO.2
[26] Falin Chen, C.F.Liu, J.Y.Yang. Supersonic Flow in Second-Throat Ejector-Diffuser System [J]. Journal of Spacecraft and Rockets, 1994, Vol.31, NO.1
[27] Y.Bartosiewicz, Zine Aidoun, P.Desevaux, Yves Mercadier. Numerical and Experiment Investigations on Supersonic Ejectors [J]. International Journal of Heat and Fluid Flow, 2004
[28] 徐华舫. 空气动力学基础 [M]. 北京航空学院出版社, 1986
[29] Fluent 用户手册
[30] 徐万武, 邹建军, 王振国. 超声速环形引射器启动特性试验研究 [J] , 火箭推进, 2005, 31(6)
[31] Stephens.S.E, Bates.L.B. Effect of Geometric Parameters on the Performance of Second Throat Annular Steam Ejectors [J]. TN:Anold Engnieering Development Center, Anold Air Force Station, 1991
[32] Hale.J.W. Diffuser Auxiliary Ejector Development for the Design of the L-3 LEM Descent Exhaust System [J]. AEDC-TR-65-255, 1965
[33] Hale.J.W. Investigation of Two-Nozzle-Cluster Diffuser-Ejector With and Without Ejected Mass [J]. AEDC-TDR-63-130, 1963
[34] Hale.J.W. Influence of Dertinent Parameters on Ejector-Diffuser Performance With and Without Ejected Mass [J]. AEDC-TDR-64-134, 1964
[35] Panesci.J.H, German.R.C. An Analysis of Second-Throat Diffuser Performance for Zero-Secondary-Flow Ejector System [J]. AEDC-TDR-63-249, 1964
[36] B.J. Huang, J.M. Chang, C.P. Wang, V.A.Petrenko. A 1-D analysis of ejector performance [J]. International Journal of Refrigeration, 1999, 354-364
[37] Dario Pastrone. An Analysis of the Ejector-Ram-Rocket Engine [J]. AIAA Journal, 2004
[38] D. Lineberry, Dr. B. Landrum, Effects of Multiple Nozzles on Asymmetric Ejector Performance [J]. AIAA Journal, 2005
[39] Hiroki Nagaoka, Sachio Suzuki, Fumio Wani. Ejector COIL Employing Coanda Effect [J]. AIAA Journal, 2005
[40] M. S. Balasubramanyam, D. B. Landrum, C. P. Chen, D. Lineberry. Numerical Investigation of Cold Flow Non-Axisymmetric Ejectors [J]. AIAA Journal, 2005
[41] Eijiro Kitamura. Pressure Recovery in Mixing Ducts of Ejector-ramjets [J]. AIAA Journal, 2005
[42] M. Ouzzane, Z. Aidoun. Model development and numerical procedure for detailed ejector analysis and design [J]. Applied Thermal Engineering, 2003
[43] Robert F.Walter, Robert A.O. Pressure Recovery in COIL Devices [J]. AIAA Journal, 1994
[44] Heuydong Kim, Youngki Lee. Numerical Simulation of the Supersonic Flows in the Second Throat Ejector-Diffuser Systems [J]. Journal of Thermal Science, 1999, Vol.8, No.4
[45] Heuy-Dong Kim, Toshiaki Setoguchi, Shen Yu, S.Raghunathan. Navier-Stokes Computations of the Supersonic Ejector-Diffuser System With a Second Throat [J]. Journal of Thermal Science, Vol.8, No.2
[46] Eijiro Kitamura, Tohru Mitani, Shenhong Huang, Goro Masuya. Pressure Recovery in Mixing Ducts of Ejector-Ramjets [J]. AIAA Journal, 2005
[47] J.A.Horkovich. Airborne Laser Pressure Recovery System Numerical Simulations [J]. AIAA Journal, 1993
[48] E.D.Rogdakis, G..K.Alexis. Design and Parametric Investigation of an Ejector in an Air-Conditioning System [J]. Applied Thermal Engineering, 2000
[49] G..N.Kumar, D.O.Griffith II, J.F.Fay. Multi-Plume Launch Vehicle Base Region Radiative Load Predictions [J]. AIAA Journal, 1994
[50] Houshang B.Ebrahimi. Numerical Investigation of Multi-Plume Rocket Phenomenology [J]. AIAA Journal, 1997
[51] 徐万武, 谭建国, 王振国. 二次流对超声速环型空气引射器真空度的影响 [J].国防科技大学学报, 2003, Vol.25, No.3
[52] 贺军科, 吴雄. 被动式引射器内流场数值研究 [J]. 固体火箭技术, 2005, Vol.28, No.2
[53] 徐万武, 王振国. 环形超声速空气引射器零二次流流场数值研究 [J]. 推进技术, 2003, Vol.24, No.1
[2] 庄琦, 桑凤亭. 短波长化学激光器 [M]. 国防工业出版社, 1997
[3] R.W.F.格罗斯, J.L.博特. 化学激光手册 [M]
[4] K.L.科姆帕. 化学激光 [M]. 科学出版社, 1981
[5] 谈洪, 朱宗厚. 气动激光技术[M]. 国防工业出版社, 1977
[6] H.Schrelber. Multi-stage steam ejector methodology:model development and application to high energy lasers [C]. AIAA paper, 1985
[7] http://www.airborne.com
[8] http://www.trw.com
[9] Dr.Josel Shwartz, Tactical High Energy Laser [J]. SPIE Vol.4632,P.10-20,2002
[10] Fabri J,Siestrunck R. Supersonic Air Ejector [J]. Advances in Applied Mechanics, 1958
[11] Emanuel.G. Optimum Performance for A Single-Stage Gaseous Ejector [J]. AIAA Journal, 1976
[12] Dutton.J.C, Mikkelsen.C.D, et al. A Theoretical and Experimental Investigation of the Constant Area, Supersonic-Supersonic Ejector [J]. AIAA Journal, 1982
[13] Nagaraja.K.S, Hammond.D.L. One-Dimensional Compressible Ejector Flows [J], AIAA,1973
[14] Tillman.T.G, Paterson.R.W, et al. Supersonic Nozzle Mixer Ejector [J]. Journal of Propulsion and Power, 1992
[15] 沈坚, 胡国新. 引射器及引射系统在工程中的应用 [J] , 煤气与热力, 2005.1
[16] 冲压发动机技术 [M],约翰霍普金斯大学应用物理实验室
[17] 徐万武. 高性能、大压缩比化学激光器压力恢复系统研究 [D], 国防科学技术大学研究生院, 博士学位论文, 2003
[18] Barton.D.L, Taylor.D. An Investigation of Ejectors Without Induced Flow,Phase I [J]. AEDC-TN-59-145, 1959
[19] Taylor.D, Barton.D.L, Simmons.M. An Investigation of Cylindrical Ejectors Equipped With Truncated Conical Inlets, Phase II [J]. AEDC-TN-60-224, 1961
[20] German.R.C, Bauer.R.C. The Effect of Diffuser Length on the Performance of Ejectors Without Induced Flow [J]. AEDC-TN-61-89, 1961
[21] Bauer.R.C, German.R.C. Some Reynolds Number Effects on the Performance of Ejectors Without Induced Flow [J]. AEDC-TN-61-87, 1961
[22] Bauer.R.C, German.R.C. The Effect of Second Throat Geometry on thePerformance of Ejectors Without Induced Flow [J]. AEDC-TN-61-133, 1961
[23] James.W.Hale. Comparison of Diffuser-Ejector Performance With Five Different Driving Fluids [J]. AEDC-TDR-63-207, 1963
[24] 张靖周, 单勇. 二维引射-混合器内流场的数值分析 [J]. 航空动力学报, 1997, Vol.23, NO.5
[25] 徐万武, 谭建国, 王振国. 高空模拟试车台超声速引射器数值研究 [J]. 固体火箭技术, 2003, Vol.26, NO.2
[26] Falin Chen, C.F.Liu, J.Y.Yang. Supersonic Flow in Second-Throat Ejector-Diffuser System [J]. Journal of Spacecraft and Rockets, 1994, Vol.31, NO.1
[27] Y.Bartosiewicz, Zine Aidoun, P.Desevaux, Yves Mercadier. Numerical and Experiment Investigations on Supersonic Ejectors [J]. International Journal of Heat and Fluid Flow, 2004
[28] 徐华舫. 空气动力学基础 [M]. 北京航空学院出版社, 1986
[29] Fluent 用户手册
[30] 徐万武, 邹建军, 王振国. 超声速环形引射器启动特性试验研究 [J] , 火箭推进, 2005, 31(6)
[31] Stephens.S.E, Bates.L.B. Effect of Geometric Parameters on the Performance of Second Throat Annular Steam Ejectors [J]. TN:Anold Engnieering Development Center, Anold Air Force Station, 1991
[32] Hale.J.W. Diffuser Auxiliary Ejector Development for the Design of the L-3 LEM Descent Exhaust System [J]. AEDC-TR-65-255, 1965
[33] Hale.J.W. Investigation of Two-Nozzle-Cluster Diffuser-Ejector With and Without Ejected Mass [J]. AEDC-TDR-63-130, 1963
[34] Hale.J.W. Influence of Dertinent Parameters on Ejector-Diffuser Performance With and Without Ejected Mass [J]. AEDC-TDR-64-134, 1964
[35] Panesci.J.H, German.R.C. An Analysis of Second-Throat Diffuser Performance for Zero-Secondary-Flow Ejector System [J]. AEDC-TDR-63-249, 1964
[36] B.J. Huang, J.M. Chang, C.P. Wang, V.A.Petrenko. A 1-D analysis of ejector performance [J]. International Journal of Refrigeration, 1999, 354-364
[37] Dario Pastrone. An Analysis of the Ejector-Ram-Rocket Engine [J]. AIAA Journal, 2004
[38] D. Lineberry, Dr. B. Landrum, Effects of Multiple Nozzles on Asymmetric Ejector Performance [J]. AIAA Journal, 2005
[39] Hiroki Nagaoka, Sachio Suzuki, Fumio Wani. Ejector COIL Employing Coanda Effect [J]. AIAA Journal, 2005
[40] M. S. Balasubramanyam, D. B. Landrum, C. P. Chen, D. Lineberry. Numerical Investigation of Cold Flow Non-Axisymmetric Ejectors [J]. AIAA Journal, 2005
[41] Eijiro Kitamura. Pressure Recovery in Mixing Ducts of Ejector-ramjets [J]. AIAA Journal, 2005
[42] M. Ouzzane, Z. Aidoun. Model development and numerical procedure for detailed ejector analysis and design [J]. Applied Thermal Engineering, 2003
[43] Robert F.Walter, Robert A.O. Pressure Recovery in COIL Devices [J]. AIAA Journal, 1994
[44] Heuydong Kim, Youngki Lee. Numerical Simulation of the Supersonic Flows in the Second Throat Ejector-Diffuser Systems [J]. Journal of Thermal Science, 1999, Vol.8, No.4
[45] Heuy-Dong Kim, Toshiaki Setoguchi, Shen Yu, S.Raghunathan. Navier-Stokes Computations of the Supersonic Ejector-Diffuser System With a Second Throat [J]. Journal of Thermal Science, Vol.8, No.2
[46] Eijiro Kitamura, Tohru Mitani, Shenhong Huang, Goro Masuya. Pressure Recovery in Mixing Ducts of Ejector-Ramjets [J]. AIAA Journal, 2005
[47] J.A.Horkovich. Airborne Laser Pressure Recovery System Numerical Simulations [J]. AIAA Journal, 1993
[48] E.D.Rogdakis, G..K.Alexis. Design and Parametric Investigation of an Ejector in an Air-Conditioning System [J]. Applied Thermal Engineering, 2000
[49] G..N.Kumar, D.O.Griffith II, J.F.Fay. Multi-Plume Launch Vehicle Base Region Radiative Load Predictions [J]. AIAA Journal, 1994
[50] Houshang B.Ebrahimi. Numerical Investigation of Multi-Plume Rocket Phenomenology [J]. AIAA Journal, 1997
[51] 徐万武, 谭建国, 王振国. 二次流对超声速环型空气引射器真空度的影响 [J].国防科技大学学报, 2003, Vol.25, No.3
[52] 贺军科, 吴雄. 被动式引射器内流场数值研究 [J]. 固体火箭技术, 2005, Vol.28, No.2
[53] 徐万武, 王振国. 环形超声速空气引射器零二次流流场数值研究 [J]. 推进技术, 2003, Vol.24, No.1