固液混合发动机燃烧与燃速特性研究
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摘要
由于混合火箭发动机具有高安全性、高可靠性和低成本等突出优点，最近几年又重
新成为了火箭推进技术的重要发展方向之一，具有广泛的应用前景。然而由于混合发动
机的结构特点，如不采取特殊的措施，混合发动机的燃烧效率和燃面后退速率都很低，
因此，开展混合发动机燃烧和燃速特性研究就显得尤为重要。
燃面后退速率以及在工作条件改变过程中的变化，对混合发动机的设计有很大的影
响。然而由于混合燃烧机理十分复杂，很难得出一个燃面后退速率统一的公式。本文首
先通过对混合发动机燃烧过程的理论分析，初步建立了混合燃烧模型，并由此得到了燃
面后退速率的理论表达式。同时，总结和分析讨论了不同类型的燃面后退速率实验模型，
这些模型对于我们以后研究燃面后退速率问题有很多的借鉴之处。
本文基于简单反应的阿累尼乌斯公式和漩涡分裂模型，建立了混合发动机的湍流燃
烧模型，并在该模型下对某实验发动机进行了模拟，研究了发动机的燃烧效率和燃面后
退速率，并对发动机尺寸对混合燃烧的影响进行了研究。本文还基于颗粒轨道模型建立
了两相混合燃烧模型，并通过数值模拟研究了液氧颗粒尺寸和蒸发过程对两相混合燃烧
效率的影响。通过计算与分析，增进了对混合发动机燃烧过程理解，增加了对燃面后退
速率认识，为混合发动机设计提供了一些有意义的结果：1．燃面后移速率沿轴向的变化
是剧烈的；2．混合发动机燃烧效率比较低，使用预燃室和补燃室、合理设计喷注器以及
采用扰流装置，可以提高燃烧效率；3．当发动机尺寸增大时，燃面后移速率会减小。
本文还完成了实验混合发动机的设计，并进行了点火实验。
Hybrid rocket motors keep the features of low cost,high reliability,and no hazards.In recent years, there has been a resurgence of interest in the development of hybrid rocket engines for advanced launch vehicle applications. But in hybrid rocket motors,the combustion efficiency and regression rate are very slow.lt is important to study the combustion processes and the performance of regression rate in hybrid rocket motors.
Of particular importance in the design of hybrid rocket motors is the fuel surface regression rate and the manner in which it varies with operation conditions. In this paper,hybrid combustion is studied and a model of hybrid combustion is presented.The paper summarizes and discusses different types of regression rate models that have been developed by several researchers during previous investigations of hybrid combustion.These analyzes are useful in guiding the development of a hybrid rocket motor.
In this paper,simple reacting flow model of hybrid rocket motor based on Arrenius formula and Eddy Break-Up model is established and used to simulate an experimental motor. The paper also discusses size scale-up studies of hybrid rocket motors and the numerical simulation of two-phase hybrid combustion. With computations and analysis, the comprehension on the combustion process and knowledge about the performance of regression rate are increased, and some significative results are listed below:1. Regression rate varies greatly along x axis. 2. The combustion efficiency of hybrid rocket motor is very low.In order to increase combustion efficiency,we can use vaporization chamber and mixing chamber. 3.Regression rate decreases as the port dimension is increased.
The paper also makes a whole design of experimental hybrid rocket motor system,and discusses the result of motor firing.
新成为了火箭推进技术的重要发展方向之一，具有广泛的应用前景。然而由于混合发动
机的结构特点，如不采取特殊的措施，混合发动机的燃烧效率和燃面后退速率都很低，
因此，开展混合发动机燃烧和燃速特性研究就显得尤为重要。
燃面后退速率以及在工作条件改变过程中的变化，对混合发动机的设计有很大的影
响。然而由于混合燃烧机理十分复杂，很难得出一个燃面后退速率统一的公式。本文首
先通过对混合发动机燃烧过程的理论分析，初步建立了混合燃烧模型，并由此得到了燃
面后退速率的理论表达式。同时，总结和分析讨论了不同类型的燃面后退速率实验模型，
这些模型对于我们以后研究燃面后退速率问题有很多的借鉴之处。
本文基于简单反应的阿累尼乌斯公式和漩涡分裂模型，建立了混合发动机的湍流燃
烧模型，并在该模型下对某实验发动机进行了模拟，研究了发动机的燃烧效率和燃面后
退速率，并对发动机尺寸对混合燃烧的影响进行了研究。本文还基于颗粒轨道模型建立
了两相混合燃烧模型，并通过数值模拟研究了液氧颗粒尺寸和蒸发过程对两相混合燃烧
效率的影响。通过计算与分析，增进了对混合发动机燃烧过程理解，增加了对燃面后退
速率认识，为混合发动机设计提供了一些有意义的结果：1．燃面后移速率沿轴向的变化
是剧烈的；2．混合发动机燃烧效率比较低，使用预燃室和补燃室、合理设计喷注器以及
采用扰流装置，可以提高燃烧效率；3．当发动机尺寸增大时，燃面后移速率会减小。
本文还完成了实验混合发动机的设计，并进行了点火实验。
Hybrid rocket motors keep the features of low cost,high reliability,and no hazards.In recent years, there has been a resurgence of interest in the development of hybrid rocket engines for advanced launch vehicle applications. But in hybrid rocket motors,the combustion efficiency and regression rate are very slow.lt is important to study the combustion processes and the performance of regression rate in hybrid rocket motors.
Of particular importance in the design of hybrid rocket motors is the fuel surface regression rate and the manner in which it varies with operation conditions. In this paper,hybrid combustion is studied and a model of hybrid combustion is presented.The paper summarizes and discusses different types of regression rate models that have been developed by several researchers during previous investigations of hybrid combustion.These analyzes are useful in guiding the development of a hybrid rocket motor.
In this paper,simple reacting flow model of hybrid rocket motor based on Arrenius formula and Eddy Break-Up model is established and used to simulate an experimental motor. The paper also discusses size scale-up studies of hybrid rocket motors and the numerical simulation of two-phase hybrid combustion. With computations and analysis, the comprehension on the combustion process and knowledge about the performance of regression rate are increased, and some significative results are listed below:1. Regression rate varies greatly along x axis. 2. The combustion efficiency of hybrid rocket motor is very low.In order to increase combustion efficiency,we can use vaporization chamber and mixing chamber. 3.Regression rate decreases as the port dimension is increased.
The paper also makes a whole design of experimental hybrid rocket motor system,and discusses the result of motor firing.
引文
[1] Altman.D.,Hybrid Rocket Development History,AIAA Paper 91--2515.
[2] 方丁酉等编著．固体火箭发动机内弹道学．长沙：国防科学技术大学出版社，1997．
[3] C.L.Merkle and S.Venkateswaran,Fundamental Phenomna on Fuel Decomposition and Boundary-Layer Combustion Processes With Application to HRM,N 1996-0050012.
[4] 贺武生等译．混合式火箭推进装置的发展前景．火箭推进，1994(1)．
[5] 单建胜等．固液火箭发动机的研制及其应用．固体火箭技术，Vol．20．No．3，1997．
[6] J.D.Sims and R.A.Frederick,Preliminary Design of a Hybrid Propulsion Multimission Missile System Journal of Spacecraft and Rockets,Vol.34,No.2,March--April 1997.
[7] 一系5005科研组译．组合推进剂火箭发动机．长沙：长沙工学院，1975．
[8] 2000年美国固液混合火箭技术进展．固体火箭技术动态，Vol．206，2001．
[9] Dijkstra,F.,and Korting,P.,Ultrasonic Regression Rate Measurement in Solid Fuel Ramjets.AIAA Paper 90--1963.
[10] Peck,M.V.,and Houser,T.J.,Research in Hybrid Combustion, Heterogeneous Combustion,559—581,1963.
[11] Klaus R.Wanger and Robert H.Schmucker,Hybrid Propulsion for Space Applictions a Critical Assessment,AIAA Paper 92--3305.
[12] Paul N. Estey and Brian G. R. Hughes, The Opportunity for Hybrid Rocket Motors in Commercial Space,AIAA Paper 92--3431.
[13] P.N.Estey, D.Altman and J.S.McFarlane,an Evaluation of Scaling Effects for Hybrid Rocket Motors, AIAA Paper 91--2517.
[14] G.Lengelle and C.Guin,Condensed-Phase Behavior and Ablation Rate of Fuels for Hybrid Propulsion,AIAA Paper 93--2413.
[15] 庄逢辰编著．液体火箭发动机喷雾燃烧的理论、模型及应用．长沙：国防科学技术大学出版社，1995．
[16] 曹泰岳、常显奇等编著．固体火箭发动机燃烧过程理论基础．长沙：国防科学技术大学出版社，1992．
[17] Sutton GE,Rocket Propulsion Element.John wiley & sons,6th ed. New York.1992.
[18] Green,L,Introductory Consideration on Hybrid Rocket Combustion,Heterogeneous Combustion,1963.
[19] Marxman, G.A.,and Gilbert,M, Turbulent Boundary Layer Combustion in the Hybrid
Rocket,Ninth Symposium(Intemational) on Combustion,New York.1963.
[20] Marxman,G.A.,Combustion in the Turbulent Boundary Layer on a Vaporizing Surface,Tenth Symposium(International) on Combustion,p.1337--1349,the Combustion Institute,1965.
[21] Smoot,L.D.,and Price,C.F.,Regression Rates of Nonmetalized Hybrid Fuel System,AIAA Journal,Vol.3,No.8,1965.
[22] Smoot,L.D.,and Price,C.F.,Regression Rates of Metalized Hybrid Fuel System,AIAA Journal,Vol.4,1965.
[23] Smoot,L.D.,and Price,C.F.,Pressure Dependence of Hybrid Fuel Regression Rates,AIAA Journal,Vol.5,1966.
[24] Marxman,G.A.,and Wooldridge,C.E.,Fundamentals of Hybrid Boundary Layer Combustion,Heterogneous Combustion,Progress in Astronautics and Aeronautics,Vol. 15,Academic Press, New York,1964.
[25] 胡建新，夏智勋等．固液混合发动机燃面后退速率若干模型评述．固体火箭技术，Vol．24．No．3，2001．
[26] 胡建新，夏智勋等．固液火箭发动机在空间发射的应用前景(已录用)．导弹与航天运载技术．
[27] 王承尧等．计算流体力学及其并行算法．长沙：国防科技大学出版社，2000．
[28] Helman,D.et al.,Theoretical Investigation of Hybrid Rocket Combustion by Numerical Methods,Combustion and Flame,Vol.22,1974.
[29] Gany,A.et al.,Two-phase Flow Effects on Hybrid Combustion,Acta Astronautica,Vol.3,1976.
[30] 陈小前，固体燃料冲压发动机的研究，长沙：国防科技大学硕士学位论文，1998．
[31] G.C.Cheng,Numerical Simulation of the Intemal Ballistics of a Hybrid Rocket Motor.AIAA Paper 94---0554.
[32] C.L.Lin et al,Numerical Analysis of Spray Combustion Hybrid Rocket,AIAA paper 95-2687.
[33] P.Liang,R.J.Ungewitter,and S.E.Claflin,CFD Analysis of the 24-inch JIRAD Hybrid Rocket Motor, AIAA Paper 95--2692.
[34] 谭建国，固体燃料冲压发动机理论与实验研究，长沙：国防科技大学硕士学位论文，1999．
[35] Hai-Tien Loh et al,Computation of Viscous Chemically Reacting Flows in Hybrid Rocket Motors Using an Upwind LU-SSOR Scheme, AIAA Paper 90---1570.
[36] 王应时等著，燃烧过程数值模拟．北京：科学出版社，1986．
[37] Philmon George and S.Krishnan,Fuel Regression Rate Enhancement Studies in HTPB/GOX Hybrid Rocket Motors,AIAA Paper 98--3188．
[38] Willians F.A, Grain Design and Throttling of Hybrid Rocket Motors,Chemical Engineering Progress Symposium Series,No.61,Vol.62,1966．
[39] B.Greiner and R.A.Frederick,Experimental Investigation of Labscale Hybrid Instability, AIAA Paper 94--2878．
[40] William H.Knuth,et al, Solid-Fuel Regreesion Rate and Combustion Behavior of Vortex Hybrid Rocke Engines, AIAA Paper 99--2318．
[41] Martin J.Chiaverini,et al,Pressure Correction of Ultrasonic Regreesion Rate Measurement of a Hybrid Slab Motor, AIAA Paper 99--2319．
[42] Philmon George and S.Krishnan,Fuel Regression Rate Enhancement Studies in HTPB/GOX Hybrid Rocket Motors,AIAA Paper 98--3188．
[43] Kniffen B.J.,Hybrid Rocket Development at the American Rocket Company,AIAA paper 90--2762．
[44] R.M.Jenkins,Cold-Flow Study of Low Frequency Pressure Instability in Hybrid Rocket,N1997-0026201．
[45] J.D.Sims and R.A.Frederick,Preliminary Design of a Hybrid Propulsion Multimission Missile System,Journal of Spacecraft and Rockets, Vol.34,No.2,March--April 1997．
[46] Adela B. Y.,Hybrid Engine Design and Analysis, AIAA Paper 93--2548．
[47] Paul N.Estey and Geroge R.Whittinghill,Hybrid Rocket Motors Propellant Selection Alternative,AIAA Paper 92--3592．
[2] 方丁酉等编著．固体火箭发动机内弹道学．长沙：国防科学技术大学出版社，1997．
[3] C.L.Merkle and S.Venkateswaran,Fundamental Phenomna on Fuel Decomposition and Boundary-Layer Combustion Processes With Application to HRM,N 1996-0050012.
[4] 贺武生等译．混合式火箭推进装置的发展前景．火箭推进，1994(1)．
[5] 单建胜等．固液火箭发动机的研制及其应用．固体火箭技术，Vol．20．No．3，1997．
[6] J.D.Sims and R.A.Frederick,Preliminary Design of a Hybrid Propulsion Multimission Missile System Journal of Spacecraft and Rockets,Vol.34,No.2,March--April 1997.
[7] 一系5005科研组译．组合推进剂火箭发动机．长沙：长沙工学院，1975．
[8] 2000年美国固液混合火箭技术进展．固体火箭技术动态，Vol．206，2001．
[9] Dijkstra,F.,and Korting,P.,Ultrasonic Regression Rate Measurement in Solid Fuel Ramjets.AIAA Paper 90--1963.
[10] Peck,M.V.,and Houser,T.J.,Research in Hybrid Combustion, Heterogeneous Combustion,559—581,1963.
[11] Klaus R.Wanger and Robert H.Schmucker,Hybrid Propulsion for Space Applictions a Critical Assessment,AIAA Paper 92--3305.
[12] Paul N. Estey and Brian G. R. Hughes, The Opportunity for Hybrid Rocket Motors in Commercial Space,AIAA Paper 92--3431.
[13] P.N.Estey, D.Altman and J.S.McFarlane,an Evaluation of Scaling Effects for Hybrid Rocket Motors, AIAA Paper 91--2517.
[14] G.Lengelle and C.Guin,Condensed-Phase Behavior and Ablation Rate of Fuels for Hybrid Propulsion,AIAA Paper 93--2413.
[15] 庄逢辰编著．液体火箭发动机喷雾燃烧的理论、模型及应用．长沙：国防科学技术大学出版社，1995．
[16] 曹泰岳、常显奇等编著．固体火箭发动机燃烧过程理论基础．长沙：国防科学技术大学出版社，1992．
[17] Sutton GE,Rocket Propulsion Element.John wiley & sons,6th ed. New York.1992.
[18] Green,L,Introductory Consideration on Hybrid Rocket Combustion,Heterogeneous Combustion,1963.
[19] Marxman, G.A.,and Gilbert,M, Turbulent Boundary Layer Combustion in the Hybrid
Rocket,Ninth Symposium(Intemational) on Combustion,New York.1963.
[20] Marxman,G.A.,Combustion in the Turbulent Boundary Layer on a Vaporizing Surface,Tenth Symposium(International) on Combustion,p.1337--1349,the Combustion Institute,1965.
[21] Smoot,L.D.,and Price,C.F.,Regression Rates of Nonmetalized Hybrid Fuel System,AIAA Journal,Vol.3,No.8,1965.
[22] Smoot,L.D.,and Price,C.F.,Regression Rates of Metalized Hybrid Fuel System,AIAA Journal,Vol.4,1965.
[23] Smoot,L.D.,and Price,C.F.,Pressure Dependence of Hybrid Fuel Regression Rates,AIAA Journal,Vol.5,1966.
[24] Marxman,G.A.,and Wooldridge,C.E.,Fundamentals of Hybrid Boundary Layer Combustion,Heterogneous Combustion,Progress in Astronautics and Aeronautics,Vol. 15,Academic Press, New York,1964.
[25] 胡建新，夏智勋等．固液混合发动机燃面后退速率若干模型评述．固体火箭技术，Vol．24．No．3，2001．
[26] 胡建新，夏智勋等．固液火箭发动机在空间发射的应用前景(已录用)．导弹与航天运载技术．
[27] 王承尧等．计算流体力学及其并行算法．长沙：国防科技大学出版社，2000．
[28] Helman,D.et al.,Theoretical Investigation of Hybrid Rocket Combustion by Numerical Methods,Combustion and Flame,Vol.22,1974.
[29] Gany,A.et al.,Two-phase Flow Effects on Hybrid Combustion,Acta Astronautica,Vol.3,1976.
[30] 陈小前，固体燃料冲压发动机的研究，长沙：国防科技大学硕士学位论文，1998．
[31] G.C.Cheng,Numerical Simulation of the Intemal Ballistics of a Hybrid Rocket Motor.AIAA Paper 94---0554.
[32] C.L.Lin et al,Numerical Analysis of Spray Combustion Hybrid Rocket,AIAA paper 95-2687.
[33] P.Liang,R.J.Ungewitter,and S.E.Claflin,CFD Analysis of the 24-inch JIRAD Hybrid Rocket Motor, AIAA Paper 95--2692.
[34] 谭建国，固体燃料冲压发动机理论与实验研究，长沙：国防科技大学硕士学位论文，1999．
[35] Hai-Tien Loh et al,Computation of Viscous Chemically Reacting Flows in Hybrid Rocket Motors Using an Upwind LU-SSOR Scheme, AIAA Paper 90---1570.
[36] 王应时等著，燃烧过程数值模拟．北京：科学出版社，1986．
[37] Philmon George and S.Krishnan,Fuel Regression Rate Enhancement Studies in HTPB/GOX Hybrid Rocket Motors,AIAA Paper 98--3188．
[38] Willians F.A, Grain Design and Throttling of Hybrid Rocket Motors,Chemical Engineering Progress Symposium Series,No.61,Vol.62,1966．
[39] B.Greiner and R.A.Frederick,Experimental Investigation of Labscale Hybrid Instability, AIAA Paper 94--2878．
[40] William H.Knuth,et al, Solid-Fuel Regreesion Rate and Combustion Behavior of Vortex Hybrid Rocke Engines, AIAA Paper 99--2318．
[41] Martin J.Chiaverini,et al,Pressure Correction of Ultrasonic Regreesion Rate Measurement of a Hybrid Slab Motor, AIAA Paper 99--2319．
[42] Philmon George and S.Krishnan,Fuel Regression Rate Enhancement Studies in HTPB/GOX Hybrid Rocket Motors,AIAA Paper 98--3188．
[43] Kniffen B.J.,Hybrid Rocket Development at the American Rocket Company,AIAA paper 90--2762．
[44] R.M.Jenkins,Cold-Flow Study of Low Frequency Pressure Instability in Hybrid Rocket,N1997-0026201．
[45] J.D.Sims and R.A.Frederick,Preliminary Design of a Hybrid Propulsion Multimission Missile System,Journal of Spacecraft and Rockets, Vol.34,No.2,March--April 1997．
[46] Adela B. Y.,Hybrid Engine Design and Analysis, AIAA Paper 93--2548．
[47] Paul N.Estey and Geroge R.Whittinghill,Hybrid Rocket Motors Propellant Selection Alternative,AIAA Paper 92--3592．