固体燃料冲压增程炮弹内流场数值模拟研究
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摘要
近年来,炮弹增程技术发展迅速。与其它吸气式发动机相比,固体燃料冲压发动机(SFRJ)由于其高比冲(8000～11000N·s/kg)、低成本、结构简单和高可靠性等优点而备受关注。然而,由于燃烧和湍流的相互耦合,固体燃料冲压发动机的内流场非常复杂,为该类发动机的研究难点之一。
针对设计马赫数Ma=3的固体燃料冲压炮弹,对其二维轴对称定常内流场进行了数值模拟,从而为初步设计提供理论依据。本文研究内容主要分为两部分:
第一部分,对进气道初始设计模型进行了数值模拟,分析了流场结构、节流特性以及流场品质,结果表明初始进气道的性能不能令人满意;针对初始模型的不足之处,作出了改进,并对改进后的进气道模型进行了数值模拟,分析了流场结构、节流特性以及流场品质,结果表明改进后进气道的性能满足要求;在确定了进气道方案之后,给出其稳定工作范围。
第二部分,在改进后进气道模型基础上,基于标准k—ε湍流模型、简单化学反应机制和涡耗散模型,建立了固体燃料冲压炮弹统一内流场的计算模型,并完成了统一内流场的数值模拟,分析了燃烧室内的流场结构、再附点位置、温度分布、化学组分分布以及总压恢复系数,研究了补燃室长度与空燃比对燃烧效率和发动机性能参数的影响。
本文的研究成果对固体燃料冲压增程炮弹的研制具有一定的参考价值。
Nowadays, the assisted-range technology of projectile develops rapidly. Compared to other air breathing engines, solid fuel ramjet (SFRJ) has become a very attractive propulsion system for its high specific impulse (8000～11000N·s/kg), low cost, structure simplicity and high reliability. However, due to the coupling of combustion and turbulent flow, the internal flow field of SFRJ is very complicated, and it is one of the puzzling problems of SFRJ.
The present paper focuses on the SFRJ assisted range projectile which the design Mach number is 3, the two-dimensional axisymmetric steady internal flow field in SFRJ is numerically simulated, thus provide theory basis for the primary design stage. The research of this paper can be divided into two parts:
In the first part, the original intake model is numerically simulated, then its flow structure, throttle character and flow field character are analyzed, and the results show that the performance of the original intake model is unsatisfactory. Aim at the shortcomings of the original intake model, the improved intake model is obtained, and also its numerical simulation is achieved, then its flow structure, throttle character and flow field character are analyzed, the results show that the performance of intake can meet the request. After the intake model is confirmed, the stable operation range of intake is obtained.
In the second part, on the basis of the improved intake model, the compute model in internal flow field of SFRJ assisted-range projectile is established, which based on the k -εturbulent model, simple react flow and Eddy Dissipation model, and also the numerical simulation of the whole internal flow field are achieved. The flow field structure, reattachment point position, temperature distribution, chemical species distribution and total pressure recovery in the combustion chamber are analyzed. The influence of aft combustion chamber and air-fuel ratio on the combustion efficiency and other performance parameters are also analyzed, respectively.
The conclusions of this paper have reference value for the research and manufacture of SFRJ assisted range projectile.
针对设计马赫数Ma=3的固体燃料冲压炮弹,对其二维轴对称定常内流场进行了数值模拟,从而为初步设计提供理论依据。本文研究内容主要分为两部分:
第一部分,对进气道初始设计模型进行了数值模拟,分析了流场结构、节流特性以及流场品质,结果表明初始进气道的性能不能令人满意;针对初始模型的不足之处,作出了改进,并对改进后的进气道模型进行了数值模拟,分析了流场结构、节流特性以及流场品质,结果表明改进后进气道的性能满足要求;在确定了进气道方案之后,给出其稳定工作范围。
第二部分,在改进后进气道模型基础上,基于标准k—ε湍流模型、简单化学反应机制和涡耗散模型,建立了固体燃料冲压炮弹统一内流场的计算模型,并完成了统一内流场的数值模拟,分析了燃烧室内的流场结构、再附点位置、温度分布、化学组分分布以及总压恢复系数,研究了补燃室长度与空燃比对燃烧效率和发动机性能参数的影响。
本文的研究成果对固体燃料冲压增程炮弹的研制具有一定的参考价值。
Nowadays, the assisted-range technology of projectile develops rapidly. Compared to other air breathing engines, solid fuel ramjet (SFRJ) has become a very attractive propulsion system for its high specific impulse (8000～11000N·s/kg), low cost, structure simplicity and high reliability. However, due to the coupling of combustion and turbulent flow, the internal flow field of SFRJ is very complicated, and it is one of the puzzling problems of SFRJ.
The present paper focuses on the SFRJ assisted range projectile which the design Mach number is 3, the two-dimensional axisymmetric steady internal flow field in SFRJ is numerically simulated, thus provide theory basis for the primary design stage. The research of this paper can be divided into two parts:
In the first part, the original intake model is numerically simulated, then its flow structure, throttle character and flow field character are analyzed, and the results show that the performance of the original intake model is unsatisfactory. Aim at the shortcomings of the original intake model, the improved intake model is obtained, and also its numerical simulation is achieved, then its flow structure, throttle character and flow field character are analyzed, the results show that the performance of intake can meet the request. After the intake model is confirmed, the stable operation range of intake is obtained.
In the second part, on the basis of the improved intake model, the compute model in internal flow field of SFRJ assisted-range projectile is established, which based on the k -εturbulent model, simple react flow and Eddy Dissipation model, and also the numerical simulation of the whole internal flow field are achieved. The flow field structure, reattachment point position, temperature distribution, chemical species distribution and total pressure recovery in the combustion chamber are analyzed. The influence of aft combustion chamber and air-fuel ratio on the combustion efficiency and other performance parameters are also analyzed, respectively.
The conclusions of this paper have reference value for the research and manufacture of SFRJ assisted range projectile.
引文
1.吴护林.炮弹增程技术的发展.专家论坛.2005.Vol(5):3-6
2.陈雄,鞠玉涛.冲压增程弹丸进气道特性分析.推进技术.2005.Vol.26(3):265-269
3.陈铮.固体火箭冲压发动机补燃室气粒反应流数值模拟.南京理工大学硕士学位论文.2007
4.赵坚行.燃烧的数值模拟.科学出版社.2002
5.Ronald G.Veraar and Alfons E.H.J.Mayer.The Role of the TNO Free Jet Test Facility in Solid Fuel Ramjet Projectile Development.AIAA Paper 2005-3828
6.Michael J Nusca.Steady Flow Combustion Model for Solid-Fuel Ramjet Projectiles [J].Journal of Propulsion and Power.1990.Vol.3(6):348-352
7.Martin R.Fink.Aerodynamic Properties of an Advanced Indirect Fire System(AIFS)Projectile[J].Journal of Spacecraft and Rockets.1982.Vol.1(19):36-40
8.Mr.Peter Wimmerstrom,Mr.Yngve Nilsson and Dr.Nils-Erik Gunners.Initial study of a 40mm SFRJ projectile[C].14th International Symposium on Ballistics.1993
9.Ronald G.Veraarand Guido Giusti.Application-an overview of the tnorwms technology demonstration programme.20th International Symposium on baliistics.2002
10.Technion-Israel Institute of Technology,32000 Haifa,Israel.Investigation of a small Solid Fuel Ramjet Combustor.J.of Propulsion and Power.1989.Vol.4(3)
11.R.G.Veraar and K.Andersson.Numerical model for analysis and specification of a ramjet propelled artillery projectile.Bringing solid fuel ramjet projectiles closer to demonstration programme.19th International Symposium on ballistics.2001.5.
12.J.-S.Hwang,C.-K.Kim,J.-H.Lee,S.-K.Kwon etc.Ramjet Propulsion of a 40mm Projectile for Increased Performance[C].20th International Symposium on Ballistics,2002
13.R.Oosthuizen,A.Stockenstrom and J.J.duBuisson.Solid fuel ramjet propulsion for artillery projectile applications-concet development overview.International- Symposium on ballistics.2002
14.北京动力机械研究所.固体燃料沖压发动机试验研究.中国国防技术报告.1998.10
15.陈雄,郑亚等.冲压增程弹丸进气道复杂湍流流场数值模拟.兵工学报.2005.Vol.26(3):303-307
16.陈雄,周长省,郑亚.冲压增程弹丸进气道内外流场分区数值模拟.弹箭与制导学报.2004.Vol.24(4):59-62
17.陈雄,周长省,郑亚.应用TTM网格研究冲压增程弹丸进气道内外流场.固体火箭技术.2004.Vol.27(4):243-246
18.陈小前,张炜.固体燃料沖压发动机两个理论问题的探讨.固体火箭技术.1998.Vol.21(2):19-23
19.谭建国,陈小前,杨涛.固体燃料冲压发动机附着点分析与模拟.推进技术.1999.Vol 20(6):36-39
20.陈小前,杨涛.二维实验固体燃料冲压发动机冷流数值模拟.固体火箭技术.1999.Vol.22(2):12-15
21.赵日恒.法国冲压发动机研究进展.航天制造技术.2006.Vol.4(2):6-10
22.R.GVeraar,EJ.M.Elands,K.Andersson and Y.Nilsson.Overview of the Swedish-Dutch co-operation programme on solid fuel ramjet propelled projectiles.18th International Symposium on Ballistics.1999
23.郭应钧.超声速进气道流场与边界层计算.空气动力学学报.1990.Vol.8(1):104-109
24.谭建国,陈小前,杨涛,张为华.固体燃料冲压发动机简单反应流模拟.固体火箭技术.1999.Vol.22(3):11-15
25.Charles A.Stevenson and David W.Netzer.Primitive-Variable Model Application to Solid Fuel Ramjet Combustion.J.of Spacecraft and Rockets.1981.Vol.18(1)
26.T.Milshtein and D.W.Netzer.Three-dimensional Primitive-variable model -for solid fuel ramjet combustion[R].ADA138756
27.美国约翰.霍甫金斯大学应用物理实验所.冲压发动机技术.国防工业出版社1980
28.刘兴洲等.飞航导弹动力装置(上).宇航出版社.1992
29.Ronald GVeraar.A computer program for flight performance prediction of solid fuel ramjet propelled projectiles.P.O.Box 45 2280 AA Rijswijk
30.鲍福廷等.固体火箭冲压组合发动机[M].北京:宇航出版社.2006
31.Deborah Pelosi-Pinhas and Alon Gany.Solid Fuel Ramjet Regulation by Means of an Air Division Valve.ADA373397
32.EA.P.G.Korting,C.W.M.vander Geld and H.F.R.Schoyer.Combustion of PMMA in a Solid Fuel Ramjets[R].AIAA86-1401.1986
33.J.Gobbo Ferreira,J.A.Carvalho Jr.and Mauricio G.Silva.Experimental investigation of polyethylene combustion in a solid fuelramjet[R].AIAA96-2698.1996
34.Amnon Netzer and Alon Gany.Burning and Flameholding Characteristics of a Miniature Solid Fuel Ramjet Combustor[R].AIAA88-3044.1988
35.C.J.Mady,P.J.Hickey and D.W.Netzer.Combustion Behavior of Solid-Fuel Ramjets[J].Journal of Spacecraft and Rockets.1978.Vol.3(15):131-132
36.EJ.M.Elands,EA.O.G.Korting and T.Wijchers.Comparsion of Combustion Experiments and Theory in Polyethlene Solid Fuel Ramjets[J].Journal of Propulsion and Power.1990. Vol.6(6):732-739
37.Benveniste Natan and Mon Gany.Effects of Bypass Air on Boron Combustion in Solid Fuel Ramjets[J].Journal of Propulsion and Power.1993.Vol.1(9):155-157
38.Benveniste Natan and David W.Netzer.Experimental investigation of the effect of bypass air on boron combustion in a solid fuel ramjet[J].Journal of Propulsion and Power.1991.Vol.2(7):427-437
39.武渊,田维平,乐发仁,余贞勇.含硼贫氧燃气补燃室反应流场研究.推进技术.2004.Vol.25(4):294-297
40.霍东兴,陈林泉,刘霓生,叶定友.硼粒子直径对点火位置及燃烧效率的影响研究.固体火箭技术.2004.Vol.27(4):272-275
41.傅德薰,马延文.计算流体力学.高等教育出版社.2002
42.王应时,范维澄,周力行,徐长旭.燃烧过程数值计算.科学出版社.1986
43.严传俊,范玮,燃烧学.西北工业大学出版社等.2005
44.董师颜,孙思诚,张兆良,徐万赋.固体火箭发动机原理(第二版).北京理工大学出版社.1996
45.向敏,张为华,王中伟.冲压增程炮弹发动机王作性能分析.弹箭与制导学报2006.Vol.26(4):185-191,
46.王保国,刘淑艳,黄伟光.气体动力学.北京理工大学出版社等(第一版).2005
47.韩占忠,王敬..FLUENT流体工程仿真计算实例与应用.北京理工大学出版社,2005
48.Fluent Inc.FLUENT User's Guide.Fluent In.2003
49.Fluent Inc.GAMBIT User's Guide.Fluent In.2003
50.谭建国,陈小前,杨涛,张为华.固体燃料冲压发动机燃速理论分析与数值模拟.航空动力学报.2000.Vol.15(2):201-204
51.马洋,杨涛.涡流对固体燃料冲压发动机性能影响分析.固体火箭技术.2007.Vol.30(5).396-399
52.袁书生,李高春,王玉峰.冲压发动机进气道流场数值模拟.固体火箭技术,2003 Vol.26(4).30-33
53.王福军.计算流体动力学分析--CFD软件原理与应用.清华大学出版社.2004
54.武晓松,陈军,王栋,杨余旺.固体火箭发动机工作过程数值仿真.高等教育出版社
55.郑亚,陈军,鞠玉涛,武晓松.固体火箭发动机传热学.北京航空航天大学出版社等.2006
56.M.J.左克罗,J.D.霍夫曼.气体动力学(上、下).国防工业出版社.1984
57.华自强,张忠进.工程热力学.第三版.高等教育出版社.2000
58.Schulte G.Fuel regreasion and flame stabilization studies of solid fuel ramjets.Journal of propulsion and power.1986.Vol.2(4)
2.陈雄,鞠玉涛.冲压增程弹丸进气道特性分析.推进技术.2005.Vol.26(3):265-269
3.陈铮.固体火箭冲压发动机补燃室气粒反应流数值模拟.南京理工大学硕士学位论文.2007
4.赵坚行.燃烧的数值模拟.科学出版社.2002
5.Ronald G.Veraar and Alfons E.H.J.Mayer.The Role of the TNO Free Jet Test Facility in Solid Fuel Ramjet Projectile Development.AIAA Paper 2005-3828
6.Michael J Nusca.Steady Flow Combustion Model for Solid-Fuel Ramjet Projectiles [J].Journal of Propulsion and Power.1990.Vol.3(6):348-352
7.Martin R.Fink.Aerodynamic Properties of an Advanced Indirect Fire System(AIFS)Projectile[J].Journal of Spacecraft and Rockets.1982.Vol.1(19):36-40
8.Mr.Peter Wimmerstrom,Mr.Yngve Nilsson and Dr.Nils-Erik Gunners.Initial study of a 40mm SFRJ projectile[C].14th International Symposium on Ballistics.1993
9.Ronald G.Veraarand Guido Giusti.Application-an overview of the tnorwms technology demonstration programme.20th International Symposium on baliistics.2002
10.Technion-Israel Institute of Technology,32000 Haifa,Israel.Investigation of a small Solid Fuel Ramjet Combustor.J.of Propulsion and Power.1989.Vol.4(3)
11.R.G.Veraar and K.Andersson.Numerical model for analysis and specification of a ramjet propelled artillery projectile.Bringing solid fuel ramjet projectiles closer to demonstration programme.19th International Symposium on ballistics.2001.5.
12.J.-S.Hwang,C.-K.Kim,J.-H.Lee,S.-K.Kwon etc.Ramjet Propulsion of a 40mm Projectile for Increased Performance[C].20th International Symposium on Ballistics,2002
13.R.Oosthuizen,A.Stockenstrom and J.J.duBuisson.Solid fuel ramjet propulsion for artillery projectile applications-concet development overview.International- Symposium on ballistics.2002
14.北京动力机械研究所.固体燃料沖压发动机试验研究.中国国防技术报告.1998.10
15.陈雄,郑亚等.冲压增程弹丸进气道复杂湍流流场数值模拟.兵工学报.2005.Vol.26(3):303-307
16.陈雄,周长省,郑亚.冲压增程弹丸进气道内外流场分区数值模拟.弹箭与制导学报.2004.Vol.24(4):59-62
17.陈雄,周长省,郑亚.应用TTM网格研究冲压增程弹丸进气道内外流场.固体火箭技术.2004.Vol.27(4):243-246
18.陈小前,张炜.固体燃料沖压发动机两个理论问题的探讨.固体火箭技术.1998.Vol.21(2):19-23
19.谭建国,陈小前,杨涛.固体燃料冲压发动机附着点分析与模拟.推进技术.1999.Vol 20(6):36-39
20.陈小前,杨涛.二维实验固体燃料冲压发动机冷流数值模拟.固体火箭技术.1999.Vol.22(2):12-15
21.赵日恒.法国冲压发动机研究进展.航天制造技术.2006.Vol.4(2):6-10
22.R.GVeraar,EJ.M.Elands,K.Andersson and Y.Nilsson.Overview of the Swedish-Dutch co-operation programme on solid fuel ramjet propelled projectiles.18th International Symposium on Ballistics.1999
23.郭应钧.超声速进气道流场与边界层计算.空气动力学学报.1990.Vol.8(1):104-109
24.谭建国,陈小前,杨涛,张为华.固体燃料冲压发动机简单反应流模拟.固体火箭技术.1999.Vol.22(3):11-15
25.Charles A.Stevenson and David W.Netzer.Primitive-Variable Model Application to Solid Fuel Ramjet Combustion.J.of Spacecraft and Rockets.1981.Vol.18(1)
26.T.Milshtein and D.W.Netzer.Three-dimensional Primitive-variable model -for solid fuel ramjet combustion[R].ADA138756
27.美国约翰.霍甫金斯大学应用物理实验所.冲压发动机技术.国防工业出版社1980
28.刘兴洲等.飞航导弹动力装置(上).宇航出版社.1992
29.Ronald GVeraar.A computer program for flight performance prediction of solid fuel ramjet propelled projectiles.P.O.Box 45 2280 AA Rijswijk
30.鲍福廷等.固体火箭冲压组合发动机[M].北京:宇航出版社.2006
31.Deborah Pelosi-Pinhas and Alon Gany.Solid Fuel Ramjet Regulation by Means of an Air Division Valve.ADA373397
32.EA.P.G.Korting,C.W.M.vander Geld and H.F.R.Schoyer.Combustion of PMMA in a Solid Fuel Ramjets[R].AIAA86-1401.1986
33.J.Gobbo Ferreira,J.A.Carvalho Jr.and Mauricio G.Silva.Experimental investigation of polyethylene combustion in a solid fuelramjet[R].AIAA96-2698.1996
34.Amnon Netzer and Alon Gany.Burning and Flameholding Characteristics of a Miniature Solid Fuel Ramjet Combustor[R].AIAA88-3044.1988
35.C.J.Mady,P.J.Hickey and D.W.Netzer.Combustion Behavior of Solid-Fuel Ramjets[J].Journal of Spacecraft and Rockets.1978.Vol.3(15):131-132
36.EJ.M.Elands,EA.O.G.Korting and T.Wijchers.Comparsion of Combustion Experiments and Theory in Polyethlene Solid Fuel Ramjets[J].Journal of Propulsion and Power.1990. Vol.6(6):732-739
37.Benveniste Natan and Mon Gany.Effects of Bypass Air on Boron Combustion in Solid Fuel Ramjets[J].Journal of Propulsion and Power.1993.Vol.1(9):155-157
38.Benveniste Natan and David W.Netzer.Experimental investigation of the effect of bypass air on boron combustion in a solid fuel ramjet[J].Journal of Propulsion and Power.1991.Vol.2(7):427-437
39.武渊,田维平,乐发仁,余贞勇.含硼贫氧燃气补燃室反应流场研究.推进技术.2004.Vol.25(4):294-297
40.霍东兴,陈林泉,刘霓生,叶定友.硼粒子直径对点火位置及燃烧效率的影响研究.固体火箭技术.2004.Vol.27(4):272-275
41.傅德薰,马延文.计算流体力学.高等教育出版社.2002
42.王应时,范维澄,周力行,徐长旭.燃烧过程数值计算.科学出版社.1986
43.严传俊,范玮,燃烧学.西北工业大学出版社等.2005
44.董师颜,孙思诚,张兆良,徐万赋.固体火箭发动机原理(第二版).北京理工大学出版社.1996
45.向敏,张为华,王中伟.冲压增程炮弹发动机王作性能分析.弹箭与制导学报2006.Vol.26(4):185-191,
46.王保国,刘淑艳,黄伟光.气体动力学.北京理工大学出版社等(第一版).2005
47.韩占忠,王敬..FLUENT流体工程仿真计算实例与应用.北京理工大学出版社,2005
48.Fluent Inc.FLUENT User's Guide.Fluent In.2003
49.Fluent Inc.GAMBIT User's Guide.Fluent In.2003
50.谭建国,陈小前,杨涛,张为华.固体燃料冲压发动机燃速理论分析与数值模拟.航空动力学报.2000.Vol.15(2):201-204
51.马洋,杨涛.涡流对固体燃料冲压发动机性能影响分析.固体火箭技术.2007.Vol.30(5).396-399
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