冲压燃烧室关键部件方案设计与性能验证试验研究
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摘要
为改善某型冲压发动机燃烧室的燃烧性能,本文对燃烧室火焰稳定器系统和供油系统的相关部件进行了方案设计,运用FLUENT软件对带火焰稳定器的燃烧室流场和油雾场进行了数值计算,最后进行了模型试验验证。
火焰稳定器系统包括薄膜蒸发型值班稳定器、径向稳定器、V型稳定器以及传焰槽。值班稳定器设计一套油路独立供油,主流采用分区和分压相结合的供油方式,含主副两套油路,并对副油路进行分区设计,适合大范围工作。
通过数值研究得到了燃烧室流场特性(包括流阻损失系数、燃烧室各区域的流量分配以及流场速度矢量图),得到了特定状态下的油雾场分布。初步验证了部件设计方案在流动和油雾特征上的可行性。
试验研究表明:主要结构参数的设计值均处于最佳设计范围,可以保证燃烧的稳定和完全;常压下燃烧效率超过90%,燃烧效率随压力变化最为明显,压力降低,燃烧效率下降;典型的组合工况下,燃烧室点火油气比在0.008左右,贫油熄火油气比在0.006左右。点火、熄火性能随流动参数变化不大,主要取决于值班稳定器的结构参数。
研究成果为冲压燃烧室的研制和定型提供了依据。
In order to improve the performance of a ramjet combustor, flameholder and fuel system components were designed in this paper. Numerical and experiment investigation were also carried out to explore the performance of the combustor based on the components design.
According to the design, flameholder system including film vapor flameholder、V-gutter flameholder and flame passage was given. A separate fuel system was designed for the film vapor flameholder. The main stream fuel was supplied by different zones and fuel pressures, and the system regulation range can reach 0.0860 to 3.2746kg/s.
The complex flow filed of the combustor was numerically simulated by using the commercial CFD (Computational Fluid Dynamics) software named FLUENT in the paper. The flow pattern、mass flow distribution、flow drag performance and fuel spray characteristics were obtained and analyzed in detail. The results show that the components design was acceptable.
Finally, the combustion performance including ignition、lean blow out performance and combustion efficiency were experimentally investigated at normal and low pressure. The experiment result show that the combustion efficiency can reach over 90% at normal pressure. In addition, the ignition and lean blow out performance were mainly depended on the structural parameters of film vapor flameholder at typical combined working conditions.
The paper can provide basis for the development of ramjet combustor.
火焰稳定器系统包括薄膜蒸发型值班稳定器、径向稳定器、V型稳定器以及传焰槽。值班稳定器设计一套油路独立供油,主流采用分区和分压相结合的供油方式,含主副两套油路,并对副油路进行分区设计,适合大范围工作。
通过数值研究得到了燃烧室流场特性(包括流阻损失系数、燃烧室各区域的流量分配以及流场速度矢量图),得到了特定状态下的油雾场分布。初步验证了部件设计方案在流动和油雾特征上的可行性。
试验研究表明:主要结构参数的设计值均处于最佳设计范围,可以保证燃烧的稳定和完全;常压下燃烧效率超过90%,燃烧效率随压力变化最为明显,压力降低,燃烧效率下降;典型的组合工况下,燃烧室点火油气比在0.008左右,贫油熄火油气比在0.006左右。点火、熄火性能随流动参数变化不大,主要取决于值班稳定器的结构参数。
研究成果为冲压燃烧室的研制和定型提供了依据。
In order to improve the performance of a ramjet combustor, flameholder and fuel system components were designed in this paper. Numerical and experiment investigation were also carried out to explore the performance of the combustor based on the components design.
According to the design, flameholder system including film vapor flameholder、V-gutter flameholder and flame passage was given. A separate fuel system was designed for the film vapor flameholder. The main stream fuel was supplied by different zones and fuel pressures, and the system regulation range can reach 0.0860 to 3.2746kg/s.
The complex flow filed of the combustor was numerically simulated by using the commercial CFD (Computational Fluid Dynamics) software named FLUENT in the paper. The flow pattern、mass flow distribution、flow drag performance and fuel spray characteristics were obtained and analyzed in detail. The results show that the components design was acceptable.
Finally, the combustion performance including ignition、lean blow out performance and combustion efficiency were experimentally investigated at normal and low pressure. The experiment result show that the combustion efficiency can reach over 90% at normal pressure. In addition, the ignition and lean blow out performance were mainly depended on the structural parameters of film vapor flameholder at typical combined working conditions.
The paper can provide basis for the development of ramjet combustor.
引文
[1]过崇伟等编著,航空航天技术概论,北京航空航天大学出版社,1992.6:p2～3.
[2]过崇伟等编著,航空航天技术概论,北京航空航天大学出版社,1992.6:p87～114.
[3]刘兴洲,冲压发动机的发展和应用,中国航天,1993,3(2):34～37.
[4]郑日恒,冲压发动机技术发展的发展动向与评论,飞航导弹,2004,24(1):p44～48.
[5]郑日恒,法国冲压发动机研究进展,航天制造技术,2006,4(2):p6～22.
[6]金永德等编著,导弹与航天技术概论,哈尔滨工业大学出版社,2002.8:p13～14.
[7]郑日恒,冲压发动机在法国的应用与研究,飞航导弹,1991,2(1):p30～36.
[8] R.Marguet,Ramjet Research and application in France ,ISABE 89-7005.
[9] Scientific and technical activities in 2004,ONERA report.
[10] J.P.Minard,M.Hallais,F.Falempin.Low Cost Ramjet Technology Missle Application,AIAA 2002-3765.
[11]从敏,张忠绍,波音公司完成HyFly高超声速导弹助推试验,飞航导弹,2006.4(1):p1～2.
[12] K.Bowcutt,R.Burrows,J.Weir.Techniques to Determine Fasthawk Missle Aerodynamics Including Inlet Effects,AIAA 99-0432.
[13] J.K.Lytle. The Numerical Propulsion System Simulation:An advanced Engineering Analysis Tool for Airbrething Engines.ISABE2001-1216.
[14] C.G.Rodrigues,CFD Analysis of the CIMA/NASA Scramjet.AIAA 2002-4218.
[15]夏焕明,冲压发动机流场、油雾场和点火性能实验研究,南京航空航天大学硕士学位论文,2001.3.
[16]刘兴洲,冲压发动机技术的发展,战术导弹技术,1989,12(4):p36～43.
[17]何小民,液体冲压发动机燃烧室方案研究报告,内部资料,2006.7.
[18]王元光,徐旭,陈兵等,冲压发动机燃烧室燃料喷射的简化计算方法研究,空气动力学学报,2007,25(1):p120～124.
[19]袁书生,王玉峰,李高春,冲压发动机燃烧室三维流场数值模拟,航空动力学报,2005.20(5):p841～846.
[20]周红梅,于胜春,李昊等,冲压发动机燃烧室内的压强振荡研究,飞航导弹,2006, 4(1):p44～47.
[21]李概奇,王家骅,低压下V型稳定器后回流区流动特性研究,中国航空科技文献HJL900069-1990.
[22]徐圃青,王家骅,低压下喷嘴雾化特性及油气分布影响的研究,CSAA-92-1992.
[23]徐圃青,单质彬,张屹等,放热率测量传感器及其系统研究,内部资料, 1994.
[24]王家骅,徐圃青,李概奇等,低压对点火性能、火焰稳定性和燃烧效率的影响研究,内部资料,1993.
[25]章晓梅,徐圃青,单质彬等,低压对放热率影响的研究,内部资料,1993.
[26]张屹,旋涡脱落对纵向振荡燃烧影响的研究,南京航空航天大学硕士学位论文,1997.3.
[27]杨开田等编,航空发动机设计手册(第11册加力燃烧室),航空工业出版社,2001.12:p127.
[28]李春光,带蒸发槽式火焰稳定器冲压燃烧室试验研究,北京航空航天大学硕士学位论文,2001.12.
[29]杨开田等编,航空发动机设计手册(第11册加力燃烧室),航空工业出版社,2001.12:p118～123.
[30]杨开田等编,航空发动机设计手册(第11册加力燃烧室),航空工业出版社,2001.12:p124.
[31]杨开田等编,航空发动机设计手册(第11册加力燃烧室),航空工业出版社,2001.12:p127.
[32] Fluent Inc.Fluent6.1 User’s Guide. Feb 2003.
[33]韩占忠等编,FLUENT流体工程仿真计算实例与应用,北京理工大学出版社,2004.6:p19～20.
[34]叶桃红,过明道,陈义良,通道中有稳定器的湍流流场分区计算方法,推进技术,1999,19(2) .
[35]章诚,叶桃红,陈义良等,三维加力燃烧室湍流流场的数值模拟,推进技术,2000,21(1) .
[36]陶文铨编著,数值传热学,西安交通大学出版社,2001.5:p333～335.
[37]陶文铨编著,数值传热学,西安交通大学出版社,2001.5:p353.
[38]周力行著,湍流两相流动与燃烧的数值模拟,清华大学出版社,1991.8:p135.
[39]周力行著,湍流两相流动与燃烧的数值模拟,清华大学出版社,1991.8:p178.
[40]王福军编著,计算流体动力学分析,清华大学出版社,2004.9:p74～81.
[41]南航,航空燃气轮机燃烧与燃烧室,内部讲义,p5～6.
[42] Takashi TAMARU, Research Reviews on Flameholders and Combustion of Afterburner and a Ramjet Engine, JSME, Series B.Vol.39,No.1,1996.
[43] P.J.Coelho, Modeling of a Solid Fuel Combustor of a Ramjet Using a Multi-block Domain Descomposition Technique, Areospace Science and Technology, 1998, n(2), 107-I 109.
[44]T.Poinsot etc ,Suppression of combustion Instabilies by ActiveControl,AIAA-07-1876.
[45] David L.Burrus. High Inlet Mach Combustor for Gas Turbine Engine. United States Patent 5619855. Apr 15, 1997.
[46] CFD Design Analysis Methodology: Hypersonics, Conjugate Heat Transfer and Liquid Spray Combustion.AIAA-2004-328.
[47] W.M.Roquemore, et al. Combustor Flame Stabilizing Structure. United States Patent 5857339, Jan 12 ,1999.
[48]付藻群,吸入式稳定器设计研究与试验,航空发动机,1998.3 .
[49]韩启祥,王家骅,沙丘驻涡蒸发式火焰稳定器低压性能的实验研究,推进技术,2001,22(1) .
[50]郑殿峰,张会强,林文漪等,蒸发式稳定器气态燃料掺混特性和蒸发管的流量系数,燃烧科学与技术,2004,10(1) .
[51]俞敏娅,节流装置设计计算书,江阴威尔胜仪表制造有限公司,2005.3.
[52]张彭岗,典型稳定器和先进值班稳定器试验研究,南京航空航天大学硕士学位论文,2005.4.
[53]崔风奎等编著,UG机械设计,机械工业出版社,2003.8.
[54]刘苏编著,计算机绘图,科学出版社,2000.7.
[55]谭浩强著,C程序设计,清华大学出版社,1999.12.
[56]刘瑞新主编,Visual C++面向对象程序设计教程,机械工业出版社,2004.7.
[2]过崇伟等编著,航空航天技术概论,北京航空航天大学出版社,1992.6:p87～114.
[3]刘兴洲,冲压发动机的发展和应用,中国航天,1993,3(2):34～37.
[4]郑日恒,冲压发动机技术发展的发展动向与评论,飞航导弹,2004,24(1):p44～48.
[5]郑日恒,法国冲压发动机研究进展,航天制造技术,2006,4(2):p6～22.
[6]金永德等编著,导弹与航天技术概论,哈尔滨工业大学出版社,2002.8:p13～14.
[7]郑日恒,冲压发动机在法国的应用与研究,飞航导弹,1991,2(1):p30～36.
[8] R.Marguet,Ramjet Research and application in France ,ISABE 89-7005.
[9] Scientific and technical activities in 2004,ONERA report.
[10] J.P.Minard,M.Hallais,F.Falempin.Low Cost Ramjet Technology Missle Application,AIAA 2002-3765.
[11]从敏,张忠绍,波音公司完成HyFly高超声速导弹助推试验,飞航导弹,2006.4(1):p1～2.
[12] K.Bowcutt,R.Burrows,J.Weir.Techniques to Determine Fasthawk Missle Aerodynamics Including Inlet Effects,AIAA 99-0432.
[13] J.K.Lytle. The Numerical Propulsion System Simulation:An advanced Engineering Analysis Tool for Airbrething Engines.ISABE2001-1216.
[14] C.G.Rodrigues,CFD Analysis of the CIMA/NASA Scramjet.AIAA 2002-4218.
[15]夏焕明,冲压发动机流场、油雾场和点火性能实验研究,南京航空航天大学硕士学位论文,2001.3.
[16]刘兴洲,冲压发动机技术的发展,战术导弹技术,1989,12(4):p36～43.
[17]何小民,液体冲压发动机燃烧室方案研究报告,内部资料,2006.7.
[18]王元光,徐旭,陈兵等,冲压发动机燃烧室燃料喷射的简化计算方法研究,空气动力学学报,2007,25(1):p120～124.
[19]袁书生,王玉峰,李高春,冲压发动机燃烧室三维流场数值模拟,航空动力学报,2005.20(5):p841～846.
[20]周红梅,于胜春,李昊等,冲压发动机燃烧室内的压强振荡研究,飞航导弹,2006, 4(1):p44～47.
[21]李概奇,王家骅,低压下V型稳定器后回流区流动特性研究,中国航空科技文献HJL900069-1990.
[22]徐圃青,王家骅,低压下喷嘴雾化特性及油气分布影响的研究,CSAA-92-1992.
[23]徐圃青,单质彬,张屹等,放热率测量传感器及其系统研究,内部资料, 1994.
[24]王家骅,徐圃青,李概奇等,低压对点火性能、火焰稳定性和燃烧效率的影响研究,内部资料,1993.
[25]章晓梅,徐圃青,单质彬等,低压对放热率影响的研究,内部资料,1993.
[26]张屹,旋涡脱落对纵向振荡燃烧影响的研究,南京航空航天大学硕士学位论文,1997.3.
[27]杨开田等编,航空发动机设计手册(第11册加力燃烧室),航空工业出版社,2001.12:p127.
[28]李春光,带蒸发槽式火焰稳定器冲压燃烧室试验研究,北京航空航天大学硕士学位论文,2001.12.
[29]杨开田等编,航空发动机设计手册(第11册加力燃烧室),航空工业出版社,2001.12:p118～123.
[30]杨开田等编,航空发动机设计手册(第11册加力燃烧室),航空工业出版社,2001.12:p124.
[31]杨开田等编,航空发动机设计手册(第11册加力燃烧室),航空工业出版社,2001.12:p127.
[32] Fluent Inc.Fluent6.1 User’s Guide. Feb 2003.
[33]韩占忠等编,FLUENT流体工程仿真计算实例与应用,北京理工大学出版社,2004.6:p19～20.
[34]叶桃红,过明道,陈义良,通道中有稳定器的湍流流场分区计算方法,推进技术,1999,19(2) .
[35]章诚,叶桃红,陈义良等,三维加力燃烧室湍流流场的数值模拟,推进技术,2000,21(1) .
[36]陶文铨编著,数值传热学,西安交通大学出版社,2001.5:p333～335.
[37]陶文铨编著,数值传热学,西安交通大学出版社,2001.5:p353.
[38]周力行著,湍流两相流动与燃烧的数值模拟,清华大学出版社,1991.8:p135.
[39]周力行著,湍流两相流动与燃烧的数值模拟,清华大学出版社,1991.8:p178.
[40]王福军编著,计算流体动力学分析,清华大学出版社,2004.9:p74～81.
[41]南航,航空燃气轮机燃烧与燃烧室,内部讲义,p5～6.
[42] Takashi TAMARU, Research Reviews on Flameholders and Combustion of Afterburner and a Ramjet Engine, JSME, Series B.Vol.39,No.1,1996.
[43] P.J.Coelho, Modeling of a Solid Fuel Combustor of a Ramjet Using a Multi-block Domain Descomposition Technique, Areospace Science and Technology, 1998, n(2), 107-I 109.
[44]T.Poinsot etc ,Suppression of combustion Instabilies by ActiveControl,AIAA-07-1876.
[45] David L.Burrus. High Inlet Mach Combustor for Gas Turbine Engine. United States Patent 5619855. Apr 15, 1997.
[46] CFD Design Analysis Methodology: Hypersonics, Conjugate Heat Transfer and Liquid Spray Combustion.AIAA-2004-328.
[47] W.M.Roquemore, et al. Combustor Flame Stabilizing Structure. United States Patent 5857339, Jan 12 ,1999.
[48]付藻群,吸入式稳定器设计研究与试验,航空发动机,1998.3 .
[49]韩启祥,王家骅,沙丘驻涡蒸发式火焰稳定器低压性能的实验研究,推进技术,2001,22(1) .
[50]郑殿峰,张会强,林文漪等,蒸发式稳定器气态燃料掺混特性和蒸发管的流量系数,燃烧科学与技术,2004,10(1) .
[51]俞敏娅,节流装置设计计算书,江阴威尔胜仪表制造有限公司,2005.3.
[52]张彭岗,典型稳定器和先进值班稳定器试验研究,南京航空航天大学硕士学位论文,2005.4.
[53]崔风奎等编著,UG机械设计,机械工业出版社,2003.8.
[54]刘苏编著,计算机绘图,科学出版社,2000.7.
[55]谭浩强著,C程序设计,清华大学出版社,1999.12.
[56]刘瑞新主编,Visual C++面向对象程序设计教程,机械工业出版社,2004.7.