大直径液氧煤油发动机燃烧室抗脉动隔板技术
|
摘要
随着发动机推力的增大,燃烧室直径也随之增大,表征燃烧室热声学特性的振型、频率及其组合振型更为复杂,燃烧室带与不带抗脉动隔板以及隔板的结构参数等对声学特性影响明显,直接影响燃烧不稳定性的裕度。为了研究抗脉动隔板结构参数对燃烧室声学特性的影响,本文基于三维柱坐标系声波动理论和COMSOL仿真平台,研究了抗脉动隔板结构对火箭发动机燃烧室声学特性的影响。通过单喷嘴声学模拟实验,验证了该仿真方法的有效性。分析了隔板高度、厚度和冷区长度对燃烧室声学特性的影响规律。研究结果表明:隔板高度由40mm增加至120mm时,燃烧室一阶切向和二阶切向振型的频率分别下降了22%和31%;隔板厚度和冷区长度对燃烧室声学频率的影响不超过5%;大推力补燃发动机燃烧室直径大,需采用结构形式更为复杂的抗脉动隔板来针对性地抑制横向振型。
Diameter of combustion chamber is enlarging as the thrust of engine increases,which makes acoustic frequency,vibration modes as well as their combination modes more complicated. The combustor with or without baffle and its structural parameters could not only significantly affect the acoustic characteristics,but also directly impact the combustion instability margin. In order to study the influence of the structure parameters of anti-pulsating baffle on the acoustic characteristics of the combustor,influence of baffle is systemically analyzed,based on the fundamental acoustic theories in three-dimensional cylindrical coordinates and COMSOL simulation platform. Firstly,acoustic finite element modeling(FEM)analysis results are verified by the experiment of acoustic characteristics with single injector chamber. On this basis,the effect modes of baffle length,thickness and length of cold area on acoustic frequency are established. The results show that the frequency of 1T and 2T falls by 22% and 31%,respectively when the length of baffle increases from 40 mm to 120 mm. Baffle thickness and cold area length have negligible impact on acoustic characteristics,which is no more than 5%. From the evolution of F-1 engine,it can be concluded that larger combustion chambers require more complex baffle pattern to inhibit the transverse vibration.
Diameter of combustion chamber is enlarging as the thrust of engine increases,which makes acoustic frequency,vibration modes as well as their combination modes more complicated. The combustor with or without baffle and its structural parameters could not only significantly affect the acoustic characteristics,but also directly impact the combustion instability margin. In order to study the influence of the structure parameters of anti-pulsating baffle on the acoustic characteristics of the combustor,influence of baffle is systemically analyzed,based on the fundamental acoustic theories in three-dimensional cylindrical coordinates and COMSOL simulation platform. Firstly,acoustic finite element modeling(FEM)analysis results are verified by the experiment of acoustic characteristics with single injector chamber. On this basis,the effect modes of baffle length,thickness and length of cold area on acoustic frequency are established. The results show that the frequency of 1T and 2T falls by 22% and 31%,respectively when the length of baffle increases from 40 mm to 120 mm. Baffle thickness and cold area length have negligible impact on acoustic characteristics,which is no more than 5%. From the evolution of F-1 engine,it can be concluded that larger combustion chambers require more complex baffle pattern to inhibit the transverse vibration.
引文
[1] Vigor Yang,William E Anderson.液体火箭发动机燃烧不稳定性[M].张宝炯,洪鑫,陈杰,译.北京:科学出版社,2001:3-30.
[2]赵文涛,周进,聂万胜,等.液体火箭发动机燃烧不稳定性分析与热释放声放大机理[J].国防科技大学学报,1997,19(2):10-14.
[3]洪鑫,程惠尔.液体火箭发动机燃烧室波动过程数值分析[J].推进技术,1999,20(2):5-8.(HONG Xin,CHENG Hui-er. Numerical Analysis of Acoustical Wavemotion in Combustion Chamber of Liquid Rocket Engine[J]. Journal of Propulsion Technology,1999,20(2):5-8.)
[4]成林,汤国建.某型号燃气发生器燃烧稳定性分析[J].航空计算技术,2012,42(4):1-5.
[5]李龙飞,陈建华,刘站国.大推力液氧煤油补燃发动机高频燃烧不稳定性的控制方法[J].导弹与航天运载技术,2011,34(3):16-19.
[6]李龙飞,陈建华,刘站国.增强大推力火箭发动机燃烧稳定性裕度的方法[J].火箭推进,2014,40(5):8-13.
[7]陈建华,李龙飞,周立新,等.液氧煤油补燃火箭发动机整流栅应用研究[J].火箭推进,2007,33(2):1-6.
[8]王枫,李龙飞,张贵田.喷嘴结构对液氧煤油火箭发动机高频燃烧不稳定性的影响[J].实验力学,2012,27(2):178-182.
[9]李龙飞,陈建华,周立新,等.补燃循环火箭发动机气液同轴式喷嘴声学特性研究[J].火箭推进,2004,30(6):5-10.
[10]薛帅杰,洪流,杨伟东.声学扰动对燃烧室声学特性的影响[J].推进技术,2016,37(2):201-208.(XUE Shuai-jie,HONG Liu,YANG Wei-dong. Effects of Acoustic Excitation on Acoustic Characteristics for Combustor[J]. Journal of Propulsion Technology,2016,37(2):201-208.)
[11]樊晓波,王敏庆,盛美萍.隔板应用于发动机燃烧室不稳定燃烧抑制中的二维数值计算分析[J].机械科学与技术,2007,26(9):1118-1121.
[12]郭灿琳,卢钢,陈建华,等.喷嘴式隔板与纵向肋式隔板阻尼效应分析[J].火箭推进,2013,39(3):32-37.
[13]李丹琳,田原,孙纪国.隔板对燃烧室声学特性的影响[J].航空动力学报,2012,27(3):715-720.
[14] Paul Ray. Independent Review of the Failure Modes of F-1 Engine and Propellants System[R]. Tuscaloosa:The University of Alabama,2002.
[15] Combs L P,Hoehn F W,Webb S R. Combustion Stability Rating Techniques-Final Report[R]. Rocketdyne:AFRPL-TR-66-229,1966.
[16] Smith R,Xia G,Anderson W A,et al. Computational Simulations of the Effect of Chamber Diameter on Single-Element Rocket Combustor Instability[R]. AIAA2008-5250.
[17]王治军,常新龙,田干,等.液体火箭发动机推力室设计[M].北京:国防工业出版社,2014.
[18]张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005.
[19]尕永靖,张会强,王希麟.隔板对燃烧室压力高频自激振荡的抑制作用[J].清华大学学报,2012,52(7):1007-1012.
[20]张蒙正,张志涛,杨国华,等.燃烧室声学特性模拟实验及应用[J].实验技术与管理,2007,24(8):39-42.
[2]赵文涛,周进,聂万胜,等.液体火箭发动机燃烧不稳定性分析与热释放声放大机理[J].国防科技大学学报,1997,19(2):10-14.
[3]洪鑫,程惠尔.液体火箭发动机燃烧室波动过程数值分析[J].推进技术,1999,20(2):5-8.(HONG Xin,CHENG Hui-er. Numerical Analysis of Acoustical Wavemotion in Combustion Chamber of Liquid Rocket Engine[J]. Journal of Propulsion Technology,1999,20(2):5-8.)
[4]成林,汤国建.某型号燃气发生器燃烧稳定性分析[J].航空计算技术,2012,42(4):1-5.
[5]李龙飞,陈建华,刘站国.大推力液氧煤油补燃发动机高频燃烧不稳定性的控制方法[J].导弹与航天运载技术,2011,34(3):16-19.
[6]李龙飞,陈建华,刘站国.增强大推力火箭发动机燃烧稳定性裕度的方法[J].火箭推进,2014,40(5):8-13.
[7]陈建华,李龙飞,周立新,等.液氧煤油补燃火箭发动机整流栅应用研究[J].火箭推进,2007,33(2):1-6.
[8]王枫,李龙飞,张贵田.喷嘴结构对液氧煤油火箭发动机高频燃烧不稳定性的影响[J].实验力学,2012,27(2):178-182.
[9]李龙飞,陈建华,周立新,等.补燃循环火箭发动机气液同轴式喷嘴声学特性研究[J].火箭推进,2004,30(6):5-10.
[10]薛帅杰,洪流,杨伟东.声学扰动对燃烧室声学特性的影响[J].推进技术,2016,37(2):201-208.(XUE Shuai-jie,HONG Liu,YANG Wei-dong. Effects of Acoustic Excitation on Acoustic Characteristics for Combustor[J]. Journal of Propulsion Technology,2016,37(2):201-208.)
[11]樊晓波,王敏庆,盛美萍.隔板应用于发动机燃烧室不稳定燃烧抑制中的二维数值计算分析[J].机械科学与技术,2007,26(9):1118-1121.
[12]郭灿琳,卢钢,陈建华,等.喷嘴式隔板与纵向肋式隔板阻尼效应分析[J].火箭推进,2013,39(3):32-37.
[13]李丹琳,田原,孙纪国.隔板对燃烧室声学特性的影响[J].航空动力学报,2012,27(3):715-720.
[14] Paul Ray. Independent Review of the Failure Modes of F-1 Engine and Propellants System[R]. Tuscaloosa:The University of Alabama,2002.
[15] Combs L P,Hoehn F W,Webb S R. Combustion Stability Rating Techniques-Final Report[R]. Rocketdyne:AFRPL-TR-66-229,1966.
[16] Smith R,Xia G,Anderson W A,et al. Computational Simulations of the Effect of Chamber Diameter on Single-Element Rocket Combustor Instability[R]. AIAA2008-5250.
[17]王治军,常新龙,田干,等.液体火箭发动机推力室设计[M].北京:国防工业出版社,2014.
[18]张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005.
[19]尕永靖,张会强,王希麟.隔板对燃烧室压力高频自激振荡的抑制作用[J].清华大学学报,2012,52(7):1007-1012.
[20]张蒙正,张志涛,杨国华,等.燃烧室声学特性模拟实验及应用[J].实验技术与管理,2007,24(8):39-42.