隔板喷嘴对燃烧室切向声学模态作用研究
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摘要
隔板喷嘴通过改变燃烧室声学特性,在抑制火箭发动机高频燃烧不稳定性方面具有重要作用。然而,目前并没有合适的理论模型,来预测隔板喷嘴对燃烧室声学特性的作用规律。为了获得隔板喷嘴对燃烧室内切向声学振荡模态作用的理论模型,通过理论推导隔板喷嘴声导纳,利用分离变量法结合实验验证,研究了径向隔板喷嘴间隙、数量及长度对燃烧室一阶切向声学振荡模态的影响。结果表明,存在最佳隔板喷嘴间隙,对燃烧室内一阶切向声学振荡模态抑制效果最佳;随着隔板喷嘴数量或长度的增加,燃烧室内一阶切向声学振荡模态频率和幅值均呈现下降趋势,且弱化了隔板喷嘴间隙的作用效果。该模型为隔板喷嘴研究奠定了一定的理论基础,研究结果为火箭发动机隔板喷嘴设计提供指导。
Baffled injectors have played an important role in suppressing high-frequency combustion insta-bility in liquid rocket engines by changing acoustic characteristics of the combustion chamber. However,no ap-propriate model can successfully predict effects of baffled injectors on acoustic characteristics of a combustionchamber. In order to obtain the theoretical model of effects of baffled injectors on the transverse acoustic mode ofthe combustion chamber,the acoustic admittance of baffled injectors was deduced theoretically. Effects of gap,number and length of baffled injectors on the first transverse mode of the combustion chamber were studied bymeans of separation variable method and experiment. Results show that the maximum suppression effects on thefirst transverse acoustic mode occurs at a certain gap. The frequency and amplitude of the first transverse acousticmode decrease with increasing the number and length of baffled injectors. Furthermore,suppression effects ofgap are weakened with the increasing of number or length of baffled injectors. This model lays a theoretical foun-dation for the study of baffled injectors,and results offer some guidance to the design of baffled injectors in liq-uid rocket engines.
Baffled injectors have played an important role in suppressing high-frequency combustion insta-bility in liquid rocket engines by changing acoustic characteristics of the combustion chamber. However,no ap-propriate model can successfully predict effects of baffled injectors on acoustic characteristics of a combustionchamber. In order to obtain the theoretical model of effects of baffled injectors on the transverse acoustic mode ofthe combustion chamber,the acoustic admittance of baffled injectors was deduced theoretically. Effects of gap,number and length of baffled injectors on the first transverse mode of the combustion chamber were studied bymeans of separation variable method and experiment. Results show that the maximum suppression effects on thefirst transverse acoustic mode occurs at a certain gap. The frequency and amplitude of the first transverse acousticmode decrease with increasing the number and length of baffled injectors. Furthermore,suppression effects ofgap are weakened with the increasing of number or length of baffled injectors. This model lays a theoretical foun-dation for the study of baffled injectors,and results offer some guidance to the design of baffled injectors in liq-uid rocket engines.
引文
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[12] Guo K K,Nie W S,Liu Y,et al. Numerical Simulation of Damping Capacity Between Injector Formed Baffle and Normal Blade Baffle in a Kero/LOX Liquid Rocket Engine[C]. USA:Advances in Engineering Research,2017.
[13] Wicker J M,Yoon M W,Yang V. Linear and Non-linear Pressure Oscillations in Baffled Combustor Chambers[J]. Journal of Sound and Vibration,1995,184(1):141-171.
[14] You D,Huang Y,Yang V. Linear Stability Analysis of Baffled Combustor Chamber with Radial and Circumferential Blades[C]. Reno:43rd AIAA Aerospace Sciences Meeting and Exhibit,2005.
[15] Martin P A,Flajolet P,Ismail M E H,et al. Multiple Scattering Interaction of Time Harmonic Waves with N Obstacles[M]. Cambridge:Multiple Scattering,2006.
[16] Tversky V T. On Scattering of Waves by the Infinite Grating of Circular Cylinders[J]. IRE Transactions on Antennas and Propagation,1962,10(6):737-765.
[17] Row RV. Electromagnetic Scattering from Two Parallel Conducting Cylinders[D]. Boston:Harvard University,1953.
[18] Rayleigh L. The Theory of Sound[M]. New York:Dover Publication,1945.
[2] Culick F E C,Yang V.液体火箭发动机燃烧不稳定[M].北京:科学出版社,2001.
[3]杨国才. F/A-18E/F飞机发动机的Caret进气道[J].推进技术,1997,18(4):31-35.(YANG Guo-cai.The Caret Inlet of the F/A-18E/F Strike Fighter[J].Journal of Propulsion Technology,1997,18(4):31-35.)
[4] Dranovsky M L,Yang V,Culick F E C,et al. Combustion Instabilities in Liquid Rocket Engines:Testing and Development Practices in Russia[C]. Reston:Progress in Astronautics and Aeronautics,2007.
[5]杨立军,富庆飞.液体火箭发动机推力室设计[M].北京:北京航空航天大学出版社,2013.
[6] Park I S,Sohn C H,Kim H J. Acoustic Damping Enhanced by Gaps in Baffled Injectors in an Acoustic Chamber[J]. Journal of Sound and Vibration,2011,330(12):2747-2757.
[7] Park I S,Sohn C H. A Numerical Study on Acoustic Damping Mechanism of Baffled Injectors in an Acoustic Chamber[C]. Nashville:46th AIAA Joint Propulsion Conference and Exhibit,2010.
[8] Lee K J,Kim H J,Seo S,et al. Experimental Verification for Acoustic Damping Enhancement by Gaps in Baffled Injectors[J]. Journal of Propulsion and Power,2009,25(2):435-442.
[9]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,2011,313(3):16-19.
[10]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):715-719.
[11]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.
[12] Guo K K,Nie W S,Liu Y,et al. Numerical Simulation of Damping Capacity Between Injector Formed Baffle and Normal Blade Baffle in a Kero/LOX Liquid Rocket Engine[C]. USA:Advances in Engineering Research,2017.
[13] Wicker J M,Yoon M W,Yang V. Linear and Non-linear Pressure Oscillations in Baffled Combustor Chambers[J]. Journal of Sound and Vibration,1995,184(1):141-171.
[14] You D,Huang Y,Yang V. Linear Stability Analysis of Baffled Combustor Chamber with Radial and Circumferential Blades[C]. Reno:43rd AIAA Aerospace Sciences Meeting and Exhibit,2005.
[15] Martin P A,Flajolet P,Ismail M E H,et al. Multiple Scattering Interaction of Time Harmonic Waves with N Obstacles[M]. Cambridge:Multiple Scattering,2006.
[16] Tversky V T. On Scattering of Waves by the Infinite Grating of Circular Cylinders[J]. IRE Transactions on Antennas and Propagation,1962,10(6):737-765.
[17] Row RV. Electromagnetic Scattering from Two Parallel Conducting Cylinders[D]. Boston:Harvard University,1953.
[18] Rayleigh L. The Theory of Sound[M]. New York:Dover Publication,1945.