Frequency characteristics of liquid rocket engine feed system
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摘要:
为了研究减少液体火箭发动机供应系统振荡的有效工程措施,对模型系统与真实系统建立适用于中高频分析的线性化复频域传递函数矩阵模型,结合节流圈阻抗与管路特征阻抗对比方法,分析系统流路在出口压力激励下的频率特性。结果表明:激励源端可能产生谐振频率偏移效应,应选取非激励源端的幅频响应来判断系统谐振频率;节流圈具有较强的频率选择性和对表现出反谐振特征的系统具有位置选择性,需重视关注的频率与位置;节流圈位置越靠近流量振型波腹,或流量波腹位置处的节流圈压降越大,对流路中振荡衰减作用越大。针对该液体火箭发动机供应系统,缩短液氧路管长0.1 m,增大煤油路管长0.05 m,并调整节流圈压降分配,可有效减小供应系统振荡。
Abstract:In order to study effective engineering measures to reduce the oscillation in the liquid rocket engine feed system, the linearized transfer matrix models in complex domain suitable for medium and high frequency analysis were established for the model system and the real system. Combined with the method of the contrast relationship between the impedance of orifices and the characteristic impedance of pipelines, the frequency characteristic of the system flow path under the excitation of outlet pressure was analyzed. The results showed that the resonance frequency shift effect may occur at the excitation source end, and the amplitude-frequency response of the non-excitation source end should be selected to judge the system resonance frequency. The throttle orifice had strong frequency selectivity and position selectivity for the system of anti-resonance characteristics, so attention shall be paid to the frequency and location. The closer the throttle orifice to the antinode of the flow mode, or the greater the pressure drop of the throttle orifice at the position of the flow antinode, indicated the greater attenuation effect on the oscillation in the flow path. For the liquid rocket engine feed system, shortening the length of the liquid oxygen pipe by 0.1 m, increasing the length of the kerosene pipe by 0.05 m, and adjusting the pressure drop distribution of the throttle orifice can effectively reduce the oscillation of the feed system.
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Key words:
- liquid rocket engine /
- feed system /
- engineering measures /
- throttle orifice /
- impedance /
- frequency characteristics
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表 1 不同压降分配情况下的阻抗值
Table 1. Impedance value under different pressure drop distributions
流路 工况 ZC/106 (m−1∙s−1) ZR1/106 (m−1∙s−1) ZR2/106 (m−1∙s−1) ZR3/106 (m−1·s−1) 液氧路 1 0.447 0.161 0.638 0.076 2 0.447 0.352 0.447 0.076 3 0.447 0.606 0.193 0.076 煤油路 1 4.297 8.266 25.376 5.434 2 4.297 16.936 16.705 5.434 3 4.297 25.607 8.035 5.433 -
[1] 刘上,刘红军,陈建华,等. 富氧燃气发生器-供应系统耦合稳定性研究[J]. 推进技术,2013,34(11): 1448-1458.LIU Shang,LIU Hongjun,CHEN Jianhua,et al. Investigation on oxidizer-rich preburner feed system coupled stability[J]. Journal of Propulsion Technology,2013,34(11): 1448-1458. (in Chinese) [2] 陈文,邢理想,徐浩海,等. 深度节流补燃循环发动机系统稳定性研究[J]. 火箭推进,2020,46(3): 41-48. doi: 10.3969/j.issn.1672-9374.2020.03.006CHEN Wen,XING Lixiang,XU Haohai,et al. Study on system stability of deep-throttling staged combustion cycled engine[J]. Jounal of Rocket Propulsion,2020,46(3): 41-48. (in Chinese) doi: 10.3969/j.issn.1672-9374.2020.03.006 [3] YOO J,YOON N,LEE S,et al. Pogo analysis for a clustered rocket engine by sophisticated branch-pipe modeling[R]. AIAA 2021-1614,2021. [4] SEKITA R,MATSUDA M,NAKAMURA R. Pressure oscillation analyses of the pressure regulator for the H-IIA propulsion system[R]. AIAA 2003-4600,2003. [5] 富庆飞,贾伯琦,杨立军,等. 燃烧室压力振荡对液-液同轴离心喷嘴混合比的影响[J]. 航空动力学报,2020,35(2): 294-297.FU Qingfei,JIA Boqi,YANG Lijun,et al. Effect of combustion chamber pressure pulsation on mixing ratio of liquid-liquid coaxial swirl injector[J]. Journal of Aerospace Power,2020,35(2): 294-297. (in Chinese) [6] NATANZON M S,CULICK F E C. Combustion instability[M]. Washington DC: American Institute of Aeronautics and Astronautics Incorporation,1999. [7] LEONARDI M,DI M F,STEELANT J,et al.System analysis of low frequency combustion instabilities in liquid rocket engines[R].AIAA 2015-4208,2015. [8] 刘上,张兴军,程晓辉,等. 火箭发动机泵后供应系统水力激振试验[J]. 航空动力学报,2018,33(11): 2635-2643.LIU Shang,ZHANG Xingjun,CHENG Xiaohui,et al. Hydraulic vibration experiment on a rocket engine feed system after pump[J]. Journal of Aerospace Power,2018,33(11): 2635-2643. (in Chinese) [9] 刘上,张兴军,程晓辉,等. 发动机泵后管路-汽蚀管系统水力激振试验[J]. 航空动力学报,2018,33(12): 3057-3064.LIU Shang,ZHANG Xingjun,CHENG Xiaohui,et al. Experiment for hydraulic vibration on rocket engine feed pipe-venturi tube system after pump[J]. Journal of Aerospace Power,2018,33(12): 3057-3064. (in Chinese) [10] WYLIE E B,STREETER V L. Fluid transients in systems[M]. Upper Saddle River,US: Prentice Hall,1993. [11] 刘曌俞. 液体火箭发动机喷注系统动力学特性研究[D]. 北京: 中国航天科技集团公司第一研究院,2018.LIU Zhaoyu. Research on the dynamic characteristic of injecting system in liquid rocket engine[D]. Beijing: the First Academy of China Aerospace Science and Technology Corporation,2018. (in Chinese) [12] SUTTON G P,BIBLARZ O. Rocket propulsion elements[M].9th ed. Hoboken, US: John Wiley and Sons Incorporation,2017. [13] 汪洪波,吴海燕,谭建国. 推进系统动力学[M]. 北京: 科学出版社,2018. [14] HITT M,LINEBERRY D,AHUJA V,et al. Experimental investigation of cavitation induced feedline instability from an orifice[R]. AIAA 2012-4029,2012. [15] AI Wanzheng,ZHOU Qi. Hydraulic characteristics of multi-stage orifice plate[J]. Journal of Shanghai Jiaotong University (Science),2014,19(3): 361-366. doi: 10.1007/s12204-014-1510-x [16] HARRJE D T,REARDON F H. Liquid propellant rocket combustion instability[M]. NASA SP-194,1972. [17] 刘上,刘红军,孙宏明,等. 液体火箭发动机中频耦合振荡初步研究[J]. 推进技术,2013,34(1): 101-108. doi: 10.13675/j.cnki.tjjs.2013.01.020LIU Shang,LIU Hongjun,SUN Hongming,et al. Preliminary study of medium frequency coupled oscillation in liquid rocket engine[J]. Journal of Propulsion Technology,2013,34(1): 101-108. (in Chinese) doi: 10.13675/j.cnki.tjjs.2013.01.020 [18] KOBAYASHI K,NUNOME Y,TOMITA T,et al. Studies on injection-coupled instability for liquid propellant rocket engines[R]. AIAA 2015-3843,2015. [19] BAZAROV V G. 液体喷嘴动力学[M]. 任汉芬,孙纪国,译.北京: 航天工业总公司第11研究所,1997. [20] FU Q,YANG L,WANG X. Theoretical and experimental study of the dynamics of a liquid swirl injector[J]. Journal of Propulsion and Power,2010,26(1): 94-101. doi: 10.2514/1.44271