Low frequency oscillation characteristics of deep throttled staged combustion LOX/kerosene engine
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摘要:
针对深度节流工况下液氧煤油补燃发动机产生低频振荡的问题，由于使用集总参数燃气管路的系统仿真模型难以算出此类振荡且对振荡机理、振荡抑制方法的研究较少，基于分布参数燃气管路模型构建了补燃发动机系统仿真模型，仿真得到了深度节流工况下发动机的低频振荡，分析了振荡机理，研究了振荡抑制方法。研究结果表明：基于分布参数燃气管路模型构建的发动机系统仿真模型较原有模型更接近深度节流工况下的工作实际，能够计算得到30%额定推力工况下的2.5 Hz低频增幅振荡，40%额定推力及更高工况振荡收敛；发动机系统存在燃气发生器-燃气管路-涡轮泵-氧供应路的反馈回路，该回路与作为能量源的燃气发生器共同激发了深度节流工况下的低频振荡；对氧供应路进行节流能够增加反馈回路上的阻尼，氧供应路流阻增大到原值40倍及以上时振荡得到抑制。
Abstract:In view of the problem of low frequency oscillation on deep throttled staged combustion LOX/kerosene engine, system simulation model based on lumped parameter gas manifold was unable to obtain this kind of oscillation, and literature was seldom devoted to oscillation mechanism and oscillation suppression method. Based on distributed-parameter gas manifold model, the simulation model of staged combustion engine system was established, the low frequency oscillation of deep throttled engine was acquired by simulation, the mechanism of oscillation was analyzed, and oscillation suppression method was studied. Results showed that, compared with the existing model, engine system simulation model covering distributed-parameter gas manifold model could better simulate a deep-throttled rocket engine, based on which 2.5 Hz low-frequency oscillation at 30% nominal thrust with increasing amplitude can be obtained. Oscillation decayed at 40% or higher thrust levels. Feedback circuit consisting of gas manifold, turbopump, and oxidizer feeding line as well as gas generator acting as energy source in engine system motivated the oscillation. Throttling the oxidizer feeding line increased damping on feedback circuit. Oxidizer feeding line resistance not less than 40 times of original value suppressed the oscillation with effect.
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图 2 燃气管路模型幅频响应特性验证
Figure 2. Verification of amplitude-frequency response characteristic of gas manifold models
图 3 燃气管路模型相频响应特性验证
Figure 3. Verification of phase-frequency response characteristic of gas manifold models
图 5 不同推力水平下燃气发生器压力振荡曲线
Figure 5. Oscillation curve of gas generator pressure at different thrust levels
图 6 不同推力水平下振荡对数衰减率
Figure 6. Logarithmic decrement of oscillation at different thrust levels
图 7 燃料副供应路及氧供应路流量振荡对比
Figure 7. Comparison of flow rate oscillation of gas generator fuel and oxidizer feeding line
图 8 通过氧供应路进入燃气发生器的反馈回路
Figure 8. Feedback circuit which enters gas generator from oxidizer feeding line
图 9 不同氧供应路流阻下燃气发生器压力振荡曲线
Figure 9. Oscillation curve of gas generator pressure at different oxidizer feeding line resistance
图 10 不同氧供应路流阻下振荡对数衰减率
Figure 10. Logarithmic decrement of oscillation at different oxidizer feeding line resistance
表 1 不同推力水平下反馈回路参数变化
Table 1. Change of parameters of feedback circuit at different thrust levels
发动机推力
与额定推力之比/%$ \Delta p/{p}_{0} $ $ {\tau }_{\mathrm{r}}/{\tau }_{\mathrm{r}0} $ 30 0.0396 1.00 40 0.0489 0.886 50 0.0561 0.804 80 0.0742 0.658 100 0.0756 0.648 
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[1] 李斌, 李程, 高玉闪, 等. 重复使用运载火箭液体动力技术发展[J]. 火箭推进, 2024, 50(1): 1-11, I0002. LI Bin, LI Cheng, GAO Yushan, et al. Development of liquid propulsion technologyfor reusable launch vehicle[J]. Journal of Rocket Propulsion, 2024, 50(1): 1-11, I0002. (in Chinese doi: 10.3969/j.issn.1672-9374.2024.01.001LI Bin, LI Cheng, GAO Yushan, et al. Development of liquid propulsion technologyfor reusable launch vehicle[J]. Journal of Rocket Propulsion, 2024, 50(1): 1-11, I0002. (in Chinese) doi: 10.3969/j.issn.1672-9374.2024.01.001 [2] 刘士杰, 王东, 田原, 等. 液体火箭发动机可重复使用性设计技术分析[J]. 火箭推进, 2024, 50(1): 67-77. LIU Shijie, WANG Dong, TIAN Yuan, et al. Analysis on reusability design technology of liquid rocket engine[J]. Journal of Rocket Propulsion, 2024, 50(1): 67-77. (in Chinese doi: 10.3969/j.issn.1672-9374.2024.01.006LIU Shijie, WANG Dong, TIAN Yuan, et al. Analysis on reusability design technology of liquid rocket engine[J]. Journal of Rocket Propulsion, 2024, 50(1): 67-77. (in Chinese) doi: 10.3969/j.issn.1672-9374.2024.01.006 [3] ГЕМРАНОВА Е А, КОЛБАСЕНКОВ А И, КОШЕЛЕВ И М, et al. Способы подавления низкочастотных колебаний в ЖРД на режимах глубокого дросселирования[J]. Труды НПО Энергомаш имени академика В. П. Глушко, 2013, 30: 104-110. [4] БЕЛЯЕВ Е Н, ЧВАКОВ В К, ЧЕРВАКОВ В В. Математическое моделирование рабочего процесса жидкостных ракетных дви-гателей[M]. Москва, Россия: Издательство МАИ, 1999. [5] 刘子岩, 苏展, 高玉闪, 等. 全流量补燃循环发动机流量调节器起调过程仿真研究[J]. 载人航天, 2023, 29(4): 478-486. LIU Ziyan, SU Zhan, GAO Yushan, et al. Study on simulation of start-up process of flow regulator of full-flow staged combustion cycle engine[J]. Manned Spaceflight, 2023, 29(4): 478-486. (in Chinese doi: 10.16329/j.cnki.zrht.2023.04.009LIU Ziyan, SU Zhan, GAO Yushan, et al. Study on simulation of start-up process of flow regulator of full-flow staged combustion cycle engine[J]. Manned Spaceflight, 2023, 29(4): 478-486. (in Chinese) doi: 10.16329/j.cnki.zrht.2023.04.009 [6] 郑大勇, 王弘亚, 胡骏. 大推力氢氧发动机瞬态特性研究[J]. 推进技术, 2021, 42(8): 1761-1769. ZHENG Dayong, WANG Hongya, HU Jun. Transient characteristics of high-thrust oxygen/hydrogen rocket engine[J]. Journal of Propulsion Technology, 2021, 42(8): 1761-1769. (in Chinese doi: 10.13675/j.cnki.tjjs.190842ZHENG Dayong, WANG Hongya, HU Jun. Transient characteristics of high-thrust oxygen/hydrogen rocket engine[J]. Journal of Propulsion Technology, 2021, 42(8): 1761-1769. (in Chinese) doi: 10.13675/j.cnki.tjjs.190842 [7] KOPTILYY D, MARCHAN R, DOLGOPOLOV S, et al. Mathematical modeling of transient processes during start-up of main liquid propellant engine under hot test conditions[R]. Madrid, Spain: 8th European Conference for Aeronautics and Space Sciences (EUCASS), 2019. [8] 张睿文, 张晓光, 李斌. 大推力液氧煤油发动机推力深度调节仿真分析[J]. 推进技术, 2023, 44(10): 2211038. ZHANG Ruiwen, ZHANG Xiaoguang, LI Bin. Simulation analysis of large-thrust LOX/kerosene engine deep throttling[J]. Journal of Propulsion Technology, 2023, 44(10): 2211038. (in ChineseZHANG Ruiwen, ZHANG Xiaoguang, LI Bin. Simulation analysis of large-thrust LOX/kerosene engine deep throttling[J]. Journal of Propulsion Technology, 2023, 44(10): 2211038. (in Chinese) [9] БУРЦЕВ И В. Исследование зависимости автоколебаний в ЖРД при глубоком дроссели-ровании от характеристик системы подачи[J]. Труды НПО Энергомаш имени академика В. П. Глушко, 2022, S38-39: 111-123. [10] ПИЛИПЕНКО О В, ПРОКОПЧУК А А, ДОЛГОПОЛОВ С И, et al. Математическое моделирование и анализ устойчивости низко-частотных процессов в маршевом ЖРД с дожиганием генераторного газа[J]. Вестник двигателестроения, 2017, 2: 34-41. [11] DI MATTEO F. Modelling and simulations of liquid rocket engine ignition transients [D]. Roma, Italy: Sapienza Università di Roma, 2012. [12] 李元启, 赵晓慧, 陈宏玉, 等. 燃烧组件时域分布参数系统动力学模型[J]. 火箭推进, 2022, 48(4): 29-35. LI Yuanqi, ZHAO Xiaohui, CHEN Hongyu, et al. Time domain distributed parameter system dynamic model of combustion components[J]. Journal of Rocket Propulsion, 2022, 48(4): 29-35. (in Chinese doi: 10.3969/j.issn.1672-9374.2022.04.004LI Yuanqi, ZHAO Xiaohui, CHEN Hongyu, et al. Time domain distributed parameter system dynamic model of combustion components[J]. Journal of Rocket Propulsion, 2022, 48(4): 29-35. (in Chinese) doi: 10.3969/j.issn.1672-9374.2022.04.004 [13] YAMANISHI N, KIMURA T, TAKAHASHI M, et al. Transient analysis of the LE-7A rocket engine using the rocket engine dynamic simulator (REDS)[R]. AIAA-2004-3850, 2004. [14] БУРЦЕВ И В, ЛЁВОЧКИН П С, МАРТИРОСОВ Д С, et al. Механизмы возникновения автоколебаний в ЖРД[J]. Труды НПО Энергомаш имени академика В. П. Глушко, 2022, S38-39: 103-110. [15] ГРОМЫКО Б М, КАТРЫШ В А, ТЕЛЕНКОВ А А, et al. Трехпозиционный клапан окислителя ЖРД[J]. Труды НПО Энергомаш имени академика В. П. Глушко, 2011, 28: 142-151. [16] ГЛИКМАН Б Ф. Автоматическое регулирование жидкостных ракетных двигателей[M]. Москва, Россия: Машиностроение, 1989. [17] ГЛИКМАН Б Ф. Нестационарные течения в пневмогидравлических целях[M]. Москва, Россия: Машино-строение, 1979. [18] CHEN C-T. Linear systems theory and design[M]. 4th Edition. New York, US: Oxford University Press, 2012. -
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