航天推进技术研究院主办
[1]樊志伟,钟战,李庚,等.基于变分模态分解的燃烧室热声振荡衰减系数辨识[J].火箭推进,2023,49(05):23-31.
FAN Zhiwei,ZHONG Zhan,LI Geng,et al.Identification of attenuation coefficient for thermoacoustic oscillation in combustion chamber based on variational mode decomposition[J].Journal of Rocket Propulsion,2023,49(05):23-31.
点击复制
FAN Zhiwei,ZHONG Zhan,LI Geng,et al.Identification of attenuation coefficient for thermoacoustic oscillation in combustion chamber based on variational mode decomposition[J].Journal of Rocket Propulsion,2023,49(05):23-31.
基于变分模态分解的燃烧室热声振荡衰减系数辨识
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年05期
页码:
23-31
栏目:
目次
出版日期:
2023-10-25
- Title:
- Identification of attenuation coefficient for thermoacoustic oscillation in combustion chamber based on variational mode decomposition
- 文章编号:
- 1672-9374(2023)05-0023-09
- Keywords:
- combustion stability; attenuation coefficient; system identification; resonant frequency; filter width; variational mode decomposition
- 分类号:
- V231.1
- 文献标志码:
- A
- 摘要:
- 利用发动机燃烧室稳定燃烧阶段的压力振荡信号,提取热声谐振模态频率及其幅值,并建立不同复杂程度热声振荡理论模型辨识获取各模态衰减系数,是当前试验评估燃烧室燃烧稳定性裕度的一种重要手段。建立了二阶随机振子热声振荡理论模型,采用基于最大峭度准则的变分模态分解算法提取压力振荡信号的热声谐振模态,开展了模态提取算法和时/频域辨识方法验证,并将其应用于某针栓式气氧/乙醇模型发动机燃烧稳定性裕度评估分析。结果表明:与传统的带通滤波算法相比,峭度最大变分模态算法有效提高了热声谐振模态的提取精度和使用便捷性。
- Abstract:
- Based on the pressure oscillation signal of the stable combustion stage of the liquid rocket engine combustion chamber, extracting the thermoacoustic resonant mode frequency and its amplitude, and establishing the theoretical model of thermoacoustic oscillation of different complexity to identify and obtain the attenuation coefficients of each mode, is an important means to evaluate the combustion stability margin of the combustion chamber in current experiments. A theoretical model of thermoacoustic oscillation with a second-order stochastic oscillator is established, and the thermoacoustic resonant mode of the pressure oscillation signal is extracted by the steep maximum variational mode decomposition algorithm, and then the mode extraction algorithm and the time/frequency domain identification method are verified. In addition, it is applied to the combustion stability margin evaluation and analysis of a needle-bolt gas oxygen/ethanol model engine. The results show that compared with the traditional bandpass filtering algorithm,the steep maximum variational mode algorithm effectively improves the extraction accuracy and convenience of thermoacoustic resonant mode.
参考文献/References:
[1] POINSOT T.Prediction and control of combustion instabilities in real engines[J].Proceedings of the Combustion Institute,2017,36(1):1-28.
[2] 杨 V,安德松 W E.液体火箭发动机燃烧不稳定性[M].张宝炯,译.北京:科学出版社,2001.
[3] REARDON F H.Guidelines for combustion stability specifications and verification procedures for liquid propellant rocket engines[EB/OL].https://www.researchgate.net/publication/24372969_Guidelines_for_combustion_stability_specifications_and_verification.procedures_for_liquid_propellant_rocket_engines,1973.
[4] 张蒙正.燃烧不稳定性模拟实验技术[M].西安:西北工业大学出版社,2017.
[5] 丁兆波,许晓勇,乔桂玉,等.氢氧火箭发动机动态燃烧稳定性评定技术研究[J].导弹与航天运载技术,2013(1):38-41.
[6] BONCIOLINI G.Modelling of thermoacoustic dynamics in gas turbines applications[Z].2019.
[7] LIEUWEN T.Online combustor stability margin assessment using dynamic pressure data[J].Journal of Engineering for Gas Turbines and Power,2005,127(3):478-482.
[8] STADLMAIR N V,HUMMEL T,SATTELMAYER T.Thermoacoustic damping rate determination from combustion noise using Bayesian statistics[EB/OL].https://asmedigitalcollection.asme.org/GT/proceedings-abstract/GT2017/50848/V04AT04A025/243077,2017.
[9] YI T X,GUTMARK E J.Online prediction of the onset of combustion instability based on the computation of damping ratios[J].Journal of Sound and Vibration,2008,310(1/2):442-447.
[10] NOIRAY N,SCHUERMANS B.Deterministic quantities characterizing noise driven Hopf bifurcations in gas turbine combustors[J].International Journal of Non-Linear Mechanics,2013,50:152-163.
[11] NOIRAY N.Linear growth rate estimation from dynamics and statistics of acoustic signal envelope in turbulent combustors[J].Journal of Engineering for Gas Turbines and Power,2017,139(4):041503.
[12] BOUJO E,NOIRAY N.Robust identification of harmonic oscillator parameters using the adjoint Fokker-Planck equation[J].Proceedings of the Royal Society A:Mathematical,Physical and Engineering Sciences,2017,473(2200):20160894.
[13] BONCIOLINI G,BOUJO E,NOIRAY N.Output-only parameter identification of a colored-noise-driven Van-der-Pol oscillator:Thermoacoustic instabilities as an example[J].Physical Review E,2017,95(6):062217.
[14] 杨尚荣,周晨初,王牧昕.同轴离心式喷嘴燃烧稳定性裕度评估[J].推进技术,2022,43(1):224-230.
[15] HUANG N E,SHEN Z,LONG S R,et al.The empirical mode decomposition and the Hilbert spectrum for nonlinear and non-stationary time series analysis[J].Proceedings of the Royal Society of London Series A:Mathematical,Physical and Engineering Sciences,1998,454(1971):903-995.
[16] DRAGOMIRETSKIY K,ZOSSO D.Variational mode decomposition[J].IEEE Transactions on Signal Processing,2014,62(3):531-544.
[17] SMITH J S.The local mean decomposition and its application to EEG perception data[J].Journal of the Royal Society Interface,2005,2(5):443-454.
[18] 吴文轩,王志坚,张纪平,等.基于峭度的VMD分解中k值的确定方法研究[J].机械传动,2018,42(8):153-157.
[19] 刘倩,李敬轩,孙纪国,等.高压氢氧火箭发动机推力室燃烧稳定性分析[J].火箭推进,2022,48(2):66-75.
LIU Q,LI J X,SUN J G,et al.Analysis on combustion stability of thrust chamber in high pressure hydrogen-oxygen rocket engine[J].Journal of Rocket Propulsion,2022,48(2):66-75.
[20] 刘红珍,田原.某液体火箭发动机燃气路异常压力脉动分析[J].火箭推进,2022,48(5):69-75.
LIU H Z,TIAN Y.Study on abnormal pressure pulsation of gas path in a liquid rocket engine[J].Journal of Rocket Propulsion,2022,48(5):69-75.
相似文献/References:
[1]沈赤兵,李清廉,罗世彬,等.三组元火箭发动机推力室试验研究[J].火箭推进,2006,32(05):1.
Shen Chibing,Li Qinglian,Luo Shibin,et al.Experimental research on the thrust chamber of tripropellant rocket engine[J].Journal of Rocket Propulsion,2006,32(05):1.
[2]葛明龙,郑孟伟.声腔深度和相对开口面积的确定[J].火箭推进,2004,(04):15.
Ge Minglong,Zheng Mengwei.Determination of the Depth and Fractional Open Area for Acoustic Cavity[J].Journal of Rocket Propulsion,2004,(05):15.
备注/Memo
收稿日期:2022-08-15; 修回日期:2022-09-15
基金项目:国家自然科学青年基金(12102482)
作者简介:樊志伟(1998—),男,硕士,研究领域为液体火箭发动机燃烧不稳定。
通信作者:何博(1985—),男,博士,副教授,研究领域为空天动力喷雾燃烧与热声不稳定。
更新日期/Last Update:
1900-01-01