基于单扇区燃烧室试验的热声模拟方法研究及验证

高贤智; 王雄辉; 冯晓星; 鄂亚佳; 何沛

doi:10.13224/j.cnki.jasp.20210117

基于单扇区燃烧室试验的热声模拟方法研究及验证

doi: 10.13224/j.cnki.jasp.20210117

中国航空发动机集团有限公司商用航空发动机有限责任公司，上海 200241

基金项目: 上海市科学技术委员会“浦江人才计划”（项目编号：19PJ1433300）

详细信息

作者简介:
高贤智（1988-），男，工程师，硕士，主要从事热声不稳定性研究。

中图分类号: V231.2
计量
- 文章访问数: 356
- HTML浏览量: 175
- PDF量: 86
- 被引次数: 0
出版历程
- 收稿日期: 2021-03-16
- 刊出日期: 2022-02-28

Research and verification of thermo-acoustic simulation method based on single-sector combustion test

Commercial Aircraft Engine Company Limited，Aero Engine Corporations of China，Shanghai 200241，China

摘要

摘要: 利用自主开发的热声网络模型研究了不同试验工况、出口边界条件、入口测量段长度对单扇区燃烧室试验台燃烧不稳定性的影响，并与试验结果进行了对比分析。结果表明：声学网络模型准确预测了不同试验工况的失稳频率。预测失稳频率与试验失稳频率相差±10 Hz以内，误差在2%以内。前期单扇区燃烧室试验表明，当入口测量段为0.4 m时，发生燃烧振荡，当入口测量段为0.25 m时，未发生燃烧振荡。数值模拟表明只有当入口测量段长度在0.35~0.44 m之间时，才会激发自激燃烧振荡，这很好地解释了上述试验结果。
- 燃烧不稳定 /
- 热声网络 /
- 特征频率 /
- 单扇区燃烧室 /
- 贫燃燃烧室
Abstract: An in-house developed thermo-acoustic network model was used to study the effects of different test conditions，outlet boundary conditions，and the length of inlet measurement section on the combustion instabilities of single sector combustion test rig，and the results were compared between simulations and tests.The results showed that the thermo-acoustic network model accurately predicted the unstable frequency at different test conditions.The differences between the predicted and test results were within ±10 Hz，and the errors were within 2%.The previous single-sector combustion chamber test showed that combustion oscillation occurred when the inlet measurement section was 0.4 m.Combustion oscillation did not happen when the inlet measurement section was 0.25 m. Numerical simulations showed that the self-excited combustion oscillation can be excited only when the length of the inlet measurement section was between 0.35 m and 0.44 m，which explained the above test results well.
- combustion instabilities /
- thermo-acoustic network /
- eigen-frequency /
- single-sector combustor /
- lean burn combustor

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参考文献(23)

[1]	O'CONNOR J,ACHARYA V,LIEUWEN T.Transverse combustion instabilities:acoustic,fluid mechanic,and flame processes[J].Progress in Energy and Combustion Science,2015,49（1）:1-39.
[2]	POINSOT T.Prediction and control of combustion instabilities in real engines[J].Proceedings of the combustion institute,2017,36（1）:1-28.
[3]	TACHIBANA S,SAITO K,YAMAMOTO T,et al.Experimental and numerical investigation of thermo-acoustic instability in a liquid-fuel aero-engine combustor at elevated pressure:validity of large-eddy simulation of spray combustion[J].Combustion and Flame,2015,162（3）:2621-2637.
[4]	RENAUD A,TACHIBANA S,ARASE S,et al.Experimental study of thermoacoustic instability triggering in a staged liquid fuel combustor using high-speed OH-PLIF[R].ASME Paper GT2017-64102,2014.
[5]	MEIER U,LANGE L,HEINZE J,et al.Optical methods for studies of self-excited oscillations and the effect of dampers in a high-pressure single sector combustor[R].ASME Paper GT2014-25873,2014.
[6]	TAAMALLAH S,LABRY Z A,SHANBHOGUE S J,et al.Thermo-acoustic instabilities in lean premixed swirl-stabilized and their link to acoustically coupled and decoupled flame macrostructures[J].Proceedings of the combustion institute,2015,35（1）:3273-3282.
[7]	WORTH N A,DAWSON J R.Modal dynamics of self-excited azimuthal instabilities in an annular combustor[J].Combustion and Flame,2013,102（4）:2476-2489.
[8]	INDLEKOFER T,FRURE-BEAULIEU A,NOIRAY N,et al.The effect of dynamic operating conditions on the thermoacoustic response of hydrogen rich flame in an annular combustor[J].Combustion and Flame,2021,223（10）:284-294.
[9]	CULLER W,CHEN Xiaoling,SAMARASINGHE J,et al.The effect of variable fuel staging transients on self-excited instabilities in a multiple-nozzle combustor[J].Combustion and Flame,2018,194（4）:472-484.
[10]	张昊,朱民.热声耦合振荡燃烧的实验研究与分析[J].推进技术,2010,31（6）:730-744.
[11]	张昊,黄铮,朱民.自激振荡预混燃烧的实验[J].航空动力学报,2011,26（1）:28-34.
[12]	高贤智,何沛,冯晓星,等.单扇区、扇形、全环燃烧室热声不稳定性试验和模拟研究[J].航空动力学报,2021,36（8）:1605-1613.
[13]	邵卫东,高贤智.耦合热声网络与激励盘模型预测燃烧室不稳定振荡的研究[J].西安交通大学学报,2021,55（3）:186-194.
[14]	DOWLING A P,STOW S R.Acoustic analysis of gas turbine combustors[J].Journal of Propulsion and Power,2003,19（5）:751-764.
[15]	LIU Yu,DOWLING A P,SWAMINATHAN N,et al.Prediction of combustion noise for aeroengine combustor[J].Journal of Propulsion and Power,2014,30（1）:114-122.
[16]	STOW S R,DOWLING A P,HYNES T P,Reflection of circumferential modes in a choked nozzle[J].Journal of Fluid and Mechanics,2002,467:215-239.
[17]	BOTHIEN M K,NOIRAY N,SCHUERMANS B.Analysis of azimuthal thermo-acoustic modes in annular gas turbine combustion chambers[J].Journal of Engineering and.Gas Turbines Power,2015,137（6）:061505.1-061505.8.
[18]	GHIRARDO G,JUNIPER M P.Azimuthal instabilities in annular combustors:standing and spinning modes[J].Proceedings of the Royal Society A:Mathematical,Physical and Engineering Sciences,2013,469（2157）:1-16.
[19]	GHIRARDO G,BOUDY F,BOTHIEN M R.Amplitude statistics prediction in thermoacoustic[J].Journal of Fluid and Mechanics,2018,844:216-246.
[20]	HAN Xingsi,LI Jingxuan,AIMEE S M.Prediction of combustion instability limit cycle oscillations by combing flame describing function simulations with a thermoacoustic network model[J].Combustion and Flame,2015,162（6）:3632-3647.
[21]	MORGANS A S,STOW S R.Model-based control of combustion instabilities in annular combustors[J].Combustion and Flame,2007,150（6）:380-399.
[22]	YANG Dong,LAERA D,MORGANS A S.A systematic study of nonlinear coupling of thermoacoustic modes in annular combustors[J].Journal of Sound and Vibration,2019,456（4）:137-161.
[23]	FREZZOTTI M L,NASUTI F,HUANG C,et al.Quasi-1D modeling of heat release for the study of longitudinal combustion instability[J].Aerospace Science and Technology,2018,75（2）:261-270.