Multi-scale kurtosis index diagnosis method of unstable combustion states
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摘要:
为建立先进航空发动机和燃气轮机燃烧室工程试验中不稳定燃烧状态评定方法,提出了一种基于燃烧室压力脉动信号多尺度峭度指标的诊断方法,联合诊断两种不稳定燃烧状态:燃烧不稳定(CI)和火焰不稳定(FI),并在气体燃料旋流燃烧室和航空煤油贫油预混预蒸发燃烧室两组试验中进行验证分析。研究结果表明:采用规范化后的平均峭度指标,可用作CI状态判据,但不适用于FI诊断;采用基于时间尺度无关性的最佳时间尺度来定义的CI峭度指标和FI峭度指标,可以反映压力振荡等级和压力时序间歇性,且各自与CI和FI程度形成递增关系;建立的瞬时压力峭度和间歇性峭度综合判定准则,可为燃烧室燃烧不稳定性在线评价提供判据。
Abstract:In order to establish a method of evaluating unstable combustion states in advanced aeroengine and gas turbine combustion chamber engineering tests, a diagnosis method based on the multi-scale kurtosis index of the combustion chamber pressure pulsation signal was proposed, two unstable combustion states: combustion instabilities (CI) and flame instabilities (FI), were diagnosed, and the test and analysis were carried out in the gas fuel swirl combustor and liquid kerosene lean premixed pre-vaporized combustor. The results of the study showed that the normalized mean kurtosis index can be used as a CI status criterion, but it is not suitable for FI diagnosis; the CI and FI kurtosis indexes defined by the optimal time scale based on time scale independence can indicate the pressure oscillation level and the intermittent feature of pressure sequence, and the parameters have an increasing relationship with the CI and FI degree correspondingly; the established comprehensive judgment norm based on instantaneous pressure kurtosis and intermittent kurtosis can provide a criterion for online evaluation of combustion instability.
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Key words:
- combustion instability /
- flame instability /
- pressure pulsation /
- kurtosis index /
- time scale
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表 1 典型工况下的DP平均峭度和间歇性峭度
Table 1. DP mean kurtosis and intermittent kurtosis under typical operating conditions
状态 ${\overline K_p}$ ${\overline K_s}$ 稳定燃烧 0.3398 0.3255 CI 1.4591 0.3371 CI前的FI 0.8428 0.5588 表 2 G燃烧室燃烧状态识别试验工况表
Table 2. Test conditions of combustion state identification in G combustor
工况 $\dot { {m} } _{ \rm{a} }$/(g/s) Φ Q/kW ${\overline K_p}$ ${\overline K_s}$ 状态 GA01 9.24 0.39 1.166 0.3398 0.3255 稳定 GA02 9.24 0.34 0.999 0.2829 0.4618 稳定 GA03 9.24 0.28 0.833 0.3725 0.4236 稳定 GA04 9.24 0.26 0.783 0.3554 0.3326 稳定 GA05 9.24 0.23 0.683 0.5478 0.4411 稳定 GA06 9.24 0.19 0.583 0.2706 0.5791 FI GB01 9.85 0.42 1.333 0.2996 0.4103 稳定 GB02 9.85 0.37 1.166 0.3162 0.4428 稳定 GB03 9.85 0.32 0.999 0.3196 0.4643 稳定 GB04 9.85 0.26 0.833 0.4334 0.4733 稳定 GB05 9.85 0.24 0.749 0.7763 0.5493 FI GB06 9.85 0.21 0.666 1.3789 0.4822 CI GC01 11.00 0.38 1.333 0.3143 0.3666 稳定 GC02 11.00 0.33 1.166 0.3582 0.3346 稳定 GC03 11.00 0.28 0.999 0.8428 0.5588 FI GC04 11.00 0.26 0.916 1.4549 0.3739 CI GC05 11.00 0.24 0.833 1.4588 0.4696 CI GC06 11.00 0.21 0.750 1.4591 0.3371 CI 表 3 L燃烧室燃烧状态识别试验工况表
Table 3. Test conditions of combustion state identification in L combustor
工况 $\dot {{m} }_{{{\rm{a}}} }$/(g/s) Φ Q/kW ${\overline K_p}$ ${\overline K_s}$ 状态 LA01 100 0.75 20.7 0.9246 0.5917 FI LA02 100 0.73 20.1 0.9645 0.9378 FI LA03 100 0.70 19.3 1.3654 0.7340 CI LA04 100 0.68 18.7 1.3750 0.8294 CI LA05 100 0.56 15.5 1.4389 0.6202 CI LA06 100 0.49 13.5 1.4496 0.6198 CI LB01 130 0.81 27.9 1.2147 0.8230 CI LB02 130 0.77 26.5 1.2261 0.9287 CI LB03 130 0.71 24.5 1.2162 0.9914 CI LB04 130 0.70 24.1 1.1748 1.1267 CI LB05 130 0.65 22.4 1.2826 0.8090 CI LB06 130 0.56 19.3 1.3995 0.6339 CI LC01 140 0.75 27.9 1.2247 1.1041 CI LC02 140 0.71 26.4 1.2773 0.8471 CI LC03 140 0.67 25.0 1.2443 0.9431 CI LC04 140 0.65 24.2 1.2227 0.9077 CI LC05 140 0.60 22.3 1.3214 0.8497 CI LC06 140 0.56 20.8 1.3188 0.8726 CI -
[1] NATANZON M S, CULICK F E C. Combustion instability[M]. Moscow: AIAA, 1999. [2] LIEUWEN T C, YANG V. Combustion instabilities in gas turbine engines: operational experience fundamental mechanisms and modeling[M]. Reston, US: AIAA, 2005: 68-73. [3] CHANDRACHUR B, O’CONNOR J, RAY A. Data-driven detection and early prediction of thermoacoustic instability in a multi-nozzle combustor[EB/OL]. [2022-05-22]. https://doi.Org/10.1080/00102202.2020.1820495. [4] SONG W J,CHA D J. Temporal kurtosis of dynamic pressure signal as a quantitative measure of combustion instability[J]. Applied Thermal Engineering,2016,104(1): 577-586. [5] SANTOS E A,MARTINS C A,JÚNIOR C L N. A new approach to treating pressure oscillations in combustion instability phenomena[J]. Applied Acoustics,2016,114: 27-35. doi: 10.1016/j.apacoust.2016.07.006 [6] ROUWENHORS D, POLIFKE W, HERMAN J. Online monitoring of thermoacoustic eigenmodes in annular combustion systems based on a state space model[R]. ASME Paper GT2016-56671, 2016. [7] KOBAYASHI H,GOTODA H,TACHIBANA S. Nonlinear determinism in degenerated combustion instability in a gas turbine model combustor[J]. Statistical Mechanics and its Applications,2018,510(15): 345-354. [8] BUSCHHAGEN T, GEJJI R, PHILO J, et al. Experimental investigation of self-excited combustion instabilities in a lean, premixed, gas turbine combustor at high pressure[R]. ASME Paper GT2017-64614, 2017. [9] LAERA D, BERTOLOTTO E, FERRANTE A, et al. Modelling of thermoacoustic combustion instabilities phenomena: application to an experimental rig for testing full scale burners[R]. ASME Paper GT2014-25273, 2014. [10] WORTH N A,DAWSON J R. Effect of equivalence ratio on the modal dynamics of azimuthal combustion instabilities[J]. Proceedings of the Combustion Institute,2017,36(3): 3743-3751. doi: 10.1016/j.proci.2016.06.115 [11] HALE A A, COTHRAN W D, SABO K M. Analysis technique to determine the underlying wave structure of combustion instabilities from surface mounted high response static pressure sensors[R]. ASME Paper GT2018-75509, 2018. [12] BALUSAMY S,LI L B,HAN Z,et al. Nonlinear dynamics of a self-excited thermoacoustic system subjected to acoustic forcing[J]. Proceedings of the Combustion Institute,2015,35(3): 3229-3236. doi: 10.1016/j.proci.2014.05.029 [13] BHATTACHARYA A, GUPTA B, HANSDA S, et al. Lean blowout phenomena and prior detection of lean blowout in a premixed model annular combustor[R].ASME Paper GTINDIA2019-2491, 2019. [14] 金如山, 索建秦. 先进燃气轮机燃烧室[M]. 北京: 航空工业出版社, 2016. [15] ANGELLO L. Tuning approaches for DLN combustor performance and reliability[R]. Palo Alto, CA: Electric Power Research Institute Report 1005037, 2005. [16] 郑丹伟,刘勇,张祥. 基于火焰图像诊断的模型燃烧室燃烧不稳定特性[J]. 航空动力学报,2021,36(7): 1481-1488. doi: 10.13224/j.cnki.jasp.20200425ZHENG Danwei,LIU Yong,ZHANG Xiang. Combustion instability characteristics of model combustor based on flame image diagnosis[J]. Journal of Aerospace Power,2021,36(7): 1481-1488. (in Chinese) doi: 10.13224/j.cnki.jasp.20200425 [17] NAIR S, LIEUWEN T. Acoustic detection of imminent blowout in pilot and swirl stabilized combustors[R]. ASME Paper GT2003-38074, 2003. [18] 郗涛, 杨威振. 优化VMD与CNN 在齿轮箱故障诊断方面的研究[EB/OL].[2022-05-22]. https://doi.org/10.13433/j.cnki.1003-8728.20200521. [19] 侯泽林. 旋转机械故障诊断的研究现状及发展前景[J]. 机械研究与应用,2021,34(4): 210-213. doi: 10.16576/j.cnki.1007-4414.2021.04.064HOU Zelin. Research status and development prospect of fault diagnosis of the rotating machinery[J]. Mechanical Research and Application,2021,34(4): 210-213. (in Chinese) doi: 10.16576/j.cnki.1007-4414.2021.04.064 [20] 吕凯波,娄培生,谷丰收,等. 基于声压信号能量峭度的早期切削颤振预警技术研究[J]. 振动与冲击,2021,40(20): 50-55. doi: 10.13465/j.cnki.jvs.2021.20.007LÜ Kaibo,LOU Peisheng,GU Fengshou,et al. A study on early chatter monitoring based on energy kurtosis index of acoustic signals[J]. Journal of Vibration and Shock,2021,40(20): 50-55. (in Chinese) doi: 10.13465/j.cnki.jvs.2021.20.007 [21] JOO S, CHOI J, LEE M C, et al. Prognosis of combustion instability in a gas turbine combustor using spectral centroid & spread[EB/OL]. [2022-05-22].https: //doi.org/10.1016/j.energy.2021.120180. [22] CHOIB J, CHOI O, LEE M C, et al. On the observation of the transient behavior of gas turbine combustion instability using the entropy analysis of dynamic pressure[EB/OL]. [2022-05-22]. https://doi.org/10.1016/j.expthermflusci.2020.110099.