轴向分级燃烧不稳定性的关键因素与控制

doi:10.7527/S1000-6893.2025.31692

Abstract

Abstract:

The axial staging combustion for industrial gas turbines significantly widens the power regulation range and effectively reduces NO _x emissions. However， the impact of secondary nozzle parameters on the combustion instability requires further investigation. To address this， a three-dimensional theoretical model is developed to consider the coupling of multiple nozzles with the perforated liner， in order to analyze the effects of axial staging combustion on combustion instability and the control mechanisms of the perforated liner.Results show that the flame response of the primary nozzle has a notable effect on the first-order axial modes， while the parameters of the secondary nozzle mainly affect the first-order azimuthal modes. Furthermore， when the secondary nozzle is located at the acoustic pressure antinode of the first-order axial mode， i.e.， near the inlet and outlet of the combustion chamber， its effects on frequency and growth rate become more important. When the circumferential angular difference between the two secondary nozzles is π/2， the combined effects of their flame responses on the nondegenerate azimuthal modes are relatively weak. In contrast， when the circumferential angular difference is $π$ ， the combined effects of the secondary nozzles’ flame responses on the nondegenerate azimuthal modes become more significant. In addition， the presence of the secondary nozzles leads to an axial sound pressure distribution for the first-order azimuthal mode， allowing the perforated liner positioned close to the secondary nozzle to effectively suppress the combustion instability.

Key words: combustion instability, axial staging combustion, secondary nozzle position, perforated liner, coupling effects

CLC Number:

V231

Lei QIN, Guangyu ZHANG, Xiaoyu WANG, Xiaofeng SUN. Key factors and control methods of combustion instability under axial staging combustion[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(5): 531692.

Figures/Tables 11

Fig.1

Fig. 2

Table 1

Parameters of axial staging combustor

参数	数值
燃烧室半径 $r t$ /m	0.1
未燃气体平均密度 $ρ ¯ u$ /（kg·m^-3）	2.32
未燃气体声速 $c ¯ u$ /（m·s^-1）	347.2
一级喷嘴半径 $r f 1$ /mm	16.5
一级喷嘴长度 $l f 1$ /mm	60
一级喷嘴内热源增益系数 $k f 1$	0.45
一级喷嘴径向位置 $r q$ /m	0.05
燃烧室轴向长度 $l d$ /m	0.36
已燃气体平均密度 $ρ ¯ b$ /（kg·m^-3）	0.7
已燃气体声速 $c ¯ b$ /（m·s^-1）	633.9
二级喷嘴半径 $r f 2$ /mm	24
二级喷嘴长度 $l f 2$ /mm	76
二级喷嘴内热源增益系数 $k f 2$	1

Table 1

Fig.3

Fig.4

Fig.5

Fig.6

Table 2

Parameters of perforated liner

参数	数值
腔深 $D z$	0.1 $r t$
声衬长度 $l p$	0.15 $l d$
穿孔率 $σ$	0.012
小孔半径 $r z$ /mm	1.5
偏流马赫数 $M a z$	0.03
板厚 $ζ z$ /mm	0.8
声衬前缘与燃烧室进口轴向距离 $l w$	可变

Table 2

Fig.7

Fig.8

Fig.9

References 27

1	U.S. Environmental Protection Agency. Aircraft： Exhaust emission standards［R］. Washington， D.C.： U.S. Environmental Protection Agency， 2016.
2	KARIM H， NATARAJAN J， NARRA V， et al. Staged combustion system for improved emissions operability and flexibility for 7HA class heavy duty gas turbine engine［C］∥ASME Turbo Expo 2017： Turbomachinery Technical Conference and Exposition. New York： ASME， 2017.
3	RAYLEIGH L. The theory of sound［M］. 2nd edition. London： Macmillan， 1896： 224-234.
4	HUANG Y， YANG V. Dynamics and stability of lean-premixed swirl-stabilized combustion［J］. Progress in Energy and Combustion Science， 2009， 35（4）： 293-364.
5	李磊，孙晓峰. 推进动力系统燃烧不稳定性产生的机理、预测及控制方法［J］. 推进技术， 2010， 31（6）： 710-720.
	LI L， SUN X F. Mechanism， prediction and control method of combustion instability in propulsion system［J］. Journal of Propulsion Technology， 2010， 31（6）： 710-720 （in Chinese）.
6	SCHULZ O. Combustion dynamics in gas turbine sequential combustors［D］. Zurich： ETH Zurich， 2019.
7	CHOI Y， KIM K T. Influences of axial-fuel-staging combustion dynamics of a lean premixed combustor［C］∥Proceedings of the 29th International Colloquium on the Dynamics of Explosions and Reactive Systems， 2023.
8	LI Y Z， JIA Y L， JIN M， et al. Experimental investigations on NO _x emission and combustion dynamics in an axial fuel staging combustor［J］. Journal of Thermal Science， 2022， 31（1）： 198-206.
9	隋永枫，张宇明，臧鹏，等. 次级燃烧对轴向分级燃烧室燃烧特性影响的试验研究［J］. 上海交通大学学报， 2024， 58（8）： 1139-1147.
	SUI Y F， ZHANG Y M， ZANG P， et al. Experimental study of influence of secondary combustion on combustion characteristics of axial staged combustor［J］. Journal of Shanghai Jiao Tong University， 2024， 58（8）： 1139-1147 （in Chinese）.
10	梁恩广，张辰杰，余志健，等. 燃气轮机轴向贫燃分级燃烧技术进展［J］. 动力工程学报， 2024， 44（9）： 1328-1339.
	LIANG E G， ZHANG C J， YU Z J， et al. Progress in axial staged lean premixed combustion technology of gas turbines［J］. Journal of Chinese Society of Power Engineering， 2024， 44（9）： 1328-1339 （in Chinese）.
11	BLAETTE L， BOETTCHER A， STREB H. Combustion system upgrades for high operation flexibility and low emission： Design， testing and validation of the SGT5-4000F［C］∥ASME Turbo Expo 2020： Turbomachinery Technical Conference and Exposition. New York： ASME， 2020.
12	GUYOT D， TEA G， APPEL C. Low NO _x lean premix reheat combustion in Alstom GT24 gas turbines［J］. Journal of Engineering for Gas Turbines and Power， 2016， 138（5）： 051503.
13	DUPÈRE I D J， DOWLING A P. The use of Helmholtz resonators in a practical combustor［J］. Journal of Engineering for Gas Turbines and Power， 2005， 127（2）： 268-275.
14	YANG D， SOGARO F M， MORGANS A S， et al. Optimising the acoustic damping of multiple Helmholtz resonators attached to a thin annular duct［J］. Journal of Sound and Vibration， 2019， 444： 69-84.
15	ELDREDGE J D， DOWLING A P. The absorption of axial acoustic waves by a perforated liner with bias flow［J］. Journal of Fluid Mechanics， 2003， 485： 307-335.
16	郭志辉，李磊，张澄宇，等. 关于热声不稳定性现象的一种控制方法［J］. 工程热物理学报， 2008， 29（6）： 947-950.
	GUO Z H， LI L， ZHANG C Y， et al. A control method for the suppression of thermoacoustic instability［J］. Journal of Engineering Thermophysics， 2008， 29（6）： 947-950 （in Chinese）.
17	孙晓峰，张光宇，王晓宇，等. 航空发动机燃烧不稳定性预测及控制研究进展［J］. 航空学报， 2023， 44（14）： 628733.
	SUN X F， ZHANG G Y， WANG X Y， et al. Research progress in aero-engine combustion instability prediction and control［J］. Acta Aeronautica et Astronautica Sinica， 2023， 44（14）： 628733 （in Chinese）.
18	ZHANG G Y， WANG X Y， LI L， et al. Effects of perforated liners on controlling combustion instabilities in annular combustors［J］. AIAA Journal， 2020， 58（7）： 3100-3114.
19	ZHANG G Y， ZHANG X X， WANG X Y， et al. Modeling analysis of combustion instability in an annular combustor equipped with circumferentially segmented perforated liner［J］. Journal of Sound and Vibration， 2023， 549： 117573.
20	QIN L， WANG X Y， ZHANG G Y， et al. Control of azimuthal combustion instability through the injector mounting surface of annular combustors［J］. AIAA Journal， 2023， 61（9）： 3795-3809.
21	QIN L， WANG X Y， ZHANG G Y， et al. Theoretical model of azimuthal combustion instability subject to non-trivial boundary conditions［J］. Chinese Journal of Aeronautics， 2024， 37（9）： 113-130.
22	SUN X， JING X， ZHANG H， et al. Effect of grazing-bias flow interaction on acoustic impedance of perforated plates［J］. Journal of Sound Vibration， 2002， 254（3）： 557-573.
23	JING X D， SUN X F. Experimental investigations of perforated liners with bias flow［J］. The Journal of the Acoustical Society of America， 1999， 106（5）： 2436-2441.
24	JING X D， SUN X F. Effect of plate thickness on impedance of perforated plates with bias flow［J］. AIAA Journal， 2000， 38（9）： 1573-1578.
25	HOWE M S. On the theory of unsteady high Reynolds number flow through a circular aperture［J］. Proceedings of the Royal Society of London， Series A： Mathematical， Physical and Engineering Sciences， 1979， 366（1725）： 205-223.
26	QIN L， WANG X Y， ZHANG G Y， et al. Suppression of azimuthal combustion instability using perforated liner under symmetry breaking［J］. Journal of Propulsion and Power， 2025， 41（1）： 27-39.
27	GOLDSTEIN M E. Aeroacoustics［M］. New York： McGraw-Hill International Book， 1976： 22-32.

[1]	Duo ZHENG, Zhichen CHU, Defu LIN, Mingjun WEI, Siyi YUE. Cooperative guidance technique considering flight safety constraints of cluster wake vortex aerodynamic coupling effects [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(18): 329906-329906.
[2]	Guangxu WANG, Baoe YANG, Yonghua TAN, Yushan GAO, Bin LI. Randomness of high frequency longitudinal combustion instability in liquid rocket engines [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(14): 129485-129485.
[3]	Guangxu WANG, Bin LI, Yonghua TAN, Yushan GAO. High frequency combustion instability in liquid rocket engines: Review [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529450-529450.
[4]	Junfeng LIAO, Xiaodong JING, Xianghai QIU, Yonglei ZHAI, Xishan YUE, Shuangchao MA, Lin DU, Xiaofeng SUN. Experimental study on grazing flow characteristics of a new aeronautical wire mesh acoustic liner [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 528537-528537.
[5]	Weidong LIU, Haoyang PENG, Shijie LIU, Hailong ZHANG, Xueqiang YUAN. Research Progresses of rotating detonation combustion and its application [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528875-528875.
[6]	Xiaofeng SUN, Guangyu ZHANG, Xiaoyu WANG, Lei LI, Xiangyang DENG, Ronghui CHENG. Research progress in aero-engine combustion instability prediction and control [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628733-628733.
[7]	Tao CHEN, Xingping XU, Hongda ZHANG, Xingsi HAN. Numerical simulation of combustion instability by SATES coupling with FGM combustion model [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628207-628207.
[8]	WANG Guangxu, TAN Yonghua, ZHUANG Fengchen, CHEN Jianhua, YANG Bao'e, HONG Liu. Suppression effect of injection intensity distribution on longitudinal combustion instability [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126018-126018.
[9]	LI Jia'nan, LEI Fanpei, YANG Anlong, ZHOU Lixin. Atomization characteristics of impinging liquid jets coupled with forced perturbation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(12): 124027-124027.
[10]	KANG Zhongtao, LI Xiangdong, MAO Xiongbing, LI Qinglian. Review on gas liquid shear coaxial injector in liquid rocket engine [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(9): 22221-022221.
[11]	LIU Zeyu, ZHANG Chi, HAN Xiao, LIN Yuzhen. Effects of stratification ratio on structure of separated stratified premixed swirl flame [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(3): 121692-121692.
[12]	JING Xiao-dong;SUN Xiao-feng. INVESTIGATION OF GRAZING FLOW EFFECT ON THE IMPEDANCE OF A PERFORATED PLATE [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2002, 23(5): 405-410.
[13]	LI Wan-yu;RUAN Ai-wu;LUO Jin-sheng;FENG Pei-de. ERROR SOURCES IN MICROMACHINED COMB DRIVE TUNING FORK GYROSCOPE [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1999, 20(5): 426-429.

Key factors and control methods of combustion instability under axial staging combustion

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 11

References 27

Related Articles 13

Recommended Articles

Metrics

Comments