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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Experimental Study on Instability Characteristics of Low-Swirl Flames in a Multinozzle Combustor With Different Swirling Arrays

[+] Author and Article Information
Weijie Liu

Institute of Turbomachinery,
School of Mechanical Engineering,
Shanghai Jiao Tong University,
Dongchuan Road 800,
Shanghai 200240, China
e-mail: zhanshen@sjtu.edu.cn

Bing Ge

Institute of Turbomachinery,
School of Mechanical Engineering,
Shanghai Jiao Tong University,
Dongchuan Road 800,
Shanghai 200240, China
e-mail: gebing@sjtu.edu.cn

Yinshen Tian

Institute of Turbomachinery,
School of Mechanical Engineering,
Shanghai Jiao Tong University,
Dongchuan Road 800,
Shanghai 200240, China
e-mail: tyshen@qq.com

Shusheng Zang

Institute of Turbomachinery,
School of Mechanical Engineering,
Shanghai Jiao Tong University,
Dongchuan Road 800,
Shanghai 200240, China
e-mail: sszang@sjtu.edu.cn

Shilie Weng

Institute of Turbomachinery,
School of Mechanical Engineering,
Shanghai Jiao Tong University,
Dongchuan Road 800,
Shanghai 200240, China
e-mail: slweng@sjtu.edu.cn

1Corresponding author.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received October 21, 2016; final manuscript received December 19, 2016; published online February 1, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(6), 061503 (Feb 01, 2017) (9 pages) Paper No: GTP-16-1505; doi: 10.1115/1.4035660 History: Received October 21, 2016; Revised December 19, 2016

This paper presents experimental study on self-excited combustion instability characteristics of premixed low-swirl flames in a multinozzle can combustor with counterswirl and coswirl arrays. Experiments were carried out over a wide range of inlet velocity from 4 m/s to 15.5 m/s and equivalence ratio from 0.5 to 0.85. Phase-locked OH planar laser-induced fluorescence was employed to measure flame shape and identify heat release rate. Four operation regions: stable combustion region, unstable combustion region, flashback region, and extinguish region are observed for both array burners. The amplitude of pressure fluctuation for counterswirl arrangement is less than the coswirl array, and the stable operating window of the counterswirl array is wider. In the unstable combustion region, the counterswirl flame triggers the 2L mode of the combustion system, while the coswirl flame incites three longitudinal modes with the highest amplitude near 3L. Rayleigh index distribution reveals neighboring flame interaction results in thermoacoustic coupling for multinozzle flames. Additionally, for the counterswirl array, thermoacoustic couplings also exit in the flame base region and shear region while, for the coswirl array, the instability driving zones also locate at the lip region and the tail of center flame which is totally different with counterswirl flame.

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References

Figures

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Fig. 1

Schematic of the structure of a single low-swirl nozzle (units: mm)

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Fig. 2

Multinozzle burner with different swirling arrays: (a) multinozzle burner, (b) coswirl array, and (c) counterswirl array

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Fig. 3

Schematic of the multinozzle combustion test rig

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Fig. 4

Pressure oscillations and phase-locked triggering signal sequences

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Fig. 5

Pressure spectra for different equivalence ratios at U0 = 9.3 m/s: (a) counterswirl array and (b) coswirl array

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Fig. 6

Pressure spectra for different bulk inlet velocities at ϕ=0.7 : (a) counterswirl array and (b) coswirl array

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Fig. 7

Operation diagrams of multinozzle burner with counterswirl (left) and coswirl (right) array. The star point at ϕ=0.67 and U0 = 9.3 m/s, marks the operating condition where acoustic analysis and phase-locked measurement are conducted.

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Fig. 8

Schematic of the acoustic model for the multinozzle combustion system

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Fig. 9

Coswirl multinozzle flame and a schematic of PLIF imaging region

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Fig. 10

Filtered pressure oscillations in the combustor and pressure drop with the assigned phase angles at which phase-locked measurements were performed

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Fig. 11

Phase-averaged flame structure evolution in one oscillation period for counterswirl array (upper) and coswirl array (down)

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Fig. 12

Heat release fluctuations of global flame, center flame and outer flame along with pressure oscillation as a function of phase angle for counterswirl and coswirl flame

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Fig. 13

Local Rayleigh index maps of the multinozzle flames

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Fig. 14

Rayleigh index profiles for counterswirl (upper) and coswirl (down) flames along three typical lines

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