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

A Hybrid Semi-empirical Model for Lean Blow-Out Limit Predictions of Aero-engine Combustors

[+] Author and Article Information
Bin Hu

Institute of Engineering Thermophysics,
Chinese Academy of Sciences,
No. 11 Beisihuan West Road,
Haidian District,
Beijing 100190, China
e-mail: hubin@iet.cn

Yong Huang

School of Energy and Power Engineering,
Beihang University,
No. 37 Xueyuan Road,
Haidian District,
Beijing 100191, China
e-mail: yhuang@buaa.edu.cn

Jianzhong Xu

Institute of Engineering Thermophysics,
Chinese Academy of Sciences,
No. 11 Beisihuan West Road,
Haidian District,
Beijing 100190, China
e-mail: xjz@iet.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 July 18, 2014; final manuscript received July 24, 2014; published online September 30, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(3), 031502 (Sep 30, 2014) (10 pages) Paper No: GTP-14-1407; doi: 10.1115/1.4028394 History: Received July 18, 2014; Revised July 24, 2014

According to the Lefebvre's model and flame volume (FV) concept, an FV model about lean blow-out (LBO) was proposed by authors in early study. On the other hand, due to the model parameter (FV) contained in FV model is obtained based on the experimental data, FV model could only be used in LBO analysis instead of prediction. In view of this, a hybrid FV model is proposed that combines the FV model with numerical simulation in the present study. The model parameters contained in the FV model are all estimated from the simulated nonreacting flows. Comparing with the experimental data for 11 combustors, the maximum and average uncertainties of hybrid FV model are ±16% and ±10%.

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Fig. 1

Comparison of the flame zone obtained by experimental image and the fuel concentration contour (cutoff by flammable limit) obtained by numerical simulation without combustion [32]

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Fig. 2

Origination of the present research approach

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Fig. 4

Combustor configuration

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Fig. 3

Schematic diagram of LBO test rig

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Fig. 5

Computational domain and numerical boundary conditions

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Fig. 6

Various views of computational grids

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Fig. 7

Computational domain and swirler configuration. (a) Computational domain of the model combustor. (b) Configuration of the swirler [34].

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Fig. 8

Comparison of the computational results operated by author with experimental and computational results operated by Davoudzadeh

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Fig. 10

Locations of the characteristic points in the symmetry plane of the combustor (grayed by axial velocity)

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Fig. 11

Comparison of β and βf,n,c

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Fig. 9

Values of Vf,n under different mf

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Fig. 12

A 3D depiction of Vf,n,c

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Fig. 15

Comparison of qLBO and qLBO,predict

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Fig. 13

Comparison of qLBO and βf,n,c

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Fig. 14

Schematic diagram of the relationship between the movement of vortex center and qLBO



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