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

Design for Thermo-Acoustic Stability: Modeling of Burner and Flame Dynamics

[+] Author and Article Information
S. Bade

e-mail: bade@td.mw.tum.de

T. Sattelmayer

Lehrstuhl für Thermodynamik,
Technische Universität München,
Garching, Germany

B. Schuermans

Alstom,
Baden, Switzerland

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 June 26, 2013; final manuscript received July 8, 2013; published online September 17, 2013. Editor: David Wisler.

J. Eng. Gas Turbines Power 135(11), 111502 (Sep 17, 2013) (7 pages) Paper No: GTP-13-1183; doi: 10.1115/1.4025001 History: Received June 26, 2013; Revised July 08, 2013

A design for thermo-acoustic stability (DeTAS) procedure is presented that aims at selecting the most stable burner geometry for a given combustor. It is based on the premise that a thermo-acoustic stability model of the combustor can be formulated and that a burner design exists, which has geometric design parameters that sufficiently influence the dynamics of the flame. Describing the flame dynamics in dependence of the geometrical parameters, an optimization procedure involving a linear stability model of the target combustor, maximizes the damping and thereby yields the optimal geometrical parameters. To demonstrate the procedure on an existing annular combustor a generic burner design was developed that features significant variability of dynamical flame response in dependence of two geometrical parameters. In this paper the experimentally determined complex burner acoustics and complex flame responses are described in terms of physics-based parametric models with excellent agreement between experimental and model data. It is shown that these model parameters correlate uniquely with the variation of the burner geometrical parameters, allowing interpolating the model with respect to the geometrical parameters. The interpolation is validated with experimental data.

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References

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Figures

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Fig. 1

Modular burner kit consisting of a swirler with different mixing tube lengths Lm and perforated plates to vary the head air ratio Rh

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Fig. 2

Network model of the annular combustor [11]

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Fig. 3

Network model of a burner with Lm = 1.875 db

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Fig. 4

Comparison of the experimental (marker) and the modeled BTM (line) of the Rh = 100% swirler with different mixing tube lengths Lm

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Fig. 5

T11 and T12 element of the BTMs of the burner with Rh = 30%, 50%, and 100% head air ratio and a mixing tube length of Lm = 1.875 db [13]

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Fig. 6

Validation of the interpolation scheme of the Rh = 100% swirler with two further mixing tube lengths Lm = 0.9375 db and Lm = 1.5625 db

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Fig. 7

Linear dependency of the flame parameters of the burner with Rh = 100% and five different mixing tube lengths (Lm = 0.625 to 1.8750 db) normalized with the values of the burner with Lm = 1.875 db

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Fig. 8

Experimentally determined FTF (FTFexp), modeled FTF (FTFmod) and the flame model separated in the parts: time delay caused by mass flow fluctuations (FTFm) and time delay caused by swirl fluctuations (FTFs) of the 100% swirler with Lm = 1.875 db

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Fig. 9

Comparison of the experimental (marker) and the modeled (line) FTFs of the Rh = 30% swirler with different mixing tube lengths Lm

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Fig. 10

Comparison of the experimental (marker) and the modeled (line) FTFs of the Rh = 50% swirler with different mixing tube lengths Lm

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Fig. 11

Comparison of the experimental (marker) and the modeled (line) FTFs of the Rh = 100% swirler with different mixing tube lengths Lm

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Fig. 12

Validation of the interpolation scheme of the Rh = 100% with two further mixing tube lengths Lm = 0.9375 db and Lm = 1.5625 db

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