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

Design for Thermo-Acoustic Stability: Procedure and Database

[+] 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,
Brown Boveri Straße 7,
Baden 5401, Switzerland

As noted above, for 2 flames of the Rh = 30%, λ = 1.4 series, the flames were stabilizing inside the burner mouth. Therefore, the experiment was repeated at a slightly higher air excess ratio of λ = 1.45 which gives the data shown Fig. 14 Comparing with the respective data of the Rh = 30%, λ = 1.4 data given in Fig. 11, the difference is very small.

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 10, 2013; final manuscript received July 15, 2013; published online September 23, 2013. Editor: David Wisler.

J. Eng. Gas Turbines Power 135(12), 121507 (Sep 23, 2013) (8 pages) Paper No: GTP-13-1252; doi: 10.1115/1.4025131 History: Received July 10, 2013; Revised July 15, 2013

A design for thermo-acoustic stability (DeTAS) procedure is presented, that aims at selecting a 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 burner and 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 two geometrical parameters that can easily be adjusted. To provide the database for the DeTAS procedure static and dynamical properties of burner and flame were measured for three by three configurations at a fixed operation point. The data is presented and discussed. It is found that the chosen design exhibits a significant variability of the flame dynamics in dependence of the geometrical parameters indicating that a DeTAS should be possible for the targeted annular combustor.

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References

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Figures

Grahic Jump Location
Fig. 2

Atmospheric single burner testrig

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Fig. 3

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. 4

Sketch of the axial velocity profiles of burners with varying head air ratios (after [20])

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Fig. 5

OH* flame images of the burners with different head air ratios Rh and mixing tube lengths Lm

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Fig. 6

Maximal OH*-chemiluminescence xOH,max and axial stand-off distances xvb of the burner with different head air ratios Rh and mixing tube lengths Lm

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Fig. 7

Normalized flame volume of the burners with Rh = 30%, 50% and 100% with Lm = 0.625 db, 1.25 db and 1.875 db

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Fig. 8

T11 and T12 element of BTMs of the burners with Rh = 100% head air ratio and Lm = 0.625 db, 1.25 db and 1.875 db mixing tube length

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Fig. 10

FTF from OH*-chemiluminescence (ub OH*) and from FTM using Rankine–Hugoniot relations (RH) for Rh = 100% and Lm = 1.875 db

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Fig. 9

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

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Fig. 11

FTF of the burners with Rh = 100% with Lm = 1.875 db, Rh = 50% with Lm = 1.250 db and Rh = 30% with Lm = 0.625 db

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Fig. 12

FTF of the burners with Rh = 100% and Lm = 0.625 db, 1.250 db, 1.875 db

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Fig. 13

FTF of the burners with Rh = 50% and Lm = 0.625 db, 1.25 db, 1.875 db

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Fig. 14

FTF of the burners with Rh = 30% and Lm = 0.625 db, 1.25 db and 1.875 db

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