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

Impact of Heat Release Distribution on the Spinning Modes of an Annular Combustor With Multiple Matrix Burners

[+] Author and Article Information
Davide Laera

DMMM,
Sez. Macchine ed Energetica,
Politecnico di Bari,
Via Re David 200,
Bari 70125, Italy
e-mail: davide.laera@poliba.it

Kevin Prieur

Laboratoire EM2C,
CNRS, CentraleSupélec,
Université Paris-Saclay,
Grande Voie des Vignes,
Chatenay-Malabry cedex 92295, France;
Safran Tech, E&P,
Châteaufort, CS 80112,
Magny-Les-Hameaux 78772, France

Daniel Durox, Thierry Schuller, Sébastien Candel

Laboratoire EM2C,
CNRS, CentraleSupélec,
Université Paris-Saclay,
Grande Voie des Vignes,
Chatenay-Malabry cedex 92295, France

Sergio M. Camporeale

DMMM,
Sez. Macchine ed Energetica,
Politecnico di Bari,
Via Re David 200,
Bari 70125, Italy

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 August 7, 2016; final manuscript received September 12, 2016; published online January 10, 2017. Assoc. Editor: Song-Charng Kong.

J. Eng. Gas Turbines Power 139(5), 051505 (Jan 10, 2017) (10 pages) Paper No: GTP-16-1393; doi: 10.1115/1.4035207 History: Received August 07, 2016; Revised September 12, 2016

The present article reports a numerical analysis of instability coupled by a spinning mode in an annular combustor. This corresponds to experiments carried out on the MICCA test facility equipped with 16 matrix burners. Each burner response is represented by means of a global experimental flame describing function (FDF). A harmonic balance nonlinear stability analysis is carried out by combining the FDF with a Helmholtz solver to determine the system dynamics trajectories in a frequency-growth rate plane. The influence of the distribution of the volumetric heat release corresponding to each burner is investigated in a first stage. Even though each of the 16 burners is compact with respect to the transverse mode wavelength, and the 16 flames occupy the same volume, this distribution of heat release is not compact in the azimuthal direction and simulations reveal an influence of this volumetric distribution on frequencies and growth rates. This study emphasizes the importance of providing a suitable description of the flame zone geometrical extension and correspondingly an adequate representation of the level of heat release rate fluctuation per unit volume. It is found that these two items can be deduced from a knowledge of the heat release distribution under steady-state operating conditions. Once the distribution of the heat release fluctuations is unequivocally defined, limit cycle simulations are performed. For the conditions explored, simulations retrieve the spinning nature of the self-sustained mode that was identified in the experiments both in the plenum and in the combustion chamber.

Copyright © 2017 by ASME
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References

Figures

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Fig. 1

(a) Photograph of the MICCA combustor with a zoomed view of a matrix injector and the waveguide outlet. (b) Schematic representation of the experimental setup with details of the matrix injector position (c) and of the mixture feeding line (d).

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Fig. 2

Top view of the MICCA chamber with microphone locations indicated

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Fig. 3

Pressure signals recorded by microphones in the plenum (a) and the combustion chamber (b) for the spinning mode analyzed in this article obtained at an equivalence ratio ϕ = 0.98 and a bulk velocity ub = 0.49 ms−1

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Fig. 4

(a) Three-dimensional model of the MICCA chamber with the temperature field in Kelvin and (b) longitudinal cut showing geometrical details of the matrix injector representation

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Fig. 5

Pressure measurements outside the combustion chamber used to determine the end correction for the first 1A–1L azimuthal mode

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Fig. 6

Interpolated flame describing function (FDF). The experimental data are displayed as white dots: (a) gain and (b) phaseφ.

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Fig. 7

Details of the flame region domain and of the reference point for the velocity fluctuations in one sector of the annular combustor

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Fig. 8

Three different flame domains characterized by the same flame volume Vf  = 16.6 cm−3. Azimuthal and longitudinal extensions: (a) lx = 6.8 cm, lz = 0.4 cm; (b) lx = 4.2 cm, lz = 1.2 cm; and (c) lx = 3.6 cm, lz = 1.6 cm.

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Fig. 9

Dynamical trajectories in the frequency (f) growth rate (α) plane colored by (a) the velocity fluctuation level |u′/u¯| and (b) the gain of the FDF. Circular marks indicate the flame volume shown in Fig. 8(a), triangular marks refer to the case shown in Fig. 8(b), and square marks to the model of Fig. 8(c).

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Fig. 10

Four different flame volumes characterized by the same longitudinal dimension but different extension in the azimuthal direction. Azimuthal dimension (lx): (a) lx = 6.8 cm; (b) lx = 4.2 cm; (c) lx = 3.6 cm; and (d) lx = 0.8 cm. Axial extension lz = 0.8 cm.

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Fig. 11

Trajectories in the frequency (f) growth rate (α) plane colored by the velocity fluctuation level |u′/u¯|. Circle marks indicate the flame volume shown in Fig. 10(a), triangular marks refer to the case shown in Fig. 10(b), square marks to the model of Fig. 10(c) and diamonds indicate the last one shown in Fig.10(d).

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Fig. 12

(a) Theoretical conical flame of diameter a and height h over a cylindrical volume. (b) Image of the flame recorded in the longitudinal combustor equipped with the perforated plate injector in a steady-state configuration.

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Fig. 13

Acoustic response of the MICCA combustor from 300 Hz to 500 Hz measured by microphones located in the (a) plenum and (b) combustion chamber. The frequency bandwidth Δf determined at half maximum provides the damping rate in both volumes.

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Fig. 14

Trajectory of the MICCA combustor colored with the growth rate projected over the contour plot of the gain of the FDF. The zoom frame highlights the limit cycle condition for a vanishing damping rate (triangular mark) and for a finite damping rate (circular mark).

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Fig. 15

Pressure mode magnitude |p̂| with pressure contour lines plotted on a cylindrical surface equidistantly located from the lateral walls

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Fig. 16

(a) Pressure distribution along the azimuthal direction in the plenum (continuous line) and in the combustion chamber (dashed line). (b) Pressure phase evolution along the azimuthal direction in the plenum (continuous line) and in the combustion chamber (dashed line).

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Fig. 17

Comparison between the plenum PM1 signal (continuous line) and chamber MC1 signal (dot-dashed line). When the angular shift due to the microphones position is taken into account, the two signals manifest a phase shift of approx. 0.18 rad.

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