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

Mixed Acoustic-Entropy Combustion Instabilities in a Model Aeronautical Combustor: Large Eddy Simulation and Reduced Order Modeling

[+] Author and Article Information
Florent Lacombe

Safran Aircraft Engines,
Rond-Point René Ravaud,
Moissy Cramayel 77550, France
e-mail: florent.lacombe@safrangroup.com

Yoann Méry

Safran Aircraft Engines,
Rond-Point René Ravaud,
Moissy Cramayel 77550, France
e-mail: yoann.mery@safrangroup.com

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 13, 2017; final manuscript received July 27, 2017; published online October 25, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(3), 031506 (Oct 25, 2017) (10 pages) Paper No: GTP-17-1354; doi: 10.1115/1.4037960 History: Received July 13, 2017; Revised July 27, 2017

This article focuses on combustion instabilities (CI) driven by entropy fluctuations which is of great importance in practical devices. A simplified geometry is introduced. It keeps the essential features of an aeronautical combustion chamber (swirler, dilution holes, and outlet nozzle), while it is simplified sufficiently to ease the analysis (rectangular vane, one row of holes of the same diameter, no diffuser at the inlet of the chamber, and circular nozzle at the outlet). A large eddy simulation (LES) is carried out on this geometry and the limit cycle of a strong CI involving the convection of an entropy spot is obtained. The behavior of the instability is analyzed using phenomenological description and classical signal analysis. One shows that the system can be better described by considering two reacting zones: a rich mainly premixed flame is located downstream of the swirler and an overall lean diffusion flame is stabilized next to the dilution holes. In a second step, dynamic mode decomposition (DMD) is used to visualize, analyze, and model the complex phasing between different processes affecting the reacting zones. Using these data, a zero-dimensional (0D) modeling of the premixed flame and of the diffusion flame is proposed. These models provide an extended understanding of the combustion process in an aeronautical combustor and could be used or adapted to address mixed acoustic-entropy CI in an acoustic code.

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Grahic Jump Location
Fig. 1

Geometrical configuration of interest. The main parts of the combustor have been simplified. The swirler is hidden for confidentiality reasons.

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Fig. 2

Scheme of the geometrical parameters which corresponds to a cut of the geometry excluding the nozzle. Lengths (L) and heights (H) of the main parts are displayed.

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Fig. 3

Field of temperature (K) averaged over 10 ms and a heat release rate isocontour at 9×108 W m−3

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Fig. 4

Takeno index (grayscale: white = premixed—black = nonpremixed) and isocontour of heat release rate at 2 MW m−3 (gray line) of the upper part of the flame tube for an instantaneous solution. The exit of the swirler is on the left of the picture.

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Fig. 5

Instantaneous fields of heat release rate (top), pressure (middle), and temperature (bottom). Left: instant where the pressure is minimal. Right: opposite instant where the pressure is maximal.

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Fig. 6

Convection of a cold pocket on four consecutive snapshots

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Fig. 7

Pressure and heat release rate in the simulation. The pressure is recorded in the center of the flame tube, and the HRR is integrated on the whole volume and averaged.

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Fig. 8

Power spectral density of pressure, heat release rate, and temperature signals normalized at 100 dB for comparison

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Fig. 9

Plane on which the DMD processing is carried out. The plane is colored by one DMD snapshot of temperature. An isocontour of HRR at 9×108 W m−3 (black line) shows the two reacting zones.

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Fig. 10

Spectrum obtained from the DMD analysis for pressure (top and bottom, for reference), HRR (top), and temperature (bottom)

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Fig. 11

DMD fields of temperature for six phases for fj=385 Hz. From left to right and top to bottom: ϕ=0,  ϕ=π/6,  ϕ=2π/6,  ϕ=3π/6,  ϕ=4π/6,  ϕ=5π/6. White: +300 K, black: −300 K.

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Fig. 12

Scheme of the flame tube with integration regions

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Fig. 13

Mean axial velocity field in the vicinity of the swirler with an isocontour of axial velocity equal to zero. The averaging line is shown downstream of the swirler.

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Fig. 14

Normalized fluctuations of the relevant parameters integrated spatially for the premixed flame as a function of phase

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Fig. 15

Normalized fluctuations of HRR as a function of phase compared with the models based on Eqs. (10) (S) and (11) (Su)

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Fig. 16

Schematic representation of the top diffusion flame located near the dilution holes

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Fig. 17

Normalized fluctuations of the relevant parameters integrated spatially for the diffusion flame as a function of phase

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Fig. 18

Normalized fluctuations of HRR as a function of phase compared with the models based on Eqs. (15) (S1) and (16) (S2)



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