Study on flame dynamics with secondary fuel injection control by large eddy simulation

Shinjo, Junji; Matsuyama, Shingo; Mizobuchi, Yasuhiro; Ogawa, Satoru

doi:10.1016/j.combustflame.2007.01.011

Cited by 16 publications

(6 citation statements)

References 24 publications

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“…The flame bifurcation phenomenon and stability boundary were investigated as a function of burner operating conditions. Shinjo et al [545] and Sengissen et al [543] studied the secondary fuel injection and fuel modulation on unsteady combustion behavior in swirl-stabilized combustors, respectively. Pollutant emissions and temperature profile in swirl combustors were also predicted by Cannon et al [519], Eggenspieler and Menon [525], Schmitt et al [542], and Boudier et al [544].…”

Section: Les Of Premixed Combustion Dynamics In Gas Turbine Enginesmentioning

confidence: 99%

Dynamics and stability of lean-premixed swirl-stabilized combustion

Huang

Yang

2009

Progress in Energy and Combustion Science

1,123

459

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Section: Les Of Premixed Combustion Dynamics In Gas Turbine Enginesmentioning

confidence: 99%

Dynamics and stability of lean-premixed swirl-stabilized combustion

Huang

Yang

2009

Progress in Energy and Combustion Science

1,123

459

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“…In the present study, all sub-grid terms ( (1)(2)(3)(4) are neglected and set to be zero. As realized in implicit LES (ILES) and Monotone Integrated LES (MILES), we expect the numerical dissipation to act like sub-grid terms and emulate the effects of the dynamics beyond the grid-scale cut-off.…”

Section: Methodsmentioning

confidence: 99%

“…To investigate the combustion instabilities encountered in premixed gas turbine combustors, Large Eddy Simulation (LES) is starting to be used. [1][2][3] In these LES studies, the combustion instabilities are successfully captured and the obtained data is analyzed to understand the coupling mechanism among acoustic wave, vortex shedding and flame oscillations. For the applications of liquid rocket engine combustions, most existing LES studies focus on the flow and combustion dynamics of a supercritical LO X /GH 2 coaxial jet flame.…”

Section: Introductionmentioning

confidence: 99%

LES of High-Frequency Combustion Instability in a Rocket Combustor

Matsuyama

Shinjo

Mizobuchi

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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In the present work, results of attempts to capture the high-frequency combustion instability in a rocket combustor equipped with hydrogen (H 2 ) / oxygen (O 2 ) injector are shown. To enhance the coupling between heat release rate fluctuations and pressure oscillations, the injector element is installed at the off-center of the combustion chamber in the simulation. Two-dimensional simulations are conducted for a single-element combustor. The flow forcing by modulating the mass flow rate of O 2 injection is attempted to excite the first transverse (1T) mode of chamber. The simulation results indicate that the amplitude of 1T mode is increased by the flow forcing. To clarify a driving mechanism for the growth of pressure oscillations, the simulation results are analyzed using the Rayleigh index. Simulations are then extended to three-dimensional LES for a combustor equipped with five shear-coaxial injector elements. The obtained results of pressure field and the Rayleigh index are compared with those of a single element combustor. The effects of multiple flames on the pressure field are examined. Nomenclature c = Speed of sound D = Width or diameter E = Total energy per unit mass f = Frequency m  = Mass flow rate p = Pressure q = Heat flux q  = Heat release rate T = Temperature t = Time u = Velocity V = Diffusion velocity or volume x = Cartesian coordinate Y = Mass fraction of species Subscripts i, j = Cartesian direction k = Species k property 0 f = Time average Superscripts f = Filtered quantity f = Resolved quantity f  = Fluctuation sgs = Sub-grid scales 1 2 Symbols  = Specific heat ratio  = Density  = Stress tensor   = Production rate

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“…Hong et al (2000) discuss a feedback controller to suppress CI in a dump combustor using distributed actuators including modeling uncertainty. Shinjo et al (2007) recently employed LES of secondary fuel injection control in a lean premixed combustor that demonstrated large-amplitude pressure oscillation without control. Extension of this technique to a two-layer control system using multiple time-scale model is reported in Hong et al (2002) where secondary fuel injection is used for control.…”

Section: Numerical Studies Of Control Of Combustion Instabilitymentioning

confidence: 99%