Solution-limited time stepping to enhance reliability in CFD applications

Lian, Chenzhou; Xia, Guoping; Merkle, Charles L.

doi:10.1016/j.jcp.2009.03.040

Cited by 75 publications

(24 citation statements)

References 38 publications

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“…[34][35][36][37][38] The numerical scheme is second order accurate in both time and space and uses an implicit formulation allowing for the use of high-aspect ratio grids near the wall. A dual-time formulation is used to eliminate approximate-factorization and linearization errors.…”

Section: B Computational Approachmentioning

confidence: 99%

Combustion Dynamics Behavior in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor

Huang

Gejji

Anderson

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A concurrent computational and experimental study of self-excited combustion dynamics in a model configuration of a lean direct injection (LDI) gas turbine combustor are described. Incoming air temperature and equivalence ratio were varied. Simulation at low equivalence ratio compared better with measurement and thus this condition was selected for a more detailed study of the underlying combustion dynamics mechanisms. First, hydrodynamic modes are investigated by conducting the simulation with an acousticallyopen combustor so that acoustic effects on the flow field are minimized. The Vortex Breakdown Bubble (VBB) proves to be an important flow structure that can easily interact with the acoustic field to sustain instability. Second, detailed cycle studies of the acoustically closed combustor simulation reveals enhanced mixing and vaporization of the JP-8 fuel spray due to acoustic compression wave. Dynamic Mode Decomposition (DMD) analysis is used to identify the coupling between axial acoustics and the vortex breakdown bubble in the lower frequency region. Presence of another important hydrodynamic mode, the Precessing Vortex Core (PVC) is also identified from the DMD analysis. The possibility of nonlinear coupling between the acoustics and PVC modes is indicated.

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Section: B Computational Approachmentioning

confidence: 99%

Combustion Dynamics Behavior in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor

Huang

Gejji

Anderson

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

show abstract

“…GEMS solves the coupled Navier-Stokes equations along with a single energy equation and coupled species equations. [23][24][25][26][27][28] The numerical scheme is second order accurate in both time and space and uses an implicit formulation which allows for the use of high-aspect ratio grids near the wall. A dual-time formulation is used to eliminate approximate factorization errors.…”

Section: B Computational Approachmentioning

confidence: 99%

Combustion Instability Mechanisms in a Pressure-coupled Gas-gas Coaxial Rocket Injector

Harvazinski

Huang

Sankaran

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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An investigation of the instability mechanism present in a laboratory rocket combustor is performed using computational fluid dynamics (CFD) simulations. Three cases are considered which show different levels of instability experimentally. Computations reveal three main aspects to the instability mechanism, the timing of the pressure pulses, increased mixing due to the baroclinic torque, and the presence of unsteady tribrachial flame. The stable configuration shows that fuel is able to flow into the combustor continuously allowing continuous heat release. The unstable configuration shows that a disruption in the fuel flow into the combustor allows the heat release to move downstream and new fuel to accumulate in the combustor without immediately burning. Once the large amounts of fuel in the combustor burn there is rapid rise in pressure which coincides with the timing of the acoustic wave in the combustor. The two unstable cases show different levels of instability and different reignition mechanisms.

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“…[15][16][17][18] The Navier-Stokes equations along with a single energy equation and five species equations are solved numerically. A hybrid detached eddy simulation (DES) turbulence model is used to compute large eddies directly and models near wall turbulence using the two equation k-ω model.…”

Section: Test Problemmentioning

confidence: 99%

Analysis of Self-Excited Combustion Instability using a Combination of Two- and Three-Dimensional Simulations

Harvazinski

Xia

Anderson

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Three-dimensional simulations of combustion instability can provide extremely valuable insight into the problem physics, but they represent an enormous investment in time and preclude parametric studies that are practical with two-dimensional simulations. Three numerical simulations of gaseous methane and decomposed hydrogen peroxide in a laboratory rocket combustor were performed in order to assess the effect of grid resolution and dimensionality on the ability to predict and model combustion instability. Computations show that two-dimensional axisymmetric simulations using both coarse and fine grids are able to capture the first longitudinal mode within an order of magnitude of the experiment. The three-dimensional calculation based on the coarse grid resolution shows excellent agreement with the experimental level of instability. The large number of experiments performed lead to a multitude of required simulations. The fast turnaround time and low computational cost of two-dimensional simulations allow for parametric studies to be performed and trends to be established over varying operating conditions. Twodimensional simulations also play a valuable role in minimizing the number of expensive three-dimensional simulations that need to be undertaken.

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Solution-limited time stepping to enhance reliability in CFD applications

Cited by 75 publications

References 38 publications

Combustion Dynamics Behavior in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor

Combustion Dynamics Behavior in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor

Combustion Instability Mechanisms in a Pressure-coupled Gas-gas Coaxial Rocket Injector

Analysis of Self-Excited Combustion Instability using a Combination of Two- and Three-Dimensional Simulations

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