Modeling of Turbulent Mixing Layer Dynamics in Ultra-High Pressure Flows

Xia, Guoping; Sankaran, Venkateswaran; Ding, Li; Merkle, Charles L.

doi:10.2514/6.2006-3729

Cited by 43 publications

(12 citation statements)

References 21 publications

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“…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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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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“…[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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“…Simulations have been conducted using an in-house code named General Equation and Mesh Solver (GEMS) [11][12][13][14] . The code uses a second order finite volume approach to numerically solve Navier-Stokes equations along with energy and species equations in a coupled way.…”

Section: Numerical Simulationmentioning

confidence: 99%

Development of Validation Approaches for Numerical Simulation of Combustion Instability using Flame Imaging

Hardi¹,

Hallum²,

Huang³

et al. 2014

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

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Combustion dynamics are controlled by the coupling between heat addition and gas dynamic modes, hence their direct measurement and comparisons with prediction are key to improving computational tools as well as our fundamental understanding of the problem. Whereas gas dynamic modes are relatively easy to measure and compare, measurement and characterization of heat addition are much more difficult due to its complexity and the lack of any direct means of measurement. This paper demonstrates several methods for characterizing and comparing heat release from experiment and simulation. A model rocket combustor is used for the study. Comparisons are made for two configurations, one stable and one unstable. High-speed, line-of-sight imaging of OH* emission from the experiment was first phase averaged, and then treated with an Abel inversion routine to produce a dynamic, two-dimensional field of heat addition. The field before inversion could be compared to line-integrated calculations of heat release rate from three-dimensional large eddy simulations, and after inversion to azimuthally averaged cross-sections from simulations. Modal decomposition analysis of the two-dimensional fields were performed. The applicability and limitations of each comparison approach are assessed. Nomenclature J 0 = zero-order Bessel function of the first kind L op = length of oxidizer post, mm|inch p′ = dynamic pressure, MPa P cc = chamber pressure, MPa Φ = equivalence ratio ′ = unsteady term of a variable ω = frequency, Hz

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Modeling of Turbulent Mixing Layer Dynamics in Ultra-High Pressure Flows

Cited by 43 publications

References 21 publications

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

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

Development of Validation Approaches for Numerical Simulation of Combustion Instability using Flame Imaging

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