Numerical Simulations of the Flame of a Single Coaxial Injector

Жуков, В. В.; Feil, Markus

doi:10.1155/2017/5147606

Cited by 10 publications

(5 citation statements)

References 15 publications

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“…The reduced mesh size decreased the computation time to several hours compared to 3-D simulations. In the previous study [12], it was found that, for the flame of a coaxial injector, the simulation results depended on the velocity profile in the (outer) annular passage of coaxial injector and that the uniform velocity profile resulted in a wrong spreading angle and poor convergence at the grid nodes near the oxygen post tip. Therefore, the numerical domain included a small part of the outer annular passage.…”

Section: A Computational Domainmentioning

confidence: 99%

“…The numerical meshes were generated using the computer program ICEM from the package ANSYS CFD. Following previous experience in CFD simulations [10,12], the generated meshes were refined near the injector post and around the shear layer between the jets of the fuel and oxidizer; here, the spacing reaches 15 μm. In a base mesh, the spacing between the nodes varies from 0.6 μm to 0.5 mm, and most of the mesh elements are stretched in the axial direction.…”

Section: A Computational Domainmentioning

confidence: 99%

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Computational Fluid Dynamics Simulations of a GO2/GH2 Single Element Combustor

Жуков

2015

Journal of Propulsion and Power

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A single-element combustor known as the "Penn State preburner combustor" is modeled numerically using the commercial computational fluid dynamics code ANSYS CFX. The aim of computational fluid dynamics modeling is to simulate the wall heat flux, which has been measured experimentally. The simulated combustion chamber has a single shear coaxial injector and operates with gaseous oxygen and hydrogen in a staged combustion configuration. The turbulent flow in the combustion chamber is modeled using the Favre-averaged Navier-Stokes equations and the shear-stress transport turbulence model. The turbulent non-premixed flame is modeled using an extended eddy dissipation model. The developed turbulent combustion model shows good agreement with the experimental data, good convergence, and a short computational time. A mesh convergence study is performed, and a mesh-independent solution is obtained on a mesh with 1.5 million nodes. The complexity of the model is gradually increased until the model is capable of predicting the wall heat flux. The analysis of numerical results shows a significant effect of boundary conditions on wall heat flux predictions. The comparison of the Reynolds-averaged Navier-Stokes simulations with the experimental data demonstrates the capability of Reynolds-averaged Navier-Stokes simulations to predict wall heat fluxes in a rocket combustion chamber.

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Section: A Computational Domainmentioning

confidence: 99%

Section: A Computational Domainmentioning

confidence: 99%

Computational Fluid Dynamics Simulations of a GO2/GH2 Single Element Combustor

Жуков

2015

Journal of Propulsion and Power

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“…The numerical analysis has been a good addition to the experimental research, and the computational fluid dynamics (CFD) is also an efficient approach [17][18][19]. Yu et al [20] applied the 13-component and 20-step reaction mechanism to investigate an oxygen/methane engine, and the results are consistent with experimental data.…”

Section: Introductionmentioning

confidence: 82%

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Jin

et al. 2021

International Journal of Aerospace Engineering

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The LOX/methane engine has an admirable performance under a supercritical state. However, the properties of methane change drastically with varying injection temperature. Because the injector can greatly affect the atomization and combustion, this study performed a three-dimensional numerical simulation of atomization, combustion, and heat transfer in a subscale LOX/methane engine to evaluate the effect of the main fluid parameters with different methane injection temperatures and different injectors on atomization performance and combustion performance. The results show that the larger propellant momentum ratio and Weber number can improve the heat flux and combustion stability in shear coaxial injector, while the influence in swirl coaxial injector is relatively small. Moreover, in shear coaxial injector and in swirl coaxial injector, the larger propellant momentum ratio and Weber number can reduce the droplet size, enhance atomization performance, and improve the combustion efficiency. The numerical model provides an economical method to evaluate the main fluid parameters and proposes new design principles of injectors in LOX/methane engine.

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“…The relevance of this phenomenon for initial mixing and combustion has been noted by several previous researchers. [83][84][85][86][87] In addition, high-frequency combustion instabilities have been associated with KHI after injection. 77 Moreover, the blanching issue mentioned in the introduction is likely related to this phenomenon, since the advection of oxygen to the combustion chamber walls must involve some sort of negative turbulent diffusion.…”

Section: Numerical Modelingmentioning

confidence: 99%

Analysis of turbulent mixing in a methane–oxygen recessed injector for space propulsion

2023

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Turbulent mixing in a methane–oxygen recessed injector is studied using direct numerical simulations. The operating point is chosen to be fuel-rich and at high pressure to recreate a representative environment for space propulsion applications. The results are used to investigate the transport of the turbulent mixture fraction statistics and the validity of conventional transport models. It is observed that molecular diffusion is only relevant near the boundary layer of the injection recess cavity and at the recirculation zone. Moreover, turbulent mixing in the axial direction is negligible as radial turbulent diffusion dominates. Radial turbulent diffusion near injection is driven by Kelvin–Helmholtz Instabilities (KHI) manifesting at large scales in the order of the injector geometry. The dominance of this process over microscale mixing originates negative turbulent diffusion, which produces a mixture resegregation and the appearance of lean pockets far from the oxidizer injection plane. Gradient models display poor capabilities for the prediction of this sort of phenomena. Closure models for the turbulent mixing transport terms are proposed and evaluated. An anisotropic gradient model is devised, providing performance improvements within the recess cavity and the recirculation region. In addition, a novel filtered Reynolds-averaged Navier Stokes approach based on the mixing state is proposed. This new methodology shows excellent prediction capabilities in the regions dominated by KHI, accurately predicting negative turbulent diffusivity. The challenges associated with this model are commented on, and strategies to enable its application are proposed.

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Numerical Simulations of the Flame of a Single Coaxial Injector

Cited by 10 publications

References 15 publications

Computational Fluid Dynamics Simulations of a GO2/GH2 Single Element Combustor

Computational Fluid Dynamics Simulations of a GO2/GH2 Single Element Combustor

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Analysis of turbulent mixing in a methane–oxygen recessed injector for space propulsion

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