Validation of a Multicomponent-Fuel Model for Spray Computations

Clercq, Patrick Le; Doué, Nicolas; Rachner, Michael; Aigner, Manfred

doi:10.2514/6.2009-1188

Cited by 21 publications

(19 citation statements)

References 16 publications

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“…S is a source vector that includes local production and destruction terms stemming from the k-ω turbulence model [33], the variance transport equations [34], and chemistry [35]. S spray results from the interaction of the spray with the gas phase [36]. Time is denoted by t, and the coordinate in the j direction is denoted by x j .…”

Section: A Governing Equationsmentioning

confidence: 99%

“…In the opposite direction, the Lagrangian spray code provides the source vector S spray , which appears in Eq. (1) [36]. It is given by …”

Section: A Governing Equationsmentioning

confidence: 99%

“…The DLR, (German Aerospace Center) in-house code SPRAYSIM [36] serves to model the liquid phase. It uses a predictor-corrector scheme (Adams-Bashforth predictor/Adams-Moulton corrector) for temporal integration of the set of ordinary differential equations (3).…”

Section: B Modeling and Numerical Schemementioning

confidence: 99%

“…Likewise, SPRAYSIM has been used with different gas-phase codes for spray modeling [36,57,58], in most cases for kerosene and aeroengine combustion. Because no detailed spray data are available for the investigated rocket combustor, an academic test case is chosen to demonstrate the accuracy of the TASCOM3D/SPRAYSIM coupling.…”

Section: Code Validationmentioning

confidence: 99%

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Unsteady High-Order Simulation of a Liquid Oxygen/Gaseous Hydrogen Rocket Combustor

Lempke¹,

Gerlinger²,

Seidl³

et al. 2015

Journal of Propulsion and Power

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Coupled Euler-Lagrange simulations are performed for a subcritically operated model rocket combustor at 10 bar pressure (MASCOTTE A-10 test case). A Lagrangian spray model is used to simulate the liquid phase. This liquid oxygen/gaseous hydrogen single element combustor experiment has been the focus of many numerical studies. In contrast to previous investigations, time-accurate unsteady Reynolds-averaged Navier-Stokes simulations are performed. A good spatial resolution is achieved by using a fifth-order multidimensional limiting process scheme to discretize the inviscid fluxes. Instead of assuming axisymmetry, the three-dimensional geometry of the rectangular combustor is taken into account. However, only a quarter of the combustor is simulated, to limit the computational cost. Presented results indicate that three-dimensional effects are important, questioning the assumption of axisymmetry. A second important finding is that time-averaged unsteady Reynolds-averaged Navier-Stokes results agree much better with experimental data than those of a comparable steady-state simulation. Close to the injector, results show a strong unsteadiness of the turbulent flame, which has been observed in the experiment, too. Finally, pressure fluctuations are monitored at several positions in the combustor and analyzed by fast Fourier transform. The peak amplitudes in the pressure spectra could successfully be assigned to the first longitudinal acoustic mode and its higher harmonics.

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Section: A Governing Equationsmentioning

confidence: 99%

“…In the opposite direction, the Lagrangian spray code provides the source vector S spray , which appears in Eq. (1) [36]. It is given by …”

Section: A Governing Equationsmentioning

confidence: 99%

Section: B Modeling and Numerical Schemementioning

confidence: 99%

Section: Code Validationmentioning

confidence: 99%

See 2 more Smart Citations

Unsteady High-Order Simulation of a Liquid Oxygen/Gaseous Hydrogen Rocket Combustor

Lempke¹,

Gerlinger²,

Seidl³

et al. 2015

Journal of Propulsion and Power

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“…Spray transport, dispersion, and evaporation processes are computed using the DLR in-house code SPRAYSIM (Le Clercq et al 2009). It is a simulation tool written in FORTRAN 95 developed at the German Aerospace Center, Institute of Combustion Technology, for spray systems found in premixing/pre-vaporizing modules and gas turbine combustors.…”

Section: Computationmentioning

confidence: 99%

Accurate analysis of multicomponent fuel spray evaporation in turbulent flow

et al. 2011

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The aim of this paper is to perform an accurate analysis of the evaporation of single component and binary mixture fuels sprays in a hot weakly turbulent pipe flow by means of experimental measurement and numerical simulation. This gives a deeper insight into the relationship between fuel composition and spray evaporation. The turbulence intensity in the test section is equal to 10%, and the integral length scale is three orders of magnitude larger than the droplet size while the turbulence microscale (Kolmogorov scales) is of same order as the droplet diameter. The spray produced by means of a calibrated droplet generator was injected in a gas flow electrically preheated. N-nonane, isopropanol, and their mixtures were used in the tests. The generalized scattering imaging technique was applied to simultaneously determine size, velocity, and spatial location of the droplets carried by the turbulent flow in the quartz tube. The spray evaporation was computed using a Lagrangian particle solver coupled to a gas-phase solver. Computations of spray mean diameter and droplet size distributions at different locations along the pipe compare very favorably with the measurement results. This combined research tool enabled further investigation concerning the influencing parameters upon the evaporation process such as the turbulence, droplet internal mixing, and liquid-phase thermophysical properties.

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Parallelization and Performance Analysis of an Implicit Compressible Combustion Code for Aerospace Applications

Keller¹,

Lempke²,

Simsont³

et al. 2014

High Performance Computing in Science and Engineering ‘14

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The compressible, implicit combustion code TASCOM3D is used with and without the spray module SPRAYSIM for different aerospace applications. A number of such cases and analysis of the performance of the code on massively parallel systems will be given. These include supersonic combustion simulations of a complete scramjet model, a model rocket combustor fueled with gaseous oxygen and hydrogen as well as two multiphase simulations. The evaporation of kerosene in a preheated, pressurized channel and the spray combustion in a LOX/GH 2 rocket combustor require an additional numerical tool to account for the liquid phase. Droplet propagation and evaporation is computed by the research code SPRAYSIM. Furthermore investigations with respect to the performance of the employed numerical codes are addressed. With respect to TASCOM3D the influence of block sizing on the performance is investigated intensively both in terms of weak and strong scaling. The strong scaling performance of SPRAYSIM is investigated for both multiphase simulations. It will be shown that both codes show a nearly ideal behavior.

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Validation of a Multicomponent-Fuel Model for Spray Computations

Cited by 21 publications

References 16 publications

Unsteady High-Order Simulation of a Liquid Oxygen/Gaseous Hydrogen Rocket Combustor

Unsteady High-Order Simulation of a Liquid Oxygen/Gaseous Hydrogen Rocket Combustor

Accurate analysis of multicomponent fuel spray evaporation in turbulent flow

Parallelization and Performance Analysis of an Implicit Compressible Combustion Code for Aerospace Applications

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