A numerical and experimental study of fuel evaporation and mixing for lean premixed combustion at high pressure

Rachner, Michael; Brandt, M.; Eickhoff, H.; Hassa, Christoph; Bräumer, A.; Krämer, Heinz; Ridder, M.; Sick, Volker

doi:10.1016/s0082-0784(96)80111-1

Cited by 13 publications

(13 citation statements)

References 6 publications

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“…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%

“…The lean premixed prevaporized (LPP) duct test case from DLR [57] provides accurate boundary conditions, as well as comprehensive spray data. Liquid kerosene (Jet-A) is injected through a centrally arranged, flat prefilming airblast atomizer into a rectangular duct with a 25 × 40 mm cross section.…”

Section: Code Validationmentioning

confidence: 99%

“…The air passing the duct has a velocity of 120 m∕s and a temperature of 750 K. The pressure in the mixing section is constant at 9 bar. The duct offers optical access, and droplet sizes, velocities, and volume fluxes have been measured [57].…”

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: Code Validationmentioning

confidence: 99%

Section: Code Validationmentioning

confidence: 99%

See 1 more Smart Citation

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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show abstract

“…It is desirable to achieve a simultaneous acquisition of two or more physical parameters at any instance in time and space, to allow a more comprehensive description of the instantaneous spray condition. For example, simultaneous planar laser-induced fluorescence (LIF) and Mie-scattering measurements were used to characterize the spray formed by a blast film atomizer and provided information about the evaporation characteristics [1]. While these measurements yielded a qualitative description of the evaporation process, no information was obtained about the droplet diameters.…”

mentioning

confidence: 99%

“…Thus, no information on instantaneous spray structures can be obtained. Rachner et al [1] used reflective optics to spectrally and spatially separate Mie-scattering and LIF signals and used two intensified CCD (ICCD) cameras for detection. While this can provide instantaneous images, no effort was made to calculate the ratio of LIF to Mie signals and thereby gaining information about the droplet diameters.…”

mentioning

confidence: 99%

Evolution and impingement of an automotive fuel spray investigated with simultaneous Mie/LIF techniques

Stojkovic

Sick

2001

Appl Phys B

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The spatial and temporal evolution of an automotive hollow-cone-type spray was investigated with laserbased imaging diagnostics. Optical conditions of an IC engine were emulated with a test cell that was built from an engine cylinder head to hold a high-pressure gasoline-fuel injector. The use of iso-octane fuel that was doped with 3-pentanone allowed measurements of laser-induced fluorescence (LIF) after excitation with a KrF excimer-laser beam. A versatile optical filter system was designed and built that permits simultaneous measurements of Mie-scattering and laser-inducedfluorescence images using a single laser-light sheet and a single intensified CCD camera. The influence of background signals, caused by reflection of signal light from surfaces, laser-sheet intensity attenuation and signal decrease by scattering, was characterized. Mass distributions showed a distinct pre-spray phase, more so than the Sauter mean diameter (SMD) that was determined from the ratio of LIF to Mie signals using single pulse as well as averaged image pairs. Significant changes in SMD distributions were found after the spray had impinged on a flat surface. The impingement also led to the buildup of a liquid film whose thickness was quantitatively determined from LIF images.

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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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A numerical and experimental study of fuel evaporation and mixing for lean premixed combustion at high pressure

Cited by 13 publications

References 6 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

Evolution and impingement of an automotive fuel spray investigated with simultaneous Mie/LIF techniques

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

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