High order numerical simulation of the thermal load on a lobed strut injector for scramjet applications

Simsont, Yann Hendrik; Gerlinger, Peter

doi:10.1002/fld.4224

Cited by 26 publications

(9 citation statements)

References 37 publications

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“…Third, on the regular grid, the fifth-order discretization is in much better agreement with the corresponding solutions on the fine grid, compared with the second-order discretization. This clearly shows the advantages of using a high-order discretization, which has also been demonstrated in [18,38]. Figure 3 compares the wall heat fluxes of the four simulations (lines) with experimentally measured values (symbols).…”

Section: Grid Convergencementioning

confidence: 91%

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Influence of spatial discretization and unsteadiness on the simulation of rocket combustors

Lempke

Keller

Gerlinger

2015

Numerical Methods in Fluids

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Summary This paper investigates some important numerical aspects for the simulation of model rocket combustors. Precisely, (1) a new high‐order discretization technique (multi‐dimensional limiting process (MLP), low diffusion, and MLPld) is presented and compared with conventional second‐order schemes with different flux limiters. (2) Time accurate unsteady Reynolds‐averaged Navier–Stokes (RANS) simulations are performed to assess possible improvements in comparison with steady‐state RANS simulations. (3) Fully 3D simulations of an axisymmetric rocket combustor are compared with 2D axisymmetric ones. All studies are based on the Penn State preburner combustor experiment, which uses gaseous oxygen and hydrogen. This comprehensive study offers unique insight into how the mentioned numerical influence factors change the flow field, flame, and wall heat fluxes in the model rocket combustor. Because wall heat fluxes are known from the experiment only, numerical results are compared with LES of other authors, too. It will be shown that the high‐order spatial discretization significantly improves the agreement with measured wall heat fluxes at low additional computational cost. In general the transition from simple to more complex numerical approaches steadily improves the qualitative agreement between simulation and experiment. Copyright © 2015 John Wiley & Sons, Ltd.

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Section: Grid Convergencementioning

confidence: 91%

“…As observed in previous studies [17,35,38], the quality of numerical results can be significantly improved by changing to higher-order spatial discretizations. MLP ld offers the possibility of a stable high-order scheme with good shock capturing capabilities.…”

Section: High-order Discretizationmentioning

confidence: 99%

Influence of spatial discretization and unsteadiness on the simulation of rocket combustors

Lempke

Keller

Gerlinger

2015

Numerical Methods in Fluids

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“…It has been shown [35,44,45] that use of the MLP increases the numerical stability of the algorithm, improves convergence, and achieves better results, for example, in cases where shock waves are oblique to the computational grid. Moreover, the fifth-order MLP scheme is able to achieve results that are reached with a second-order discretization on significantly finer grids only [47]. A detailed discussion of the MLP ld (low diffusion) version used in this paper may be found in [35].…”

Section: B Modeling and Numerical Schemementioning

confidence: 96%

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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“…Figure 32 compares the experimental results and numerical simulations of the surface temperature of the injector. Simsont [119] studied another numerical calculation model for thermal load of cascade oil injectors, and the spatial fourth-order multidimensional limiting process (MLP) [120] was used based on a compressible finite volume scheme [121] to simulate the flow field of combined propulsion. Coupled simulation of the vane-type column injector can calculate the flow field distribution, heat flux inside and outside the column, and the temperature distributed in the solid materials (see Figure 33), thus greatly contributing to the calculation of thermal conduction of components in thermal management.…”

Section: Thermal Control Systemsmentioning

confidence: 99%

“…Simulated distribution diagrams of fluid flow rate, pressure, and temperature of symmetrical cross section and isometric cross section[119].…”

mentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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High order numerical simulation of the thermal load on a lobed strut injector for scramjet applications

Cited by 26 publications

References 37 publications

Influence of spatial discretization and unsteadiness on the simulation of rocket combustors

Influence of spatial discretization and unsteadiness on the simulation of rocket combustors

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

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

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