Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Hoste, J.J.O.E.; Casseau, Vincent; Fossati, Marco; Taylor, Ian; Gollan, Rowan

doi:10.2514/6.2017-2411

Cited by 10 publications

(7 citation statements)

References 46 publications

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“…hy2Foam is a fusion of additional physical models to incorporate thermochemical nonequilibrium with the existing solver called rhoCentralFoam, developed for compressible flows and based on the OpenFOAM framework [16]. The thermochemical nonequilibrium modelling of the solver was validated for several cases ranging from zero-dimensional chemical kinetics to multidimensional hypersonic flows [9,[17][18][19], and the Energies 2020, 13, 606 4 of 17 underlying numerics of the solver was also validated for the hypersonic cases relevant to the present study [20][21][22].…”

Section: Methodsmentioning

confidence: 99%

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

Han

Lee

2020

Energies

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This numerical study was conducted to investigate the flow properties in a model scramjet configuration of the experiment in the T4 shock tunnel. In most numerical simulations of flows in shock tunnels, the inflow conditions in the test section are determined by assuming the thermal equilibrium of the gas. To define the inflow conditions in the test section, the numerical simulation of the nozzle flow with the given nozzle reservoir conditions from the experiment is conducted by a thermochemical nonequilibrium computational fluid dynamics (CFD) solver. Both two-dimensional (2D) and three-dimensional (3D) numerical simulations of the flow in a model scramjet were conducted without fuel injection. Simulations were performed for two types of inflow conditions: one for thermochemical nonequilibrium states obtained from the present nozzle simulation and the other for the data available using the thermal equilibrium and chemical nonequilibrium assumptions. The four results demonstrate the significance of the modelling approach for choosing between 2D or 3D, and thermal equilibrium or nonequilibrium.

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Section: Methodsmentioning

confidence: 99%

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

Han

Lee

2020

Energies

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“…In this work, the RANS equations are solved with the Eilmer (19) open-source CFD package, developed at the University of Queensland. The finite volume solver with explicit time stepping addresses turbulence closure by means of Wilcox's 2006 k − ω model (20) and has been previously validated with Eilmer for scramjet type flows (21)(22)(23) , demonstrating similar predictive capability to the more widely adopted k − ω SST model. Shock capturing is ensured by treating the inviscid fluxes with an adaptive method switching between Macrossan's Equilibrium Flux Method (EFM) (24) and Liou and Wada's Advection Upstream Splitting Method combining Difference and Vector splitting (AUSMDV) (25) .…”

Section: Numerical Modelling Of Scramjetsmentioning

confidence: 99%

Characterisation of the eddy dissipation model for the analysis of hydrogen-fuelled scramjets

et al. 2019

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The eddy dissipation model (EDM) is analysed with respect to the ability to address the turbulence–combustion interaction process inside hydrogen-fuelled scramjet engines designed to operate at high Mach numbers (≈7–12). The aim is to identify the most appropriate strategy for the use of the model and the calibration of the modelling constants for future design purposes. To this end, three hydrogen-fuelled experimental scramjet configurations with different fuel injection approaches are studied numerically. The first case consists of parallel fuel injection and it is shown that relying on estimates of ignition delay from a 1D kinetics program can greatly improve the effectiveness of the EDM. This was achieved through a proposed zonal approach. The second case considers fuel injection behind a strut. Here the EDM predicts two reacting layers along the domain which is in agreement with experimental temperature profiles close to the point of injection but not the case any more at the downstream end of the test section. The first two scramjet test cases demonstrated that the kinetic limit, which can be applied to the EDM, does not improve the predictions in comparison to experimental data. The last case considered a transverse injection of hydrogen and the EDM approach provided overall good agreement with experimental pressure traces except in the vicinity of the injection location. The EDM appears to be a suitable tool for scramjet combustor analysis incorporating different fuel injection mechanisms with hydrogen. More specifically, the considered test cases demonstrate that the model provides reasonable predictions of pressure, velocity, temperature and composition.

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“…The current version is not then able to solve real gas flow in which real thermodynamic process and chemical reactions take place. The bottom-line idea for the implementation is to merge the different peculiarities of available solvers as rhoCentralFoam, densityBasedTurbo, hyFoam [7] etc. in order to build a robust and reliable CFD tool to analyse high-speed air-breathing engines.…”

Section: Numerical Implementationmentioning

confidence: 99%

“…The overall implementation was finally verified on a test case available in literature, typical for propulsion applications. The 2D scramjet geometry was investigated both numerically and experimentally by Lorrain et al [7]. The inlet consists of two ramps of different slopes, to promote the compression, leading to a constant area combustor which ends with a nozzle of constant expansion ratio.…”

Section: Fuel-off 2d Scramjet Enginementioning

confidence: 99%

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Development of a robust solver to model the flow inside the engines for high-speed propulsion

Nista

Saracoglu

2019

MATEC Web Conf.

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The demand for discovering new commercial routes as well as the possibility to shortening civilian long-haul flights boosted the interest of civil hypersonic vehicle designs. Among all the multiple projects started by the various nations, the European community funded project STRATOFLY aims at refining the baseline LAPCAT II-MR2.4 design for further improvements. The new aircraft would enable a flight shorter that 3 hours from Brussels to Sydney, carrying 300-passengers above the already crowed atmosphere. The wide Mach range operability, up to Mach 8, demands the use of multiple engines, leading to a highly integrated propulsion system. The current study is focused on the development of new CFD platform to estimate the performance of the combined propulsion system during the supersonic to hypersonic transition. In order to control the complex flow physics, highfidelity CFD simulations remain the fundamental tools for the preliminary investigations. On the current framework, an advanced robust compressible solver has been develop d in order to handle the different flow regimes. The new tool solves Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations by employing cell-centered Finite Volume Method constructed on openFoam toolbox. Two innovative high-order discretization schemes, with different abilities, based on approximated Riemann solvers were developed for capturing the flow physics within high-speed propulsion systems. Advanced time discretization has been taken into account to increase the temporal accuracy. At the end, the whole implementation has been validated in multiple test cases, ranging from incompressible to hypersonic regimes, confirming its excellent stability, robustness and accuracy.

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Numerical Modeling and Simulation of Supersonic Flows in Propulsion Systems by Open-Source Solvers

Cited by 10 publications

References 46 publications

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

Characterisation of the eddy dissipation model for the analysis of hydrogen-fuelled scramjets

Development of a robust solver to model the flow inside the engines for high-speed propulsion

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