Numerical simulation of angular injection of hydrogen fuel in scramjet combustor

Murty, M.S.R. Chandra; Chakraborty, Debasis

doi:10.1177/0954410011414320

Cited by 11 publications

(6 citation statements)

References 38 publications

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“…The former is obtained with Arrhenius law by defining a pre-exponential constant A and an activation temperature T A . Several options are available in the open-literature for the Arrhenius law constants and this work adopts the values A =1.1e19 and T A =8052 K as proposed by Chandra Murty and Chakraborty ( 15 ) . These values have been obtained for hydrogen combustion by requiring that the flame speed of the single-step kinetics match with those from full chemistry as pointed out by Sekar and Mukunda ( 30 ) .…”

Section: Numerical Modelling Of Scramjetsmentioning

confidence: 99%

“…In the context of RANS-based approaches, the eddy dissipation model (EDM) introduced by Magnussen and Hjertager (12) is a capable approach to address TCI for mixing-limited scramjets. The use of EDM in the modelling of hydrogen-fuelled scramjet flows has been reported in the literature by Edwards et al (13) using the REACTMB CFD solver and it has also been largely documented in the case of commercially available software (14)(15)(16)(17) . However, little information is found in the open literature about the optimal use of the EDM for scramjets with different types of fuel injection configurations or possible improvements of the model to increase its accuracy.…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Numerical Modelling Of Scramjetsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

et al. 2019

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“…The characteristics of oblique injection in supersonic crossflows have been studied. 19–23 This strategy is more efficient in near-field mixing and has a greater thrust than transverse injection with a smaller total pressure loss. Gruber et al.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of the expansion characteristics of vaporized kerosene jets in a quiescent atmospheric environment

Yang

Wang

Pan

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, the time-averaged and instantaneous information of the vaporized kerosene jet injection into a quiescent atmospheric environment, including the expansion angle, deflection angle and shock wave structure, were acquired by natural light and a schlieren system. The results show that the jet expansion angle increases first and then decreases during the kerosene vaporization, which is mainly governed by the pressure change inside the shear layer and the variation in the jet axial speed. Compared with straight injection, the oblique scheme inhibits the jet expansion process and enhances the expansion property in the vertical and parallel directions of the bevel face. Because of the asymmetric configuration of the injector exit and the adsorptive effect of the bevel face, the jet plume in the oblique injection scheme obviously deflects along the axial direction. In addition, the expansion angle fluctuates when the vaporized kerosene is injected into some specific conditions. The frequency of the jet pulse is approximately 2.1 Hz, and the pulsation mode gradually converts during the vaporization process. The two-phase flow instability occurring in upstream heated kerosene might be responsible for this unique phenomenon.

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“…8. The reacting flow field of SCHolAR experiment was simulated extensively numerically through RANS as well as lES models by many researchers with different chemical kinetics schemes, turbulence models and well reported in the literature [23][24][25][26][27] . Front section of the combustor (containing the isolator and injector) is made of copper while the rear section is made of carbon steel.…”

Section: Hydrogen Fuelled Scramjet Combustor With Wall Injectionmentioning

confidence: 99%

A Novel CFD Method to Estimate Heat Transfer Coefficient for High Speed Flows

et al. 2016

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Accurate prediction of surface temperature of high speed aerospace vehicle is very necessary for the selection of material and determination of wall thickness. For aerothermal characterisation of any high speed vehicle in its full trajectory, it requires number of detailed computational fluid dynamics (CFD) calculations with different isothermal calculations. From the detailed CFD calculations for different flow conditions and geometries, it is observed that heat transfer coefficients scale with the difference of adiabatic wall temperature and skin temperature. A simple 'isothermal method', is proposed to calculate heat flux data with only two CFD simulations one on adiabatic condition and other on isothermal condition. The proposed methodology is validated for number of high speed test cases involving external aerodynamic heating as well as high speed combusting flow. The computed heat fluxes and surface temperatures matches well with experimental and flight measured values.

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Numerical simulation of angular injection of hydrogen fuel in scramjet combustor

Cited by 11 publications

References 38 publications

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

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

Experimental investigation of the expansion characteristics of vaporized kerosene jets in a quiescent atmospheric environment

A Novel CFD Method to Estimate Heat Transfer Coefficient for High Speed Flows

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