Experimental and computational flammability limits in a solid fuel ramjet

Elands, P.J.M.; Dijkstra, F.; Zandbergen, B.T.C.

doi:10.2514/6.1990-1964

Cited by 8 publications

(3 citation statements)

References 3 publications

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“…Flame-holding limits are identified by the distribution of temperature in the combustor 32 and by the average temperature in the cavity 33 under different fuel/air ratio, which is indicating that the self-ignition limits could be characterized by the value of average temperature in the cavity. As is shown in Table 2, some of average temperature in the cavity are larger while some are smaller than the inlet total temperature, corresponding to the selfignition and un-ignition state, respectively.…”

Section: B the Effect Of Length And Depth Of Cavity On Self-ignitionmentioning

confidence: 99%

Numerical Investigation on Self-ignition and Flammability Characteristics in Solid Fuel Scramjet Combustor

Chi¹,

Wei²,

Li³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The characteristics of self-ignition and self-sustained combustion of a solid fuel under supersonic cross flow have been investigated theoretically and numerically. A time dependent two-dimensional, axisymmetric compressible Navier-Stokes equations and species transport equations are solved numerically. Turbulence model is using the Shear Stress Transportk  model. The PMMA fuel and a global one step reaction mechanism are used in this study. The reaction rate is determined by finite-rate chemical kinetics with the turbulence-chemistry interaction modeled using eddy-dissipation model. The numerical model is validated by comparing the numerical results with experimental data. The flame spread and pressurization during self-ignition of PMMA in combustor have been studied. The behaviors of both sustained and un-sustained combustion in SFSCRJ combustor have been analyzed. The simulation results reveal that three stages of flame spread are identified during the self-ignition transient, which consists of heat accumulation, self-ignition in the secondary recirculation zone, and whole combustor self-ignition orderly. The pressure suddenly rises in combustor during the third stage. The difference of combustor shape affects the self-ignition. There have always been high temperature zone and high mass fraction of reaction products in combustor during sustained combustion. Once the recirculation zone area and residual time provided by cavity are unable to meet the time needed for chemical reaction of reactants and the ignition of fresh mixture, flame is blew out by supersonic cross flow. NomenclatureSubscripts g_ini = initial state of gas s_ini = initial state of solid 0 = total parameter fh = flame-holder cyl = cylindrical section div = diverging section

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Section: B the Effect Of Length And Depth Of Cavity On Self-ignitionmentioning

confidence: 99%

Numerical Investigation on Self-ignition and Flammability Characteristics in Solid Fuel Scramjet Combustor

Chi¹,

Wei²,

Li³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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show abstract

“…1. A number of researchers have attempted numerical simulation of the SFRJ combustion chamber; however all of them focused on the flow field within the chamber after the motor ignition [1][2][3][4][5][6][7][8][9][10][11]. This is due to complexities in simulating dynamics of the ignition process of this type of motors.…”

Section: Introductionmentioning

confidence: 98%

Igniter jet dynamics in solid fuel ramjets

Tahsini¹,

Farshchi²

2009

Acta Astronautica

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“…However, more literature can be found on a similar type of device, the solid fuel ramjet, in particular in studies dedicated to its upper flammability limit [16][17][18][19]. These papers provide experimentally determined upper mass flux limits as functions of several design parameters.…”

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confidence: 99%