Combustion of a double-base homogeneous propellant in a rocket motor

Tseng, I.; Yang, Vigor

doi:10.1016/0010-2180(94)90102-3

Cited by 59 publications

(17 citation statements)

References 14 publications

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“…The unclosed terms u 00 j u 00 i , E 00 u 00 j , and Y 00 k u 00 j in Eqs. (2-4), respectively, are treated using a two-layer model that is well calibrated for transpiration and accelerating flows [28,29]. The model shows superior performance in terms of numerical accuracy and convergence, compared with the conventional low-Reynoldsnumber k-" schemes.…”

Section: Turbulence Closurementioning

confidence: 99%

Chemical Erosion of Carbon-Carbon/Graphite Nozzles in Solid-Propellant Rocket Motors

Thakre

Yang

2008

Journal of Propulsion and Power

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122

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Section: Turbulence Closurementioning

confidence: 99%

Chemical Erosion of Carbon-Carbon/Graphite Nozzles in Solid-Propellant Rocket Motors

Thakre

Yang

2008

Journal of Propulsion and Power

Self Cite

122

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“…The situation is especially true for problems involving transient and erosive burning, where Eq. (36) offers more accurate predictions [28]. Mitani and Williams [29] developed an expression similar to Eq.…”

Section: Mathematical Formulationmentioning

confidence: 98%

Modeling of combustion and ignition of solid-propellant ingredients

Beckstead

Puduppakkam

Thakre

et al. 2007

Progress in Energy and Combustion Science

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213

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“…The turbulent kinetic energy is found from equation (4). The dissipation rate is calculated by using an algebraic dependence with allowance for the influence of flow unsteadiness on the turbulence scale [21], rather than by means of numerical integration of equation (5).…”

Section: In Cartesian Coordinatesmentioning

confidence: 99%

Pressure oscillations and instability of working processes in the combustion chambers of solid rocket motors

et al. 2017

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Cite this article as: V.N. Emelyanov, I.V. Teterina, K.N. Volkov and A.U. Garkushev, Pressure oscillations and instability of working processesin the combustion chambers of solid rocket motors, Acta Astronautica, http://dx.doi.org/10. 1016/j.actaastro.2016.09.029 This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting galley proof before it is published in its final citable form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. AbstractMetal particles are widely used in space engineering to increase specific impulse and to supress acoustic instability of intra-champber processes. A numerical analysis of the internal injection-driven turbulent gas-particle flows is performed to improve the current understanding and modeling capabilities of the complex flow characteristics in the combustion chambers of solid rocket motors (SRMs) in presence of forced pressure oscillations. The two-phase flow is simulated with a combined Eulerian-Lagrangian approach. The Reynolds-averaged Navier-Stokes equations and transport equations of -model are solved numerically for the gas. The particulate phase is simulated through a Lagrangian deterministic and stochastic tracking models to provide particle trajectories and particle concentration. The results obtained highlight the crucial significance of the particle dispersion in turbulent flowfield and high potential of statistical methods. Strong coupling between acoustic oscillations, vortical motion, turbulent fluctuations and particle dynamics is observed.

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Combustion of a double-base homogeneous propellant in a rocket motor

Cited by 59 publications

References 14 publications

Chemical Erosion of Carbon-Carbon/Graphite Nozzles in Solid-Propellant Rocket Motors

Chemical Erosion of Carbon-Carbon/Graphite Nozzles in Solid-Propellant Rocket Motors

Modeling of combustion and ignition of solid-propellant ingredients

Pressure oscillations and instability of working processes in the combustion chambers of solid rocket motors

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