Comprehensive modeling of a liquid rocket combustion chamber

Liang, P. Y.; Fisher, Scott; Chang, Y. M.

doi:10.2514/3.22851

Cited by 31 publications

(7 citation statements)

References 4 publications

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“…This has been approached by analyzing a series of generic problems that reveal the controlling parameters in carefully defined steps. Theoretical and numerical modelling has also been used to resolve some of the difficult questions raised by combustion of cryogenic propellants at high pressures by for example: Liang et al (1985); Sirignano (1993a, 1993b); Daou et al (1995); Oefelein and Yang (1998); Oefelein and Aggarwal (2000); Harstad and Bellan (2001);Okong'o et al (2002);Okong'o and Bellan (2003); Jay et al (2005); and the reviews by Yang (2000Yang ( , 2004.…”

Section: Introductionmentioning

confidence: 98%

Structure and Dynamics of Cryogenic Flames at Supercritical Pressure

Candel

Juniper

Singla

et al. 2006

Combustion Science and Technology

129

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A detailed understanding of liquid propellant combustion is necessary for the development of improved and more reliable propulsion systems. This article describes experimental investigations aimed at providing such a fundamental basis for design and engineering of combustion components. It reports recent applications of imaging techniques to cryogenic combustion at high pressure. The flame structure is investigated in the transcritical range where the pressure exceeds the critical pressure of oxygen ðp > p c ðO 2 ¼ 5:04 MPaÞÞ but the temperature of the injected liquid oxygen is below its critical value ðT O2 < T c ðO 2 Þ ¼ 154 KÞ. Data obtained from imaging of OH Ã radicals emission, CH Ã radicals emission in the case of LOx=GCH 4 flames and backlighting provide a detailed view of the flame structure for a set of injection conditions. The data may be used to guide numerical modelling of transcritical flames and the theoretical and numerical analysis of the stabilization process. Calculations of the flame edge are used to illustrate this aspect. Results obtained may also be employed to devise engineering modelling tools and We wish to thank CNES, Snecma and CNRS for their continuous support of our work in rocket propulsion. The assistance of the ''Mascotte'' team of Onera under the leadership of Lucien Vingert and Mohamed Habiballah is gratefully acknowledged.

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Section: Introductionmentioning

confidence: 98%

Structure and Dynamics of Cryogenic Flames at Supercritical Pressure

Candel

Juniper

Singla

et al. 2006

Combustion Science and Technology

129

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“…However, because of the coexistence of liquid fuel droplets, liquid oxidizer droplets, fuel vapor, and oxidizer vapor in the combustion environment, the combustion process taking place in the liquid rocket engines represents one of the most complicated physical problems at present, and only very few papers making progress in advanced liquid rocket engine modeling have been published in the literature. 2 ' 3 Recent development in the high-speed large-capacity digital computer and computational techniques to solve coupled partial differential equations as well as the theoretical and experimental advances in the physical modeling such as group combustion/evaporation models, 4 " 6 turbulent flow models, 6 -7 turbulent combustion models, 8 and two-phase interaction models, 9 make the comprehensive computer simulation code for spray combustion more feasible. In fact, it has been applied successfully to the prediction of the operational and performance characteristics of combustors for airbreathing engines 6 ' 10 " 12 and liquid rocket engines.…”

Section: Nomenclaturementioning

confidence: 99%

“…In fact, it has been applied successfully to the prediction of the operational and performance characteristics of combustors for airbreathing engines 6 ' 10 " 12 and liquid rocket engines. 2 The objective of this paper is, therefore, to develop a comprehensive computer simulation code of bipropellant combustion in order to analyze the vaporization and combustion characteristics of a cylindrical liquid rocket engine combustor operating at a choked flow condition. According to the theory of conjugate, normal, and composite combustion, 3 the oxidizer droplets present in a fuel-rich zone are capable of combusting in much the same manner as fuel droplets burning in an oxidizer-rich environment.…”

Section: Nomenclaturementioning

confidence: 99%

Bipropellant combustion in a liquid rocket combustion chamber

Jiang

Chiu

1992

Journal of Propulsion and Power

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A comprehensive computer simulation code is developed for the combustion-flow analysis of a bipropellant liquid rocket engine combustor. A bipropellant group combustion model is built in the computer code to facilitate the determination of various combustion modes, including the combustion of oxidizer droplets, fuel droplets and gas mixture. Several physical submodels are also adopted to account for the interaction between bipropellant droplets and the gas-phase flow. An axisymmetric cylindrical liquid rocket engine combustion chamber installed with two annular-ring injectors is selected to demonstrate the capabilities of the present computer simulation code. Two types of injection processes are analyzed. One is characterized by a non-premixed spray process and the other is a premixed spray process. Selected numerical computations show that the premixed spray results in a better utilization of combustion chamber space and gives a higher combustion efficiency in general. But finer-droplet sprays do not necessarily lead to a higher combustion efficiency as traditionally speculated. Nomenclature A = Arrhenius law constant B = transfer number C D = drag coefficient C f = correction factor for the droplet vaporization due to the convective effect C p = specific heat at constant pressure C s = stoichiometric fuel/oxidizer ratio D = energy dissipation due to drag force D k = turbulent kinetic energy shared by droplets E = activation energy F = aerodynamic drag force G = viscous tensor stress G c = spray group combustion number H = heat transfer between gas and droplet phases h = total enthalpy, fC p dT + q°Y f /w f K = turbulent kinetic energy L = latent heat m = droplet evaporation/combustion rate N t -mean droplet number density n = droplet number density n = droplet number density decaying sink caused by droplet evaporation/combustion P -pressure q° = heat of combustion R = universal gas constant R f = fuel consumption rate R 0 = characteristic length r f = volume-mean droplet size T = temperature u = velocity in x direction V = velocity vector v = velocity in r direction w = molecular weight Y = species concentration as mass fraction e = turbulent dissipation rate 0 = droplet void-deducted volume ratio A = heat conductivity

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“…We now present the numerical scheme used to solve equations (l), (2); this scheme is a mixed finite element/finite volume scheme. More precisely, it uses for the hyperbolic terms appearing in the left-hand side of system (1) an upwind formulation which is derived by extending to mixtures some of the usual approximate Riemann solvers used to solve the Euler equations of a single inviscid gas.6 Moreover, it operates on an unstructured finite element triangulation, which makes it possible to employ a computational mesh fitted to complex geometries and adapted to complex solutions (involving, for instance, strong shocks or thin flames).…”

Section: Spatial Approximationmentioning

confidence: 99%

“…To specify the scheme, we first rewrite system (l), (2) The time derivative and source terms integrals are approximated using a mass-lumped approximation:…”

Section: Spatial Approximationmentioning

confidence: 99%

Upwind adaptive finite element investigations of the two‐dimensional reactive interaction of supersonic gaseous jets

Chargy

Dervieux

Larrouturou

1990

Numerical Methods in Fluids

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SUMMARYWe describe an upwind finite element method aimed at numerically simulating the two-dimensional transonic flow of a reactive gaseous mixture. The method uses in particular a triangular finite element mesh, with an adaptive procedure based on mesh refinement by triangle division, and a n upwind non-oscillatory scheme based on a n approximate Riemann solver for the evaluation of the convective terms for all species. Results concerning the reactive interaction of two supersonic gaseous jets are presented.

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Comprehensive modeling of a liquid rocket combustion chamber

Cited by 31 publications

References 4 publications

Structure and Dynamics of Cryogenic Flames at Supercritical Pressure

Structure and Dynamics of Cryogenic Flames at Supercritical Pressure

Bipropellant combustion in a liquid rocket combustion chamber

Upwind adaptive finite element investigations of the two‐dimensional reactive interaction of supersonic gaseous jets

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