An aerothermochemical analysis of carbon-carbon nozzle regression insolid-propellant rocket motors

Borie, Vincent; Brulard, J.; Lengellé, G.

doi:10.2514/6.1988-3346

Cited by 4 publications

(1 citation statement)

References 4 publications

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“…alumina from solid rocket motors) are not present in the combustion gases. [18][19][20] The second assumption is justified by chemical equilibrium calculations 15 showing little effect on the concentration of oxidizing species between the chamber and the throat region (where the erosion is most important). This is particularly true when fuel-rich propellant combinations are analyzed, as for the present study.…”

Section: Iia Governing Equations For the Gas Phasementioning

confidence: 99%

Ablative Material Behavior in Oxygen/Methane Thruster Environment

Turchi

Bianchi

Nasuti

et al. 2012

43rd AIAA Thermophysics Conference

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Ablative materials represent a low cost and reliable means to insulate rocket engine components from high-temperature, corrosive combustion product environments. Besides their diffuse application in solid rocket nozzles, their use also emerges as a valid alternative in liquid rocket engines. Together with the growing interest in oxygen/methane liquid rocket engines, these materials have gained attention as possible insulator for small upperstage engines or in-space thrusters. In this framework, a validated approach for the study of carbon-based pyrolyzing and non-pyrolyzing materials, together with a novel boundary condition developed to analyze the silica-based material behavior, has been used to numerically reproduce the material response in the highly oxidizing environment generated by the combustion of oxygen and methane. At first, the validation against experimental data of the silica-based material erosion model is presented. Subsequently, the behavior and the response of different ablators in a oxygen/methane environment is numerically investigated for a wide range of operating conditions. Commonly made assumptions in the simulation of the material response are thoroughly analyzed and a critical overview of the results is presented. Nomenclaturebinary diffusion coefficient, m 2 /s h = enthalpy, J/kg k = thermal conductivity, W/m · K N c = number of specieṡ m = mass blowing rate per unit area, kg/m 2 · s p = pressure, N/m 2 q radout = wall radiative heat flux, W/m 2 s = erosion rate, m/s T = temperature, K t = time, s v = flow velocity, m/s v = velocity component normal to surface, m/s * Ph.D. Student, Dipartimento di Ingegneria Meccanica e Aerospaziale, Via Eudossiana 18. AIAA Student Member. alessandro.turchi@uniroma1.it. ẇ i = species source term in control volume, kg/m 3 · s x = mole fraction y = mass fraction y + = dimensionless wall distance Subscripts c = charred state f = failed material g = pyrolysis gas i = species s = solid state v = virgin state w = gas properties at gas/solid interface Symbols η = outward coordinate normal to surface Γ m = mass resin fraction Γ V = volume resin fraction µ = viscosity, kg/m · s µ t = turbulent viscosity, kg/m · s ρ = density, kg/m 3 ρ A = primary resin component density, kg/m 3 ρ B = secondary resin component density, kg/m 3 ρ R = reinforcing material density, kg/m 3

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Section: Iia Governing Equations For the Gas Phasementioning

confidence: 99%

Ablative Material Behavior in Oxygen/Methane Thruster Environment

Turchi

Bianchi

Nasuti

et al. 2012

43rd AIAA Thermophysics Conference

View full text Add to dashboard Cite

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Modelling of carbon–carbon composite ablation in rocket nozzles

Vignoles¹,

Aspa²,

Quintard³

2010

Composites Science and Technology

113

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Analytical modeling of the steady state ablation of a 3D C/C composite

Lachaud

Aspa

Vignoles

2008

International Journal of Heat and Mass Transfer

109

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Following an analysis of surface roughness features that develop on a 3D C/C composite during ablation, i.e. wall recession by oxidation and/or sublimation, a modeling strategy is set up in order to predict the composite behavior from that of its components. It relies on two changes of scale: (i) microscopic scale (fiber, matrix) to mesoscopic scale (bundle) and (ii) mesoscopic scale (bundle, matrix) to macroscopic scale (composite). The physical basis is a general model for receding surfaces under a gasification process coupled to mass transfer. At each scale, the 3D surface equation is analytically solved in steady state considering a 1D mass transfer perpendicular to the overall surface. The models are validated by comparison to experimental data.

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An aerothermochemical analysis of carbon-carbon nozzle regression insolid-propellant rocket motors

Cited by 4 publications

References 4 publications

Ablative Material Behavior in Oxygen/Methane Thruster Environment

Ablative Material Behavior in Oxygen/Methane Thruster Environment

Modelling of carbon–carbon composite ablation in rocket nozzles

Analytical modeling of the steady state ablation of a 3D C/C composite

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