A numerical approach for the study of the gas–surface interaction in carbon–phenolic solid rocket nozzles

Turchi, Alessandro; Bianchi, Daniele; Nasuti, Francesco; Onofri, Marcello

doi:10.1016/j.ast.2012.06.003

Cited by 48 publications

(19 citation statements)

References 22 publications

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“…In the present study the modeling of gas-surface interaction already developed and validated for ablating surfaces [15][16][17][18][19] is extended to the case of fuel pyrolysis in hybrid rocket engines. In particular, a detailed finiterate gas/surface interaction model is coupled with a three-dimensional chemically-reacting fluid dynamics (CFD) code.…”

Section: Theoretical and Numerical Modelmentioning

confidence: 99%

Numerical Modeling of GOX/HTPB Hybrid Rocket Flowfields and Comparison with Experiments

Bianchi¹,

Betti

Nasuti

et al. 2014

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

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Numerical simulations of the flowfield in a GOX/HTPB hybrid rocket engine are carried out with a Reynolds averaged Navier-Stokes solver including detailed gas surface interaction modeling based on surface mass and energy balances. Fuel pyrolysis is modeled via finite-rate Arrhenius kinetics. A simplified two-step global reaction mechanism is considered for the gas-phase chemistry to model the combustion of 1,3-butadiene in oxygen. Results are compared with firing test data from a lab-scale hybrid rocket in which gaseous oxygen is fed into axisymmetric HTPB cylindrical grains through an axial conical subsonic nozzle. With the oxidizer fed by this kind of injector, which generates nonuniform conditions at the entrance of the fuel port, the fuel regression rate is shown to increase several times with respect to the case of homogeneous injection of the oxidizer through all the grain port area, in agreement with the experimental findings. The spatial distribution of the regression rate is substantially different from the one expected in a turbulent developing flow, because of the presence of a strong recirculation zone. Numerical simulations, yet not capturing the absolute regression rate values, are fairly able to predict the main ballistic features, i.e. the regression rate weaker dependence on the mass flux, the influence of port diameter and the pressure evolution over time

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Section: Theoretical and Numerical Modelmentioning

confidence: 99%

Numerical Modeling of GOX/HTPB Hybrid Rocket Flowfields and Comparison with Experiments

Bianchi¹,

Betti

Nasuti

et al. 2014

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

View full text Add to dashboard Cite

show abstract

“…In the present study, the modeling of the gas/surface interaction already developed and validated for ablating surfaces [25][26][27][28][29] is extended to the case of fuel pyrolysis in hybrid rocket engines. In particular, a detailed finite-rate gas/surface interaction model is coupled with a three-dimensional chemically reacting fluid dynamics code.…”

Section: Theoretical and Numerical Modelmentioning

confidence: 99%

Simulation of Gaseous Oxygen/Hydroxyl-Terminated Polybutadiene Hybrid Rocket Flowfields and Comparison with Experiments

Bianchi

Betti

Nasuti

et al. 2015

Journal of Propulsion and Power

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Numerical simulations of the flowfield in a gaseous oxygen/hydroxyl-terminated polybutadiene hybrid rocket engine are carried out with a Reynolds-averaged Navier–Stokes solver including detailed gas/surface interaction modeling based on surface mass and energy balances. Fuel pyrolysis is modeled via finite-rate Arrhenius kinetics. A simplified two-step global reaction mechanism is considered for the gas-phase chemistry to model the combustion of 1,3-butadiene in oxygen. Results are compared with the firing test data obtained from a laboratory-scale hybrid rocket in which gaseous oxygen is fed into axisymmetric hydroxyl-terminated polybutadiene cylindrical grains through an axial conical subsonic nozzle. With the oxidizer fed by this injector, which generates nonuniform conditions at the entrance of the fuel port, the fuel regression rate is shown to increase several times with respect to the case of homogeneous injection of the oxidizer through all the grain port area, in agreement with the experimental findings. The spatial distribution of the regression rate is substantially different from the one expected in a turbulent developing flow through a pipe because of the presence of a strong recirculation zone at the motor head end. Numerical simulations, although not capturing the absolute regression-rate values, are fairly able to predict the main ballistic features: that is, the regression rate’s weaker dependence on the mass flux, the influence of port diameter, and the pressure evolution over time, as well as the general trends of different firing tests

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“…The results from system reliability analyses calculated on small data samples are affected by significant errors. Therefore numerical models have been widely used to simulate the thermal-structural response of the nozzle and integrate the reliability-based approach [13][14][15][16][17]. Morozov and de la Beaujardiere [13] developed a finite element method to investigate the dynamic thermo-structural response of a composite rocket nozzle throat.…”

Section: Introductionmentioning

confidence: 99%

“…Goyal et al [16] developed reliable reduced size models based on 2D plane strain assumptions for SRM structural analysis. Turchi et al [17] suggested a numerical approach to describe a carbon-phenolic SRM nozzle model and then investigated the role of the most important uncertainty parameters affecting the design. Heller et al [11,12] pioneered a methodology for reliability analysis of C/C composites, and analyzed the stress state of a cylindrical structure consisting of multiple layers of C/C composite under thermal and pressure shock by assuming elasticity within the structure.…”

Section: Introductionmentioning

confidence: 99%

Probabilistic Reliability Analysis of Carbon/Carbon Composite Nozzle Cones with Uncertain Parameters

Xie¹,

Yang²,

Meng³

et al. 2019

Journal of Spacecraft and Rockets

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A numerical approach for the study of the gas–surface interaction in carbon–phenolic solid rocket nozzles

Cited by 48 publications

References 22 publications

Numerical Modeling of GOX/HTPB Hybrid Rocket Flowfields and Comparison with Experiments

Numerical Modeling of GOX/HTPB Hybrid Rocket Flowfields and Comparison with Experiments

Simulation of Gaseous Oxygen/Hydroxyl-Terminated Polybutadiene Hybrid Rocket Flowfields and Comparison with Experiments

Probabilistic Reliability Analysis of Carbon/Carbon Composite Nozzle Cones with Uncertain Parameters

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