Chemical Erosion of Carbon-Phenolic Rocket Nozzles with Finite-Rate Surface Chemistry

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

doi:10.2514/1.b34791

Cited by 63 publications

(24 citation statements)

References 37 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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

Self Cite

View full text Add to dashboard Cite

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

show abstract

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

Self Cite

View full text Add to dashboard Cite

show abstract

“…Evaluation of the nozzle inner wall temperature To evaluate the inner wall temperature of the nozzle the thermal resistance approach was used. This strategy is justified because despite the outer wall has a very long transient the inner wall rapidly reach the steady state condition [5]. Since the inner surface of the tube suffers a continuous regression, the energy balance in the internal boundary can be expressed as:…”

Section: 2mentioning

confidence: 99%

“…In this context, it is of great interest to predict the efficacy of insulation protection system on a SRM and its behavior during operating time. Several ablation models and computational tools have been developed in order to study the ablation mechanism, with several levels of complexity [3,4,5].…”

Section: Introductionmentioning

confidence: 99%

A Fast Method for Preliminary Evaluation of Chemical Erosion on a Composite Nozzle

Untem¹,

Calciolari²,

Almeida³

et al. 2018

Proceedings of the 4th Brazilian Conference on Composite Materials

View full text Add to dashboard Cite

Most solid rocket motors (SRM) make use of polymeric composites as ablative thermal protection system (TPS). One of the main advantages of this type of cooling is its simplicity and cost; however, the mechanism of erosion on the composite surface is very complex and tricky to model. In the present work, an ablation model was developed considering the reaction of H2O and CO2 molecules, present in the combustion gases, with the ablative material. This approach is valuable for a preliminary assessment of the behaviour of ablative layers. The investigation was based on a particular case of a SRM ablative nozzle since it is a critical setup for this type of thermal protection system. The bisection method was used for 02 particular propellant formulations in order to predict the mass consumption rate of the ablative material in function of the nozzle diameter and the mass fraction of aluminium.

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

Self Cite

View full text Add to dashboard Cite

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

show abstract

Chemical Erosion of Carbon-Phenolic Rocket Nozzles with Finite-Rate Surface Chemistry

Cited by 63 publications

References 37 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

A Fast Method for Preliminary Evaluation of Chemical Erosion on a Composite Nozzle

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

Contact Info

Product

Resources

About