Computational Fluid Dynamics Simulation of Hybrid Rockets of Different Scales

Lazzarin, Marta; Faenza, Martina; Barato, Francesco; Bellomo, Nicolas; Bettella, Alberto; Pavarin, Daniele

doi:10.2514/1.b35528

Cited by 28 publications

(11 citation statements)

References 9 publications

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“…If the number of chemical species used is too low, the flame temperature of the reaction would become higher than the real flame adiabatic temperature, thus creating an error in the simulation. A similar reaction was used for paraffin wax by Lazzarin [19], even though the paraffin used in her research is Pentacontane, C 50 H 102 .…”

Section: Chemical Reactionmentioning

confidence: 99%

“…The baseline used for the CFD simulations conducted in this thesis is the setup finally developed by Lazzarin [19]. It will be discussed in the chapter concerning the CFD.…”

Section: Computational Fluid Dynamicsmentioning

confidence: 99%

“…The authors of [11] suggest that the approximations of the models probably tend to compensate each other. So they used k-in most of their works, preferring a simple and robust model to avoid nontrivial errors in the solution [19]. In [15], a CFD investigation on the influence of swirling flow field inside the combustion chamber is carried out, and the model used is k-again.…”

Section: Turbulencementioning

confidence: 99%

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CFD Simulations of Self-pressurized Nitrous Oxide Hybrid Rocket Motors

Paccagnella

Barato

Gelain

et al. 2018

2018 Joint Propulsion Conference

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Delft Aerospace Rocket Engineering has developed a 1 kN hybrid rocket motor, using Nitrous Oxide as oxidizer and a mixture of Sorbitol and Paraffin as fuel. During the campaign, different motor configurations were tested. The thesis starts with the numerical simulation of the rocket motor firing in the different tests, modelling the discharge of self-pressurized Nitrous Oxide. The simulation provides the trend over time of motor parameters such as mass flow rates, vapor quality of the oxidizer, and fuel grain thickness. Once validated through comparison with the test data, these values have been used to setup CFD simulations of the combustion chamber. An instant of the burning is simulated in steady state conditions using the eddy dissipation combustion model, gaseous injection of the fuel and no entrainment of liquefying paraffin with the oxidizer flow. The oxidizer is injected in both liquid and gas phase using the results of the numerical simulations to initialize the boundary conditions. The results are compared with the numerical data, the experimental data and the values predicted by the theory, to show the improvements that CFD simulations can provide to the designer during the development of a new hybrid rocket motor.

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Section: Chemical Reactionmentioning

confidence: 99%

“…The baseline used for the CFD simulations conducted in this thesis is the setup finally developed by Lazzarin [19]. It will be discussed in the chapter concerning the CFD.…”

Section: Computational Fluid Dynamicsmentioning

confidence: 99%

Section: Turbulencementioning

confidence: 99%

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CFD Simulations of Self-pressurized Nitrous Oxide Hybrid Rocket Motors

Paccagnella

Barato

Gelain

et al. 2018

2018 Joint Propulsion Conference

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“…These are modeling, first, the formation, the breaking up and the entrainment of the liquid film on the melting fuel surface; and, second, the transformation of the melted fuel into a gaseous species participating in the combustion process. These demanding efforts have probably discouraged researchers, so drastic simplifications are usually introduced, such as giving the regression rate calculation away by assuming it from experiments [31,[37][38][39], or limiting the analysis to one-dimensional integral-differential models [40]. In other cases, by observing that the melted paraffin wax is in the supercritical state under the hybrid rocket chamber characteristic conditions (thus, surface tension vanishes and the sharp distinction at droplets surface between gas and liquid phases disappear), the melted layer break up and, subsequently, the liquid paraffin injection in the flowfield is disregarded, supposing that the entrainment is part of the turbulent mixing process [41,42].…”

Section: State Of the Art Of Cfd Techniques For Rocket Internal-ballimentioning

confidence: 99%

“…This allows for correctly taking the blocking effect on the heat transfer to the wall into account, while, as explained in the previous section, Equation (37) is needed to ensure the mixture fraction has a global balance.…”

Section: Liquefying Fuelsmentioning

confidence: 99%

The Application of Computational Thermo-Fluid-Dynamics to the Simulation of Hybrid Rocket Internal Ballistics with Classical or Liquefying Fuels: A Review

et al. 2019

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The computational fluid dynamics of hybrid rocket internal ballistics is becoming a key tool for reducing the engine operation uncertainties and development cost as well as for improving experimental data analysis. Nevertheless, its application still presents numerous challenges for the complexity of modeling the phenomena involved in the fuel consumption mechanism and its coupling with the chemically reacting flowfield. This paper presents a review of the computational thermo-fluid-dynamic models developed for the internal ballistics of hybrid rockets burning gaseous oxygen with classical polymeric or paraffin-based fuels, with a special focus on the interaction between the fluid and the solid fuel surface. With the purpose of predicting the local fuel regression rate, which is the main parameter needed for the hybrid rocket design, the model is coupled with an improved gas/surface interface treatment based on local mass, energy and mean mixture-fraction balances, combined to either a pyrolysis-rate equation in the case of classical polymers, or to an additional equation for the liquid paraffin entrainment fraction of the total fuel consumption rate. A number of experimental test cases obtained from the static firing of two different laboratory-scale rockets are simulated to determine the models’ capabilities, showing very good agreement between the calculated and measured fuel regression rates with both standard pyrolyzing and liquefying fuels. The prediction of the chamber pressure measured with paraffin fuel resulted in it being more cumbersome for the single-phase flow assumption. The advantages and limitations of the models are discussed.

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