Chemical Reaction Effects on Heat Loads of CH4/O2 and H2/O2 Rockets

Betti, B.; Bianchi, Daniele; Nasuti, Francesco; Martelli, Emanuele

doi:10.2514/1.j054606

Cited by 41 publications

(13 citation statements)

References 25 publications

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“…The importance of taking into account recombination reactions in the wall heat flux evaluations is well-known and has been discussed in Ref. [18]. The differences on heat flux values obtained with and without considering recombination reactions is shown in Fig.…”

Section: Resultsmentioning

confidence: 89%

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Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

Concio

Migliorino

Nasuti

2020

Aerotec. Missili Spaz.

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The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a challenge, because of the little experimental information. Such a problem is of obvious importance in general, and becomes even more important when considering reusable engines. Unfortunately, only few indirect experimental data are available for the validation of throat heat flux prediction. On the numerical side, a detailed solution would require a huge resolution and codes able to solve at the same time combustion, boundary layer with possible finite-rate reactions, expansion up to at least sonic speed, and in some cases radiative heat flux. Therefore, it is important to validate, with the few experimental data available in the literature, simplified CFD approaches whose aim is to predict heat flux in the nozzle in affordable times. Results obtained by different numerical models based on a RANS approach show the correctness and quality of the approximations made, indicating the main phenomena to be included in modeling for the correct prediction of throat heat flux.

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Section: Resultsmentioning

confidence: 89%

“…Constant values are assumed for turbulent Schmidt and Prandtl numbers, equal to Sc T = 0.7 and Pr T = 0.9 , respectively. Oxygen/methane kinetics is modeled by means of the JL-R finite-rate chemical reaction mechanism [18,20], shown in Table 1. As explained in Sect.…”

Section: Theoretical and Numerical Modelmentioning

confidence: 99%

Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

Concio

Migliorino

Nasuti

2020

Aerotec. Missili Spaz.

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“…The CFD tool is a finite-volume solver for three-dimensional compressible multicomponent turbulent reacting flows [22,23], with temperature-variable thermodynamic and transport properties. The thermodynamic properties of individual species were approximated by seventh-order polynomials of temperature, while the transport properties were approximated by fourth-order polynomials [27].…”

Section: Theoretical and Numerical Modelmentioning

confidence: 99%

“…The numerical simulations presented here were carried out by solving the Reynolds-averaged Navier-Stokes equations for multicomponent, single-phase, turbulent reacting flows [22,23], including the sub-models required in order to describe the homogeneous combustion in the gaseous phase, the radiative energy exchange, and the gas-surface interaction in the combustion chamber (fuel pyrolysis model) for HDPE grains. The in-house computational tool used for the simulations, and its gas-surface interaction capability has been validated for high-speed re-entry flows [24], for the analysis of Hydroxyl-Terminated Polybutadiene (HTPB) fuel grains [3,4,25], and for hybrid rocket nozzle thermal protection systems' ablation [3,19,26].…”

Section: Introductionmentioning

confidence: 99%

Modeling of High Density Polyethylene Regression Rate in the Simulation of Hybrid Rocket Flowfields

et al. 2019

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Numerical analysis of hybrid rocket internal ballistics is carried out with a Reynolds-averaged Navier–Stokes solver integrated with a customized gas–surface interaction wall boundary condition and coupled with a radiation code based on the discrete transfer method. The fuel grain wall boundary condition is based on species, mass, and energy conservation equations coupled with thermal radiation exchange and finite-rate kinetics for fuel pyrolysis modeling. Fuel pyrolysis is governed by the convective and radiative heat flux reaching the surface and by the energy required for the propellant grain to heat up and pyrolyze. Attention is focused here on a set of static firings performed with a lab-scale GOX/HDPE motor working at relatively low oxidizer mass fluxes. A sensitivity analysis was carried out on the literature pyrolysis models for HDPE, to evaluate the possible role of the uncertainty of such models on the actual prediction of the regression rate. A reasonable agreement between the measured and computed averaged regression rate and chamber pressure was obtained, with a noticeable improvement with respect to solutions without including radiative energy exchange.

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“…In addition to the mentioned disadvantages, the chemical equilibrium assumption could lead to an overestimation of the heat flux inside the nozzle wall, compared to a finite-rate chemistry. 26…”

Section: E Reactive Nozzle Flow In Chemical Equilibriummentioning

confidence: 99%