Numerical Study of Fuel Regression in Hybrid Rocket Engine

Durand, Jean-Étienne; Raynaud, Florent; Lamet, Jean-Michel; Tessé, Lionel; Lestrade, Jean-Yves; Anthoine, J.

doi:10.2514/6.2018-4593

Cited by 9 publications

(3 citation statements)

References 32 publications

(44 reference statements)

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“…This can be specially significant for rich fuel mixtures (weak oxidizer mass fluxes), when soot production is important. Radiation contribution has been observed to produce an increase in v r going from 5 to 10% in experiments [54] to 35% [33] in CFD codes for different couples and mass flow values. e) The specified thermophysical properties of the solid propellant, such as density, specific heat, depolymerization enthalpy of the fuel or even the coefficients used in the Arrhenius law.…”

Section: Error Sourcesmentioning

confidence: 98%

Development and Validation of a 1.5-D Combustion Chamber Model for a Hybrid Rocket Engine Applied to a Cylindrical HDPE Chamber

Granado¹,

Hijlkema²,

Lestrade³

et al. 2021

AIAA Propulsion and Energy 2021 Forum

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A 1.5-D model for the cylindrical combustion chamber of a hybrid rocket is developed in this article with the purpose of its integration in a design system tool allowing to estimate the rocket performances. A compromise of simplicity and accuracy is then required in the formulation of the model. Transient boundary layer equations are included through an integral approach and are coupled with the mass and energy balances performed at the fuel surface. Fuel pyrolysis is described by way of an Arrhenius law. Several studies to assess the impact of the geometry of the fuel port, the oxidizer mass flux, and the motor size on the computed fuel regression rate are accomplished. A final validation phase of this model is executed by the comparison with experimental tests realized at ONERA's HYCAT test bench with a Hydrogen Peroxide / High-Density Polyethylene couple.

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Section: Error Sourcesmentioning

confidence: 98%

Development and Validation of a 1.5-D Combustion Chamber Model for a Hybrid Rocket Engine Applied to a Cylindrical HDPE Chamber

Granado¹,

Hijlkema²,

Lestrade³

et al. 2021

AIAA Propulsion and Energy 2021 Forum

Self Cite

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“…The most used numerical approach in the literature is based on Reynolds-averaged Navier-Stokes (RANS) simulations employing different sub-models [6], which either rely on a prescribed fuel mass flow rate [9][10][11][12][13] or employ a parametric gassurface interaction model [14,15]. Radiation effects on the regression rate, which can be important in HRE operating conditions [16][17][18][19], are also usually neglected when dealing with paraffin-based engines.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulations of the Internal Ballistics of Paraffin–Oxygen Hybrid Rockets at Different Scales

2021

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Hybrid rockets are considered a promising future propulsion alternative for specific applications to solid or liquid rockets. In order to raise their technology readiness level, it is important to perform predictive numerical simulations of their internal ballistics. The objective of this work is to describe and validate a numerical approach based on Reynolds-averaged Navier–Stokes simulations with sub-models for fluid–surface interaction, radiation, chemistry, and turbulence. Particular attention is given to scale effects by considering two different paraffin–oxygen hybrid rocket engines and a simplified grain evolution approach from the initial to the final port diameter. Moreover, a mild sensitivity of the computed regression rate to paraffin’s melting temperature, surface radiation emissivity, and Schmidt numbers is observed. Results highlight the increasing importance of radiation effects at larger scales and pressures. A numerical rebuilding of regression rate and pressure is obtained with simulations at the time-space-averaged port diameter, producing a reasonable agreement with the available experimental data, but a noticeable improvement is obtained by considering the grain evolution in time.

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“…RANS simulations tipically rely either on the assignment of a prescribed fuel mass flow rate [11][12][13][14][15], or employ a parametric gas-surface interaction model, i.e., tuned to match one experimental firing test [16,17]. All previous numerical studies dealing with paraffin-wax neglect radiation effects, which can be prominent in HRE combustion chambers [18][19][20], and, in addition, neglect its thermal cracking reaction by directly injecting ethylene from the fuel grain surface to the flow field. One open challenge is the ability to predict the internal ballistic of paraffin-based HREs without compromising the simplicity and inclusiveness of the model strategy, and without tuning to experimental data.…”

Section: Introductionmentioning

confidence: 99%