Turbulence Modeling Effects on Fuel Regression Rate in Hybrid Rocket Numerical Simulations

Durand, Jean-Étienne; Raynaud, Florent; Lestrade, Jean-Yves; Anthoine, J.

doi:10.2514/1.b37528

Cited by 19 publications

(9 citation statements)

References 25 publications

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“…It has been observed numerically that, despite the little acceleration suffered by the flow at the flame level, the shape of velocity profiles in the BL of a HRE does not vary significantly from the nonreactive case distribution [2]. This is the reason why we will neglect the increase of velocity produced by the lower density gases at the flame level, and consider the law of Eq.…”

Section: Integral Boundary Layer Equationsmentioning

confidence: 99%

“…Equations of mass, axial and radial momentum, as well as the energy and mass fraction balances are integrated along the radial direction (0 ≤ r ≤ R − δ), resulting in the set of Eqs. (1)(a-f): 2 2…”

Section: External Flow Equationsmentioning

confidence: 99%

“…The high costs implied in the realization of experimental test campaigns in the space domain, has boosted the development of numerical models. Indeed, two-dimensional / three-dimensional (2-D / 3-D) Computational Fluid Dynamics (CFD) codes allow the obtention of quite accurate results in the simulation of combustion of hybrid rockets [2][3][4], being able to simulate combustion kinetics, turbulence transport and parietal injection precisely. Nevertheless, the large computing time thereof represents a substantial hindrance for their applicability during the engine predesign phases, in which the thrust and the specific impulse are the results of interest.…”

Section: Introductionmentioning

confidence: 99%

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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: Integral Boundary Layer Equationsmentioning

confidence: 99%

Section: External Flow Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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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

View full text Add to dashboard Cite

show abstract

“…Hence, the calculation domain can be solved in a two-dimensional axisymmetric domain. Gas governing equations [10] can be expressed as…”

Section: Gas Equationsmentioning

confidence: 99%

Transient numerical investigation on thermochemical erosion of C/C nozzles in hybrid rocket motors

Jiang,

Tian,

2024

J. Phys.: Conf. Ser.

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Nozzle erosion is a vital important issue that impacts the performance of hybrid rocket motors. Serious nozzle erosion may significantly decrease the combustion chamber pressure and thrust, which increases the difficulty in designing flight control systems. This paper aims to reveal erosion mechanism systematically. In this paper, transient numerical simulations of thermochemical erosion in hybrid rocket motors are conducted, and combustion flow and thermochemical erosion are coupled calculated. The numerical computation of combustion flow is based on the chemical reactions of propellants and regression rate model, and that of thermochemical erosion is based on the surface reactions between oxidizing species and carbon. The movement of burning surface and nozzle inner surface is simulated through dynamic mesh method. The hybrid rocket motor adopts 90% hydrogen peroxide and hydroxyl-terminated polybutadiene. Distributions of flow field parameters and fuel regression rate are given. The spatial developing process of nozzle surface is presented, and it is found that the roughness of nozzle profile increases with time. The nozzle wall temperature and wall pressure decline with time. Erosion by different species is calculated. OH and H2O make a major contribution to the nozzle thermochemical erosion, while nozzle erosion contributed by CO2 and O2 are quite low. Time-varying characteristics of the erosion rate are unveiled. At the first 1.5 s, the total erosion rate remains almost constant, and then it reduces over time.

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“…The team currently comprises of a few students from interdisciplinary fields but widening its horizon to engage several multidisciplinary students. Using several tools for the design of liquid propellant rocket parts will enable the students from diverse fields to communicate efficiently by seeing the practical applications of the different laws of physics (such as the Newton's law of motion) directly to real-life scenarios in order to make analytical predictionssuch as fluid flow and heat transfer [12]. In order to develop new courses in the Rocketry Program of MSU, major courses offered in the Aerospace Program by several other universities were investigated.…”

Section: Core Competencies and Professional Skill Developmentmentioning

confidence: 99%

Engaging Multidisciplinary Minority Students in The Aerospace Program and Education at Morgan State University

Alamu,

Caballes,

Chen

et al.

2020 Mid-Atlantic Spring Conference Proceedings

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where he conducts qualitative and quantitative research works leading to development. He has participated and led several research work being published in reputable journals and presented at several international conferences.Mr. Marc J Louise Orque Caballes, Morgan State University Mr. Marc Caballes was born and raised in Bogo City, Philippines. He arrived here in America last 2009. As a kid, every time his Mom asked him to do something, he always looked for the most efficient approach to get the job done. Thus, it is no surprise that he is currently pursuing a doctorate in Systems Engineering at Morgan State University (MSU), where his Professors help him enhance his capabilities in looking for the most optimal solution while delivering quality results. Some people might say that it is okay to make mistakes as long as you learn from them. However, Mr. Caballes beg to differ. For him, it is more convenient to eliminate that "mistake" before it happens. Hence, he always wants to have an outcome of a 99.9998% success rate (mistake-proof). Marc has extensive knowledge and experience in Additive Manufacturing (AM), 3D Modeling and Design, Design of Experiments (DOE), Systems and Reliability Engineering, Lean Practices and Techniques, and Process Simulations.Aside from being a Professor in Robotics and Mechatronics Engineering Department at Baltimore City Community College (BCCC), Marc is the team lead in MSU's Liquid Propellant Rocket Subtask Team, where he reviews and designs the essential rocket components such as the nose cone and all the way to the rocket's boat tail. In addition, he is also responsible for leading diverse and highly motivated engineering students in the RockOn program, where they implement and test a rocket payload that can measure and record the acceleration, humidity, pressure, temperature, and radiation counts during flight. The payload system was launched on NASA's Terrier Improved-Orion Sounding Rocket at their flight facility in Wallops, Virginia, and was successfully recovered at the Atlantic Ocean. Marc made several presentations and publications in domestic and international conferences, including MDSGC, FTC, ASEE, SISE, ICTAA, INCOSE, and INFORMS. His maxim in life is, "Never confuse movement with progress. Because you can run in places and not get anywhere."

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Turbulence Modeling Effects on Fuel Regression Rate in Hybrid Rocket Numerical Simulations

Cited by 19 publications

References 25 publications

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

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

Transient numerical investigation on thermochemical erosion of C/C nozzles in hybrid rocket motors

Engaging Multidisciplinary Minority Students in The Aerospace Program and Education at Morgan State University

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