Numerical investigations of hybrid rocket engines

Бетелин, В. Б.; Kushnirenko, A.G.; Смирнов, Н.Н.; Никитин, В. Ф.; Tyurenkova, V.V.; Стамов, Л.И.

doi:10.1016/j.actaastro.2018.01.009

Cited by 141 publications

(14 citation statements)

References 15 publications

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“…. m gas = ap n gas ρ p A p (1) where a and n are the burning rate coefficient and the pressure exponent, respectively; ρ p and A p are the density and burning area of the solid propellant, respectively; and p gas is the pressure in the gas generator. When the propellant is made, these parameters of a, n, ρ p , and A p have also been determined.…”

Section: Working Characteristics Of the Gas Generatormentioning

confidence: 99%

“…Equation (1) shows that the pressure is positively correlated with the mass flow of the fuel-rich gas. Due to this, the mass flow gradually increases during the test.…”

Section: Working Characteristics Of the Gas Generatormentioning

confidence: 99%

“…Powered hypersonic flight (Ma > 5) is currently a research hotspot in the field of aerospace, with the scramjet being an ideal propulsion equipment for this purpose [1][2][3][4]. While most of the current research is based on liquid fuels, the scramjet that employs solid fuel (SSRJ) has many advantages, including simple structure, high energy density, low cost, and safety [5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

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Direct-Connect Test of Solid Scramjet with Symmetrical Structure

Yang

Xia

et al. 2021

Energies

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The solid scramjet has become one of the most promising engine types. In this paper, we report the first direct-connect test of a solid scramjet with symmetrical structure, carried out using boron-based fuel-rich solid propellant as fuel. During the test, which simulated a flight environment at Mach 5.6 and 25 km, the performance of the solid scramjet was obtained by measuring the pressure, thrust, and mass flow. The results show that, due to the change in the combustion area of the propellant and the deposition of the throat in the gas generator during the test, the equivalence ratio gradually increased from 0.54 to 0.63. In a solid scramjet, it is possible to obtain a symmetrical distribution of the flow field within the combustor. Moreover, in a multi-cavity combustor, the combustion state expands from the cavity to the center of the flow channel. The performance of the solid scramjet increased during the test, reaching a combustion efficiency of about 42%, a total pressure recovery coefficient of 0.35, and a thrust gain specific impulse of about 418 s. The solid scramjet with symmetrical structure is feasible. The cavity configuration adopted in this paper can reduce the ignition delay time of fuel-rich gas and improve the combustion efficiency of gas-phase combustible components. The shock trains in the isolator are conducive to the recovery of the total pressure. The performance of the solid scramjet is limited by the low combustion efficiency of the particles.

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Section: Working Characteristics Of the Gas Generatormentioning

confidence: 99%

“…Equation (1) shows that the pressure is positively correlated with the mass flow of the fuel-rich gas. Due to this, the mass flow gradually increases during the test.…”

Section: Working Characteristics Of the Gas Generatormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Direct-Connect Test of Solid Scramjet with Symmetrical Structure

Yang

Xia

et al. 2021

Energies

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“…CFD modelling of polymer pyrolysis is also extensively applied in hybrid rocket engines [ 21 ]. Tyurenkova et al [ 22 , 23 , 24 , 25 ] conducted a comprehensive series of numerical studies on solid fuel pyrolysis in hybrid rocket engines and investigated the regression behaviour in different flow regimes. It has been found that turbulent transfer coefficients, such as Prandtl number play an essential role to model the gas-solid surface interactions and the regression rate.…”

Section: Introductionmentioning

confidence: 99%

An Investigation towards Coupling Molecular Dynamics with Computational Fluid Dynamics for Modelling Polymer Pyrolysis

et al. 2022

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Building polymers implemented into building panels and exterior façades have been determined as the major contributor to severe fire incidents, including the 2017 Grenfell Tower fire incident. To gain a deeper understanding of the pyrolysis process of these polymer composites, this work proposes a multi-scale modelling framework comprising of applying the kinetics parameters and detailed pyrolysis gas volatiles (parent combustion fuel and key precursor species) extracted from Molecular Dynamics models to a macro-scale Computational Fluid Dynamics fire model. The modelling framework was tested for pure and flame-retardant polyethylene systems. Based on the modelling results, the chemical distribution of the fully decomposed chemical compounds was realised for the selected polymers. Subsequently, the identified gas volatiles from solid to gas phases were applied as the parent fuel in the detailed chemical kinetics combustion model for enhanced predictions of toxic gas, charring, and smoke particulate predictions. The results demonstrate the potential application of the developed model in the simulation of different polymer materials without substantial prior knowledge of the thermal degradation properties from costly experiments.

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“…The time stepping algorithm was organized into 4 main cycles by cells and faces; the last cycle assembling all the fluxes together and creating the new state of parameters. The promotion to the 2nd order approximation in time was made repeating this algorithm once more with some modifications; the details are shown in [16] and [17].…”

Section: The Calculating Systemmentioning

confidence: 99%

3D Problems of Rotating Detonation Wave in a Ramjet Engine Modeled on a Supercomputer

Никитин

Filippov

Стамов

et al. 2018

JSFI

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A rotating detonation engine (RDE) combustion chamber was modeled in the work numerically using 3D geometry. The RDE is a new type of engines capable to create higher thrust than the traditional ones, which are based on the combustible mixture deflagration process. In the numerical experiment, different scenarios of the engine performance were obtained. The calculations were made at a compact supercomputer APK-5 with a peak performance of 5.5 Tera Flops.

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Numerical investigations of hybrid rocket engines

Cited by 141 publications

References 15 publications

Direct-Connect Test of Solid Scramjet with Symmetrical Structure

Direct-Connect Test of Solid Scramjet with Symmetrical Structure

An Investigation towards Coupling Molecular Dynamics with Computational Fluid Dynamics for Modelling Polymer Pyrolysis

3D Problems of Rotating Detonation Wave in a Ramjet Engine Modeled on a Supercomputer

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