Numerical and experimental investigation on hybrid rocket motor with two-hole segmented rotation grain

Tian, Hui; He, Lingfei; Zhu, Hao; Wang, Pengfei; Xu, Xu

doi:10.1016/j.ast.2019.07.006

Cited by 24 publications

(5 citation statements)

References 16 publications

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“…Because combustion in hybrid engines is predominantly influenced by the physical mass transfer process, designing flow field structures with intricate geometries can effectively enhance the regression rate by prolonging the residual time and improving the heat exchange process. − A variety of physical methods have been proposed to improve the regression rate, including the turbulence-induced grain configurations, multisection fuels, multistage injection of oxidizers, and swirl injection. − Tian et al conducted research on three-dimensional (3D) steady numerical simulation models for grains with complex geometries, , two-hole segmented grains, and star-segmented rotation grains . Their investigation involved studying the distribution of the regression rate through convective heat transfer calculations.…”

Section: Introductionmentioning

confidence: 99%

“…20−22 A variety of physical methods have been proposed to improve the regression rate, including the turbulence-induced grain configurations, multisection fuels, multistage injection of oxidizers, and swirl injection. 23−25 Tian et al conducted research on three-dimensional (3D) steady numerical simulation models for grains with complex geometries, 26,27 two-hole segmented grains, 28 and star-segmented rotation grains. 29 Their investigation involved studying the distribution of the regression rate through convective heat transfer calculations.…”

Section: ■ Introductionmentioning

confidence: 99%

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Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Chen,

Fu,

Yang

et al. 2024

Langmuir

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Despite hybrid rocket motors offering distinct advantages over solid or liquid rocket motors, their low regression rate and insufficient combustion efficiency remain significantly unimproved. This study focuses on the effects of the helix lead on the regression rate distribution and combustion efficiency of vat-polymerized fuel grains with a spiral star port for a hybrid rocket. Both experimental and numerical investigations were conducted to study the combustion characteristics and regression rate distribution of three-dimensional (3D) print grains. Spiral star grains with varying helix leads of 60, 90, and 120 mm were fabricated using light-curing 3D printing technology. A 3D simulation model was developed to obtain the temperature distribution, species mass distribution, and combustion efficiency. Furthermore, firing tests were performed on a two-dimensional radial hybrid combustion test stand to measure the regression rate. Digital image processing of computed tomography images was used to determine the regression rate. Simulation results indicated that the spiral star grain port helps to improve the combustion efficiency compared with those seen with round tube and straight star port grains. With an increase in the axial distance, the flame zone gradually shrinks, and the smaller the helix lead, the faster the shrinkage. At a mass flow rate of 1.50 g/s for oxygen, the regression rate of the spiral star grains is significantly higher than that of the straight star grain and the conventional round tubular grains, and the regression rate gradually increases with a decrease in the helix lead. This finding is expected to solve the problem of the low regression rate of solid fuels with spiral star pore-shaped grains prepared by the light-curing 3D printing method.

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Section: Introductionmentioning

confidence: 99%

Section: ■ Introductionmentioning

confidence: 99%

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Chen,

Fu,

Yang

et al. 2024

Langmuir

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“…Recent studies on solid fuel ramjet engines showed that increasing the mass flow rate, swirl number, and temperature of the inlet oxidizer gas can improve the heat and mass transfer between the burning surface of the solid fuel and the gas phase region [20,21]. Oxidizer inlet conditions also significantly affect the motorʹs regression rate and heat release characteristics [22][23][24]. Numerical simulation of hydrogen-fueled scramjet showed that the combustion chamber cavity caused a high-pressure gradient and significant horizontal flow and strengthened mixing between air and hydrogen, resulting in a higher combustion heat release rate [25].…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Mixing Effect on Coupled Heat Release and Transfer Performance of a Novel Segregated Solid Rocket Motor

Liu,

Zhang,

Wang

et al. 2024

Aerospace

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The effect of mixing on coupled heat release and transfer performance of a novel segregated solid motor is numerically evaluated with a transient two-dimensional combustion model. The results show that vortex structures are formed and evolved in the combustion chamber. Quantitative calculation of the mixing effect shows the inhomogeneous distribution of oxidant and fuel species. The well-mixing area is located in a narrow belt-like coupled combustion region near the burning surface of the propellant. Heat transfer coefficient decreases greatly due to lower combustion reaction rate and enlarged flow channel area. Heat transfer coefficients near the two ends of the propellant grain are higher than other parts due to the influence of vortex mixing. Raising the inlet mass flow rate leads to enhanced mixing and heat transfer, which results in a lower temperature and regression rate of the propellant with combustion time. Temperature and oxidation rates of H2 and CO are unevenly distributed in the boundary layer of coupled combustion. Increasing the mass flux of inlet oxidizer gas leads to a higher combustion heat release rate. Therefore, the gas-phase temperature increases significantly. The heat release rate reaches the maximum near the ends of the propellant grain, where vortex mixing strengthens the coupled combustion process in the motor.

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“…In order to achieve a higher regression rate with common fuel block manufacturing, multiple grains with different geometries or geometrical orientations can be stacked. Examples are stepped fuel blocks [2] or multiport geometries, which are rotated against each other [3][4][5]. The disadvantage of such methods is the inconsistent regression rate over the fuel block length due to higher regression rates only occurring in vortex areas [2,4,5].…”

Section: Introductionmentioning

confidence: 99%

“…Examples are stepped fuel blocks [2] or multiport geometries, which are rotated against each other [3][4][5]. The disadvantage of such methods is the inconsistent regression rate over the fuel block length due to higher regression rates only occurring in vortex areas [2,4,5]. Common ways to create a geometry of the fuel grain are limited to a constant shape over the fuel block length due to manufacturing effort.…”

Section: Introductionmentioning

confidence: 99%

Design, Production and Evaluation of 3D-Printed Mold Geometries for a Hybrid Rocket Engine

et al. 2021

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The feasibility of 3D-printed molds for complex solid fuel block geometries of hybrid rocket engines is investigated. Additively produced molds offer more degrees of freedom in designing an optimized but easy to manufacture mold. The solid fuel used for this demonstration was hydroxyl-terminated polybutadiene (HTPB). Polyvinyl alcohol (PVA) was chosen as the mold material due to its good dissolving characteristics. It is shown that conventional and complex geometries can be produced reliably with the presented methods. In addition to the manufacturing process, this article presents several engine tests with different fuel grain geometries, including a short overview of the test bed, the engine and first tests.

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Numerical and experimental investigation on hybrid rocket motor with two-hole segmented rotation grain

Cited by 24 publications

References 16 publications

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Evaluation of Mixing Effect on Coupled Heat Release and Transfer Performance of a Novel Segregated Solid Rocket Motor

Design, Production and Evaluation of 3D-Printed Mold Geometries for a Hybrid Rocket Engine

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