Regression rate and combustion performance investigation on hybrid rocket motor with head-end swirl injection under high geometric swirl number

Cai, Guobiao; Zhao, Zeng; Zhao, Bo; Liu, Yu-Fei; Yu, Nanjia

doi:10.1016/j.ast.2020.105922

Cited by 31 publications

(8 citation statements)

References 19 publications

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“…It is determined by the ratio of the axial flux of the tangential momentum (G angular ) to the axial momentum flux (G linear ) of fluid and can be used for all kinds of swirl flows. [32,33] The equation of the SN is formulated as follows [34,35] : Here, u a and u θ denote the fluid's axial and tangential velocity ingredients, respectively. R represents the inner radius of the annular pipe.…”

Section: Impact Of Swirler Geometric Parametersmentioning

confidence: 99%

Insights into the hydrodynamics in the annular pipe of industrial‐scale top‐blown smelting furnace

Wan,

Yang,

Tang

et al. 2024

Can J Chem Eng

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The coaxial jet consisting of swirl jet and axial jet plays a critical role in the industrial processes but is rarely investigated; therefore, it is numerically explored by means of the computational fluid dynamics (CFD) approach in the present work. The force on the swirler, axial and tangential velocity at the annular pipe outlet, and the spatial distribution of swirl number (SN) are selected to evaluate the effect of geometrical parameters on the swirling performance. The results clarify that the velocity and their azimuthal components in the transverse cross‐section can be categorized into six segments based on high/low velocity values. The coaxial jets form a weak swirl with high axial, certain tangential, and low radial velocities. x‐ and y‐vorticity vary within −200 to 200 s−1. Coaxial jet mixing decays the SN. Based on the multi‐objective matrix analysis, swirler height has the largest effect on swirl performance followed by diameter, angle, and number based on analysis. Optimal parameters are 130° vane angle, 240 mm diameter, 10 vanes, and 250 mm height of the swirler.

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Section: Impact Of Swirler Geometric Parametersmentioning

confidence: 99%

Insights into the hydrodynamics in the annular pipe of industrial‐scale top‐blown smelting furnace

Wan,

Yang,

Tang

et al. 2024

Can J Chem Eng

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“…𝜌 𝑓𝑢𝑒𝑙 ℎ 𝑣 (10) where 𝑞ẇ 𝑎𝑙𝑙 , 𝜌 𝑓𝑢𝑒𝑙 , and ℎ 𝑣 represent wall heat flux, the density of fuel grain, and decomposition heat of fuel respectively. The physical properties of the paraffin wax are shown in Table 1 [28].…”

Section: 𝑟̇= 𝑞̇𝑤 𝑎𝑙𝑙mentioning

confidence: 99%

“…This type of rocket propulsion is attractive and provides many advantages over conventional liquid or solid rocket propulsion systems due to their low-cost, fuel handling simplicity, durability, throttling capability, and eco-friendly attributes [2][3][4][5][6][7][8]. It is easy to throttle the hybrid rocket engines by adjusting the oxidizer mass flow rate, which serves as ideal candidates for adjustable thrust rocket and is appropriate for all applications where rockets are used [9][10][11][12]. This is due to the versatility of the propellant, the wide range of performance, and the flexibility of the thrust [13].…”

Section: Introductionmentioning

confidence: 99%

Modelling of Hybrid Rocket Flow-Fields with Computational Fluid Dynamics

Ismail

Rozainuddin

Nordin

et al. 2022

CFDL

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A low regression rate is a major limitation in the hybrid rocket propulsion system. This paper is to study the regression rate characteristics of a cylindrical solid grain with cryogenic propellants. Paraffin (P) fuel is coupled with two types of oxidizers, namely gaseous oxygen (GOX) and nitrous oxide (N2O). ANSYS software is used as the CFD platform to observe the hybrid rocket flow-fields. The modelling values obtained from the pressure, temperature, velocity, and wall heat flux contours are used to calculate the hybrid rocket performance in terms of regression rate, thrust, specific impulse, characteristic velocity, and exit Mach number. The numerical results show that the mass-flow-inlet boundary conditions, initial design feature, and type of propellant play an important role in the enhancement of hybrid rocket performance. Result shows that enhanced of 68 % of the regression rate, 59 % of thrust, 6 % of specific impulse and exit Mach number, and % of characteristic velocity by improved 50% of mass flow rate. Due to the high flame temperature, the GOX/P propellants produce the best hybrid rocket motor compared with the others.

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“…Due to its unique structure of liquid oxidizer and solid fuel, hybrid rocket motors show great superiorities compared to traditional solid or liquid propulsion systems, including multiple restart capability, thrust throttling, high reliability, and safety [1] . However, the diffusive nature of turbulent flames due to its unique structure leads to low regression rate and combustion efficiency, which have hindered hybrid rocket motors for many practical applications.…”

Section: Introductionmentioning

confidence: 99%

“…It should be in a one-column format. References are often noted in the text 1 and cited at the end of the paper.…”

Section: Introductionmentioning

confidence: 99%

Mid‑infrared laser absorption tomography for in‑situ quantitative thermochemistry measurements of hybrid rocket motors

Fang

Lin

De-sheng

et al. 2022

Sixth International Symposium on Laser Interaction With Matter

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Further development of hybrid propulsion systems requires a deeper understanding of the complex physicochemical mechanisms governing its combustion performance. A tunable diode laser absorption tomography (TDLAT) method was developed for investigating the thermochemical processes at the nozzle exit of an oxygen/Poly Methyl MethAcrylate (PMMA) hybrid rocket motor. Firing tests were conducted for different oxidizer mass fluxes ranging from 2.73 to 3.51 g/ (cm2·s). A distributed feedback (DFB) laser was tuned to cover three H2O absorption lines near 2.5 μm, using scanned-wavelength direct absorption (DA) mode with 2.0 kHz repetition rate. Under an assumption of cylindrical symmetry, a Radon transformation was applied to yield radially- and time- resolved absorption coefficient, from which the radial distribution of temperature and H2O partial pressure were reconstructed. Based on the Taylor series method (TSM), measurement uncertainty was analyzed in detail considering line-strength uncertainty, Voigt fitting residuals and Radon transformation. Finally, the radial distribution and dynamic variations of both temperature and H2O partial pressure were obtained in all firing tests, both the constructed results show measurement sensitivity to chemical kinetic progress and oxidizer mass flux changes. Our experimental results highlight the capability of TDLAT to characterize combustion processes of hybrid rocket motors.

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Regression rate and combustion performance investigation on hybrid rocket motor with head-end swirl injection under high geometric swirl number

Cited by 31 publications

References 19 publications

Insights into the hydrodynamics in the annular pipe of industrial‐scale top‐blown smelting furnace

Insights into the hydrodynamics in the annular pipe of industrial‐scale top‐blown smelting furnace

Modelling of Hybrid Rocket Flow-Fields with Computational Fluid Dynamics

Mid‑infrared laser absorption tomography for in‑situ quantitative thermochemistry measurements of hybrid rocket motors

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