Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Xu, Jiabao; Jin, Pengfei; Li, Ruizhi; Wang, Jue; Cai, Guobiao

doi:10.1155/2021/6670813

Cited by 4 publications

(1 citation statement)

References 40 publications

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“…Liquid rocket engine has been widely used in space propulsion system because of its advantages of high thrust, high reliability, and low cost [1]. As the key subassembly of a rocket engine, the thrust chamber provides thrust by accelerating the hot gas to supersonic velocity across the throat.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer Analysis and Structural Optimization for Spiral Channel Regenerative Cooling Thrust Chamber

Ping

et al. 2023

International Journal of Aerospace Engineering

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There is currently a lack of efficient heat transfer analysis methodologies for spiral channel regenerative cooling that has been increasingly applied in liquid rocket engines. To figure out the heat transfer characteristics of the spiral channel regenerative cooling thrust chamber, a simple 1D method based on the traditional semi-empirical formula after correcting the flow velocity is proposed. The accuracy of this approach is verified by the 3D numerical simulation. The verified method is further used to analyze the distribution of inner wall temperature in the test case and optimize the channel’s parameters. The research shows that the maximum inner wall temperature cooled by the spiral channel is 8.5% lower than that of the straight channel under the same channel size and boundary condition, indicating that the application of the spiral channel significantly improves the cooling effect. In addition, the 1D model combined with the second-order response surface model is employed to optimize the channel width, channel height, pitch, and inner wall thickness aiming for the best cooling effect. The calculated maximum temperature of the inner wall after the structure optimization is 586.6 K, which is 29.8% lower than the initial structure before optimization.

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Section: Introductionmentioning

confidence: 99%

Heat Transfer Analysis and Structural Optimization for Spiral Channel Regenerative Cooling Thrust Chamber

Ping

et al. 2023

International Journal of Aerospace Engineering

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Numerical investigation on atomization characteristics of sustainable aviation biofuel

Liu,

Ding,

Xiong

et al. 2023

AIP Advances

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It is critical to investigate the atomization features of sustainable aviation biofuel (SAF) to reduce carbon emissions. Fluent software was used to quantitatively simulate the atomization of the fuel. The control variable method was utilized to compare SAF to Chinese aviation fuel RP-3. The volume of fluid model (VOF) and the discrete phase model (DPM) were used to explore the variation law of SAF atomization characteristics in a two-way centrifugal nozzle with a pressure drop of 2–8 MPa and various nozzle configurations. The experimental results suggest that the model is effective. The results demonstrate that when pressure increases, the average diameter of SAF’s Sauter mean diameter reduces from 80 to 23 µm and the spray penetration distance increases from 0.32 to 0.6 m, allowing for more stable fuel combustion. Meanwhile, as the nozzle outlet aspect ratio increases, such as increasing the nozzle diameter from 2.0 to 2.6 mm, the atomization cone angle varies from 60° to 110° and gradually declines, although the average diameter of Sauter only varies minimally within a limited range of 30–40 µm. All of these findings indicate that SAF has good atomization properties and the potential to be used as an aviation fuel.

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Interferometric laser imaging for droplet-size measurement in spray

2022

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An upgraded droplet-size measurement method, based on laser interference particle imaging (IPI) technology, is applied to accomplish high-precision measurement of particle size and spatial distribution of gas–liquid two-phase flow in the atomization field. In this study, an improved morphological-Hough transform interference fringe location algorithm is applied to IPI measurement. The particle size of the standard particle field with a diameter of 24 µm is measured by the upgraded IPI measurement experimentally, whose absolute error and relative error are 0.14 µm and 0.58%, respectively. The atomization field of the 400 µm centrifugal nozzle under different pressures is demonstrated by direct imaging and IPI technology, where the assessment results are evaluated by SMD value and particle size distribution, and the results exhibit good agreement.

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Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Cited by 4 publications

References 40 publications

Heat Transfer Analysis and Structural Optimization for Spiral Channel Regenerative Cooling Thrust Chamber

Heat Transfer Analysis and Structural Optimization for Spiral Channel Regenerative Cooling Thrust Chamber

Numerical investigation on atomization characteristics of sustainable aviation biofuel

Interferometric laser imaging for droplet-size measurement in spray

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