Computational simulation of multi-strut central lobed injection of hydrogen in a scramjet combustor

Choubey, Gautam; Pandey, Krishna Murari; Sharma, Deepak; Debbarma, Ajoy

doi:10.1016/j.pisc.2016.04.032

Cited by 49 publications

(5 citation statements)

References 5 publications

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“…Lakka et al compared the performance of cavity and noncavity strut-stabilized combustion and found that cavity-based strut burners had better mix efficiency. Choubey et al , conducted computational and simulation studies on multistrut combustors with a Mach number of 2.5. The research found that multistrut fuel injectors improved the turbulent fuel mixing process and improved the performance of combustors.…”

Section: Introductionmentioning

confidence: 99%

Effect of Kerosene Dual-Jet Spacing on the Mixing and Combustion Characteristics of a Scramjet Combustor

Peng,

Zhou,

et al. 2024

ACS Omega

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As the core of a hypersonic propulsion system, the effective mixing efficiency of fuel and air in a supersonic combustor is crucial for its performance. This study focuses on a cold supersonic flow and employs computational fluid dynamics (CFD) techniques combined with Euler−Lagrange method's discretephase model (DPM) for multiphase flows, K−H and R−T (Kelvin−Helmholtz and Rayleigh−Taylor) mixing and atomization models, turbulence models, and surface evaporation models to investigate the injection, atomization, and mixing characteristics of kerosene in supersonic airflow. In order to enhance the mixing efficiency between kerosene and air while reducing flow losses, this study examines a staggered dual-jet injection scheme, with the dual jets arranged at the center of the cavity and having a dual-jet spacing of 10 and 20 mm, respectively. Starting from the interaction mechanism between jets, the impact of different staggered dualjet spacings on the kerosene jet penetration height, span expansion area, angle of the shock wave, and Sauter mean diameter distribution was analyzed. The results show that a short dual-jet spacing (10 mm) leads to greater penetration height, wider span expansion, and a larger angle of the shock wave. When the dual-jet spacing is shorter, the interaction between the fuel jet and the cavity shear layer is stronger, resulting in an improved fuel mixing efficiency. The achievements of this study are consistent with previous experimental measurements and the literature, demonstrating a strong theoretical foundation for optimizing the design of hypersonic engines by deepening the understanding of the fundamental atomization mechanisms of kerosene jets in cold-state supersonic flows. Moreover, these results hold practical significance in improving the efficiency of kerosene combustion and enhancing the performance of flame stabilization devices.

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Section: Introductionmentioning

confidence: 99%

Effect of Kerosene Dual-Jet Spacing on the Mixing and Combustion Characteristics of a Scramjet Combustor

Peng,

Zhou,

et al. 2024

ACS Omega

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“…In order to achieve hypersonic flight, currently, the United States, Russia, France, the United Kingdom, Japan, and other countries have, respectively, proposed hypersonic propulsion technical solutions, and studied combined power engines based on scramjet (supersonic combustion ramjet). Among them, it is of great significance to break through and master the key technology of the scramjet engine, which is the necessary prerequisite for realizing hypersonic flight [5][6][7][8][9][10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Flame Stabilization of Cavity-Based Scramjet Combustor Using Compressible Modified FGM Model

Zhang

Zhu

Yang

et al. 2022

International Journal of Chemical Engineering

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The technology of flame stabilization on cavity-based scramjet combustor has great significance in the field of future spacecraft. In this paper, a compressible modified FGM model was established based on the idea of the flamelet model, which was adopted to simulate the unsteady combustion process of the hydrogen transverse jet in the upper cavity of the scramjet. The results show that the compressible modified FGM model can accurately reflect the flow field and the propagation process of the flame in the supersonic cavity, and can capture the fine shock structure in the flow field. The coupling effect of shock waves and shear layer cause the shear layer to quickly destabilize, resulting in the turbulence effect, which promotes the mixing of air and fuel. The boundary layer separation at the upper wall of the combustion chamber will reduce the stability of the shear layer.

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“…[13][14][15][16] Meanwhile, several books and papers have been published in this field of study. [17][18][19][20][21][22] The film injection, cavity technique, and porthole injections are the most conventional approaches for the fuel injection system. Some of the scholars concentrated on the application of the strut as a shock producer or free stream deflector for mixing augmentation of the fuel jets.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, computational fluid dynamics as a virtual laboratory is extensively used for research in this field. [35][36][37][38][39][40] The key advantage of the computational approach is low cost and informative results about details of flow feature. [41][42][43][44][45] Thus, several codes and software are developed for the simulation of compressible flow inside the scramjet engine.…”

Section: Introductionmentioning

confidence: 99%

“…To investigate the scramjet engine, numerous techniques and models have been proposed and studied by scientists 13‐16 . Meanwhile, several books and papers have been published in this field of study 17‐22 . The film injection, cavity technique, and porthole injections are the most conventional approaches for the fuel injection system.…”

Section: Introductionmentioning

confidence: 99%

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Computational investigation of multi hydrogen jets at inclined supersonic flow

2020

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Summary Scramjet design is directly associated with the fuel mixing inside the combustor. In this study, the influences of the free stream angle on the fuel mixing zone of eight microjets are fully investigated. This study mainly tries to disclose the importance of the fuel jet interaction with a supersonic free stream on penetration and distribution of hydrogen jets. The effects of jet paces and different free stream angles are fully examined in this work. For the computational study, CFD numerical method is applied to obtain the fuel jet structure at supersonic cross‐flow. RANS equations with SST turbulence scheme is employed for the simulation of our model. Our simulations show that a positive angle of supersonic incoming flow is effective for the uniform expansion of the fuel mixing zone inside the combustor. According to our findings, increasing the angles of the free stream declines the mixing zone when the fuel jet interaction of the last jets with main stream decreases. Our results indicate that mixing efficiency of ‐20° is about 30% more than other angles.

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Computational simulation of multi-strut central lobed injection of hydrogen in a scramjet combustor

Cited by 49 publications

References 5 publications

Effect of Kerosene Dual-Jet Spacing on the Mixing and Combustion Characteristics of a Scramjet Combustor

Effect of Kerosene Dual-Jet Spacing on the Mixing and Combustion Characteristics of a Scramjet Combustor

Numerical Investigation on Flame Stabilization of Cavity-Based Scramjet Combustor Using Compressible Modified FGM Model

Computational investigation of multi hydrogen jets at inclined supersonic flow

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