Experimental and numerical investigation of hydrogen and ethylene combustion in a Mach 3-5 channel with a single injector

Ortwerth, P. J.; Mathur, A.; Vinogradov, Viacheslav A.; Grin, V. T.; Goldfeld, M. A.; Starov, A. V.

doi:10.2514/6.1996-3245

Cited by 36 publications

(7 citation statements)

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“…That said, even the high reactivity of ethylene cannot match that of pure hydrogen fuel. Therefore, a flame holding geometry like a cavity flameholder is often needed in scramjet combustors to increase the fuel-residence time, − allowing the buildup of a radical pool and enabling ignition of the fuel.…”

Section: Introductionmentioning

confidence: 99%

Small Skeletal Kinetic Reaction Mechanism for Ethylene–Air Combustion

2017

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Ethylene is a fuel considered for high-speed ram- and scramjet combustion applications, mainly because of the short ignition delay time resulting from its high reactivity. Further research and development on these combustion systems would benefit from simulations of large eddy (LES) type, which allow some chemical detail to accurately predict combustion characteristics and pollutant formation. In the present work, a chemical kinetic mechanism suitable for LES is presented, consisting of 66 irreversible reactions between 23 species. The mechanism is extensively validated for combustion characteristics related to ignition and flame propagation over a wide range of pressure, temperature, and equivalence ratios that previously published mechanism of this size have not covered. Agreement with a detailed reference mechanism is good for ignition delay, flame temperature, and laminar burning velocities. In addition, overall concentration profiles of major stable products are in overall good agreement with a reference mechanism. The skeletal mechanism shows an overall good performance in combination with a numerical stability and short computation time, making it highly suitable for combustion LES.

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Section: Introductionmentioning

confidence: 99%

Small Skeletal Kinetic Reaction Mechanism for Ethylene–Air Combustion

2017

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“…Although their non-intrusive nature translates into reduced drag, total pressure losses, and aerodynamic heating when compared with other flameholder designs, it also leads to a limited influence of the piloting zone on the core flow and large local wall heat fluxes. Nonetheless, their effectiveness in enabling sustained combustion and improving supersonic combustor performance has been demonstrated in both ground and flight test experiments [51,61,49,28,32,40].…”

Section: Introductionmentioning

confidence: 97%

Cavity-based flameholding for chemically-reacting supersonic flows

Barnes

Segal

2015

Progress in Aerospace Sciences

166

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“…The Central Institute of Aviation Motors (CIAM) was the first to use a cavity structure to test a dual-mode hydrogen-fueled scramjet engine jointly developed by Russia and France [2]. Subsequently, many scholars have confirmed the significant role of the cavity structure in stabilizing the flame in the scramjet combustion chamber based on extensive experiments [3][4][5]. Currently, the cavity flame-holding structure has become one of the most common flame stabilization structures in scramjet combustion chambers.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Combustion Mechanism with Multi-Position Injection in a Dual-Mode Combustor

Dong³

et al. 2023

Aerospace

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To improve the flame propagation, combustion stability, and uniformity of the temperature field, multi-position injection is applied in a dual-mode combustor by controlling heat release in different locations. Using the chemical reaction of the finite rate combustion model and the detailed reaction mechanism of hydrogen combustion as described by Jachimowski, the influence of different multi-position injection patterns in a dual-mode combustor is analyzed. The one-equation Large Eddy Simulation (LES) turbulence model was chosen to define the sublattice turbulent viscous terms in a three-dimensional scramjet model. Based on a combustion chamber, the effect of the injection equivalent ratio (0.35–0.70), the relative position of the nozzle holes, and the injection pressure on the combustion process and flow field characteristics are analyzed with multi-position injection. The combustion efficiency, total pressure recovery coefficients, and pressure distribution under different operation conditions are compared. We observed that the combustion intensity increases and the upstream combustion shock string distance becomes greater with increased equivalent ratios. When the global equivalent ratio of multi-position injection remains unchanged, the arrangement of nozzles with the small injection spacing, i.e., two injection holes arranged face to face on the upper and lower walls, or the setting of multiple injection holes with the same pressure, can effectively increase the stability rate of the combustion flow field. In addition, the combustion efficiency at the outlet and the internal pressure of the combustion chamber in the stable state are also improved, relative to the increased total pressure loss.

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Experimental and numerical investigation of hydrogen and ethylene combustion in a Mach 3-5 channel with a single injector

Cited by 36 publications

References 0 publications

Small Skeletal Kinetic Reaction Mechanism for Ethylene–Air Combustion

Small Skeletal Kinetic Reaction Mechanism for Ethylene–Air Combustion

Cavity-based flameholding for chemically-reacting supersonic flows

Numerical Investigation of Combustion Mechanism with Multi-Position Injection in a Dual-Mode Combustor

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