Numerical investigation of the local and global supersonic combustion characteristics of ethylene fuel

Kannaiyan, Kumaran

doi:10.1016/j.ast.2020.106178

Cited by 13 publications

(3 citation statements)

References 30 publications

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“…Kannaiyan [22] conducted a study on the combustion of ethylene fuel under singlestep and multi-step reactions based on the heat release rate parameters at different locations in the combustion chamber. He et al [23] conducted experimental and numerical studies on the flame stability characteristics of ethylene fuel in a scramjet concave cavity combustor.…”

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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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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“…[14] experimentally and numerically studied the flame propagation and deflagration to detonation transition process of an ethylene/air mixture at an equivalent concentration in a curved pipe. Kannaiyan [15] performed numerical simulations on the local and global supersonic combustion characteristics of ethylene. Zhao et al.…”

Section: Introductionmentioning

confidence: 99%

“…Pan et al [14] experimentally and numerically studied the flame propagation and deflagration to detonation transition process of an ethylene/air mixture at an equivalent concentration in a curved pipe. Kannaiyan [15] performed numerical simulations on the local and global supersonic combustion characteristics of ethylene. Zhao et al [16] examined the deflagration-to-detonation (DDT) process of a H 2 /O 2 /N 2 mixture under different initial thermodynamic conditions at different oxygen concentrations.…”

Section: Introductionmentioning

confidence: 99%

Energy Output of High‐speed Flowing Two‐phase IPN/Air in the Combustion Chamber

Wan

Wen

Zhang

2022

Propellants Explo Pyrotec

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Fuel-air cloud explosions or detonations are often affected by initial ambient conditions. A two-dimensional (2D) semi-confined model was established to study the effects of the inflowing air temperature and initial temperature of the combustor on the explosion process of isopropyl nitrate (IPN)/air mixture. The results showed that at different initial temperatures (1000-3000 K), the first peak pressure (P 1 ) and second peak pressure (P 2 ) decreased with the increase in initial temperature; the maximum flame temperature (2338-3534 K) increased with the increasing initial temperature; the explosion pressure and temperature had the opposite trends with the initial temperature, indicating that the oxygen content in the combustor had a greater impact on the explosion pressure, while the initial temperature had a more significant effect on the flame temperature. Under different incoming air temperatures (1000-3000 K), the flame temperature (~2700 K) of the two-phase explosion had a small difference at the incoming temperature of � 2500 K, signifying that the airflow temperature (< 3000 K) and the oxygen content in air jointly dominated the flame temperature; the flame temperature was 3100 K at the incoming temperature of 3000 K, which was about 300 K higher than other incoming flow temperatures, indicating that the flame temperature was more sensitive to the incoming air temperature (� 3000 K). At 600 m/s airflow, the explosion parameter curves at the inflow temperatures of 300 K and 600 K were compared, and the critical inflow temperature of the explosion process was also investigated.

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Development of a fast-stabilized fuel injection system using a solenoid actuator

Jeong,

Kim,

Jang

et al. 2023

J Mech Sci Technol

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Numerical investigation of the local and global supersonic combustion characteristics of ethylene fuel

Cited by 13 publications

References 30 publications

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

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

Energy Output of High‐speed Flowing Two‐phase IPN/Air in the Combustion Chamber

Development of a fast-stabilized fuel injection system using a solenoid actuator

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