Nonlinear characteristics and detection of combustion modes for a hydrocarbon fueled scramjet

Zhang, Cong; Yang, Qingchun; Chang, Juntao; Tang, Jingfeng; Bao, Wen

doi:10.1016/j.actaastro.2014.11.023

Cited by 32 publications

(4 citation statements)

References 12 publications

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“…With the results discussed in Section 3.1, it is clear that nonuniformity of the radial fuel temperature led to the nonuniformity of the parameters such as the effective thermal From Equation (6), with the constant turbulent Prandtl number, the turbulent thermal conductivity increased with the increase in the constant-pressure specific heat capacity and turbulent viscosity. As seen in Figure 6a, before Z = 400 mm, the trend of the effective thermal conductivity was consistent with that of the turbulent viscosity.…”

Section: Comparison Of the Overall Heat Transfer Coefficient With/wit...mentioning

confidence: 91%

“…Regenerative cooling technology is one of the key technologies for the thermal protection of a hypersonic propulsion system. Fuel used as a propellant is also adopted as a coolant to cool the engine walls before combustion, which helps avoid the quantity penalty caused by carrying extra coolant [5,6]. Compared with liquid hydrogen, liquid hydrocarbon fuel is widely used as a coolant for a scramjet (Ma < 8) because of its simple storage and production.…”

Section: Introductionmentioning

confidence: 99%

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Overall Heat Transfer Coefficient Evaluation Method for Uncracked Hydrocarbon Fuel in a Regeneratively-Cooled Heat Exchanger of a Scramjet

Lin

et al. 2022

Applied Sciences

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Regenerative cooling is critical for the thermal protection of hypersonic propulsion systems, wherein the flow and heat transfer characteristics of the hydrocarbon fuel in the cooling channel are crucial. Restricted by measurement, the distribution of the fuel temperature inside the cooling channel cannot be directly detected. As a result, the measurement of the convective heat transfer coefficient is more an overall heat transfer coefficient. Furthermore, the existing overall heat transfer coefficient calculation method is derived without considering the flow state of the hydrocarbon fuel in the cooling channel, which should be taken into consideration. Therefore, a modified calculation method of the overall heat transfer coefficient is proposed in this study. The results of the characteristics of the turbulence-related parameters show that the overall heat transfer coefficient is mainly determined by the effective thermal conductivity and surface convective heat transfer coefficient, which are related to the fuel temperature and flow state. Furthermore, the existing method might overestimate the overall heat transfer coefficient. The modified method is suitable for the calculation of the overall heat transfer coefficient in the heat transfer enhancement process in a cooling channel.

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Section: Comparison Of the Overall Heat Transfer Coefficient With/wit...mentioning

confidence: 91%

Section: Introductionmentioning

confidence: 99%

Overall Heat Transfer Coefficient Evaluation Method for Uncracked Hydrocarbon Fuel in a Regeneratively-Cooled Heat Exchanger of a Scramjet

Lin

et al. 2022

Applied Sciences

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“…Another challenge is the proper selection of injection fuel. Hydrocarbon fuels such as hydrogen, kerosene, methane, ethylene, etc., have immense potential in the future of Scramjet technology [21][22][23]. Among the stated hydrocarbon fuels, hydrogen fuel is the most favorable fuel for supersonic condition combustion due to certain characteristics such as high energy density and eco-friendly [13,24,25].…”

Section: Challenges In the Design Of Scramjet Enginesmentioning

confidence: 99%

Numerical Investigation on the Effect of Inflow Mach Numbers on the Combustion Characteristics of a Typical Cavity-Based Supersonic Combustor

Bordoloi

Pandey

Sharma

2021

Mathematical Problems in Engineering

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The air-breathing engines, commonly known as Supersonic Combustor Ramjet (SCRAMJET) engines, are one of the most prominent technologies among researchers due to their high thrust-to-weight ratio. The researchers are constantly making efforts for improved performance of the combustor under the required boundary conditions. The present working computational model studies a hydrogen-fueled parallel cavity scramjet combustor to recognize the complex flow field characteristics and performance of the combustor in Ansys 15.0. The computational model developed is a replica of an experiment conducted in China which slightly modified the boundary conditions. The standard two-equation K- ε turbulence model and Reynolds averaged Navier Stokes (RANS) equation with finite-rate/eddy dissipation species reaction model are used to simulate the problem. The validation of the present model is achieved by comparing the results with already available experimental data in conformity with the literature. The results of the simulations are in satisfactory accord with the experimental data and images. Furthermore, to achieve the stated objective, different incoming Mach numbers, namely, 2.25, 2.52, and 2.75, are considered for a more clear understanding of variables that affects the characteristics of the flow field. The temperature, Mach number, density pressure, and H2O mass fraction contours were studied to facilitate proper understanding. The maximum temperature rise observed is 2711.467 K for M = 2.25. Additionally, the performance parameters, namely, combustion and mixing efficiencies, are also studied. The maximum combustion and mixing efficiencies are 87.47% and 98.15% for M = 2.25 and 2.75, respectively.

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“…Dual-mode combustor, as one of the most important component for the engineering implementation of the combined cycle engine of space mission vehicles [1], has attracted a great deal of attention, and a number of studies have investigated the combustion mode transition under the supersonic state using different flameholding devices since the adequate mixing and combustion between the fuel and air must take place at a time scale of the order of milliseconds [2] [3], such as the strut [4] [5] the backward-facing step [6] [7], aeroramp [8], wall mounted cavity [9], and the combinational strategies [10] [11] [12]. Zhang et al [13] investigated the nonlinear characteristics in the combustion mode transition and proposed a pressure-magnitude-based approach to detect the combustion modes experimentally.…”

Section: Introductionmentioning

confidence: 99%

Numerical exploration of mixing and combustion in a dual-mode combustor with backward-facing steps

Huang

Yan

et al. 2016

Acta Astronautica

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Dual-mode scramjet combustor is the crucial component for the combined cycle engine of space mission vehicles. The Reynolds Averaged Navier-Stokes (RANS) equations, Spalart-Allmaras turbulence model and the finite-rate reaction model have been utilized to investigate the mixing and combustion in a dual-mode combustor with backward-facing steps, and the species distributions and the Mach number profile of a turbulent diffusion combustion problem have been employed to validate the numerical approach. Moreover, the influences of the injection strategy and the fuel equivalence ratio arrangement on its mixing and combustion flow fields have been explored. The obtained results show that the vertical injection is beneficial for mode transition, and an obvious high pressure region is generated with the vertical injection strategy. Accordingly, its mass-weighted average Mach number drops more sharply. The lower total equivalence ratio is beneficial for the mixing augmentation, as well the smaller fuel equivalence ratio discrepancy. However, the larger total equivalence ratio is beneficial for the mode transition.

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Nonlinear characteristics and detection of combustion modes for a hydrocarbon fueled scramjet

Cited by 32 publications

References 12 publications

Overall Heat Transfer Coefficient Evaluation Method for Uncracked Hydrocarbon Fuel in a Regeneratively-Cooled Heat Exchanger of a Scramjet

Overall Heat Transfer Coefficient Evaluation Method for Uncracked Hydrocarbon Fuel in a Regeneratively-Cooled Heat Exchanger of a Scramjet

Numerical Investigation on the Effect of Inflow Mach Numbers on the Combustion Characteristics of a Typical Cavity-Based Supersonic Combustor

Numerical exploration of mixing and combustion in a dual-mode combustor with backward-facing steps

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