Experimental Study on Combustion Modes in a Supersonic Combustor

Masumoto, Ryota; Tomioka, Sadatake; Kudo, Kenji; Murakami, Atsuo; Kato, Kanenori; Yamasaki, Hiroyuki

doi:10.2514/1.53223

Cited by 6 publications

(5 citation statements)

References 14 publications

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“…To address this challenge, proper designing of the combustion chamber by implementing an appropriate fuel injection/ flame holding approach into the combustor is necessary. Inside the scramjet combustor, the introduction of different flame holding mechanisms and different ignition mechanisms has been investigated by researchers in terms of various fuel injection mechanisms and different cavity and strut-based flame holders [11][12][13] are found in the literature.…”

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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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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“…One is the global combustion mode classified based on the reaction intensity or flow regimes within the combustor. For example, Masumoto et al 6 experimentally studied combustion modes in a supersonic combustor, where four combustion modes were observed: non-ignition, weak combustion (with little pressure rise), supersonic combustion and dual-mode combustion. These modes were found to be organized in terms of combustor length and total temperature at different equivalence ratios.…”

Section: Stabilization Modes and Mechanismsmentioning

confidence: 99%

Review of cavity-stabilized combustion for scramjet applications

Wang

Sun

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

108

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Cavities are widely used as flameholders in supersonic combustors due to their outstanding potential to stabilize combustion without excessive total pressure loss. A review of cavity-stabilized combustion for scramjet applications is provided in this article. The topics cover the fundamental problems and recent advances regarding cavity-organized combustion in high-speed flows, including combustion stabilization modes and mechanisms, flame stability analyses and correlations, combustion oscillations, and other related issues. Remarkable questions such as cavity-coupled fuel injection, flow and combustion coupling, optimal cavity geometry and scale, auto-ignition and flame propagation interactions, and unsteady effects are discussed. Then, an attempt is made to provide some guidelines for the future research of cavity flameholders.

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“…A supersonic combustor with several combustor lengths, total temperatures and equivalence ratios was tested in a directly connected wind tunnel, and four combustion modes were observed, namely nonignition, weak combustion, supersonic combustion and dual-mode combustion. These combustion modes are related to combustion length and total temperature [18]. However, to the best of the authors' knowledge, as a crucial and efficient tool to cut the expensive cost in the experimental or flight test and support the results obtained by the theoretical analysis, the computational fluid dynamic approach has been widely employed to explore the flow field information in the airbreathing propulsive system firstly and comprehensively.…”

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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Experimental Study on Combustion Modes in a Supersonic Combustor

Cited by 6 publications

References 14 publications

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

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

Review of cavity-stabilized combustion for scramjet applications

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

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