CFD analysis of a scramjet combustor with cavity based flame holders

Kummitha, Obula Reddy; Pandey, Krishna Murari; Gupta, R.

doi:10.1016/j.actaastro.2018.01.005

Cited by 71 publications

(6 citation statements)

References 39 publications

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“…A structure that can generate a subsonic recirculation zone can increase the residence time of fuel in a supersonic combustor, promote the mixing between fuel gas and airflow, and play a role in flame holding. Currently, the cavity is mainly used in the liquid fuel scramjet [33][34][35][36]. Pei and Hou [37] studied the influences of cavity length/deep ratio on the performance of combustor in a SFSCRJ.…”

Section: Solid-fuel Gas Generatormentioning

confidence: 99%

Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

Xia

et al. 2019

Energies

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Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) k − ω turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is demonstrated based on the validation of the numerical method. Results show that the scramjet combustor configuration with a backward-facing step can resist high pressure generated by the combustion in the supersonic combustor. The total combustion efficiency of the SFRSCRJ combustor mainly depends on the combustion of particles in the fuel-rich gas. A proper combustion organization can promote particle combustion and improve the total combustion efficiency. Among the four configurations considered, the combustion efficiency of the mid-cavity configuration is the highest, up to about 70%. Therefore, the cavity can effectively increase the combustion efficiency of the SFRSCRJ combustor.

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Section: Solid-fuel Gas Generatormentioning

confidence: 99%

Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

Xia

et al. 2019

Energies

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“…The combustion chamber of a scramjet typically utilizes regenerative cooling. Resolving the flow and heat-transfer processes within this chamber entails addressing various physical and chemical phenomena, including radiation heat transfer, convective heat transfer, combustion, and heat conduction [14][15][16][17]. Three-dimensional numerical simulation of the combustion chamber is difficult and complicated.…”

Section: Introductionmentioning

confidence: 99%

Research on the Zooming Method for Determining the Flow, Heat Transfer, and Infrared Radiation of an Air-Breathing Hypersonic Vehicle Powered by a Scramjet

Wei,

Shi,

et al. 2024

Aerospace

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In order to study the infrared radiation characteristics of an air-breathing hypersonic vehicle powered by a scramjet, it is necessary to solve the internal and external flow field of the air-breathing hypersonic vehicle. Owing to the complexity and difficulty of solving the three-dimensional flow and heat-transfer process in a scramjet combustor, a quasi-one-dimensional calculation method was established. Utilizing zooming technology, a combination of quasi-one-dimensional simulation within the combustion chamber and three-dimensional numerical simulation elsewhere on the vehicle was employed to obtain the flow field. The accuracy of the zooming method in determining flow, heat transfer, and infrared radiation was verified through comparison with experimental data. The results show that under the flight condition of Ma = 6, the gas temperature and wall heat flux in the scramjet combustor first increased and then decreased along the flow direction. The Mach number of the plume was smaller than that of the free flow, while the velocity of the plume was slightly larger. In the wavelength range of 3–5 μm, as the azimuth angle increased, the integrated radiation intensity of the air-breathing hypersonic vehicle demonstrated a characteristic pear-shaped distribution.

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“…Numerical simulations help investigate the performances of such engines while avoiding the repetition of experimental tests, which can be expensive and difficult to set up. For instance, the fuel injection strategy has a varying impact on the efficiency of mixing and combustion that can be attained in scramjets, and several injection configurations have been numerically investigated, such as cavity-based [4][5][6], dual-cavity [7,8], strut [9,10], multi-strut injections [11], or the combination of multiple strategies [12][13][14], to assess whether design variations are advantageous for experimental testing and prototyping.…”

Section: Introductionmentioning

confidence: 99%

Mixing time scale analysis of the Partially Stirred Reactor model for high-speed turbulent combustion of hydrogen in vitiated air

Piscopo,

Iavarone,

Savarese

et al. 2024

Acta Astronautica

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CFD analysis of a scramjet combustor with cavity based flame holders

Cited by 71 publications

References 39 publications

Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

Research on the Zooming Method for Determining the Flow, Heat Transfer, and Infrared Radiation of an Air-Breathing Hypersonic Vehicle Powered by a Scramjet

Mixing time scale analysis of the Partially Stirred Reactor model for high-speed turbulent combustion of hydrogen in vitiated air

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