Numerical investigation of mode transition and hysteresis in a cavity-based dual-mode scramjet combustor

Zhang, Xu; Yue, Lianjie; Huang, Tinglong; Zhang, Qi-Fan; Zhang, Xinyu

doi:10.1016/j.ast.2019.105420

Cited by 27 publications

(2 citation statements)

References 40 publications

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“…In general, the solid fuel scramjet can be categorized into four categories: solid fuel scramjet (SFSRJ), [2][3][4][5][6][7][8] dual mode combustion ramjet (DMRJ), 4,9,10 solid fuel rocket scramjet (SFRSRJ), 11,12 and combined solid fuel scramjet (CSFSRJ). 1,13 In SFSRJ, solid fuel is placed on the wall of combustor.…”

Section: Introductionmentioning

confidence: 99%

Numerical research on the performance of solid fuel rocket scramjet combustor

Huang

Feng

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Combustion efficiency is the main factor affecting the performance of solid fuel rocket scramjet. To reveal the influence of combustor configuration on performance and further improve combustion efficiency, the influence of the width-height ratio of the rectangle-section combustor on the performance of solid fuel rocket scramjet is investigated numerically in this article. Three-dimensional compressible Reynolds-averaged Navier-Stokes equations coupled with shear stress transport k– ω turbulence model are employed to simulate the aerodynamics. The Euler–Lagrange approach is used to calculate the multiphase flow. Combustion of carbon particles is modeled by the improved Moving Flame Front model. Accuracy of the present numerical model is validated by the experimental data of a rectangle-section combustor from literature. Results show that as the width-height ratio increases, the combustion efficiency increases first and then decreases. The influence of cavity and its position on the performance are also investigated. Results show that cavity can significantly improve combustion efficiency. The effect of cavity position on performance is related to the distribution of particles.

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Section: Introductionmentioning

confidence: 99%

Numerical research on the performance of solid fuel rocket scramjet combustor

Huang

Feng

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Therefore, water cooled pressure sensors with tubes [41,42] and pressure probes [38,43] are still used in high enthalpy airflow. With the increasing high-speed aerodynamic tests including the supersonic inlet [44,45], isolator [46] and combustor [39,40,47,48] of the scramjet, the influence of pressure transmission tubes on unsteady pressure measuring results in supersonic flow needs studying. The effect of tube cooling should also be assessed.…”

Section: Introductionmentioning

confidence: 99%