Author
Binbin Chen
Bio: Binbin Chen is an academic researcher from National University of Defense Technology. The author has contributed to research in topics: Combustion & Scramjet. The author has an hindex of 5, co-authored 12 publications receiving 56 citations.
Topics: Combustion, Scramjet, Combustor, Propellant, Ignition system
Papers
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TL;DR: In this paper, an extended model of boron combustion and combustion was proposed for a single particle, and the influence of forced convection on the particle was considered in both the ignition and combustion stage.
25 citations
TL;DR: In this article, a new solid rocket scramjet equipped with two combined cavity and strut device was studied by experimental and numerical approaches, and the experimental results showed that the combined cavity can play a role as ignition and flame holding in the solid rocket scrambling combustor.
23 citations
TL;DR: In this paper, the influence of vortex generator on the performance of a solid rocket scramjet was investigated by means of direct-connected fire tests, and the experimental results showed that compared with the benchmark configuration, the configurations with vortex generator can promote significantly the ignition and stable combustion of the primary fuel-rich mixture produced in the gas generator.
18 citations
TL;DR: In this paper, a numerical approach for the internal reaction flow in SPDR was built, and an improved combustion model of boron particles was used, which indicated that combustion efficiencies increase from 88% to 95% with swirling flow.
14 citations
TL;DR: In this article, a new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed, and a numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude.
Abstract: 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.
14 citations
Cited by
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TL;DR: In this article, the present status and underlying challenges in synthesis process of boron nanoparticles, dispersion and stability of BORON nanoparticles in liquid hydrocarbon fuels, effect of surfactant or surface modification on dispersion stability, ignition and combustion characteristics of Boron loaded liquid fuel as well as particle combustion, understanding the positive thermal contribution from borón particles burning, and characterization of post-combustion products in terms of chemical and physical properties.
62 citations
TL;DR: In this paper, composites containing either Bi or BiF3 ignited more readily than pure boron when heated by a CO2 laser beam, and for most composites combustion temperatures were higher.
27 citations
TL;DR: By double displacement reaction in aqueous media, bismuth fluoride, BiF3, was coated onto micron-sized boron particles to target two compositions with 5 and 10% mass fractions as discussed by the authors.
25 citations
TL;DR: In this paper, a new solid-fuel ramjet design was proposed and numerically investigated to enhance the regression rate of the SFRJ by using two solid fuels with keeping the simplicity in the design of the classic solid- fuel ramjet.
23 citations
TL;DR: In this paper, the influence of vortex generator on the performance of a solid rocket scramjet was investigated by means of direct-connected fire tests, and the experimental results showed that compared with the benchmark configuration, the configurations with vortex generator can promote significantly the ignition and stable combustion of the primary fuel-rich mixture produced in the gas generator.
18 citations