Numerical Study of Hypervelocity Flows Through a Scramjet Combustor

1997 ◽  
Vol 13 (1) ◽  
pp. 131-141 ◽  
Author(s):  
R. Krishnamurthy ◽  
R. C. Rogers ◽  
S. N. Tiwari
Keyword(s):  
Numerical Study ◽  
Scramjet Combustor ◽  
Hypervelocity Flows

scholarly journals Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity

Energies ◽  
2019 ◽  
Vol 12 (7) ◽  
pp. 1235 ◽  
Author(s):  
Chaolong Li ◽  
Zhixun Xia ◽  
Likun Ma ◽  
Xiang Zhao ◽  
Binbin Chen
Keyword(s):  
Solid Fuel ◽  
Stokes Equations ◽  
Numerical Study ◽  
Three Dimensional ◽  
Combustion Efficiency ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Particle Combustion ◽  
Scramjet Combustor ◽  
Cavity Configuration

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.

Experimental and numerical study of solid rocket scramjet combustor equipped with combined cavity and strut device

2019 ◽  
Vol 162 ◽  
pp. 145-154 ◽  
Author(s):  
Chaolong Li ◽  
Zhixun Xia ◽  
Likun Ma ◽  
Xiang Zhao ◽  
Binbin Chen
Keyword(s):  
Numerical Study ◽  
Scramjet Combustor ◽  
Solid Rocket

scholarly journals Numerical Study on Configuration of Scramjet Combustor

2018 ◽  
Vol 408 ◽  
pp. 012022
Author(s):  
Wenjia Yang ◽  
Juntao Fu ◽  
Xinpeng Ma ◽  
Ruikang Xing
Keyword(s):  
Numerical Study ◽  
Scramjet Combustor

Numerical study on solid-fuel scramjet combustor with fuel-rich hot gas

2018 ◽  
Vol 77 ◽  
pp. 25-33 ◽  
Author(s):  
Xiang Zhao ◽  
Zhi-xun Xia ◽  
Bing Liu ◽  
Zhong Lv ◽  
Li-kun Ma
Keyword(s):  
Solid Fuel ◽  
Numerical Study ◽  
Hot Gas ◽  
Scramjet Combustor

A numerical study on the mixing of air and hydrogen in a scramjet combustor

2005 ◽  
Vol 109 (1097) ◽  
pp. 325-335
Author(s):  
M. Ali ◽  
T. Fujiwara
Keyword(s):  
Stokes Equations ◽  
Numerical Study ◽  
Side Wall ◽  
Recirculation Region ◽  
Mixing Efficiency ◽  
Main Stream ◽  
Two Dimensional ◽  
Injection Angle ◽  
Scramjet Combustor ◽  
Flow Field Characteristics

Abstract A numerical study on mixing of air and hydrogen is performed by solving two-dimensional full Navier-Stokes equations. The main stream is air of Mach 5 entering through the configured inlet of the combustor and gaseous hydrogen is injected from the configured jet on the side wall. Supersonic mixing and diffusion mechanisms of a transverse hydrogen jet in two-dimensional finite air streams have been analyzed and discussed. The computed results are compared with the experimental data and show good agreement. For an otherwise fixed combustor geometry, the air inlet width and injection angle are varied to study the physics of mixing and flow field characteristics. On the effect of inlet width variation, two competing phenomena have been observed: (i) upstream of injector the strength of recirculation is higher for wider inlet and consequently the mixing increases, and (ii) downstream, the diffusion of hydrogen decreases with the increase of inlet width and eventually mixing decreases. As a result, in far downstream the mixing efficiency increases up to certain inlet width and then decreases for further increment of inlet width. For the variation of injection angle results show that upstream of injector the mixing is dominated by recirculation and downstream the mixing is dominated by mass concentration of hydrogen. Upstream recirculation is dominant for injecting angle 60° and 90°. Incorporating the various effects, perpendicular injection shows the maximum mixing efficiency and its large upstream recirculation region has a good flame holding capability.

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