Numerical study of a scramjet combustor fueled by an aerodynamic ramp injector in dual-mode combustion

2001 ◽  
Author(s):  
D. Eklund ◽  
R. Baurle ◽  
M. Gruber
Keyword(s):  
Numerical Study ◽  
Dual Mode ◽  
Scramjet Combustor

Experimental and Numerical Study of a Dual-mode Scramjet Combustor

2006 ◽  
Vol 22 (3) ◽  
pp. 481-489 ◽  
Author(s):  
C. P. Goyne ◽  
C. G. Rodriguez ◽  
R. H. Krauss ◽  
J. C. McDaniel ◽  
C. R. McClinton
Keyword(s):  
Numerical Study ◽  
Dual Mode ◽  
Scramjet Combustor

Numerical Simulation of Dual-Mode Scramjet Combustor with Significant Upstream Interaction

2012 ◽  
Vol 2 (3) ◽  
pp. 60-74
Author(s):  
Rahul Ingle ◽  
Debasis Chakraborty
Keyword(s):  
Surface Pressure ◽  
Stokes Equations ◽  
Numerical Study ◽  
Three Dimensional ◽  
Interaction Model ◽  
Navier Stokes ◽  
Dual Mode ◽  
Fast Kinetics ◽  
Scramjet Combustor ◽  
Flow Features

This paper is concerned with a numerical study corresponding to experimental investigation of Chinzei and co-workers on hydrogen fueled dual-mode scramjet engine essentially to understand the key features of upstream interaction, mixing and combustion. Three dimensional Navier Stokes equations along with a K-? turbulence model and infinitely fast kinetics are solved using commercial CFD software. Reasonable agreement has been obtained between the computed surface pressure with experimental values and the results of other numerical simulations. Insights into the flow features inside the combustor are obtained through analysis of various thermochemical parameters. The comparison of surface pressure with experimental results and other numerical results demonstrated that simple kinetics and turbulence – chemistry interaction model may be adequate to address the overall flow features in the combustor. A principal conclusion is that the boundary layer at the combustor entry has a pronounced effect on the flow development in the dual-mode scramjet combustor and causes significant upstream interaction.

Hybrid Large Eddy Simulation/Reynolds-Averaged Navier–Stokes Analysis of a Premixed Ethylene-Fueled Dual-Mode Scramjet Combustor

AIAA Journal ◽  
2021 ◽  
pp. 1-17
Author(s):  
Tanner B. Nielsen ◽  
Jack R. Edwards ◽  
Harsha K. Chelliah ◽  
Damien Lieber ◽  
Clayton Geipel ◽  
...  
Keyword(s):  
Large Eddy Simulation ◽  
Navier Stokes ◽  
Dual Mode ◽  
Eddy Simulation ◽  
Scramjet Combustor ◽  
Large Eddy ◽  
Reynolds Averaged Navier Stokes

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 A numerical study on the closed packed array of gold discs as an efficient dual mode plasmonic tweezers

2021 ◽  
Vol 11 (1) ◽  
Author(s):  
Abolfazl Aqhili ◽  
Sara Darbari
Keyword(s):  
Numerical Study ◽  
Gold Surface ◽  
Plasmon Mode ◽  
Spatial Proximity ◽  
Periodic Pattern ◽  
Gradient Force ◽  
Dual Mode ◽  
Incident Wavelength ◽  
Trapped Particles ◽  
Thermal Simulations

AbstractIn this report, we propose the closed pack array of gold discs on glass, as a dual mode plasmonic tweezers that benefits from two trapping modes. The first trapping mode is based on leaky surface plasmon mode (LSPM) on the gold discs with a longer penetration depth in the water and a longer spatial trapping range, so that target nanoparticles with a radius of 100 nm can be attracted toward the gold surface from a vertical distance of about 2 µm. This trapping mode can help to overcome the inherent short range trapping challenge in the plasmonic tweezers. The second trapping mode is based on the dimer surface plasmonic mode (DSPM) in the nano-slits between the neighboring gold discs, leading to isolated and strong trapping sites for nanoparticles smaller than 34 nm. The proposed plasmonic tweezers can be excited in both LSPM and DSPM modes by switching the incident wavelength, resulting in promising and complementary functionalities. In the proposed plasmonic tweezers, we can attract the target particles towards the gold surface by LSPM gradient force, and trap them within a wide half widthhalfmaximum (HWHM) that allows studying the interactions between the trapped particles, due to their spatial proximity. Then, by switching to the DSPM trapping mode, we can rearrange the particles in a periodic pattern of isolated and stiff traps. The proposed plasmonic structure and the presented study opens a new insight for realizing efficient, dual-mode tweezers with complementary characteristics, suitable for manipulation of nanoparticles. Our thermal simulations demonstrate that the thermal-induced forces does not interefe with the proposed plasmonic tweezing.

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.

Sign in / Sign up

Export Citation Format

Share Document