Supersonic flow over a cone with heat release in the neighborhood of the apex

1993 ◽  
Vol 28 (2) ◽  
pp. 244-247 ◽  
Author(s):  
V. A. Levin ◽  
L. V. Terent'eva
Keyword(s):  
Supersonic Flow ◽  
Heat Release

scholarly journals Some Effects of Hydrogen Self-Ignition and Combustion in Supersonic Flow

2014 ◽  
Vol 16 (2-3) ◽  
pp. 245
Author(s):  
U. Zhapbasbayev ◽  
V. Zabaykin ◽  
Y. Makashev ◽  
A. Tursynbay ◽  
B. Urmashev
Keyword(s):  
Supersonic Flow ◽  
Heat Release ◽  
Chemical Reactions ◽  
Laboratory Data ◽  
Combustion Process ◽  
Supersonic Combustion ◽  
Low Flow ◽  
Diffusion Combustion ◽  
Maximum Pressure ◽  
Combustion Mode

<p>Results are presented of computational and experimental investigations of the influence of temperature and flow composition on the hydrogen combustion kinetics for a coaxial fuel supersonic flow. Depending on the flow parameters, combustion is shown to occur with an intense heat release governed by the speed of chemical reactions, or a diffusion combustion with heat release governed by mixing. The computational results are in good agreements of with laboratory data and portrays many important features of supersonic combustion. The influence of the gas temperature and composition on the diffusion combustion of a circular hydrogen jet in supersonic coaxial flow at the over expanded exhaust regimes is investigated. It is found that at low flow temperatures (Т<sub>2 </sub>~ 900 K) and in the absence of water vapors in the oxidizer gas composition, the speed of chemical reactions is the determining factor for combustion. An increase in the flow temperature (Т<sub>2</sub> &gt; 1200 K) causes a reduction of the induction time of the reactive mixture, because the mixing of fuel with oxidizer decreases, and a “sluggish” diffusion combustion of non-mixed gases is observed. The presence of water vapor and active radicals in the gas ensures the self-ignition from the start of the mixing, and the diffusion combustion mode is limited by mixing of the hydrogen jet with the coaxial flow (similar to the case with high initial temperatures of the air stream). In the case of the delay combustion process the maximum pressure level on the wall is 10% more than that in the combustion mode with ignition at the start of mixing. A sluggish combustion regime may lead to an incomplete hydrogen burnout.</p>

Effects of combustor geometry on the combustion process of an RBCC combustor in high-speed ejector mode

2019 ◽  
Vol 33 (27) ◽  
pp. 1950330
Author(s):  
Taiyu Wang ◽  
Zhenguo Wang ◽  
Zun Cai ◽  
Jian Chen ◽  
Mingbo Sun ◽  
...  
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Heat Release ◽  
Reaction Mechanisms ◽  
Total Pressure ◽  
High Speed ◽  
Combustion Process ◽  
Numerical Approach ◽  
Combined Cycle ◽  
Chemical Reaction Mechanisms

The combustion characteristics of high-speed ejector mode in a 2-dimensional strut-based RBCC (rocket-based combined cycle) combustor had been investigated numerically in a Mach 2.5 supersonic flow. The numerical approach had been validated by comparing numerical results with available experimental data. Besides, three different hydrogen-air chemical reaction mechanisms had also been compared. The effect of the combustor geometry on the combustion process was then discussed by analyzing the heat release distribution and flow field. It was found that the wall configuration, closeout angle of the converging location and converging ratio all have significant influences on the heat release distribution and flow field structures. It is demonstrated that a converging–diverging wall configuration is beneficial for the combustion process with significant heat release increase compared to the other wall configurations. In addition, the closeout angle of the converging location is also closely related to the combustion performance, and there exists an optimized closeout angle in a specific combustor geometry. It is also revealed that the major heat release region moves upstream obviously with increase in the converging ratio, leading to an enhanced combustion process. However, the converging ratio is still to be optimized to keep a balance between heat release increase and total pressure loss of the supersonic flow.

Numerical Studies on Behavior of Lorentz-Force-Applied Boundary Layer in Supersonic Flow

2009 ◽  
Vol 129 (6) ◽  
pp. 831-839
Author(s):  
Keisuke Udagawa ◽  
Sadatake Tomioka ◽  
Hiroyuki Yamasaki
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Lorentz Force ◽  
Numerical Studies

Dynamics of Subcooled Liquid with Pulse Heat Release in a Heater

2001 ◽  
Vol 32 (4-6) ◽  
pp. 8
Author(s):  
E. A. Tairov ◽  
B. G. Pokusaev ◽  
D. A. Kazenin ◽  
S. A. Chizhikov ◽  
L. V. Syskov
Keyword(s):  
Heat Release ◽  
Subcooled Liquid ◽  
Pulse Heat

CONTROL OF HEAT RELEASE ENERGY DURING HEATING FROM SOLID-SOLID PHASE CHANGE MATERIAL

2018 ◽  
Author(s):  
Ryohei Gotoh ◽  
Tsuyoshi Totani ◽  
Masashi Wakita ◽  
Harunori Nagata
Keyword(s):  
Phase Change ◽  
Heat Release ◽  
Phase Change Material ◽  
Solid Phase ◽  
Change Material
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