This paper analyzes traveling wave profiles possessing an internal resonance point for a class of systems of partial differential equations describing oxidation and vaporization of liquid fuel in a porous medium when an oxidizer (air) is injected. It is shown that the resonance is characterized by a saddle point of an associated vector field defined on a folded surface in state space. We prove ...

Because ammonia is one of the most promising candidates for energy carrier in future, various applications as a fuel are currently considered. One medium utilizing by introducing it to coal-fired boilers. To best our knowledge, this paper first report fundamental mechanism flame propagation phenomenon pulverized coal/ammonia co-combustion. The effects equivalence ratio ammonia-oxidizer mixture ...

Homogeneous Charge Compression Ignition (HCCI) combustion is a pioneer method of combustion in which pre-mixed fuel and oxidizer (typically air) are compressed to the point of auto-ignition. HCCI engines can operate with most alternative fuels, especially, dimethyl ether (DME) which has been tested as a possible diesel fuel due to its simultaneously low NOx and PM emissions. In this paper a ...

We study a system of semilinear hyperbolic equations passively advected by smooth white noise in time random velocity fields. Such a system arises in modeling non-premixed isothermal turbulent flames under single-step kinetics of fuel and oxidizer. We derive closed equations for one-point and multi-point probability distribution functions (PDFs) and closed form analytical formulas for the one p...

Extreme weather often contributes to crown fires, where the fire spreads from one tree crown to the next as a series of piloted ignitions. An important aspect in predicting crown fires is understanding the ignition of fuel particles. The ignition criterion considered in this work is the critical mass flux criterion – that a sufficient amount of pyrolysis gases must be generated for a diffusion ...

The MaCH-SR1 project involved the design of a 1000lb thrust hybrid rocket with the effort being undertaken during two semesters by 8 senior aerospace engineering students at the University of Colorado at Boulder. The 2002-2003 team was the second year for the project, as the previous team built two static engines and performed test burns on both. The hybrid implemented a liquid O2/HTPB oxidizer...

The combustion of an oxygen/paraffin hybrid rocket motor was experimentally characterized. Firing tests were conducted for different oxidizer mass fluxes ranging from 2.47 to 3.40 g/ (cm2·s). Variations in temperature and H2O partial pressure at the nozzle exit diagnosed using mid-infrared tunable diode laser absorption spectroscopy (TDLAS) based on near 2.5 μm. Three lines simultaneously cover...

Liquid propellant rocket utilizes an engine that uses liquid as a propellant. In rockets, fuel and oxidizer are pumped into the combustion chamber, where they get mixed burned. hydrogen is mainly used fuel, oxygen oxidizer. Slosh can occur with propellants. acts tuned damper helps in reducing dynamic response of vehicle. baffles tanks intelligent control rules guidance system be to this. A pote...