by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English
|Statement||Nicholas S. Winowich.|
|Series||NASA contractor report -- NASA CR-188991.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Numerical prediction of burning velocity and flame thickness in a radial-flow porous burner The domain of the analysis is a lean premixed prevaporized burner equipped with an air blast. Winowich, N. S., , “Numerical Prediction of Turbulent Flame Stability in Premixed/Prevaporized (HSCT) Combustors,” National Aeronautics and Space Administration Contractor Report NASA-CR Cited by: 3. Zhang, Man, Wu, Hao, and Wang, Hao. "Numerical Prediction of NOx Emission and Exit Temperature Pattern in a Model Staged Lean Premixed Prevaporized Combustor." Proceedings of the ASME Turbo Expo Turbine Technical Conference and Exposition. Volume 3C: Heat Transfer. San Antonio, Texas, USA. June 3–7, V03CT17A by: 1. Most numerical computations of turbulent combustion gases are currently performed with the use of Large Eddy Simulation (LES) model . Consequently, the gaseous mixture in the combustion chamber may be feature by the equivalence ratio that may compromise the targeted objective in terms of pollutants emission reduction and also the control Cited by: 7.
Impact of the Equivalence Ratio and the Mass Flow Rate on Turbulent Lean Premixed Prevaporised Combustion Article (PDF Available) in Energy Procedia December with 86 Reads. Validation of this idea has been provided by two recent DNS studies of a flat turbulent flame in a box by Bell et al. and Hawkes and Chen. They considered a flat turbulent flame that has 1-D mean properties and were able to compute the magnitude of both sides of the equation: (29) m ˙ R / (ρ R A c ¯ = ) S L 0 = I 0 ∫-∞ ∞ Σ d η. by: Numerical prediction of turbulent flame stability in premixed/prevaporized (HSCT) combustors [microform]  Winowich, Nicholas S. [Washington, DC: National Aeronautics and Space Administration ; Springfield, Va.: National Technical Information Service, distributor, ]. Concept of Lean Premixed-Prevaporized Combustion A schematic of LPP combustion is seen in Fig. 1; a premixed, prevaporized Main flame surrounds a central non-premixed Pilot flame. The liquid Main fuel (Jet-A) is injected as a jet-in-a-cross-flow . Because of the high velocities associated with the Main air, most of the Main flame.
Experimental study has been carried out for investigating fuel type, fuel blends, equivalence ratio, Reynolds number, inlet mixture temperature, and holes diameter of perforated plate affecting combustion process for turbulent prevaporized premixed air flames for different operating conditions. CO 2, CO, H 2, N 2, C3H8, C2H6, C2H4 Author: Mohamed S. Shehata, Mohamed M. ElKotb, Hindawi Salem. They were the ones with high atomizing pressures and quarls, which provided no or low effect on flame stability. The spectrum of the straight flame was dominated by frequencies between 3 and 4 kHz. This band starts to fade as the flame approaches the transitory regime with the increasing combustion air flow rate, and hence S ’. By increasing. Han X, Laera D, Yang D, Zhang C, Wang J, Hui X, Lin Y, Morgans AS, Sung C-J et al., , Flame interactions in a stratified swirl burner: Flame stabilization, combustion instabilities and beating oscillations, Combustion and Flame, Vol: , Pages: , ISSN: The present article investigates the interactions between the pilot and main flames in a novel stratified swirl burner. planar, lean premixed prevaporized kerosene flame, stabilized by means of a movable stagnation plate. The experimental setup displayed in figure 1 comprises a co-annular jet arrangement with a shielding air flow around a central fuel loaded jet, both impinging on the stagnation plate. The turbulent flames investigated show an.