Influences of Nitrogen Dilution in the Near Flow Field of Transition Regime Lifted Natural Gas Jet Flames

Author(s):  
Tamir S. Hasan ◽  
James S. Kribs ◽  
Kevin M. Lyons

Flame liftoff height data were obtained on lifted methane jet flames diluted with nitrogen at transition regime Reynolds numbers. The data were analyzed to better understand and model natural gas combustion phenomena, in particular the effects of dilution in the near transition regime of methane jet flames. Images of the stable lifted flames were obtained at low Reynolds numbers from 2000 to 3800. This regime of Reynolds numbers was chosen due to the instability of laminar, lifted methane flames at these lower Reynolds numbers. Amongst other applications, lifted flames are often utilized in boilers and industrial burners to reduce thermal stresses, and are thus of importance in natural gas and low calorific fuel gas combustion. Radial and axial locations of the lowest flammable regions were observed. Since definitive models depicting lifted flames in the transition regime between laminar and turbulent flows have not yet been developed, the data was compared to the approximations of a turbulent flame model. The mass fraction model proposed by Tieszen et al (1996), which approximates the flammable regions based on mass fraction of fuel, was utilized in the analysis. For the conditions examined, turbulent lifted methane flames exist between mass fractions of 0.05 and 0.15. Applying this model showed that experimental results occurred outside of the leanest combustion zone predicted. At low Reynolds numbers, the model’s limit for radial location was the most pronounced factor which distinguished the predicted and observed values. These findings could be a result of the instabilities in the transition regime that result from lower stream velocities, such as unsteady vortical structures or small radial variance. It may also be a result of the data occurring at the lower limit of the model’s applicable regime. Some examination of the data also shows a correlation between mass flow rate of the diluent and the deviation of the experimental data from the theoretical data. Further investigations will continue to observe the effects of dilution into higher Reynolds number jet flames under dilution and co-flow, since they are important in understanding fundamental behavior seen in syngas and low calorific gas combustion.

1997 ◽  
Vol 343 ◽  
pp. 235-265 ◽  
Author(s):  
ANIL PRASAD ◽  
CHARLES H. K. WILLIAMSON

There has recently been a surge in activity concerning the development of three-dimensionality in the wakes of nominally two-dimensional bluff bodies, yielding the realization that end effects can influence the wake vortex shedding pattern over long spanlengths. Much of this work has been focused on low Reynolds numbers (Re), but virtually no studies have investigated to what extent it is possible to control shedding patterns at higher Reynolds numbers, through the use of end manipulation. In the present paper, we demonstrate that it is possible to induce parallel shedding, oblique shedding and vortex dislocations, by manipulation of the end conditions, over a large range of Reynolds number. Such patterns affect the frequency of primary wake instability and its amplitude of fluctuation, as they do at low Reynolds number, although distinct differences are found at the higher Reynolds numbers.We find that imposition of oblique shedding conditions at high Reynolds number leads to a spatial variation of both the oblique shedding angle and shedding frequency across the span, and to sparse dislocations which are not restricted to the spanwise end regions, as they are at low Reynolds numbers (under similar geometrical conditions). In the wake transition regime (Re=190–250), it is confirmed that the spontaneous appearance of vortex dislocations in mode-A shedding precludes the control of shedding patterns using end manipulation. However, it has proven possible to extend the regime of Reynolds number where dislocations ‘naturally’ exist to Re>250, by introducing them artificially through end control, where they would otherwise not occur. The possibility of introducing dislocations and of inducing oblique vortex shedding at higher Reynolds numbers has practical significance, if one can deliberately decorrelate the vortex shedding, and hence reduce the spanwise-integrated unsteady fluid forces on the body.We confirm the existence of a transition in the mode of shedding at Re≈5000 (originally found by Norberg 1987) under conditions where parallel shedding is attempted. This mode transition displays similarities to an inverse of the mode A→mode B transition that is found in the wake transition regime. It is clear that vortex dislocations occur beyond Re=5000, although it is not clear why the flow is unstable to such a mode. Furthermore, there appears to be some support for the suggestion that vortex dislocations may be a feature of the flow for Re at least up to 30×103, as evidenced by the work of Norberg (1994).


2020 ◽  
Vol 21 (6) ◽  
pp. 621
Author(s):  
Veerapathiran Thangaraj Gopinathan ◽  
John Bruce Ralphin Rose ◽  
Mohanram Surya

Aerodynamic efficiency of an airplane wing can be improved either by increasing its lift generation tendency or by reducing the drag. Recently, Bio-inspired designs have been received greater attention for the geometric modifications of airplane wings. One of the bio-inspired designs contains sinusoidal Humpback Whale (HW) tubercles, i.e., protuberances exist at the wing leading edge (LE). The tubercles have excellent flow control characteristics at low Reynolds numbers. The present work describes about the effect of tubercles on swept back wing performance at various Angle of Attack (AoA). NACA 0015 and NACA 4415 airfoils are used for swept back wing design with sweep angle about 30°. The modified wings (HUMP 0015 A, HUMP 0015 B, HUMP 4415 A, HUMP 4415 B) are designed with two amplitude to wavelength ratios (η) of 0.1 & 0.24 for the performance analysis. It is a novel effort to analyze the tubercle vortices along the span that induce additional flow energy especially, behind the tubercles peak and trough region. Subsequently, Co-efficient of Lift (CL), Co-efficient of Drag (CD) and boundary layer pressure gradients also predicted for modified and baseline (smooth LE) models in the pre & post-stall regimes. It was observed that the tubercles increase the performance of swept back wings by the enhanced CL/CD ratio in the pre-stall AoA region. Interestingly, the flow separation region behind the centerline of tubercles and formation of Laminar Separation Bubbles (LSB) were asymmetric because of the sweep.


2010 ◽  
Vol 1 (1-2) ◽  
pp. 15-20 ◽  
Author(s):  
B. Bolló

Abstract The two-dimensional flow around a stationary heated circular cylinder at low Reynolds numbers of 50 < Re < 210 is investigated numerically using the FLUENT commercial software package. The dimensionless vortex shedding frequency (St) reduces with increasing temperature at a given Reynolds number. The effective temperature concept was used and St-Re data were successfully transformed to the St-Reeff curve. Comparisons include root-mean-square values of the lift coefficient and Nusselt number. The results agree well with available data in the literature.


2004 ◽  
Author(s):  
Andrew D. Ketsdever ◽  
Michael T. Clabough ◽  
Sergey F. Gimelshein ◽  
Alina Alexeenko

2020 ◽  
Vol 32 (11) ◽  
pp. 119901
Author(s):  
Cathal Cummins ◽  
Ignazio Maria Viola ◽  
Enrico Mastropaolo ◽  
Naomi Nakayama

2021 ◽  
Vol 33 (5) ◽  
pp. 053602
Author(s):  
Shubiao Wang ◽  
Wenming Cheng ◽  
Run Du ◽  
Yupu Wang ◽  
Qingrong Chen

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