Experimental Observations of Flow Instability in a Helical Coil (Data Bank Contribution)

1993 ◽  
Vol 115 (3) ◽  
pp. 436-443 ◽  
Author(s):  
D. R. Webster ◽  
J. A. C. Humphrey
Keyword(s):  
Cross Section ◽  
Flow Instability ◽  
Time Integration ◽  
Circular Cross Section ◽  
Frequency Doubling ◽  
Outer Wall ◽  
Data Bank ◽  
Curvature Radius ◽  
Number Range ◽  
Pipe Cross Section

Experimental observations were made for the nominally fully developed flow through a helically coiled pipe of circular cross-section with a curvature radius to pipe radius ratio Rc/a = 18.2. Laser-Doppler measurements of the instantaneous streamwise velocity, uθ, and the cross-stream circumferential velocity, uφ, components were obtained along the midplane of the pipe cross-section. The Reynolds number range explored was 3800 < Re < 10500 (890 < De < 2460) and spans the laminar and turbulent flow regimes. Time integration of the velocity records has yielded previously unavailable mean and rms velocity profiles. In the range 5060 < Re < 6330, the time records of the velocity components reveal periodic flow oscillations with St ≈ 0.25 in the inner half of the pipe cross-section while the flow near the outer wall remains steady. A frequency doubling (St ≈ 0.5) is also observed at some midplane locations. This low frequency unsteadiness is distinct from the shear-induced turbulent fluctuations produced with increasing Re first at the outer wall and later at the inner wall of the coiled pipe. Simple considerations suggest that the midplane jet in the recirculating cross-stream flow is the source of instability.

Flow in Rotating Straight Pipes of Circular Cross Section

1971 ◽  
Vol 93 (3) ◽  
pp. 383-394 ◽  
Author(s):  
H. Ito¯ ◽  
K. Nanbu
Keyword(s):  
Friction Factor ◽  
Cross Section ◽  
Circular Cross Section ◽  
Constant Angular Velocity ◽  
Smooth Wall ◽  
Good Qualitative Agreement ◽  
Fully Developed Flow ◽  
Number Range ◽  
Friction Factors ◽  
Laminar And Turbulent Flow

The friction factor for fully developed flow in smooth wall straight pipes of circular cross section rotating at a constant angular velocity about an axis perpendicular to its own has been measured in the Reynolds number range from 20 to 60,000. Empirical equations for friction factors for small values of RΩ/R were presented for both laminar and turbulent flow. In the case of laminar flow, an approximate analysis based on the assumption that the flow consists of a frictionless central core surrounded by a boundary layer was presented. The results were in good qualitative agreement with experimental results in regard to the friction factor, velocity distribution in the plane of symmetry and pressure distribution along the circumferential wall of the pipe.

Fluid Flow and Heat Transfer Characteristics in the Entrance Regions of Circular Pipes

1985 ◽  
Author(s):  
S. Lloyd ◽  
A. Brown
Keyword(s):  
Heat Transfer ◽  
Cross Section ◽  
Circular Cross Section ◽  
Flow Visualisation ◽  
Pressure Measurements ◽  
Hot Wire ◽  
Heat Transfer Characteristics ◽  
Number Range ◽  
Flow And Heat Transfer ◽  
Circular Pipes

This paper describes the results of an experimental investigation into the velocity and turbulence fields and to a lesser extent the heat transfer in the entrance regions of short, circular cross-section pipes with length to diameter ratios up to 20 over the Reynolds number range from 35,000 to 170,000. The velocity and turbulence fields were measured by hot-wire anemometers backed up with pressure measurements and flow visualisation and the heat transfer by heat flux meters.

Heat Transfer and Pressure Loss in a Two-Pass, Rectangular Channel Featuring a Reduced Cross-Sectional Area After the 180- Degree Tip Turn with Different Turning Vane Configurations

2021 ◽  
pp. 1-44
Author(s):  
Sulaiman Alsaleem ◽  
Lesley Wright ◽  
Je-Chin Han
Keyword(s):  
Heat Transfer ◽  
Aspect Ratio ◽  
Cross Section ◽  
Pressure Loss ◽  
Guide Vane ◽  
Circular Cross Section ◽  
Cross Sectional Area ◽  
Sectional Area ◽  
Cross Sectional ◽  
Number Range

Abstract Serpentine, multi-pass cooling passages, are used in cooling advanced gas turbine blades. In open literature, most internal cooling studies use a fixed cross-sectional area for multi-pass channels. Studies that use varying aspect ratio channels, along with a guide vane to direct the flow with turning, are scarce. Therefore, this study investigates the effect of using different guide vane designs on both detailed heat transfer distribution and pressure loss in a multi-pass channel with an aspect ratio of (4:1) in the entry passage and (2:1) in the second passage downstream of the vane (s). The first vane configuration is one solid-vane with a semi-circular cross-section connecting the two flow passages. The second configuration has three broken-vanes with a quarter-circular cross-section; two broken vanes are located downstream in the first passage, and one broken vane is upstream in the second passage. Detailed heat transfer distributions were obtained on all surfaces within the flow passages by using a transient liquid crystal method. Results show that including the semi-circular vane in the turning region enhanced the overall heat transfer by around 29% with a reduction in pressure loss by around 20%. Moreover, results show the quarter-circular vane design provides higher overall averaged heat transfer enhancement than the semi-circular vane design by around 9% with penalty of higher pressure drop by 6%, which yields higher thermal performance by 7%, over a Reynolds number range from 15,000 to 45,000.

scholarly journals Flow Instability through a Curved Duct with Square Cross Section

1970 ◽  
Vol 29 ◽  
pp. 71-85
Author(s):  
Rabindra Nath Mondal ◽  
Md Saidul Islam ◽  
Shah Md Tarif Hossain
Keyword(s):  
Time Evolution ◽  
Cross Section ◽  
Flow Instability ◽  
Outer Wall ◽  
Dean Number ◽  
Square Duct ◽  
Curved Duct ◽  
Wide Range ◽  
Comprehensive Survey ◽  
Steady Solutions

Flow instability through a curved duct with square cross section is numerically studied by using the spectral method over a wide range of the Dean number 0≤Dn≤5000 for the curvature δ= 0.1. A temperature difference is applied between the vertical sidewalls for the Grashof number Gr=100, where the outer wall is heated and the inner wall is cooled. After a comprehensive survey over the parametric ranges, two branches of asymmetric steady solutions are obtained by the Newton-Raphson iteration method. Linear stability of the steady solutions is then investigated. It is found that only the first branch is linearly stable in a couple of interval of Dn while the other branch is linearly unstable. Steady values of the Nusselt numbers, Nu, are also calculated for two differentially heated vertical sidewalls. When there is no stable steady solution, time evolution of Nu is obtained and it is found in the unstable region the flow undergoes through various flow instabilities, if Dn is increased. Key words: Curved square duct; Steady solutions; Time evolution; Dean number; Nusselt number GANIT J. Bangladesh Math. Soc. (ISSN 1606-3694) 29 (2009) 71-85  DOI: http://dx.doi.org/10.3329/ganit.v29i0.8517

Heat Transfer and Pressure Loss in a Two-Pass, Rectangular Channel Featuring a Reduced Cross-Sectional Area After the 180-Degree Tip Turn With Different Turning Vane Configurations

2020 ◽  
Author(s):  
Sulaiman M. Alsaleem ◽  
Lesley M. Wright ◽  
Je-Chin Han
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Pressure Drop ◽  
Aspect Ratio ◽  
Cross Section ◽  
Pressure Loss ◽  
Circular Cross Section ◽  
Sectional Area ◽  
Cross Sectional ◽  
Number Range

Abstract Serpentine, varying aspect ratio cooling passages, are typically used in cooling advanced gas turbine blades. These passages are usually connected by sharp, 180-deg bends. In the open literature, most of the internal cooling studies use a fixed cross-sectional area for multi-pass channels. Studies that use varying aspect ratio channels, along with a guide (turn) vane to direct the flow with turning, are scarce. In general, studies show that the incorporation of turning vanes in the bend region of a multi-pass channel keeps the heat transfer rate high while reducing pressure loss. Therefore, the current study investigates the effect of using different guide (turn) vane designs on both the detailed heat transfer distribution and pressure loss in a multi-pass channel with an aspect ratio of (4:1) in the entry passage and (2:1) in the second passage downstream of the vane (s). The first vane configuration is one solid-vane with a semi-circular cross-section connecting the two flow passages. The second configuration has three broken-vanes with a quarter-circular cross-section; two broken vanes are located downstream in the first passage (entering the turn), and one broken vane is upstream in the second passage (exiting the turn). For a Reynolds number range 15,000 to 45,000, detailed heat transfer distributions were obtained on all surfaces within the flow passages by using a transient liquid crystal method. The results show that the turning vane configurations have large effects on the heat transfer, in the turning bend and second passage, and the overall pressure drop. Results show that including the semi-circular vane in the turning region of a multi-pass channel enhanced the overall heat transfer by around 29% with a reduction in pressure loss by around 20%. Moreover, results show that the quarter-circular vane design provides higher overall averaged heat transfer enhancement than the semi-circular vane design by around 9% with penalty of higher pressure drop by 6%, which yields higher thermal performance by 7%, over the Reynolds number range.

The Influence of a 90° Mitre Bend on Transition in Smooth Pipes

1962 ◽  
Vol 66 (622) ◽  
pp. 649-650
Author(s):  
E. Szomanski
Keyword(s):  
Reynolds Number ◽  
Product Development ◽  
Fluid Mechanics ◽  
Cross Section ◽  
Circular Cross Section ◽  
Number Range ◽  
Flow Losses ◽  
Different Types ◽  
Definition Of ◽  
Development Laboratory

In this note a brief description is given of some interesting results obtained in smooth pipes of circular cross section during an investigation of the steady flow losses in a 90° mitre bend at the Endicott Product Development Laboratory of I.B.M. The tests indicated that in a certain Reynolds number range the presence of a mitre bend was sufficient to cause flows of different types to exist in the upstream and downstream tangents of the bend. The definition of the bend loss in the light of this phenomenon is considered.It is hoped that this paper will stimulate comment on similar occurrences, which would lead to a better understanding of flow behaviour in this rather neglected area of fluid mechanics.

CFD analysis of unsteady and anisotropic turbulent flow in a circular-sectioned 90° bend pipe with and without ribs: A comparative computational study

2021 ◽  
Vol 15 (2) ◽  
pp. 7964-7982
Author(s):  
Rachid Chiremsel ◽  
Ali Fourar ◽  
Fawaz Massouh ◽  
Zakarya Chiremsel
Keyword(s):  
Turbulent Flow ◽  
Axial Velocity ◽  
Computational Study ◽  
Circular Cross Section ◽  
Maximum Velocity ◽  
Curvature Radius ◽  
Reynolds Stresses ◽  
Dean Number ◽  
Number Range ◽  
Bend Pipe

The Reynolds–averaged Navier–Stokes (RANS) equations were solved along with Reynolds stress model (RSM), to study the fully-developed unsteady and anisotropic single-phase turbulent flow in 90° bend pipe with circular cross-section. Two flow configurations are considered the first is without ribs and the second is with ribs attached to solid walls. The number of ribs is 14 ribs regularly placed along the straight pipe. The pitch ratios is 40 and the rib height e (mm) is 10% of the pipe diameter. Both bends have a curvature radius ratio, of 2.0. The solutions of these flows were obtained using the commercial CFD software Fluent at a Dean number range from 5000 to 40000. In order to validate the turbulence model, numerical simulations were compared with the existing experimental data. The results are found in good agreement with the literature data. After validation of the numerical strategy, the axial velocity distribution and the anisotropy of the Reynolds stresses at several downstream longitudinal locations were obtained in order to investigate the hydrodynamic developments of the analyzed flow. The results show that in the ribbed bend pipe, the maximum velocity value is approximately 47% higher than the corresponding upstream value but it is 9% higher in the case of the bend pipe without ribs. It was also found for both cases that the distribution of the mean axial velocity depends faintly on the Dean number. Finally, it can be seen that the analyzed flow in the bend pipe without ribs appears more anisotropic than in bend pipe with ribs.

SAF file: It's really three dimensional file

2018 ◽  
Vol 14 (1) ◽  
pp. 1
Author(s):  
Prof. Dr. Jamal Aziz Mehdi
Keyword(s):  
Cross Section ◽  
Root Canal ◽  
Three Dimensional ◽  
Circular Cross Section ◽  
Circular Motion ◽  
Root Canal Treatment ◽  
Metal Core ◽  
Rotating Blade

The biological objectives of root canal treatment have not changed over the recentdecades, but the methods to attain these goals have been greatly modified. Theintroduction of NiTi rotary files represents a major leap in the development ofendodontic instruments, with a wide variety of sophisticated instruments presentlyavailable (1, 2).Whatever their modification or improvement, all of these instruments have onething in common: they consist of a metal core with some type of rotating blade thatmachines the canal with a circular motion using flutes to carry the dentin chips anddebris coronally. Consequently, all rotary NiTi files will machine the root canal to acylindrical bore with a circular cross-section if the clinician applies them in a strictboring manner

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