Content  Background Information  Related Useful Properties  Mesh Independence Study  Taylor-Couette Validation  Wavy Taylor Validation  Turbulent Validation  Thermal Validation  Simple Model Test  Plans for Next Period

Background InformationBackground Information

Classical Types of Taylor VorticesClassical Types of Taylor Vortices Laminar Couette Flow According to the stability analysis without considering the viscous, the flow inside the cylinders should be always instable when outer cylinder is kept fixed. However, viscosity has an important stabilizing influence at low Reynolds numbers. Stability will be broken only if the angular velocity of inner cylinder exceeds a critical value.

Classical Types of Taylor VorticesClassical Types of Taylor Vortices Taylor vortex forms when Re exceeds Re c When the angular velocity of the inner cylinder is increased above a certain threshold, Couette laminar flow becomes unstable and a secondary steady state characterized by axi-symmetric toroidal vortices, known as Taylor vortex flow, emerges.

Classical Types of Taylor VorticesClassical Types of Taylor Vortices Wavy taylor vortex forms when Re exceeds Re c2 Subsequently increasing the angular speed of the cylinder the system undergoes a progression of instabilities which lead to states with greater spatio-temporal complexity, with the next state being called as Wavy Vortex Flow. The rotational speed approximately 20% higher than the critical speed for transition to Taylor vortices.

Classical Types of Taylor VorticesClassical Types of Taylor Vortices Chaotic Flow Happens Before Fully Turbulence The flow undergoes a series of transitions before it becomes fully turbulent. By using spectral method, there is only one peak at the initial period of the wavy vortex flow, while more peaks will be formed when Re is increasing, this period is called Chaotic Flow until no peaks appear.

Terminology k- Thermal Conductivity or circumferential wave number ν - Kinematic Viscosity u θ - Azimuthal Velocity u 0 - Tangential Velocity of Inner Cylinder r- Distance from Centre Axis N-number of cells m-number of azimuthal waves ω -fundamental angular frequency of the wave Radius Ratio η =R 1 /R 2 Gap Width d=b-a Aspect Ratio Г =H/d Re=R 1 Ω d/ ν Axial Wavelength λ =2H/N=(2 Г /N)d Wave Speed s= ω /(m Ω ) Mean Equivalent Conductivity Keq= -h*r*ln(R 1 /R 2 )/k h- Convective Heat Transfer Coefficient R 1 - Radius of Inner Cylinder R 2 - Radius of Outer Cylinder H- height Ω - angular velocity of inner cylinder

Important ParametersImportant Parameters  Rec  Aspect ratio  Axial wavelength  Wave number  Endwall  Wave speed  Flow profile 与 axial flow 以及温度场的关系

Mesh Independence Study Objectives & Methodology  After comparing with experiment data, we can find the minimum mesh density that can appropriately simulate the physical phenomenon. With such confidence, a more reasonable mesh structure would be selected as a final reference for the later mesh building.  All the boundary conditions are kept the same with changing the mesh grid numbers only.  The length was cut into half to save computing time. Radial Grids Axial Grids Circle Grids

Mesh Independence Study Boundary Conditions  R 1 =0.1906m R 2 =0.2622m H=1.6714m (full length)  Re=4Re c Ω = rad/s  End walls are rotating with inner cylinder while outer was fixed  Laminar mode  Fluid: Water (µ= kg/m-s ρ =998kg/m 3 ν =1.005*e-6 m 2 /s)

Mesh Independence StudyMesh Independence Study Circle Grids Radial Grids Axial Grids Cells Numbe r Residual for Continuity Accordingly Wavelength E E *Axial grid number here is for full length. In computing convenience, the number was cut into half of that in the form. *The experimental value of wavelength is 1.59 No influence on the cells number for decreasing the circle grid number. So keep it as 100.

Mesh Independence StudyMesh Independence Study Circle Grids Radial Grids Axial Grids Cells Numb er Residual for Continuity Accordingly Wavelength E E E E *Axial grid number here is for full length. In computing convenience, the number was cut into half of that in the form. *The experimental value of wavelength is 1.59 No influence on the cells number for an interval of circle grid numbers.

Mesh Independence StudyMesh Independence Study Cross Section View with MeshCross Section View with Mesh

Mesh Independence StudyMesh Independence Study  According to the above figures, simulation shall be kept reasonable with each cell shares at least 3 grid axial. In order to achieve relatively accurate result, the one with axial grid number of 400 is selected as the reference.

Mesh Independence StudyMesh Independence Study Circle Grids Radial Grids Axial Grids Cells Numb er Residual for Continuity Accordingly Wavelength E-02N/A E E E-02N/A *Axial grid number here is for full length. In computing convenience, the number was cut into half of that in the form. *The experimental value of wavelength is The minimum for the radial grid number is 60.

Mesh Independence StudyMesh Independence Study  According to the real computing condition, the mesh with circle 100, radial 60 and axial 400 (full length) is good enough which can be regarded as the reference for later mesh building. Conclusion

Taylor-Couette Validation Objectives & Methodology  After comparing with the experiment data from J.E. Burkhalter & E.L. koschmieder (1974) and check wavelength versus taylor number. We shall confirm that fluent is able to simulate the Taylor- Couette phenomena.

Taylor-Couette Validation Boundary Conditions  Since author have mentioned that neither the end wall nor the column length have significant influence on the experiment result, so we kept the same boundary condition with former mesh independence study, only changing the taylor number which is exact a non- dimension value.

Taylor-Couette ValidationTaylor-Couette Validation Wavelength T/Tc Full Length Typical wavelengths after sudden starts

Taylor-Couette Validation Conclusion  From above figure, we tried both full length and half length geometries to run cases with different taylor numbers. The results under 8Tc are well fit with the experiment data. Those above 8Tc are absolutely among the wavy taylor vortices period which will possibly cause the unstable measurement for the wavelength. However, the discrepancy is acceptable

Wavy Taylor Validation Objectives & Methodology  Taking KIKG,G. P., Lr, Y., LEE, W., SWINNEY, H. L. & MARCUS, P.S Wave speeds in wavy Taylor-vortex flow. J. Fluid Mech. 141, as the reference paper to compare with. Check wave speed versus different radius ratio which is the most significant factor.  Set measure point located in the gap centre from 2D cross section view to record the z-velocity during the time interval which can derive the fundamental frequency of the azimuthal waves. m can be observed by applying Tecplot to stretch out the cylinder. 插入示 意图

Wavy Taylor Validation Boundary Conditions *All the meshes are built with reference of “ ” which has been mentioned in the former part. η (R1/R2)R1(cm)R2(cm)H(cm)Re(11Rc) Ω (rad/s) Upper Boundcircumradialaxial Free Free Free  Laminar mode  Fluid: Water (µ= kg/m-s ρ =998kg/m3 ν =1.005*e-6 m2/s)  Keep Г =30, Re=11Rc, λ /d=2.4

Wavy Taylor ValidationWavy Taylor Validation η (R1/R2)R1(cm)R2(cm)H(cm)Re(11Rc) Ω (rad/s) Upper Boundcircumradialaxial Free Fundamental angular frequency ω = s= ω /(m Ω )=0.334

Wavy Taylor ValidationWavy Taylor Validation Two fundamental frequencies ω = s= ω /(m Ω )=0.362 η (R1/R2)R1(cm)R2(cm)H(cm)Re(11Rc) Ω (rad/s) Upper Boundcircumradialaxial Free

Wavy Taylor ValidationWavy Taylor Validation Fundamental angular frequency ω = s= ω /(m Ω )=0.458 η (R1/R2)R1(cm)R2(cm)H(cm)Re(11Rc) Ω (rad/s) Upper Boundcircumradialaxial Free

Wavy Taylor Validation Conclusion η (a/b)Computed S1Measured S ± ± ±0.001 The difference is located in the reasonable region of uncertainty Need to be calculated longer. Dependence of s1 on radius ratio

Turbulent Validation Objectives & Methodology Comparison of normalized mean angular momentum pro fi les between present simulation (Re=8000) and the experiment of Smith & Townsend (1982).  Using two models (k-epsilon and k- omega) to compare with the experiment data (left), after which an appropriate model would be selected for later calculation.  Couple of measure points are located in the midline across the gap from 2D view of the cross section. They are applied to record the tangential velocity during time interval and calculate the average value. 插入示意图

Turbulent Validation Boundary Conditions R 1 = m R 2 = m Ω = rad/s (Re=17295) H = 1.80 m End walls are free surfaces k- epsilon and k- omega were chosen to compare Fluid: Water (µ= kg/m-s ρ =998kg/m3 ν =1.005*e-6 m2/s) Mesh Density Axial = 400 Circle = 100 Radial = 60

Turbulent Validation Comparing with Experiment Data

Turbulent Validation Conclusion  Flow time interval is not enough ΔT epsilon =27.68s ΔT omega =20.48s  Sampling frequency f experiment =10kHz f simulation =200Hz  Mesh density Tip: 文章名称 used k-epsilon as the turbulent model

Thermal Validation Objectives & Methodology Variation of mean equivalent conductivity with Reynolds number for different Grashof numbers  By comparing with experiment data from K.S. Ball (1989), we would confirm the capability of fluent on simulating the heat transfer for taylor- couette flow.  We simplified the condition by ignore the effect of both conduction and radiation which will cause at most 5% error but saving much calculating time. Average heat transfer coefficient in the inner cylinder surface can be directly achieved from fluent.

Thermal Validation Boundary Conditions K eq = -h*r*ln(R 1 /R 2 )/k Re = Ω* (R 1 -R 2 )*R 1 /ν R 1 = cm R 2 = cm H = cm Gr= 1000 ΔT= K Ti = 293K To= K End walls are fixed and insulated Fluid: Air (k=0.0257w/m-k β=3.43*e -3 1/k ν=15.11*e -6 m 2 /s) Re=[ ] Ω=[ ] rad/s Since for η=0.565 Re c = 70, All the three cases are in laminar mode. Mesh Density Axial = 1000 Circle = 100 Radial = 60

Comparing with Experiment Data Re 2 h(w/m 2 k)k eq Experiment DataResidue e e e-03

Comparing with Experiment Data

Possible Reasons for Difference  Boundary condition set-up ideal gas, pressure based, real apparatus error (axial temperature gradient, end walls effect)  Wrong understanding of the experiment

Simple Model TestSimple Model Test R 1 = mm R 2 = 97.5 mm Height = 140 mm Q=4 L/min V in = m/s T in = 308K T out = 551K Ω= rad/s End walls are fixed and insulated Measure points are located in the vertical lines close to the inner cylinder. Since for η=0.975 Re c = , In this case Re= So, it is in laminar mode.

Important TipsImportant Tips  Combined fl ows in annular space not only on the operating point (axial Reynolds and Taylor numbers), but also e and strongly e on geometry and, to a lesser degree, on parietal thermal conditions.

Plans for Next PeriodPlans for Next Period  Keep running both of the turbulent cases  Finish the thermal validation  Repeat Taylor-couette validation with full length  Wavy validation should be finished with running 0.95 case long enough  More validation of the thermal part (optional)  Keep turbulent case running  Finish simple model test  Check geometry related paper