Numerical Investigation of a Gas Turbine Stator Vane

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Numerical Investigation of a Gas Turbine Stator
Vane
Anantha Abhishek
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Objective
CFD Analysis of flow over Gas Turbine Stator
Vane Evaluation of various turbulence
models Evaluation of various inlet
conditions Verification of the results with
Experimental Data
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Assumptions

• Flow ? 2D, Steady and In Compressible
• Geometry ? Translational Periodic

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Geometric Details
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Geometric Details
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Model Description
Working Fluid Air Density (?) 1.1143
Kg /m3 Molecular Viscosity (m) 1.8528E-05
Ns/m Thermal Conductivity (k) 0.0263
Wm-1K-1 Specific Heat (Cp) 1007JKg-1K-1
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CFD Meshes
Grid for High Re Models
Grid for Low Re Models
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Boundary Conditions
Inlet BCs Velocity 5.85 ms-1, Temperature
292.2 K Normal to Boundary Outlet BCs Outflow
(Unit weightage) Periodic Faces Periodic
BC Blade No Slip Wall Constant Heat Flux
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Cases
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Results 1. Y Distribution
Average 80
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Results 1. Y Distribution
Average 4
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Results 2. Velocity Distribution (m/s)
Velocity magnitude for Std k-e model
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Results 3. Normalized Velocity
Normalized velocity Magnitude at TI 0.6 from
L k-w SST R Std k-e
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Results 4. Temperature Distribution (K)
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Results 4. Temperature Distribution (K)
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Results 4. Temperature Distribution (K)
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Results 5. Stanton Number Distribution
High Re Models
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Results 5. Stanton Number Distribution
High Re Models
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Results 5. Stanton Number Distribution
Higher TI, Higher the Heat Transfer
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Results 6. Relative Static Pressure
Distribution (Pa)
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Results 7. Static Pressure Coefficient
Cp variation along stator vane for Experimental
and V2F model 1 D with Realizability
constraint F without.
Cp variation along the vane surface for k-e and
k-w SST model
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Conclusions

• Out of the higher Re number turbulence models
  evaluated, k-e with standard wall function
  predicted the Stanton number better compared to
  experimental results. In the same line, for low
  Re models, k-w SST did a reasonable job.
• Higher order schemes always gives better accurate
  results, though there is no significant
  difference between the higher order schemes
  themselves.
• Standard k-e models fails in this case, since it
  can not predict the flows with huge change in
  strain rates as the flow goes around the suction
  side of the airfoil.
• The pressure coefficient computed matches closely
  with the experimental value.
• Increase in the turbulence intensity increases
  the heat transfer rate.

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Thank You!!!