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Numerical and experimental investigation of turbine blade film cooling

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Abstract

The blades in a gas turbine engine are exposed to extreme temperature levels that exceed the melting temperature of the material. Therefore, efficient cooling is a requirement for high performance of the gas turbine engine. The present study investigates film cooling by means of 3D numerical simulations using a commercial code: Fluent. Three numerical models, namely k-ε, RSM and SST turbulence models; are applied and then prediction results are compared to experimental measurements conducted by PIV technique. The experimental model realized in the ENSEMA laboratory uses a flat plate with several rows of staggered holes. The performance of the injected flow into the mainstream is analyzed. The comparison shows that the RANS closure models improve the over-predictions of center-line film cooling velocities that is caused by the limitations of the RANS method due to its isotropy eddy diffusivity.

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Abbreviations

x, y, z:

Cartesian coordinates (mm)

U:

Axial velocity component (m.s−1)

V:

Vertical velocity component (m.s−1)

T:

Temperature (°C)

y+ :

Dimensionless value of y (mm)

Ue :

Crossflow inlet velocity (m.s−1)

Ui :

Injection flow velocity (m.s−1)

D:

Diameter of the jet hole (mm)

K:

Turbulent kinetic energy (m2.s−2)

M:

Blowing ratio

α:

Jet angle inclination (°)

δ:

Boundary layer thickness (mm)

\( {\ \upmu}_{\mathrm{t}} \) :

Eddy viscosity

ω:

Dissipation frequency rate (s−1)

\( {\mathrm{u}}^{\ast } \) :

Friction velocity (m.s−1)

\( {\uptau}_{\mathrm{w}} \) :

Wall shear stress (kg.m.s−2)

\( {\ \uprho}_{\mathrm{e}} \) :

Injection density flow (kg.m−3)

\( {\ \uprho}_{\mathrm{i}} \) :

Main density flow (kg.m−3)

ε:

Turbulent energy dissipation (m2.s−3)

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Acknowledgements

The reported work was performed within the LMESC of the USTHB University research project “Aerothermal Investigation of Turbine Blades”. The present work was partially supported by ISAE-ENSMA Schools (P′ institute), University of Poitiers in France. The welcome received for conducting the experiments is gratefully acknowledged by the authors. The authors would like to warm fully acknowledge Prof. Eva Dorignac and Dr. Gildas Lalizel for their precious and fundamental support in this activity.

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Authors and Affiliations

  1. Energy Mechanics and Conversion Laboratory (LMESC), Mechanical Engineering Department, USTHB University, 32, El Alia, 16111, Bab Ezzouar, Algiers, Algeria

    Amar Berkache & Rabah Dizene

Authors
  1. Amar Berkache
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  2. Rabah Dizene
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Correspondence to Amar Berkache.

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Berkache, A., Dizene, R. Numerical and experimental investigation of turbine blade film cooling. Heat Mass Transfer 53, 3443–3458 (2017). https://doi.org/10.1007/s00231-017-2062-z

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