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Research Papers

A Combined Experimental and Numerical Investigation of the Flow and Heat Transfer Inside a Turbine Vane Cooled by Jet Impingement

[+] Author and Article Information
Emmanuel Laroche

The French Aerospace Lab,
ONERA,
Toulouse F31055, France
e-mail: emmanuel.laroche@onera.fr

Matthieu Fenot, Eva Dorignac, Jean-Jacques Vuillerme, Laurent Emmanuel Brizzi

PPRIME Institute,
Chasseneuil Futuroscope,
Futuroscope Chasseneuil F86962, France

Juan Carlos Larroya

Safran Aircraft Engines,
Moissy Cramayel,
Moissy Cramayel F77550, France

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 8, 2017; final manuscript received November 3, 2017; published online December 20, 2017. Editor: Kenneth Hall.

J. Turbomach 140(3), 031002 (Dec 20, 2017) (9 pages) Paper No: TURBO-17-1154; doi: 10.1115/1.4038411 History: Received September 08, 2017; Revised November 03, 2017

The present study aims at characterizing the flow field and heat transfer for a schematic but realistic vane cooling scheme. Experimentally, both velocity and heat transfer measurements are conducted to provide a detailed database of the investigated configuration. From a numerical point of view, the configuration is investigated using isotropic and anisotropic Reynolds-averaged Navier–Stokes (RANS) turbulence models. A hybrid RANS/large eddy simulation (LES) technique is also considered to evaluate potential unsteady effects. Both experimental and numerical results show a very complex three-dimensional (3D) flow. Air is not evenly distributed between different injections, mainly because of a large recirculation flow. Due to the strong flow deviation at the hole inlet, the velocity distribution and the turbulence characteristics at the hole exit are far from fully developed profiles. The comparison between particle image velocimetry (PIV) measurements and numerical results shows a reasonable agreement. However, coming to heat transfer, all RANS models exhibit a major overestimation compared to IR thermography measurements. The Billard–Laurence model does not bring any improvement compared to a classical k–ω shear stress transport (SST) model. The hybrid RANS/LES simulation provides the best heat transfer estimation, exhibiting potential unsteady effects ignored by RANS models. Those conclusions are different from the ones usually obtained for a single fully developed impinging jet.

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References

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Figures

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Fig. 4

Heat transfer determination principle

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Fig. 5

Fine mesh overview

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Fig. 3

PIV measurements planes

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Fig. 1

Experimental apparatus

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Fig. 6

Mesh overview for ZDES modeling

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Fig. 9

Velocity magnitude in a slice going through row 2 (CEDRE kω SST)

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Fig. 10

Mass flow rate distribution

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Fig. 11

Velocity magnitude distribution, PIV (top: plane (C), bottom: plane (D))

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Fig. 12

Velocity RMS distribution, PIV (top: plane (C), bottom: plane (D))

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Fig. 16

Velocity distribution/streamlines colored by velocity inside the hole

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Fig. 7

ZDES velocity magnitude overview

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Fig. 8

Fddes function distribution

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Fig. 17

Heat transfer coefficient distribution (top: Exp., middle: kω SST, bottom: Billard–Laurence)

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Fig. 13

Velocity magnitude distribution, plane (A) (top: PIV, middle: CEDRE RANS, bottom: CEDRE, ZDES)

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Fig. 14

Axial velocity RMS distribution, plane (A) (top: PIV, bottom: CEDRE kω SST)

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Fig. 15

Velocity magnitude distribution, plane (B), PIV

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Fig. 18

Heat transfer coefficient profile along the second column of holes

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