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Aero-Thermal Investigation of the Flow Developing in a 180-Degree Turn Channel

DOI: 10.1615/ICHMT.1994.IntSympHetatTransTurb.220
pages 301-312

Tony Arts
Turbomachinery & Propulsion Department, Von Kármán Institute for Fluid Dynamics, Rhode-Saint-Genése, B-1640, Belgium

Muriel Lambert de Rouvroit
von Karman Institute for Fluid Dynamics, 72 Chaussee de Waterloo B-1640 Rhode Saint Genese, Belgium

Guido Rau
von Karman Institute for Fluid Dynamics, 72 Chaussee de Waterloo B-1640 Rhode Saint Genese, Belgium

Paola Acton
von Karman Institute for Fluid Dynamics, 72 Chaussee de Waterloo B-1640 Rhode Saint Genese, Belgium

Abstract

The internal cooling of gas turbine blades is usually provided by air flowing through inner narrow passages. The latter are often connected by sharp 180 deg turns. The aerodynamic and associated convective heat transfer characteristics observed in this type of geometry are significantly influenced by strong secondary flows and flow separations. The purpose of the present experimental effort is to give a description as complete and detailed as possible of the multiple aspects of this particular flow pattern. The heat transfer measurements are obtained by means of a steady state method; the wall temperature distributions are quantified by using liquid crystals. Detailed velocity distributions are performed by means of a two-component Laser Doppler Anemometry system. Surface flow visualizations are conducted through the use of an ink dot matrix and solvent film technique.

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