DOI: 10.1615/ICHMT.1994.IntSympHetatTransTurb
ISBN Print: 1-56700-016-9
ISBN Print: 978-1-56700-016-0
Aero-Thermal Investigation of the Flow Developing in a 180-Degree Turn Channel
ABSTRAKT
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.