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TURBINE-09. Proceedings of International Symposium on Heat Transfer in Gas Turbine Systems
August, 9-14, 2009, Antalya, Turkey

DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst


ISBN Print: 978-1-56700-263-8

EXPERIMENTAL DETERMINATION OF THE AERO-THERMAL PERFORMANCE OF HIGH PRESSURE GAS TURBINE BLADES

page 2
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.170
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RESUMO

Modern gas turbines work today at temperature levels far above the metal melting limit. In order to maintain reliability and life time, an accurate assessment of the operating conditions and of their consequences in terms of aero-thermal performance is an absolute requirement. Engine parts are hard to instrument; measuring details into the engine is difficult because of the limited space available and because of the local very harsh environment. An alternative approach is therefore needed. A lot of information is still expected from the experimental approach; proper turbulence and transition modelling, to only mention these two challenges, do still request extensive attention and validation.

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