THMT-12. Proceedings of the Seventh International Symposium On Turbulence Heat and Mass Transfer
DOI: 10.1615/ICHMT.2012.ProcSevIntSympTurbHeatTransfPal
ISBN Print: 978-1-56700-302-4
ISSN: 2377-2816
Modelling of an advanced film cooling scheme for a gas turbine blade using TLC
pages 205-208
DOI: 10.1615/ICHMT.2012.ProcSevIntSympTurbHeatTransfPal.230
Краткое описание
The paper presents early stages of experiments of modeling of an advanced cooling scheme for a gas turbine. Main purpose of the research is to determine the effect of thermophysical parameters, the primary jet flow and blowing jet flow on the surface of gas turbine blades and the surface between blade cascades. Test section and methodology has been presented. Liquid Crystal Thermography and Particle Image Velocimetry as well as numerical calculations will be used during research.