Modelling of an advanced film cooling scheme for a gas turbine blade using TLC

DOI: 10.1615/ICHMT.2012.ProcSevIntSympTurbHeatTransfPal.230
pages 205-208

T. Borda
Department of Energy and Industrial Apparatus, Gdansk University of Technology,G.Narutowicza 11/12, 80-233 Gdansk, Poland

P. Flaszynski
Department of Energy and Industrial Apparatus, Gdansk University of Technology, G.Narutowicza 11/12, 80-233 Gdansk, Poland

P. Doerffer
The Szewalski Institute of Fluid-Flow Machinery, Polish Academy of Sciencies, Fiszera 14, 80-231 Gdansk, Poland

M. Jewartowski
Department of Energy and Industrial Apparatus, Gdansk University of Technology, G.Narutowicza 11/12, 80-233 Gdansk, Poland

Jan Stasiek
Department of Energy and Industrial Apparatus, Gdansk University of Technology, Narutowicza 11/12, Gdansk, Poland

Resumo

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.