Thermal Behaviour Analysis of a Leading Edge Ribbed Channel Using Crystal Technique

摘要

The continuous developing of gas turbines as Aeroengines leads the designers to the reaching of higher performances in terms of increasing operating temperatures and lower emissions standards. Thus the necessity for more effective blade cooling, in order to maintain the metal temperature fields at levels consistent with blade design life, is required. This work intends to give informations about the thermal behaviour of the fluid inside a turbine blade cooling system. We analyzed a 5:1 model of an actual blade cooling system (leading edge ribbed channel) designed by FiatAvio, in order to retrieve the surface heat transfer coefficient distribution inside the model we used a transient method based on Thermochromic Liquid Crystal technique. To control the results provided from image analysis and data reduction we compared our results with those coming from correlations available in literature. From image visualization and surface heat transfer maps we are able to see how the geometry of the system influences the heat transfer inside the blade.