Suscripción a Biblioteca: Guest
Página principal de la Biblioteca Digital de ICHMT Año actual Archivos Comité Ejecutivo Centro Internacional de Transferencia de Calor y Masa


DOI: 10.1615/ICHMT.2000.TherSieProcVol2.710
155 pages

Miroslav Rusevljan
Department for Termotechniqe and Process Engineering, Faculty of Mechanical Engineering and Naval Architecture, Ivana Lucica 5, 10 000 Zagreb, Croatia

Zvonimir Guzovic
Faculty of Mechanical Engineering and Naval Architecture, University of Zagreb, Ivana Lucica 5, Zagreb, Croatia

Jasenko Josipovic
Start 6, Gotovcev vijenac 8/2, 10 000 Zagreb, Croatia


Improved cooling of typical internally air-cooled gas turbine vanes and blades is proposed, with the intention of reducing temperature gradients within the blade material. Inside and/or outside blade surfaces are covered with the graphite foil, which has an anisotropic heat conductivity, as well as with the protective metal foil. It is supposed that the good contact heat transfer between the blade material and the graphite foil can be assured by vacuum. On the rotor blades, artificial roughening of internal surfaces can compensate the low strength of the graphite foil, but with external surfaces the problem is more complex. Numerical calculations of temperature distribution, performed for typical heat transfer conditions, show advantages of applying the graphite foil with anisotropic heat conductivity. Temperature gradients are substantially reduced by applying the graphite foil on the inside and/or outside surfaces of the turbine blade, compared to the turbine blade of the same geometry but without the graphite foil. When applied to cooling passages, the graphite foil can reduce local concentrations of the heat flux, and thus the cooling-air consumption can also be reduced. Although there are technological problems that have to be solved to enable a successful application of this new approach to the cooling of vanes and blades, its potential in reducing temperature gradients within the turbine blade material, simplifying the cooling channels geometry, and thus the reduction of the cooling air flow rate and the pressure drop, seems to be worth of investigation.

ICHMT Digital Library

Bow shocks on a jet-like solid body shape. Thermal Sciences 2004, 2004. Pulsed, supersonic fuel jets - their characteristics and potential for improved diesel engine injection. PULSED, SUPERSONIC FUEL JETS - THEIR CHARACTERISTICS AND POTENTIAL FOR IMPROVED DIESEL ENGINE INJECTION
View of engine compartment components (left). Plots of temperature distributions in centreplane, forward of engine (right). CHT-04 - Advances in Computational Heat Transfer III, 2004. Devel... DEVELOPMENT AND CURRENT STATUS OF INDUSTRIAL THERMOFLUIDS CFD ANALYSIS
Pratt & Whitney's F-135 Joint Strike Fighter Engine under test in Florida is a 3600F class jet engine. TURBINE-09, 2009. Turbine airfoil leading edge stagnation aerodynamics and heat transfe... TURBINE AIRFOIL LEADING EDGE STAGNATION AERODYNAMICS AND HEAT TRANSFER - A REVIEW
Refractive index reconstructed field. (a) Second iteration. (b) Fourth iteration. Radiative Transfer - VI, 2010. Theoretical development for refractive index reconstruction from a radiative ... THEORETICAL DEVELOPMENT FOR REFRACTIVE INDEX RECONSTRUCTION FROM A RADIATIVE TRANSFER EQUATION-BASED ALGORITHM
Two inclusion test, four collimated sources. Radiative Transfer - VI, 2010. New developments in frequency domain optical tomography. Part II. Application with a L-BFGS associated to an inexa... NEW DEVELOPMENTS IN FREQUENCY DOMAIN OPTICAL TOMOGRAPHY. PART II. APPLICATION WITH A L-BFGS ASSOCIATED TO AN INEXACT LINE SEARCH