The present contribution is devoted to the experimental study of the conjugate heat transfer in a turbine blade cooling cavity located near the trailing edge. The cooling scheme is characterized by a trapezoidal cross-section, one rib-roughened wall, and slots along two opposite walls. The Reynolds number, defined at the inlet of the test section, is set at 67,500 for all the experiments. The values of all the important nondimensional parameters characterizing the experiment, including the solid-to-fluid conductivity ratio, are engine-representative. Uniform heat flux is imposed along the outer side of the rib-roughened wall. The measurements are performed using three different ribbed walls, with thermal conductivities ranging from to . Highly resolved distributions of nondimensional temperature and Nusselt number over the rib-roughened wall are obtained by means of infrared thermography and finite element analysis. The impact of the conduction through the wall on the thermal performance is demonstrated by comparison with purely convective results, previously published by the authors on the same configuration.
Skip Nav Destination
e-mail: coletti@vki.ac.be
e-mail: scialanga@vki.ac.be
e-mail: arts@vki.ac.be
Article navigation
July 2012
Research Papers
Experimental Investigation of Conjugate Heat Transfer in a Rib-Roughened Trailing Edge Channel With Crossing Jets
Filippo Coletti,
Filippo Coletti
Department of Turbomachinery and Propulsion,
e-mail: coletti@vki.ac.be
von Karman Institute for Fluid Dynamics
, 1640 Rhode-St-Genèse, Belgium
Search for other works by this author on:
Manfredi Scialanga,
Manfredi Scialanga
Department of Turbomachinery and Propulsion,
e-mail: scialanga@vki.ac.be
von Karman Institute for Fluid Dynamics
, 1640 Rhode-St-Genèse, Belgium
Search for other works by this author on:
Tony Arts
Tony Arts
Department of Turbomachinery and Propulsion,
e-mail: arts@vki.ac.be
von Karman Institute for Fluid Dynamics
, 1640 Rhode-St-Genèse, Belgium
Search for other works by this author on:
Filippo Coletti
Department of Turbomachinery and Propulsion,
von Karman Institute for Fluid Dynamics
, 1640 Rhode-St-Genèse, Belgiume-mail: coletti@vki.ac.be
Manfredi Scialanga
Department of Turbomachinery and Propulsion,
von Karman Institute for Fluid Dynamics
, 1640 Rhode-St-Genèse, Belgiume-mail: scialanga@vki.ac.be
Tony Arts
Department of Turbomachinery and Propulsion,
von Karman Institute for Fluid Dynamics
, 1640 Rhode-St-Genèse, Belgiume-mail: arts@vki.ac.be
J. Turbomach. Jul 2012, 134(4): 041016 (11 pages)
Published Online: July 21, 2011
Article history
Received:
December 1, 2010
Revised:
February 11, 2011
Online:
July 21, 2011
Published:
July 21, 2011
Citation
Coletti, F., Scialanga, M., and Arts, T. (July 21, 2011). "Experimental Investigation of Conjugate Heat Transfer in a Rib-Roughened Trailing Edge Channel With Crossing Jets." ASME. J. Turbomach. July 2012; 134(4): 041016. https://doi.org/10.1115/1.4003727
Download citation file:
Get Email Alerts
Evaluating Thin-Film Thermocouple Performance on Additively Manufactured Turbine Airfoils
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
High-Resolution Measurements of Local Heat Transfer Coefficients From Discrete Hole Film Cooling
J. Turbomach (October,2001)
High-Resolution Measurements of Local Effectiveness From Discrete Hole Film Cooling
J. Turbomach (October,2001)
Heat Transfer Experiments in a Confined Jet Impingement Configuration Using Transient Techniques
J. Heat Transfer (September,2011)
Meso Scale Pulsating Jets for Electronics Cooling
J. Electron. Packag (December,2005)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Introduction
Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis
Thermal Design Guide of Liquid Cooled Systems
Thermal Design of Liquid Cooled Microelectronic Equipment