This paper presents our latest efforts in an ongoing program to improve the understanding of aerodynamic and thermal phenomena of internal blade cooling by forced convection and to incorporate this knowledge into predictive tools. The particular objectives of this program are to estimate the use of the 2D Particle Image Velocimetry technique and to produce experimental data obtained for various boundary conditions in order to anchor a computer code being developed in parallel. In this paper we compare the results of the investigations of the flow in two different configurations of the channel: 1) smooth internal walls, 2) internal walls of only one branch equipped with square profile ribs inclined at 90 ° to the main flow and placed on oppo...
In a 2-pass cooling system the pressure driven air flow dis-tribution is investigated experimentally...
International audienceThis paper investigates, both experimentally and computationally, the heat tra...
The flow field inside a cooling channel for the trailing edge of gas turbine blades has been numeric...
The internal cooling of turbine blades is an important part of overall blade cooling that is necessa...
A rotating cooling system with a 180 deg turn is investigated experimentally using the 2C PIV techni...
The present experimental study is dealing with a detailed aero/thermal investigation of the turbulen...
Numerical investigations of a two-pass internal cooling channel with engine-similar cross-sections w...
The present study deals with a detailed experimental investigation of the turbulent flow inside a ri...
The present study deals with a detailed experimental investigation of the turbulent flow inside a ri...
The present work is part of a wider research program which concerns the aero-thermal characterizatio...
The flow field inside a modern internal cooling channel specifically designed for the trailing edge ...
The purpose of this dissertation is to provide a strong background knowledge about the flow field be...
In the present study, a two-pass internal cooling channel with engine-similar cross-sections was inv...
Modern turbomachines operate at combustion temperatures well beyond the incipient melting point of t...
The present study deals with a detailed experimental investigation of the turbulent flow inside a ri...
In a 2-pass cooling system the pressure driven air flow dis-tribution is investigated experimentally...
International audienceThis paper investigates, both experimentally and computationally, the heat tra...
The flow field inside a cooling channel for the trailing edge of gas turbine blades has been numeric...
The internal cooling of turbine blades is an important part of overall blade cooling that is necessa...
A rotating cooling system with a 180 deg turn is investigated experimentally using the 2C PIV techni...
The present experimental study is dealing with a detailed aero/thermal investigation of the turbulen...
Numerical investigations of a two-pass internal cooling channel with engine-similar cross-sections w...
The present study deals with a detailed experimental investigation of the turbulent flow inside a ri...
The present study deals with a detailed experimental investigation of the turbulent flow inside a ri...
The present work is part of a wider research program which concerns the aero-thermal characterizatio...
The flow field inside a modern internal cooling channel specifically designed for the trailing edge ...
The purpose of this dissertation is to provide a strong background knowledge about the flow field be...
In the present study, a two-pass internal cooling channel with engine-similar cross-sections was inv...
Modern turbomachines operate at combustion temperatures well beyond the incipient melting point of t...
The present study deals with a detailed experimental investigation of the turbulent flow inside a ri...
In a 2-pass cooling system the pressure driven air flow dis-tribution is investigated experimentally...
International audienceThis paper investigates, both experimentally and computationally, the heat tra...
The flow field inside a cooling channel for the trailing edge of gas turbine blades has been numeric...