Analysis and test of coolant flow and heat transfer of an advanced full-coverage film-cooled laminated turbine vane
Abstract
The main objective of the present investigation is related to the establishment of an advanced cooling configuration for gas turbines operating at high temperatures. A turbine vane for studies of 'full coverage film cooling' approaches was prepared with the aid of the diffusion bonding method. The turbine vane is composed of 400 wafers, fabricated by photochemical etching procedures and laminated in the chordwise direction. The vane has curved film-cooling holes and is formed with only four kinds of wafers. A numerical analysis was conducted to determine the total coolant flow rate and details regarding the flow conditions at the individual coolant passage. A cascade test was performed to obtain experimental data. There was fairly good agreement between computed and experimental results.
- Publication:
-
American Society of Mechanical Engineers
- Pub Date:
- April 1982
- Bibcode:
- 1982gatu.conf.....Y
- Keywords:
-
- Computational Fluid Dynamics;
- Engine Coolants;
- Film Cooling;
- Gas Turbines;
- Heat Transfer Coefficients;
- Laminates;
- Vanes;
- Cascade Flow;
- Conductive Heat Transfer;
- Diffusion Welding;
- Flow Characteristics;
- Flow Measurement;
- Flow Velocity;
- Mach Number;
- Radiative Heat Transfer;
- Static Pressure;
- Wafers;
- Fluid Mechanics and Heat Transfer