Krishnamoorthy, V (1981) Influence of aerodynamic parameters on the heat transfer in gas turbine blade cascade. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
A technique was developed to obtain the local heat transfer coefficient under constant heat flux boundary condition.13; Initial experiments were done on a model cylinder to ascertain the accuracy of the technique. Subsequently a turbine blade model was fabricated with 22 surface, thermocouples, experiments were conducted in a two dimensional subsonic cascade tunnel (Tunnel A) with a five bladed cascade assembly. The heat transfer blade was located in the middle. In addition the surface pressure distribution was also obtained by replacing the heat transfer blade by a blade model with 20 surface pressure tappings
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Aerodynamic parameters;Blade cascade;Heat transfer;Gas turbine |
| Subjects: | AERONAUTICS > Aircraft Propulsion and Power |
| Division/Department: | Propulsion Division |
| Depositing User: | Mr. Ravikumar R |
| Date Deposited: | 27 Nov 2006 |
| Last Modified: | 24 May 2010 09:53 |
| URI: | http://nal-ir.nal.res.in/id/eprint/3510 |
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