Singh, Karan and Murugesan, K (1974) Design of a highly loaded gas turbine stage. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
The report deals with the design of a model turbine simulation a highly loaded axial turbine stage, which is to be employed to investigate and optimise the performance and the efficiency levels for such stages. The flow parameters for the model turbine have been decided on the basis of similarity conditions keeping in mind the limitations of the in-house test rig facility for the blades free vortex design has been initially adopted to obtain a base-line performance level. The complete aerodynamic design of the blades is detailed in this report, highlighting the methodical procedure evolved for such a design.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Gas turbine stage;Aerothermodynamic design;Rotor blade |
| Subjects: | AERONAUTICS > Aerodynamics |
| Division/Department: | Propulsion Division, Propulsion Division |
| Depositing User: | M/S ICAST NAL |
| Date Deposited: | 10 Nov 2006 |
| Last Modified: | 24 May 2010 09:53 |
| URI: | http://nal-ir.nal.res.in/id/eprint/3313 |
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