Nagapurwala, QH and Girigoswamy, H and Mohan, K (1987) Effect of variable geometry inlet guide vanes on the performance of a high speed compressor stage. Technical Report. National Aeronautical Laboratory, Bangalore,India.
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Abstract
This reprt describes the design and analysis of variable13; staglrer Inlet Guide Vanes (IGVS) to study their effect on the performance of a high speed, axial flow compressor stage. Aerodynamic design of the IGVs was carried out selecting an appropriate off- design point on the compressor performance map, corresponding to 60% design speed and 40% corrected mass flow rate. At design point, with axial inlet operating condition, the prewhirl imparted by the IGVs was kept zero. NACA 63-.(C A K ) 0613; aerofoils were choeen and the basic blading geometry was13; established using the available cascade data. A suitable turning mechinism was designed to vary the stagger angle setting of the IGVs.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | High speed compressor;Aerodynamic design;Stagger angle;Axial flow compressor stage |
| Subjects: | ENGINEERING > Electronics and Electrical Engineering AERONAUTICS > Aerodynamics |
| Division/Department: | Propulsion Division, Propulsion Division, Propulsion Division |
| Depositing User: | M/S ICAST NAL |
| Date Deposited: | 14 Nov 2006 |
| Last Modified: | 24 May 2010 09:53 |
| URI: | http://nal-ir.nal.res.in/id/eprint/3394 |
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