Effect of variable geometry inlet guide vanes on the performance of a high speed compressor stage

Nagapurwala, QH and Girigoswami, 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: Monograph (Technical Report)
Uncontrolled Keywords: High speed compressor;Aerodynamic design;Stagger angle;Axial flow compressor stage
Subjects: ENGINEERING > Electronics and Electrical Engineering
AERONAUTICS > Aerodynamics
Depositing User: M/S ICAST NAL
Date Deposited: 14 Nov 2006
Last Modified: 11 Aug 2015 06:29
URI: http://nal-ir.nal.res.in/id/eprint/3394

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