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

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.

Full text available as:
[img] PDF
Restricted to Archive staff only

Download (573Kb)

    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

    Actions (login required)

    View Item