Influence of aerodynamic parameters on the heat transfer in gas turbine blade cascade

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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