Effect of discrete hole film injection on aerodynamic performance of a turbine cascade

Manickam, MD and Murugesan, K (1989) Effect of discrete hole film injection on aerodynamic performance of a turbine cascade. In: 9th International Symposium on Air Breathing Engines, Sep 1989, Athens, Greece.

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Abstract

The aerodynamic performance of a turbine cascade with single-row and double- row injection on the suction surface of the blade is studied. The aerodynamic performance of the blade is obtained under different conditions of injections, both in the midspan zone (which is free from mainstream secondary-flow effects) and near the endwall (at a location of strong mainstream secondary flow effects). A correction parameter is obtained for the measured loss so that the actual losses due to viscous and other dissipation effects can be estimated.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Aerodynamic characteristics;Cascade flow;Engine coolants;Film cooling;Turbine blades;Wind tunnel tests;Computational fluid dynamics;Gas turbines;Reynolds number
Subjects: AERONAUTICS > Aerodynamics
Division/Department: Propulsion Division, Other
Depositing User: shankar sk nadoor
Date Deposited: 26 Oct 2006
Last Modified: 24 May 2010 09:52
URI: http://nal-ir.nal.res.in/id/eprint/3144

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