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.Full text not available from this repository.
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|
Actions (login required)