Krishnamoorthy, V and Pai, BR and Sreenath, GS (1991) Heat transfer study of a turbine blade cooling passage with ribs, pin fins and lateral ejection holes. In: International Symposium on Air Breathing Engines, 1-6 Sep 1991, Nottingham, England.Full text not available from this repository.
Detailed flow visualization and heat transfer investigations under uniform heat flux boundary conditions were carried out to obtain the heat transfer characteristics of an internal cooling passage of a turbine blade with rib elements, pin fins and with lateral flow of coolant from hub to tip through trailing edge ejection holes. For the passage geometry considered, the static pressure distribution in the passage was uniform and was equal to the value at the inlet indicating that the pressure drop was dominated by exit blockage. Assuming the predominant flow velocity in the passage to be equal to the mean inlet velocity, the heat transfer coefficient for the rib element and pin fin regions were estimated, using available correlations. The hydraulic mean diameter of the passage and the pin fin diameter were taken as the respective length scales in the correlating parameters. The estimated heat transfer coefficient in pin fin region was 130 percent of the value in the rib element region. The measured surface temperature distribution also indirectly indicated a similar trend. The estimated heat ried away by the coolant was in agreement with the net heat flux supplied within + or - 10 percent.
|Item Type:||Conference or Workshop Item (Paper)|
|Uncontrolled Keywords:||Cooling fins;Engine coolants;Flow visualisation;Heat transfer coefficients;Riblets;Turbine blades;Flow distribution;Heat flux;Holes (Mechanics)|
|Subjects:||ENGINEERING > Fluid Mechanics and Thermodynamics|
|Division/Department:||Propulsion Division, Propulsion Division, Aerodynamics|
|Depositing User:||M/S ICAST NAL|
|Date Deposited:||01 Apr 2008|
|Last Modified:||24 May 2010 09:55|
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