The Numerical Modelling Of Heat Transfer In Turbine Blades

Advanced aircraft engines employ turbine entry temperatures so high that cooling of the turbine blades is crucial. This paper focuses on the ribs generally used to enhance the heat transfer in turbine blade cooling passages. Secondary flows associated with these ribs are responsible for significant...

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Bibliographic Details
Published in:WIT Transactions on Engineering Sciences 1994-01, Vol.5
Main Authors: Visser, J A, Lippert, A M, J. du Plessis
Format: Article
Language:English
Subjects:
Aerodynamics
Aircraft engines
Computational fluid dynamics
Computer simulation
Cooling
Ducts
Fluid flow
Heat transfer
Reynolds number
Ribs (structural)
Turbine blades
Turbines
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Summary:Advanced aircraft engines employ turbine entry temperatures so high that cooling of the turbine blades is crucial. This paper focuses on the ribs generally used to enhance the heat transfer in turbine blade cooling passages. Secondary flows associated with these ribs are responsible for significant local heat transfer variations. Furthermore, the ribs produce a complex flow structure so that there is continuing need for a better understanding of the flow physics in ribbed ducts. The flow in a channel with four consecutive ribs on two opposite walls and a blockage ratio equal to 0.063 were simulated for angles of 90° and 60° to the flow direction and a Reynolds number of 80000. An inlet condition approximating fully developed flow in a smooth duct were used. In the case of the 60° angl
ISSN:1746-4471
1743-3533
DOI:10.2495/HT940641