Heat transfer technology for internal passages of air-cooled blades for heavy-duty gas turbines.
The present review paper, although far from being complete, aims to give an overview about the present state of the art in the field of heat transfer technology for internal cooling of gas turbine blades. After showing some typical modern cooled blades, the different methods to enhance heat transfer in the internal passages of air-cooled blades are discussed. The complicated flows occurring in bends are described in detail, because of their increasing importance for modern cooling designs. A short review about testing of cooling design elements is given, showing the interaction of the different cooling features as well. The special focus of the present review has been put on the cooling of blades for heavy-duty gas turbines, which show several differences compared to aero-engine blades.
Weigand
B
B
Institute for Aerospace Thermodynamics, University of Stuttgart, 70569 Stuttgart, Germany.
Semmler
K
K
von Wolfersdorf
J
J