Film-cooling is commonly used in modern gas turbines to increase inlet temperatures without compromising the mechanical strength of the hot components. The main objective of the study reported here is the critical evaluation of the capability of CFD, to predict film-cooling on three-dimensional engine realistic turbine aerofoil geometries. To achieve this aim two different film-cooling systems for NGV aerofoils are predicted and compared against experiments. The application concerns the following turbine vanes: • the AGTB-B1 blade investigated by the “Institut fur Strahlantriebe of the Universitat der Bundeswehr Munchen (Germany)”; • the MT1 HP NGV investigated by QinetiQ (ex DERA, UK). In the first test case the application mainly focuses on the interaction between the main flow and the coolant jets on the leading edge of the cooled aerofoil. In the second case, vane heat transfer rate is predicted with the film-cooling system made of six rows of cylindrical holes in single and staggered configuration.

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