Abstract
Every modern high-pressure turbine needs a highly sophisticated cooling system. The most frequently used cooling method of to date is film cooling, characterized by a high degree of interaction between the main flow and the cooling flow. Therefore the effects of film cooling have to be taken into account in the aerodynamic design of film cooled high-pressure turbines.
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Hildebrandt, T. et al. (2006). UNSTEADY 3D NAVIER-STOKES CALCULATION OF A FILM-COOLED TURBINE STAGE WITH DISCRETE COOLING HOLE. In: Hall, K.C., Kielb, R.E., Thomas, J.P. (eds) UNSTEADY AERODYNAMICS, AEROACOUSTICS AND AEROELASTICITY OF TURBOMACHINES. Springer, Dordrecht. https://doi.org/10.1007/1-4020-4605-7_39
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DOI: https://doi.org/10.1007/1-4020-4605-7_39
Publisher Name: Springer, Dordrecht
Print ISBN: 978-1-4020-4267-6
Online ISBN: 978-1-4020-4605-6
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