Abstract
For the determination of the film‐cooling heat transfer, the design of a turbine blade relies on the conventional determination of the adiabatic film‐cooling effectiveness and heat transfer conditions for test configurations. Thus, additional influences by the interaction of fluid flow and heat transfer and influences by additional convective heat transfer cannot be taken into account with sufficient accuracy. Within this paper, calculations of a film‐cooled duct wall and a film‐cooled real blade with application of the adiabatic and a conjugate heat transfer condition have been performed for different configurations. It can be shown that the application of the conjugate calculation method comprises the influence of heat transfer within the cooling film. The local heat transfer rate varies significantly depending on the local position.
Highlights
Due to high turbine inlet temperatures in gas turbine engines, film-cooling iswidely used for the vanes and blades of the front stages in order to reduce materialtemperatures to levels of required acceptable life span of each component
The aim of the experimental and numerical studies is to receive a detailed understanding of the secondary flow development in the jets and to create a reliable database on the adiabatic film cooling effectiveness and heat transfer conditions
Detailed numerical analyses of the film cooling physics in the case of a flat plate with one row of cooling holes have been presented by Walters and Leylek [2] for cylindrical holes and by Hyams and Leylek [3] for shaped holes
Summary
Due to high turbine inlet temperatures in gas turbine engines, film-cooling iswidely used for the vanes and blades of the front stages in order to reduce materialtemperatures to levels of required acceptable life span of each component. The positive influence of shaped holes on film cooling is well known for a long time (e.g., Goldstein et al [1]), a large number of papers has been published in recent. The aim of the experimental and numerical studies is to receive a detailed understanding of the secondary flow development in the jets and to create a reliable database on the adiabatic film cooling effectiveness and heat transfer conditions. Bohn and Moritz [4] have performed a numerical study on the influence of hole shaping of staggered multi-hole configurations on the cooling-film secondary flows. Recent numerical studies on the leading edge filmcooling physics by York and Leylek [6, 7] focus on the determination of the adiabatic film cooling effectiveness and heat transfer coefficients. It becomes obvious that when applying heat transfer boundary conditions for numerical simulations based on conventional adiabatic analysis or fixed thermal boundary conditions, these effects cannot be taken into account
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