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Heat Transfer Research
インパクトファクター: 0.404 5年インパクトファクター: 0.8 SJR: 0.264 SNIP: 0.504 CiteScore™: 0.88

ISSN 印刷: 1064-2285
ISSN オンライン: 2162-6561

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Heat Transfer Research

DOI: 10.1615/HeatTransRes.v42.i2.40
pages 143-164

Influence of Internal Cyclone Flow on Adiabatic Film Cooling Effectiveness

Andreas Lerch
Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, 64287 Darmstadt, Germany
Heinz-Peter Schiffer
Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, 64287 Darmstadt, Germany

要約

The adiabatic film cooling effectiveness on the surface of a symmetrical blade model was measured for eight cylindrical, 59° inclined cooling holes. The holes were fed with different flow types using a cylindrical leading-edge channel. Two configurations were compared: on the one hand, a leading-edge channel flow without swirl (datum configuration), using a sharp-edged inlet; on the other hand, a new cyclone cooling configuration with a positive swirl. The experiments were carried out using the calibrated ammonia diazo technique. The blowing ratios were varied between 0.6 and 1.2, and the film cooling discharge was set to either 20% or 50%. For all these operation points, multiple experiments were conducted and combined using a weighting average method to produce a high full-range resolution. The lateral and area-averaged adiabatic effectiveness is presented up to 45D downstream of the cooling holes. The measurements show a higher area-averaged effectiveness immediately downstream of the cooling holes when using the cyclone cooling configuration. This is due to nonsymmetric flow structures inside the cooling holes. Further downstream, however, it decreases faster. With a low film cooling discharge and rising blowing ratios, these effects are more pronounced.


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