TLC experimental measurements were conducted, to study the effect of an aerothermal performances of a 30:1 PMMA scaled trailing edge (TE) model reproducing an internal cooling system under stationary and rotating conditions. The studied geometry, selected capitalizing the experience about industrial collaboration, reproduces the typical shape of ribbed surface (with an angular orientation of 60 [deg] with respect to the radial direction) of a high pressure turbine blade TE, with one row of enlarged pedestals. The airflow pattern inside the device simulates a highly loaded rotor blade cooling scheme with a 90[deg] turning flow from the radial hub inlet to the tangential TE outlet. Detailed heat transfer coefficient 2D maps describing the experimental results of the effect of different rotating number [in the range from 0 to 0.3 for a fixed Reynolds number of 10000, and in the range from 0 to 0.15 corresponding to diverse Reynolds number varying from 20000 to 40000] are presented. The effect of the rotation on the heat transfer variation at different Reynolds number is highlighted by a comparison with static settings at the same flow conditions.
TLC Measurements of Heat Transfer Under Rotating Conditions at High Reynolds Number in an Innovative Trailing Edge Cooling System
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Beniaiche, A, Bonanni, L, & Carcasci, C. "TLC Measurements of Heat Transfer Under Rotating Conditions at High Reynolds Number in an Innovative Trailing Edge Cooling System." Proceedings of the ASME 2012 Gas Turbine India Conference. ASME 2012 Gas Turbine India Conference. Mumbai, Maharashtra, India. December 1, 2012. pp. 413-422. ASME. https://doi.org/10.1115/GTINDIA2012-9560
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