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 Inovative Trailing Edge Cooling System / Beniaiche Ahmed; Carcasci Carlo; Bonanni Leonardo. - ELETTRONICO. - (2012), pp. 1-8. (Intervento presentato al convegno ASME 2012 Gas Turbine India Conference, GTIndia2012-9560 tenutosi a Mumbai, Maharashtra, India nel December 1, 2012).
TLC Measurements of Heat Transfer Under Rotating Conditions at High Reynolds Number in an Inovative Trailing Edge Cooling System
CARCASCI, CARLO;
2012
Abstract
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.File | Dimensione | Formato | |
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