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AERO-THERMAL INVESTIGATION OF TURBULATOR CROSS SECTION SHAPE ON TURBINE COOLING CHANNELS

DOI: 10.1615/ICHMT.2014.IntSympConvHeatMassTransf.560
pages 743-754

Yavuzer Karakus
Aeronautical and Astronautical Engineering Department Istanbul Technical University, 34469 Istanbul, Turkey

Isa Kavas
Aerospace Engineering Department Middle East Technical University, 06531 Ankara, Turkey

Tolga Yasa
TUSAS Engine Industries, 26003 Eskisehir, Turkey

Abstract

Almost all the gas turbine blades are cooled by internal cooling channels in modern aero engines. The cooling effectiveness of such configuration is therefore a critical design choice. Those channels are generally equiped with square cross section turbolators (rib) in order to enhance the heat transfer. In this paper, the rib cross section is slightly modified and its effect on flow field and heat transfer are studied using numerical simulations. The square cross section is selected as a reference case and the simulation methodology is validated with experimental results. The manufacturing imperfections like rounded edges are the primary focus. Then, the effect of trapezoid shape is investigated. The results show that trapezoid shape has a pozitive effect on cooling effectiveness.

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