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Second Thermal and Fluids Engineering  Conference

ISSN: 2379-1748
ISBN: 978-1-56700-430-4

A NUMERICAL STUDY ON THE EFFECTS OF NUMBER OF JETS ON SWIRL COOLING OF A GAS TURBINE BLADE LEADING EDGE

Zhao Liu
Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment, School of Energy & Power Engineering, Xi'an Jiaotong University, Xi'an, Shaanxi 710049, China

Jun Li
Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment, School of Energy & Power Engineering, Xi'an Jiaotong University, Xi'an, Shaanxi 710049, China

Zhenping Feng
Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment, School of Energy & Power Engineering, Xi'an Jiaotong University, Xi'an, Shaanxi 710049, China

Terrence W. Simon
Department of Mechanical Engineering, University of Minnesota, 111 Church St. S.E., Minneapolis, Minnesota 55455, USA

Abstract

In this paper, a numerical simulation is performed to characterize swirl cooling of the first stage rotor blade internal leading edge cooling passage of a GE-E3 high-pressure gas turbine. The swirling cooling performance is investigated for cases of rectangular section inlets that cause flow to impinge tangentially on the internal surface of the leading edge cooling passage. The effects of Reynolds number and number of jet nozzles, for cases with and without variations of total jet nozzle area, on the local and average flow losses and heat transfer performance are investigated. The results present the increasing pattern in pressure losses and globally-averaged Nusselt numbers of the swirl chamber with Reynolds number and the number of jet nozzles, especially when the total jet nozzle area is fixed.

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