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ISSN Online: 2379-1748

ISBN Flash Drive: 978-1-56700-469-4

ISBN Online: 978-1-56700-470-0

Second Thermal and Fluids Engineering Conference
April, 2-5, 2017, Las Vegas, NV, USA

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

Get access (open in a dialog) pages 325-336
DOI: 10.1615/TFEC2017.cfn.017934

要約

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.