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主页 旧刊 有关人员 未来大会 American Society of Thermal and Fluids Engineering

ISSN 在线: 2379-1748

ISBN 打印: 978-1-56700-517-2 (Flash drive)

5-6th Thermal and Fluids Engineering Conference (TFEC)
May, 26–28, 2021 , Virtual

STRESS ANALYSIS OF GAS TURBINE BLADE WITH FILM COOLING

Get access pages 765-776
DOI: 10.1615/TFEC2021.fip.032224

摘要

The external surface of a gas turbine blade is exposed to hot gas and it is internally cooled with the air from the compressor. In a film-cooled blade, this relatively cold air enters the radial channels at the root of the blade and then exists through film holes. A high gradient of the temperature field takes place in a blade and further contributes to high mechanical stresses in blade material. Additionally, the blades of the turbine are subjected to high mechanical pressure resulting mainly from centrifugal forces. This study deals with effects of the temperature gradient, rotational velocity, and film cooling hole spacing (pitch) on structural stresses. A complex 3-D problem with a multidisciplinary approach consisting of a conjugate heat transfer (CHT) and static structural analysis is solved in this work with variations in rotational velocity and film hole pitch. The blade stress and deformation distribution in all cases are presented and the impact of the film cooling, rotational velocity, and film hole spacing on blade stress and deformation is discussed.
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