TURBINE BLADE AIRFOIL PROFILE

A turbine blade for a gas turbine engine has an airfoil including leading (54) and trailing (54) edges joined by spaced-apart pressure and suction sides to provide an exterior airfoil surface extending from a platform (58) in a spanwise direction to a tip (60). The external airfoil surface is formed...

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Bibliographic Details
Main Authors ROY, Francois, ENNACER, Mohammed, LUYMES, Benjamin, TARDIF, Marc, DORAI, Jonathan
Format Patent
LanguageEnglish
French
German
Published 19.04.2023
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Summary:A turbine blade for a gas turbine engine has an airfoil including leading (54) and trailing (54) edges joined by spaced-apart pressure and suction sides to provide an exterior airfoil surface extending from a platform (58) in a spanwise direction to a tip (60). The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
Bibliography:Application Number: EP20220202022