TURBINE BLADE PLATFORM COOLING HOLES

During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling...

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Bibliographic Details
Main Authors BOGNATZ Donald Joseph, OKPARA Nnawuihe Asonye, NEGRETE Estevan Daniel, DICK Aaron J, DUMITRASCU Marius
Format Patent
LanguageEnglish
Spanish
Published 18.08.2023
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:During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade. Durante la operación de un motor de turbina de gas, los álabes de turbina se someten a temperaturas extremadamente altas. Aunque se pueden proporcionar pasajes de enfriamiento internos dentro de los álabes de turbina para enfriar los alerones, las plataformas de los álabes de turbina también experimentan altas temperaturas. En una modalidad se proporcionan orificios de enfriamiento en cada plataforma para enfriar las ubicaciones defectuosas en la plataforma y mejorar la durabilidad de cada álabe de turbina.
Bibliography:Application Number: MX20230007216