Cooling scheme for the leading edge of a turbine blade of a gas turbine

A turbine blade (12) of a gas turbine comprises a radially extending airfoil (29) with a suction side (26) and pressure side (27), which extend each in axial direction between a leading edge (24) and a trailing edge of said airfoil (29), whereby said leading edge (24) is cooled by means of impingeme...

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Bibliographic Details
Main Author Shchukin, Sergey
Format Patent
LanguageEnglish
French
German
Published 12.06.2019
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 (12) of a gas turbine comprises a radially extending airfoil (29) with a suction side (26) and pressure side (27), which extend each in axial direction between a leading edge (24) and a trailing edge of said airfoil (29), whereby said leading edge (24) is cooled by means of impingement cooling with rows of radially distributed jets of a cooling medium impinging on the inner side of said leading edge (24), and whereby said row of radially distributed jets is generated at an internal web (16), which divides the hollow interior of the airfoil (29) into first and second cavities (15, 17), with the second cavity (17) being arranged at said leading edge (24). An enhanced cooling is achieved by said internal web (16) comprising two rows of radially distributed cooling medium supply holes (18, 19), through which cooling medium enters said second cavity (17) in form of impinging jets, whereby said cooling medium supply holes (18, 19) are oriented such that the directions of said jets of one row cross the directions of said jets of the other row.
Bibliography:Application Number: EP20140186560