TRAILING EDGE TIP COOLING OF BLADE OF A GAS TURBINE BLADE

The present technique presents a blade (1) for a gas turbine (10). The blade (1) includes an airfoil (100) having an airfoil tip (100a) and a pressure side (102) and a suction side (104) meeting at a leading edge (106) and a trailing edge (108) and defining an airfoil cavity (100s). A squealer tip (...

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Bibliographic Details
Main Authors RATHMANN, Ulrich, HOFFMANN, Willy H, BRANDL, Herbert, KRUECKELS, Joerg
Format Patent
LanguageEnglish
French
German
Published 24.07.2024
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:The present technique presents a blade (1) for a gas turbine (10). The blade (1) includes an airfoil (100) having an airfoil tip (100a) and a pressure side (102) and a suction side (104) meeting at a leading edge (106) and a trailing edge (108) and defining an airfoil cavity (100s). A squealer tip (60) is arranged at the airfoil tip part (100a). The squealer tip (60) comprises a suction side rail (64) and a pressure side rail (62) meeting at a trailing edge tip portion (70) of the squealer tip (60) and thus defining a squealer tip pocket (60s). The squealer tip pocket (60s) includes tip cooling holes (65a, 65b) that provide cooling air from the airfoil cavity (100s) to the squealer tip pocket (60s). The trailing edge tip portion (70) of the squealer tip (60) includes a chamfer (90) disposed towards the pressure side (102) of the airfoil (100), and a groove (80) extending between the chamfer (90) and the squealer tip pocket (60)s to provide cooling air from the squealer tip pocket (60s) to the chamfer (90).
Bibliography:Application Number: EP20200207341