TRAILING EDGE TIP COOLING OF BLADE OF A GAS TURBINE BLADE

• Main Authors: RATHMANN, Ulrich, HOFFMANN, Willy H, BRANDL, Herbert, KRUECKELS, Joerg
• Format: Patent
• Language: English; 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

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).