Turbinenschaufel

Details

Veröffentlichungs-Nr.

EP4764160

Anmeldetag

17. Dezember 2024

Veröffentlichung

24. Juni 2026

Rechtsraum

EP

IPC

F01D5/18, F01D5/20

Abstract

A turbine blade having a dovetail (7) and an airfoil (2) extending therefrom and having a tip (8) with a squealer cavity (9) formed therein, a leading edge (3) and a trailing edge (4) which are located opposite to each other, and a pressure side (6) and a suction side (5) which are opposite to each other and extend between the leading edge (3) and the trailing edge (4); wherein the turbine blade comprises an internal cooling system arranged in an internal space defined between the pressure side (5) the suction side (6), the trailing edge (4) and the leading edge (3); the internal cooling system comprising a serpentine second cooling passage (21) extending through the dovetail (7) and the airfoil (2) and having a second inlet (23) disposed in the dovetail (7), longitudinal first, second and third subpassages (21a, 21b, 21c) extending preferably through the entire extension of the airfoil (2) and successively connected with each other by turns being arched parts of the second cooling passage (21) and at least one second tip cooling hole (14) exiting in the squealer cavity (9) of the tip (8) and connected to an end of one of the first, second and third subpassage (21a, 21b, 21c); the cooling system further comprising a vertical row of third cooling holes (13) connected to the second cooling passage (21) and located in the area of trailing edge (4) of the airfoil (2); is characterized in that in the tip (8), in the vicinity of the trailing edge (3) at least one ventilation hole (16) is arranged, which is connected to the second cooling passage (21) and inclined with respect to the top surface of the tip (8) towards the trailing edge (4), for cooling a corner area formed by the tip (8) and the trailing edge (4) of the airfoil (2).

Anmelder

Firma

GE Aerospace Poland Sp. z o.o.

Land

🇵🇱 Polen