Turbinenmotorkomponente mit Kühlöffnung

Details

Veröffentlichungs-Nr.

EP4814258

Anmeldetag

25. März 2026

Veröffentlichung

30. September 2026

Rechtsraum

EP

IPC

F01D5/18

Abstract

A turbine blade assembly (100) for a gas turbine engine (10) can include a cooling aperture (140) for local thermal heat management and to provide a cooling film along an exterior (134) of an airfoil (104). The cooling aperture (140) is positioned within an outer wall (118) of the airfoil (104) defining an interior (130) for the airfoil (104) and a cooling circuit (132) provides a cooling fluid flow to the cooling aperture (140). The cooling aperture (140) includes a cavity (142) at least partially defined by an outer surface (148), an inner surface (156), a first side (150), and a second side (152). The cavity (142) exhausts at a diffuser outlet (144) extending between the first side (150) and the second side (152).

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA

Fachgebiete