Turbinenmotorkomponente mit Kühlöffnung

Details

Veröffentlichungs-Nr.

EP4818470

Anmeldetag

7. April 2026

Veröffentlichung

7. Oktober 2026

Rechtsraum

EP

IPC

F01D5/18

Abstract

A turbine blade assembly (100) for a gas turbine engine (10) can include a cooling aperture (150) for local thermal heat management and to provide a cooling film along an exterior surface (134) of an airfoil (104) of the turbine blade assembly (100). The cooling aperture (150) is positioned within an outer wall (118) defining an interior (130) for the airfoil (104) and a cooling circuit (132) provides a cooling fluid flow to the cooling aperture (150). The cooling aperture (150) is at least partially defined by an outer surface (160), an inner surface (162), a first side (164), a second side (166), and a flared portion (170). The cooling aperture (150) exhausts at a diffuser outlet (156) extending between the first side (164) and the second side (166).

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA

Fachgebiete