Turbinentriebwerk für ein Flugzeug mit Integriertem Rahmen

Details

Veröffentlichungs-Nr.

EP4737688

Anmeldetag

31. Oktober 2025

Veröffentlichung

6. Mai 2026

Rechtsraum

EP

Abstract

A turbine engine (100) for an aircraft includes an integral frame. The integral frame includes an inner hub (240), a frame case (220) having an outer band portion (222) and a containment portion (224) integrally formed with the outer band portion (222), and a plurality of struts (210) connecting the inner hub with the outer band portion. The outer band is opposite the inner hub to form an air flow path (187) therebetween, and the containment portion extends in an axial direction of the turbine engine away from the outer band. The containment portion is positioned radially outward of a plurality of rotating airfoils (262) and extends axially over the plurality of rotating airfoils. The outer band portion and the containment portion of the frame case can be an integral composite having a plurality of reinforcing fibers (272) embedded in a matrix (270) or an integral metallic part.

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA