Montageanordnungen für Antriebssystem mit Offenem Rotor

Details

Veröffentlichungs-Nr.

EP4806790

Anmeldetag

16. März 2026

Veröffentlichung

16. September 2026

Rechtsraum

EP

IPC

B64D27/40, B64D27/10

Abstract

An assembly is provided for an aircraft. This aircraft assembly includes a turbine engine (32) and a mounting structure (36). The turbine engine (32) extends axially along an axis (24). The mounting structure (36) is configured to mount the turbine engine (32) to an airframe (106) of the aircraft. The mounting structure (36) includes a frame (124) and a linkage (168). The frame (124) is spaced radially outboard from the turbine engine (32). The frame (124) extends circumferentially about the turbine engine (32). The linkage (168) includes a linkage first end (170) and a linkage second end (172). The linkage (168) extends longitudinally between the linkage first end (170) and the linkage second end (172). The linkage (168) is attached to the frame (124) at the linkage first end (170) and the linkage second end (172). The linkage (168) is arranged tangent to and attached to the turbine engine (32) at an intermediate section (174) of the linkage (168) longitudinally between the linkage first end (170) and the linkage second end (172).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete