Flugzeugantriebssystem mit Flusswegeinlass mit Vorwärtsem Kern

Details

Veröffentlichungs-Nr.

EP4818492

Anmeldetag

16. März 2026

Veröffentlichung

7. Oktober 2026

Rechtsraum

EP

IPC

F02C7/04, F02K3/06, F02K3/077

Abstract

An aircraft system includes a propulsion system (24A,24B) mounted to an airframe (22). The propulsion system (24A,24B) includes a fan rotor (82), an engine core (72), an outer housing structure (62), an inner housing structure (60), a bypass flowpath (77) and a core flowpath (76). The engine core (72) is configured to drive rotation of the fan rotor (82) about an axis (54). The engine core (72) includes a compressor section (67), a combustor section (68) and a turbine section (69). The outer housing structure (62) houses the fan rotor (82) and forms an outer peripheral boundary of the bypass flowpath (77). The inner housing structure (60) forms an inner peripheral boundary of the bypass flowpath (77). The core flowpath (76) includes a core inlet (112) and a core exhaust (116). The core flowpath (76) extends longitudinally through the compressor section (67), the combustor section (68) and the turbine section (69) from the core inlet (112) to the core exhaust (116). The core inlet (112) is located axially forward of the fan rotor (82) and radially between the axis (54) and the airframe (22).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete