Antriebssystem für ein Flugzeug mit Open Rotor und Bypasskanal

Details

Veröffentlichungs-Nr.

EP4596419

Aktenzeichen

EP25155664

Anmeldetag

3. Februar 2025

Veröffentlichung

6. August 2025

Rechtsraum

EP

IPC

B64D33/02B64D33/10F02C3/14F02C7/04F02K3/077

Abstract

A propulsion system (20) for an aircraft includes an open propulsor rotor (34) and a turbine engine (30) configured to drive rotation of the open propulsor rotor (34) about an axis (22). The turbine engine (30) includes a core flowpath (84), a bypass flowpath (86), a fan section (75) and an engine core (90). The engine core (90) includes a compressor section (76), a combustor section (77) and a turbine section (78). The core flowpath (84) extends through the compressor section (76), the combustor section (77) and the turbine section (78) from an inlet (124) into the core flowpath (84) to an exhaust (128) from the core flowpath (84). The inlet (124) is next to and downstream of the fan section (75). The bypass flowpath (86) extends outside of and along the engine core (90) from an inlet (126) into the bypass flowpath (86) to an exhaust (130) from the bypass flowpath (86). The inlet (126) is next to and downstream of the fan section (75). The engine core (90) is arranged axially between the fan section (75) and the open propulsor rotor (34).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete