Flugzeugantriebssystem mit Selektiv Drehbarem Offenem Antriebsrotor

Details

Veröffentlichungs-Nr.

EP4725844

Anmeldetag

13. Oktober 2025

Veröffentlichung

15. April 2026

Rechtsraum

EP

IPC

B64D27/33, F02C3/107

Abstract

A propulsion system (20) for an aircraft includes a first open propulsor rotor (40), a second open propulsor rotor (42), a turbine engine (32) and a drive system (34). The second open propulsor rotor (42) is next to and downstream of the first open propulsor rotor (40). The turbine engine (32) includes a flowpath (72), a compressor section (67), a combustor section (68), a turbine section (69) and a rotating assembly (90). The rotating assembly (90) includes a turbine rotor (81) in the turbine section (69). The rotating assembly (90) is configured to drive rotation of the first open propulsor rotor (40) during a first mode and a second mode. The drive system (34) is discrete from the rotating assembly (90). The drive system (34) is configured to drive rotation of the second open propulsor rotor (42) during the first mode. The second open propulsor rotor (42) is rotationally fixed during the second mode.

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA