Antriebssystem für ein Flugzeug mit Offenem Rotor und Versetztem Getriebe

Details

Veröffentlichungs-Nr.

EP4722106

Anmeldetag

1. Oktober 2025

Veröffentlichung

8. April 2026

Rechtsraum

EP

Abstract

An open propulsor rotor (58) is configured to rotate about a first axis (62). An open guide vane structure (60) includes a plurality of open guide vanes (78) arranged circumferentially about a second axis (112) offset from the first axis (62). The open guide vanes (78) include a first open guide vane. A turbine engine (54) includes a flowpath (96), a compressor section (91), a combustor section (92), a turbine section (93) and a rotating assembly. The flowpath (96) extends through the compressor section (91), the combustor section (92) and the turbine section (93) from an airflow inlet (98) into the flowpath to a combustion products exhaust (100) from the flowpath (96). The airflow inlet (98) is axially aligned with or located forward of the first open guide vane along the second axis (112). The rotating assembly includes a turbine rotor disposed in the turbine section (93). The rotating assembly is configured to drive rotation of the open propulsor rotor (58) through an offset geartrain (122).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA