Flugzeugantriebssystem mit Hilfsströmungswegsystem

Details

Veröffentlichungs-Nr.

EP4782676

Anmeldetag

26. Januar 2026

Veröffentlichung

29. Juli 2026

Rechtsraum

EP

IPC

F02K1/66, F02K3/02, F02K3/075

Abstract

An aircraft propulsion system (20) includes an open propulsor rotor (34), a turbine engine (32) and an auxiliary flowpath (114). The turbine engine includes an engine flowpath (72), a compressor section (67), a combustor section (68) and a turbine section (69). The engine flowpath extends through the compressor section, the combustor section and the turbine section from an engine flowpath inlet (74) to an engine flowpath exhaust. The auxiliary flowpath extends longitudinally along a trajectory from an auxiliary flowpath inlet (122) to an auxiliary flowpath outlet (124). The auxiliary flowpath inlet is disposed along an exterior of the propulsion system that borders an environment external to the propulsion system. The auxiliary flowpath outlet is disposed along the engine flowpath. The turbine engine is axially aft of the open propulsor rotor along an axis. The trajectory extends axially forward along the axis as the auxiliary flowpath extends longitudinally from the auxiliary flowpath inlet.

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete