Flugzeugantriebssystem mit Seitenströmungswegeinlass(en)

Details

Veröffentlichungs-Nr.

EP4807161

Anmeldetag

16. März 2026

Veröffentlichung

16. September 2026

Rechtsraum

EP

IPC

F02C6/20, F02K3/077

Abstract

An aircraft system (20) includes an open propulsor rotor (38), an engine core (94), an engine flowpath (36) and a flow regulator (146). The open propulsor rotor (38) includes a plurality of open propulsor blades (46) arranged circumferentially about an axis (24). Each of the open propulsor blades (46) is disposed in an external environment (22). The engine core (94) includes a compressor section (89), a combustor section (90) and a turbine section (91). The engine flowpath (36) includes an end flowpath inlet (134), a side flowpath inlet (136) and a flowpath exhaust (138). The engine flowpath (36) extends longitudinally through the compressor section (89), the combustor section (90) and the turbine section (91) from the end flowpath inlet (134) to the flowpath exhaust (138). The side flowpath inlet (136) is disposed to a radial outer side of the engine flowpath (36) longitudinally between the end flowpath inlet (134) and the compressor section (89). The flow regulator (146) is configured to regulate a flow of air from the external environment (22) into the engine flowpath (36) through the side flowpath inlet (136).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete