Antriebssystem mit Offenem Rotor und Vorwärtsabgasauslass(en)

Details

Veröffentlichungs-Nr.

EP4722105

Anmeldetag

1. Oktober 2025

Veröffentlichung

8. April 2026

Rechtsraum

EP

Abstract

An aircraft propulsion system (20) includes a propulsion section (28) and a turbine engine (30). The propulsion section (28) includes an open propulsor rotor (32) and an open guide vane structure (34). The turbine engine (30) is configured to drive rotation of the open propulsor rotor (32). The turbine engine (30) includes an engine core (68), an inlet section (60), an exhaust section (65) and a flowpath (70). The engine core (68) includes a compressor section (61), a combustor section (62) and a turbine section (63) with the turbine section (63) disposed axially between the compressor section (61) and the open propulsor rotor (32). The inlet section (60) includes a flowpath inlet (72). The exhaust section (65) includes a flowpath exhaust (74). At least a portion of the exhaust section (65) is disposed axially between the open propulsor rotor (32) and the open guide vane structure (34). The flowpath (70) extends from the flowpath inlet (72), through the inlet section (60), the compressor section (61), the combustor section (62), the turbine section (63) and the exhaust section (65), to the flowpath exhaust (74).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA