Antriebssystem mit Offenem Rotor und Abgasmischer(n)

Details

Veröffentlichungs-Nr.

EP4722104

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) disposed next to the open propulsor rotor (32). 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. The engine core (68) includes a compressor section (61), a combustor section (62) and a turbine section (63). The inlet section (60) includes a flowpath inlet (72). The exhaust section (65) includes a flowpath exhaust (74) and a mixer at the flowpath exhaust (74). The flowpath 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). The mixer is configured to mix combustion products exhausted from the flowpath through the flowpath exhaust (74) with ambient air outside of the propulsion system.

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA