Versetzter Kern mit Seitenausstossgondeldüsen

Details

Veröffentlichungs-Nr.

EP4722516

Anmeldetag

29. April 2024

Veröffentlichung

8. April 2026

Rechtsraum

EP

IPC

F02C3/22, F02C3/30, F02C7/16F02C7/16

Abstract

A propulsion system (20) for an aircraft includes a fan (22), a core engine (24) configured for generating a gas flow (36) utilized to generate shaft power for driving the fan (22), a nacelle (48) that surrounds the core engine (24) and the fan (22), a condenser (58) where water in the gas flow (36) is condensed into a liquid form, an exhaust duct assembly (52) where the gas flow (36) is directed to the condenser (58), an ejector duct (60) where a portion of a bypass airflow (38) is thermally communicated with the condenser (58) to cool the gas flow (36), and an evaporator assembly (54), that is in thermal communication with the exhaust duct (60), where water recovered by the condenser (58) is heated to generate a steam flow (56) that is subsequently communicated to the core engine (24).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA