Antivereisungssystem für einen Abgeschirmten Drallgasturbinenmotoreinlass

Details

Veröffentlichungs-Nr.

EP4749104

Anmeldetag

31. Oktober 2025

Veröffentlichung

27. Mai 2026

Rechtsraum

EP

IPC

F02C7/04, B64D15/04, B64D33/02

Abstract

A gas turbine engine inlet anti-ice system includes a nacelle having an inlet lip, an anti-ice air supply duct, and a flow deflector. The inlet lip has an annular anti-icing chamber formed therein that is defined by an inner surface of the inlet lip and an aft wall that has an aft wall opening formed therein. The anti-ice air supply duct is configured to direct a flow of pressurized air into the aft wall opening. The flow deflector is coupled to the aft wall and extends over the aft wall opening. The flow deflector has an inner surface, an outer surface, a closed end, and an open end. The flow deflector and aft wall define a flow channel that extends between the closed end and the open end and in a direction that is tangential to the aft wall opening.

Anmelder

Firma

Honeywell International Inc.

Land

🇺🇸 USA

Fachgebiete