Systeme und Verfahren zum Abbau von Bodenwirbeln in einem Flugzeugantriebssystemeinlass

Details

Veröffentlichungs-Nr.

EP4745381

Anmeldetag

17. November 2025

Veröffentlichung

20. Mai 2026

Rechtsraum

EP

IPC

F02C9/00

Abstract

An aircraft propulsion system (20) includes a gas turbine engine (22), a nacelle (24), and a controller (78). The gas turbine engine (22) includes a rotational assembly rotatable about an axis (44). The rotational assembly includes a bladed fan rotor (58). The bladed fan rotor (58) includes a plurality of fan blades (62). The nacelle (24) houses the gas turbine engine (22). The nacelle (24) includes an air inlet (68). The air inlet (68) forms an inlet flow region (76). The inlet flow region (76) includes a reference section (98) at and upstream of the plurality of fan blades (62). The reference section (98) includes a cross-sectional flow area of the inlet flow region (76). The controller (78) is configured to control the gas turbine engine (22) to operate at or above a target engine speed corresponding to corrected air mass flow rate per unit area through the reference section (98) which is greater than a vortex breakdown threshold for the reference section (98).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA