Anordnungen für Flugzeugantriebssysteme

Details

Veröffentlichungs-Nr.

EP4628707

Aktenzeichen

EP25168942

Anmeldetag

7. April 2025

Veröffentlichung

8. Oktober 2025

Rechtsraum

EP

IPC

F01D17/14F02K3/075// F01D5/14

Abstract

An assembly is provided for an aircraft propulsion system. This assembly includes a bladed rotor (44), an inner flowpath (72), an outer flowpath (76), a splitter (86) and a flowpath wall (90). The bladed rotor (44) is rotatable about an axis (24). The inner flowpath (72) includes an inner flowpath inlet (70) downstream of the bladed rotor (44). The outer flowpath (76) includes an outer flowpath inlet (74) downstream of the bladed rotor (44). The outer flowpath inlet (74) is radially outboard of the inner flowpath inlet (70). The splitter (86) is disposed radially between and partially forms the inner flowpath inlet (70) and the outer flowpath inlet (74). The flowpath wall (90) is arranged with the splitter (86) and forms a radial inner peripheral boundary of the outer flowpath (76). The flowpath wall (90) includes an inflatable bladder (100) and a radial outer surface (98). The inflatable bladder (100) is configured to change a geometry of the radial outer surface (98).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete