In-Situ-Ausgleichsmasse(en) für Flugzeugtriebwerke

Details

Veröffentlichungs-Nr.

EP4782653

Anmeldetag

27. Januar 2026

Veröffentlichung

29. Juli 2026

Rechtsraum

EP

IPC

F01D5/02, F04D29/66, F16F15/32

Abstract

An aircraft powerplant (20) apparatus includes a rotating structure (70) configured to rotate about an axis (72). The rotating structure (70) includes a bladed rotor, a first component, a second component, a first balancing mass (150A), a second balancing mass (150B) and a spring element (152). The first balancing mass (150A) and the second balancing mass (150B) are configured to rotationally balance the rotating structure (70) about the axis (72). The first component include a plurality of first component teeth (160). The second component includes a plurality of second component teeth (226). The first balancing mass (150A) includes a first mass ring (174A) and a plurality of first mass teeth (178A). The first mass teeth (178A) are meshed with the first component teeth (160). The second balancing mass (150B) includes a second mass ring (174B) and a plurality of second mass teeth (178B). The second mass teeth (178B) are meshed with the second component teeth (226). The spring element (152) is engaged with the first balancing mass (150A) and the second balancing mass (150B).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete