System und Verfahren zum Festklemmen einer Komponente eines Flugzeugmotors Während eines Herstellungsverfahrens

Details

Veröffentlichungs-Nr.

EP4782150

Anmeldetag

21. Januar 2026

Veröffentlichung

29. Juli 2026

Rechtsraum

EP

Abstract

A system (30) for use in the manufacturing of an aircraft engine (10) includes an engine component (20) to be machined. The component (20) has an opening (23) leading to an inner cavity (22) in an axial direction. The inner cavity (22) has an inner wall (25) with a tapered portion (25c) extending axially and a surface to be clamped (25d) extending radially outwardly from the opening (23) to the tapered portion (25c). The system (30) further includes a clamping device (40), for clamping the component (20), having a base (41), a shaft (42) displaceable relative to the base (41) and inserted through the opening (23), and a clamp (44) coupled to the shaft (42). The clamp (44) is movable, based on a position of the shaft (42) relative to the base (41), between an undeployed state in which the clamp (44) is free of contact with the inner wall (25) of the component (20) and a deployed state in which the clamp (44) engages the surface to be clamped (25d) to axially retain the component (20).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada