Parallellastpfad einer Zahnradpumpe

Details

Veröffentlichungs-Nr.

EP4764187

Anmeldetag

19. Dezember 2025

Veröffentlichung

24. Juni 2026

Rechtsraum

EP

Abstract

A gear pump arrangement (201) of an aircraft gas turbine engine is provided. The gear pump arrangement (201) includes an accessory (210), a quill shaft (220), two gear pumps (240, 250) in series, axial retention members (271, 272) at the accessory (210) and one of the two gear pumps (250) to axially retain the quill shaft (220) and torque transmitting members (TTMs). The TTMs include a first TTM (281) between the one of the two gear pumps (250) and the quill shaft (220) and a second TTM (282) between the quill shaft (220) and the accessory (210) whereby the quill shaft (220) directly links the one of the two gear pumps (250) to the accessory (210).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada