Ölsystem für Flugzeugtriebwerk mit Merkmalen zur Verhinderung von Flüssigkeits-Ablauf aus einer Komponente

Details

Veröffentlichungs-Nr.

EP4749105

Anmeldetag

21. November 2025

Veröffentlichung

27. Mai 2026

Rechtsraum

EP

IPC

F02C7/06, F02K3/06, F01D25/18

Abstract

An aircraft engine (10) having a centerline (11) has: an oil system (28; 100) including: a component (101) located above the centerline (11) and having an inlet (101A) and an outlet (101B); an oil circuit (110) interconnecting the components (101) and including an input line (111) connected to the inlet (101A) and an output line (112) connected to the outlet (101B), the input line (111) defining an input U-shaped section (111A), the output line (112) defining an output U-shaped section (112A); a valve (113, 114) connected on the input line (111) or the output line (112) and located between the component (101) and a respective one of the input U-shaped section (111A) and the output U-shaped section (112A); and an anti-siphon line (120) connecting the input line (111) to the output line (112) and defining a flow path of a lesser flow circulating area of the input line (111) and the output line (112), the input U-shaped section (111A), the output U-shaped section (112A), and the component (101) located between connection points (121, 122) defined between the anti-siphon line (120) and the input and output lines (111, 112).

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada

Fachgebiete