Erkennung von Gas- oder Brennstofflecks in einem Gasturbinenmotor

Details

Veröffentlichungs-Nr.

EP4528091

Aktenzeichen

EP24201997

Anmeldetag

23. September 2024

Veröffentlichung

26. März 2025

Rechtsraum

EP

IPC

F02C7/25F02C9/46

Abstract

An aircraft engine diagnostic system (100) includes at least one sensor (102, 104, 106) and a diagnostic controller (110). The at least one sensor (102, 104, 106) measures a parameter of a gas turbine engine (20). The diagnostic controller (110) is in signal communication with the at least one sensor (102, 104, 106). The diagnostic controller (110) determines an actual thrust output of the gas turbine engine (20) and an execution of at least one control system limiter configured to limit control of the gas turbine engine (20) based on the measured parameter. The diagnostic controller (110) further determines an existence of an engine fault based on the actual thrust output of the gas turbine engine (20) and an execution of the at least one control system limiter.

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada

Fachgebiete