Brennstoff- und Wasserwärmeverwaltungssystem

Details

Veröffentlichungs-Nr.

EP4571082

Aktenzeichen

EP24215973

Anmeldetag

28. November 2024

Veröffentlichung

18. Juni 2025

Rechtsraum

EP

IPC

F02C7/22F02C7/14F02C3/24F02K3/04F01D17/26

Abstract

A gas turbine engine (10) for an aircraft comprises an engine core (11) comprising a turbine (19), a combustor (16), a compressor (14), and a core shaft (26) connecting the turbine to the compressor. The engine comprises a fan (23) located upstream of the engine core and arranged to be driven by the core shaft. The engine comprises a nacelle (21) surrounding the fan and the engine core and defining a bypass duct (22) located radially outside of the engine core, where the bypass ratio, defined as the ratio of the mass flow rate of the flow through the bypass duct to the mass flow rate of the flow through the core at cruise conditions, is at least 4. The engine comprises an engine heat management system (1700) and an actuator (1704) configured to actuate at least one valve (1704a) within that system. The engine comprises a fuel supply system (152) arranged to supply fuel to fueldraulically drive the actuator. The actuator is configured to actuate said valve so as to enable non-binary position adjustment between an open valve position and a closed valve position.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete