Gasturbinenkraftstoffrückführleitung

Details

Veröffentlichungs-Nr.

EP4571078

Aktenzeichen

EP24215978

Anmeldetag

28. November 2024

Veröffentlichung

18. Juni 2025

Rechtsraum

EP

IPC

F02C7/06F02C7/14F02C7/224F02C9/36

Abstract

A gas turbine engine (10) for an aircraft (1), comprising: a combustor (16); a fuel-oil heat exchanger (1004; 1006; 1204; 1206; 1404; 1406; 1704; 1706) arranged to receive fuel from a fuel tank (50) on board the aircraft (1) and transfer heat from the oil to the fuel; a fuel return line (1011; 1211; 1411b; 1711b) arranged to return at least some fuel that has passed through the heat exchanger (1004; 1006; 1204; 1206; 1404; 1406; 1704; 1706) to the fuel tank (50); and a modulator valve (1010; 1210; 1410; 1710) arranged to modulate the flow of fuel along the fuel return line (1011; 1211; 1411b; 1711b) such that a ratio of a temperature, in Kelvin, of fuel in the fuel tank (50) to a temperature, in Kelvin, of fuel being delivered to the combustor (16) is less than 0.56. Methods (2000) of operating a gas turbine engine (10) are also disclosed.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete