Mit Wasserstoff Betriebenes Flugzeuggasturbinentriebwerk-Kraftstoffsystem

Details

Veröffentlichungs-Nr.

EP4733558

Anmeldetag

25. September 2025

Veröffentlichung

29. April 2026

Rechtsraum

EP

IPC

F02C3/22, F02C7/232, F02C9/40

Abstract

A fuel system for an aircraft gas turbine engine (103) comprises: a main fuel conduit (206) configured to deliver hydrogen fuel to a combustor (203) of the gas turbine engine (103); a fuel metering valve (213) configured to modulate a mass flow of fuel delivered to the gas turbine engine combustor (206); and a bypass valve (209, 210) provided upstream in main fuel conduit hydrogen fuel flow of the fuel metering valve (213) and configured to vent a portion of hydrogen fuel upstream of the fuel metering valve (213). The fuel system further comprises a controller (218) configured to control the fuel metering valve (213) and the vent valve (209, 210). The controller (218) is configured to, during an engine start procedure, open the fuel metering valve (213) and open the vent valve (209, 210) to flow a first fuel portion to the combustor (206) via the fuel metering valve (213) and to vent a second fuel portion via the vent valve.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete