A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct. The gas turbine engine further comprises an inner cowl which provides an aerodynamic fairing surrounding the engine core, the inner cowl being rearwards of and axially spaced from the inner ring, and including one or more door sections which are openable to enable maintenance access to the engine core. The gas turbine engine further comprises an inner barrel which surrounds the engine core and bridges the inner ring and the inner cowl, the inner barrel having a circumferentially extending rear edge which provides an engagement formation for engagement with the door sections when they are closed
GAS TURBINE ENGINE INNER BARREL
INNERES GEHÄUSE EINES GASTURBINENMOTORS
TAMBOUR INTERNE DUN MOTEUR À TURBINE À GAZ
2019-10-30
Patent
Electronic Resource
English
IPC: | F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke |
INNER BARREL OF AN ENGINE INLET WITH LASER-MACHINED ACOUSTIC PERFORATIONS
European Patent Office | 2019
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