A gas turbine engine (10) for an aircraft comprising: an engine core (11); a fan (23) located upstream of the engine core (11), the fan (23) comprising a plurality of fan blades (64); a nacelle (21) surrounding the gas turbine engine (10), the nacelle (21) comprising an inner surface at least partly defining a bypass duct (22); and a bypass duct outlet guide vane (58) extending radially across the bypass duct (22) between an outer surface of the engine core (11) and the inner surface of the nacelle. An outer wall axis (59) is defined joining a radially outer tip of a trailing edge of the bypass duct outlet guide vane (58) and a rearmost tip (21b) of the inner surface of the nacelle (21), wherein the outer wall axis (59) lies in a longitudinal plane containing the centreline (9) of the gas turbine engine (10), an outer bypass duct wall angle (126) is defined as the angle between the outer wall axis (59) and the centreline (9), and the outer bypass duct wall angle (126) is in a range between -15 to 1 degrees.
TURBOFAN GAS TURBINE ENGINE WITH BYPASS DUCT
MANTELSTROM-GASTURBINENTRIEBWERK MIT BYPASS-KANAL
MOTEUR À TURBINE À GAZ À DOUBLE FLUX AYANT UNE VEINE SECONDAIRE
2020-06-24
Patent
Elektronische Ressource
Englisch
An intake duct liner for a turbofan gas turbine engine
Europäisches Patentamt | 2018
|