An apparatus and method for mounting a turbine engine 20 to an aircraft 10 can include an engine core 40 for the turbine engine 20 including a compressor section 42, a combustor section 48, and a turbine section 52 in flow arrangement. At least one strut 110 couples to the engine core 40 about a single mount plane 120. A structural wall 116 at least partially defining a mainstream flow path 118 couples to the at least one strut 110 and passes through the compressor section 42 and the turbine section 52.
TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE
TURBINENMOTOR MIT EINWANDIGER FREITRAGENDER ARCHITEKTUR
MOTEUR DE TURBINE À ARCHITECTURE EN PORTE-À-FAUX À PAROI UNIQUE
2019-02-27
Patent
Elektronische Ressource
Englisch
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