An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.
TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE
28.02.2019
Patent
Elektronische Ressource
Englisch
TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE
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