A gas turbine engine has an engine core including a low pressure compressor, a high pressure compressor, a high pressure turbine and a low pressure turbine coaxially mounted about an engine axis and fluidly connected in series by a core gaspath. The low pressure turbine is drivingly connected to the low pressure compressor via an external shaft disposed radially outwardly of the core gaspath.
GAS TURBINE ENGINE ARCHITECTURE WITH SPLIT COMPRESSOR SYSTEM
02.08.2018
Patent
Elektronische Ressource
Englisch