A propulsion system for an aircraft includes a propulsor section that includes a fan with a plurality of fan blades that are rotatable about a fan axis, a core engine that is configured to generate a gas flow, a power turbine where the gas flow from the core engine is expanded to generate shaft power, and a power turbine shaft that is coupled between the power turbine and the propulsor section. The power turbine shaft is of an axial length between a first end portion and a second end portion along the fan axis that is greater than half a distance between a leading edge of the fan blades and a mechanical coupling of the power turbine shaft to the power turbine, and includes an outer diameter that increases in a direction away from each of the first end portion and the second end portion.
Power turbine shaft for decoupled gas generator
2024-09-17
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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