A self-contained counter rotating turbo prop system (14) is driven by a gas turbine engine (10) through a reduction gearbox (12). A gear train housed separate from the reduction gearbox (12) provides the counter-rotation of a first and second pluralities of propeller blades (18,20). The entire counter-rotating propeller system (14) is disposed within cowlings (16A,16B) and is separate from the gas turbine engine (10) and reduction gearbox (12). The counter rotating propeller system (14) includes a collective blade angle actuation system (55) that provides for adjustment of blade angle of both the first and second plurality of propeller blades (18,20) with a single actuator.
Modular counter rotating propeller system
Modulares gegenläufigen Propeller-System
Système modulaire d'hélices contrarotatives
2019-10-02
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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