A blade shank assembly (100) for an aircraft propeller blade includes a blade shank (101); a split blade retention race (103) encircling the blade shank, the split blade retention race including two splits (104), wherein the split blade retention race comprises: inner chamfers (201) located between the blade shank and the split blade retention race at each of the two splits; and outer chamfers (202) located adjacent to a race surface of the split blade retention race at each of the two splits; and a plurality of ball bearings (102) located on the race surface of the split blade retention race.
Split blade retention race with inner and outer chamfers
Geteilter Blatthalterlaufring mit inneren und äußeren Fasen
Bague de rétention de pale divisée avec des chanfreins internes et externes
2015-07-22
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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