A propeller blade assembly (12) includes a spar (18) extending along a propeller blade axis (16) and an outer sleeve (20) surrounding the spar (18) at a root end of the rotor blade assembly. The spar (18) is adhesively bonded to the outer sleeve (20) at an interface portion. A spar maximum diameter (38) along the interface portion is larger than an outer sleeve minimum diameter (40) along the interface portion. A method of assembling a propeller blade includes installing an outer sleeve (20) over a spar (18) at a root end of the spar (18), the spar (18) a not fully cured composite component, and urging the spar (18) into compressive conformance with the outer sleeve (20) at an interface portion of the propeller blade assembly. A spar maximum diameter (38) along the interface portion is larger than an outer sleeve minimum diameter (40) along the interface portion. The spar (18) is cured thereby adhesively bonding the spar (15) to the outer sleeve (20) at the interface portion.
LIGHTWEIGHT PROPELLER BLADE WITH IMPROVED RETENTION CAPACITY
LEICHTGEWICHTIGES PROPELLERBLATT MIT VERBESSERTER RETENTIONSKAPAZITÄT
PALE D'HÉLICE LÉGÈRE PRÉSENTANT UNE CAPACITÉ DE RÉTENTION AMÉLIORÉE
2019-02-27
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
LIGHTWEIGHT PROPELLER BLADE WITH IMPROVED RETENTION CAPACITY
Europäisches Patentamt | 2016
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