A proprotor assembly (26a, 26b) for a tiltrotor aircraft (10) having a forward flight mode. The proprotor assembly (26a, 26b) includes a spinner (28a, 28b) subjected to freestream airflow during forward flight. The spinner (28a, 28b) is elongated to form a tapered leading portion (32a, 32b) and a substantially cylindrical aft portion (34a, 34b). The spinner (28a, 28b) forms a plurality of rotor blade cutouts (36a, 36b) exposing an inner chamber (38a, 38b). The proprotor assembly (26a, 26b) includes a plurality of proprotor blade assemblies protruding radially from the spinner (28a, 28b) through the rotor blade cutouts (36a, 36b). The rotor blade cutouts (36a, 36b) are formed at the substantially cylindrical aft portion (34a, 34b) of the spinner (28a, 28b) to reduce the freestream airflow into the inner chamber (38a, 38b) via the rotor blade cutouts (36a, 36b) during forward flight, thereby reducing drag experienced by the tiltrotor aircraft (10).
SPINNERS FOR USE ON TILTROTOR AIRCRAFT
PROPELLERHAUBE ZUR VERWENDUNG AUF KIPPROTOR-FLUGZEUG
CASSEROLE D'HELICE DESTINÉES À ÊTRE UTILISÉES SUR UN AÉRONEF À ROTOR BASCULANT
2019-08-28
Patent
Electronic Resource
English