SPINNERS FOR USE ON TILTROTOR AIRCRAFT

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 su...

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Bibliographische Detailangaben
Hauptverfasser:	FARRELL, Michael Kenneth, LANIGAN, Brendan Patrick, KOELZER, Helmuth Peter
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING COSMONAUTICS HEATING HELICOPTERS LIGHTING MACHINES OR ENGINES FOR LIQUIDS MECHANICAL ENGINEERING OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR PERFORMING OPERATIONS PRODUCING MECHANICAL POWER TRANSPORTING WEAPONS WIND MOTORS WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS
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Beschreibung
Zusammenfassung:	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).