ROTATING COMPOSITE TECHNOLOGIES, LLC Patent applications |
Patent application number | Title | Published |
20110194937 | PRELOADED BEARING FOR ROTOR BLADE - A rotor for a propulsive thrust device comprises a hub having a peripheral surface; a plurality of rotor blades received at the peripheral surface of the hub; a first bearing assembly located in the hub and around a shank of a respective rotor blade to support the rotor blade in the hub under centrifugal loading and to allow the rotor blade to rotate about a longitudinal axis; and a second bearing assembly located in the hub and around a shank of a respective rotor blade and inward of the first bearing assembly to preload the first bearing assembly. A preload bearing assembly comprises an outer race; a plurality of rolling elements located therein; and a plurality of studs located in communication with the outer race. Adjustment of the studs distributes a tensile load around the outer race to exert a preload force on a bearing assembly supporting the rotor blade. | 08-11-2011 |
20100003139 | PROPULSOR DEVICES HAVING VARIABLE PITCH FAN BLADES WITH SPHERICAL SUPPORT AND DAMPING SURFACES - A system for providing support to a fan blade of an aircraft engine includes a rotatable hub; a cradle pivotally mounted on the rotatable hub, the cradle comprising a flexible member and an adjacently positioned support member; a fan blade attached at a first end thereof to the cradle such that the flexible member engages a first surface of the fan blade at the first end of the fan blade and the support member engages a second opposing surface of the fan blade at the first end of the fan blade and such that the flexible member and the support member provide support to the fan blade relative to the rotatable hub; and means for rotating the cradle relative to the rotatable hub to vary the pitch of the fan blade. The system may include spherical support surfaces located on sides of the cradle. | 01-07-2010 |
20090285686 | FAN BLADE RETENTION AND VARIABLE PITCH SYSTEM - A system for providing variable pitch to a rotor blade of an aircraft engine includes a rotatable hub; at least one blade mounted on the rotatable hub; a gear mechanism operably connected to the rotatable hub; a timing ring rotatably and operably connected to the gear mechanism; and a pitch arm operably connecting the timing ring and the at least one blade mounted on the rotatable hub. In the operation of the system, the gear mechanism facilitates the rotation of the timing ring to vary the pitch of the at least one blade mounted on the rotatable hub. | 11-19-2009 |