Patent application number | Description | Published |
20110286841 | COUNTER-ROTATING OPEN-ROTOR (CROR) - A method of controlling a Counter-Rotating Open-Rotor (CROR) includes measuring a speed of a first rotor and deriving a speed of a second rotor and controlling a pitch of the first rotor and the second rotor. | 11-24-2011 |
20110286842 | COUNTER-ROTATING OPEN-ROTOR (CROR) - A method of controlling a Counter-Rotating Open-Rotor (CROR) includes mechanically linking a pitch change system of a first rotor with a pitch change system of a second rotor and commanding a Blade Angle (Beta1 commanded) of the first rotor such that a Blade Angle (Beta2 Actual) of the second rotor is a function of the commanded Blade Angle (Beta1 commanded) to provide a linear relationship between an actual Blade angle (Beta1 Actual) and Beta1 commanded of the first rotor and a non-linear relationship between Beta2 Actual and Beta1 commanded. | 11-24-2011 |
20130280065 | PROPELLER BLADE PITCH ACTUATION SYSTEM - A propeller blade pitch actuation system includes a propeller control module (PCM), a PCM drain line, a first drain line, a drain line restriction, a second drain line, and a valve. The PCM drain line connects to the PCM to drain hydraulic fluid. The first drain line is downstream of the PCM drain line and the drain line restriction is downstream of the first drain line. The second drain line is downstream of the PCM drain line. The valve includes a first valve position and a second valve position. The first valve position connects the PCM drain line to the first drain line and the second valve position connects the PCM drain line to the second drain line. Hydraulic pressure of the first drain line between the valve and the drain line restriction is greater than hydraulic pressure of the second drain line. | 10-24-2013 |
20130280084 | PROPELLER BLADE WITH INTERNAL STIFFENER - A propeller blade includes a foam core having a slot formed through it from a camber side to a face side, an internal stiffener disposed through the slot and including flanges in contact with both the camber and face sides and a structural layer that surrounds at least a portion of the foam core and in contact with the flanges on both the camber and face sides. | 10-24-2013 |
20130336796 | MODIFIED TAPER ROLLER EDGE - A tapered roller bearing element includes a first end and a second end, the second end having a second end radius. There is an apex ring between the two ends having an apex ring radius. There is also a base cone extending between the first end and the apex ring, the base cone tapering outwardly at a base cone angle. In addition, a relief cone extends between the apex ring and the second end, the relief cone tapers inwardly at a relief cone angle, and relief cone angle is larger than the base cone angle. | 12-19-2013 |
20140102246 | ROTATING ASSEMBLY INCLUDING A DYNAMIC BALANCING SYSTEM - A rotating assembly includes a shaft having a driven end and a driving end. At least one rotating member coupled to the driven end. A support member is operatively connected to the at least one rotating member. A dynamic balancing system is operatively coupled to the support member. The dynamic balancing system includes a first balancing weight rotatably mounted to the support member. The first balancing weight is operatively connected to a first motor. A second balancing weight is rotatably mounted to the support member. The second balancing weight is operatively connected to a second motor. A controller is operatively connected to the first and second motors. The controller is configured and disposed to signal each of the first and second motors to rotate and to establish a desired position of the first balancing weight and the second balancing weight relative to at least one rotating member. | 04-17-2014 |
20140133984 | ELECTRICAL POWER TRANSFER SYSTEM FOR PROPELLER SYSTEM - A propeller system for an aircraft includes a propeller assembly rotatable about a central axis and a reduction gearbox operably connected to the propeller assembly via a propeller shaft. An electrical power transfer system is positioned such that the gearbox is located axially between the electrical power transfer system and the propeller assembly. The electrical power transfer system includes a slip ring assembly operably connected to an oil transfer tube extending to the propeller assembly and a brush block interactive with the slip ring assembly to transfer electrical power to a plurality of lead wires extending from the slip ring assembly to the propeller assembly. The brush block is positioned such that brush block tips of the brush block extend toward the slip ring assembly in a substantially axial direction relative to the central axis. | 05-15-2014 |
20140147275 | ELECTRICAL POWER TRANSFER SYSTEM FOR PROPELLER SYSTEM - A propeller system for an aircraft includes a propeller assembly rotatable about a central axis and a reduction gearbox operably connected to the propeller assembly via a propeller shaft. An electrical power transfer system is positioned such that the gearbox is located axially between the electrical power transfer system and the propeller assembly. The electrical power transfer system includes a slip ring assembly secured to an oil transfer tube extending to the propeller assembly and a brush block interactive with the slip ring assembly to transfer electrical power to a plurality of lead wires extending from the slip ring assembly to the propeller assembly. The brush block is positioned such that brush block tips of the brush block extend toward the slip ring assembly in a substantially radial direction relative to the central axis of the propeller assembly. | 05-29-2014 |
20140169961 | PROPELLER ROTOR BALANCING SYSTEM - A propeller rotor has a hub mounting a plurality of blades and a drive shaft for driving the hub and the blades about a central axis. A motor to change its position is operably connected to drive at least one counterweight. A sensor senses vibration on the propeller rotor and communicates with a controller. The controller controls the motor to change a position of the counterweight in response to a sensed imbalance. A method of operating a propeller rotor is also disclosed. | 06-19-2014 |
20140193253 | Propeller Blade With Relatively Movable Counterweight - A propeller rotor has a hub mounting a plurality of blades. A counterweight is movably mounted on the blade. A pitch change mechanism for changing an angle of incidence of an airfoil is associated with each of the blades. The counterweight twists the blades toward an increased pitch direction should the pitch change mechanism fail. A stop member stops rotation of the counterweight as the blade moves to a feather position. | 07-10-2014 |