Propeller Pitch Regulator (Patent No: 367536)

Inventor: O'Leary, Daniel

Location: Calgary

Comments: N/A

Description: Amended and additional claims.
1. In a multiple blade propeller of the automatic variable pitch type, the combination of a propeller shaft, a plurality of rotable bearing members freely rotatable within a hub, propeller blades fixedly attached to said rotable bearing members, the axes of said bearing members and the neutral axes of said propeller blades being constantly aligned to meet at a common focal point on the said shaft, these respective aces bearing such a relation such a relation to each other that a portion of the actual air-stream passing over the cross section of a rotable bearing member's axis must come in constant contact with the section of the blade as well as with the centre of aerodynamic blade resistant and with the centre of aerodynamic blade thrust.
2. In a multiple blade propeller of the automatic variable pitch type, the combination of a propeller shaft, a hub, a plurality of rotable bearing members freely rotatable within said hub, propeller blades adjustably fixed to said rotable bearing members, the axes of said bearing members and the neutral axes of said propeller blades being constantly aligned to meet at a common focal point on the axis of said shaft, the respective bearing member and propeller axes bearing such relation to each other that the line of the air-stream passing over the cross section of a rotable bearing member's axis must come in contact with or pass immediately on either side of the section of the blade containing the centre of the centrifugal force effect in the blade as well as with the centre of aerodynamic blade resistance and with the centre of aerodynamic blade thrust.
3. In a multiple blade propeller of the automatic variable pitch type, the combination of a propeller shaft, a hub, a plurality of rotable bearing members freely rotatable within said hub, propeller blades fixedly attached to said rotable bearing members, the axes of the said bearing members and the centre line of eachblade converging permanently at a common focal point on the propeller shaft axis, the angularity of the axis of each bearing member to the normal perpendicular and to the neutral axis of each propeller blade bearing such proportional relationships that the airstream passing the axis of the rotable bearing members must come in contact with the propeller blade.
4. In a multiple blade propeller of the automatic variable pitch type, the combination of a propeller shaft, a hub, a plurality of rotable bearing members freely rotatable within said hub, a single all-purpose bearing to support said bearing members, propeller blades attached to said rotable bearing members, the axes of said bearing members and the neutral axes of the said propeller blades being constantly aligned to meet at a common focal point on the axis of the said shaft, the angularity of the axis of each bearing member to the normal perpendicular and to the neutral axis of each propeller blade bearing such proportional relationships to each other that a portion of the actual air-stream passing over the cross section of the axis of each rotable bearing member must come in contact with the section of the blade containing the centre of the centrifugal force effect in the blade as well as the centre of aerodynamic blade resistance and with the centre of aerodynamic blade thrust.
5. In a multiple blade propeller of the automatic variable pitch type, the combination of propeller shaft, a hub, a plurality of rotable bearing members freely rotatable within said hub, a bearing at the inner extremity and a bearing at the outer extremity of each said rotable bearing member, propeller blades attached to said rotable bearing members the axes of said bearing members and the neutral axes of the said propeller blades being constantly aligned to meet at a common focal point on the axis of the said shaft, the angularity of the axis of each bearing member to the normal perpendicular and to the neutral axis of each propeller blade bearing such proportional relationships to each other that a portion of the air-stream passing over the cross section of the axis of each rotable bearing member must come in constant contact with the section of the blade containing the centre of centrifugal force effect in the blade as well as with the centre of aerodynamic blade resistance and with the centre of aerodynamic blade thrust.
6. In a multiple blade propeller of the automatic variable pitch type, the combination of a propeller shaft, a hub, a plurality of rotable bearing members freely rotatable within said hub, propeller blades adjustably or fixedly attached to said bearing members, the axes of said bearing members and the neutral axes of the said propeller blades being constantly aligned to meet at a common focal point on the axis of said shaft, the angularity of the axis of each bearing member to the normal perpendicular, and the angularity of the axis of each propeller blade bearing definite proportional relationships.
7. In a multiple blade propeller of the automatic variable pitch type, the combination of a propeller shaft, a hub, a plurality of rotable bearing members freely rotatable within said hub, propeller blades adjustably or fixedly attached to said bearing members, the axes of the said bearing members and the neutral axes of said propeller blades being constantly aligned to meet at a common focal point on the axis of said shaft, the angle of the axis of a rotable bearing member to a normally perpendicular plane, and the angle of the neutral axis of a propeller blade to the axis of a rotable bearing member, being proportionately equal.
8. In a multiple blade propeller of the automatic variable pitch type, the combination of a propeller shaft, a hub, a plurality of rotable bearing members freely rotatable within said hub, propeller blades adjustably or fixedly attached to said bearing members, the axes of said bearing members and the neutral axes of said propeller blades being constantly aligned to meet at a common focal point on the axis of said shaft, the angle of the axis of a rotable bearing to the normally perpendicular plane, and the angle of the neutral axis of a propeller blade to the axis of a rotable bearing member being proportionately equal, the air-stream passing the cross section of the rotable member's axis coming in contact with the portion of the blade containing the centre of centrifugal force effect on the blade and the centre of aerodynamic blade resistance and the centre of aerodynamic blade thrust.