Hamilton Sundstrand Corporation

United Technologies Corporation

Matthew C Soule

Paul A Carvalho

Thomas G Corley

Peter Ventura

Robert H Perkinson

John A Violette

Robert W Pruden

Herbert J Holl

A blade shank assembly for an aircraft propeller blade includes a blade shank; and a split blade retention race encircling the blade shank, the split blade retention race comprising two sections separated by two splits, the two splits being perpendicular to a race surface of the split blade retention race, wherein the split blade retention race comprises: an inner chamfer located between a surface of the split blade retention race that is adjacent to the blade shank and a split surface of the split blade retention race at each of the two splits; and an outer chamfer located between the race surface of the split blade retention race and the split surface at each of the two splits.

Split blade retention race with inner and outer chamfers

A propeller assembly includes a hub and a blade installed in the hub. A bearing arrangement retains the blade in the hub and includes an outer bearing race at the hub including a first outer race radius and a second outer race radius different from the first outer race radius, connected by an outer relief. The bearing arrangement further includes an inner bearing race at the blade including a first inner race radius and a second inner race radius different from the first inner race radius, connected by an inner relief. A plurality of bearing balls are installed between the inner race and outer race thereby retaining the blade at the hub.

Ball bearing retention for propeller blade and method of assembly

A blade shank assembly for an aircraft propeller blade includes a blade shank; a split blade retention race encircling the blade shank, the split blade retention race including two splits, wherein the split blade retention race comprises: inner chamfers located between the blade shank and the split blade retention race at each of the two splits; and outer chamfers located adjacent to a race surface of the split blade retention race at each of the two splits; and a plurality of ball bearings located on the race surface of the split blade retention race.

A bearing assembly includes first and second races, a plurality of ball bearings positioned between the first and second races, and a spacer positioned between each of the ball bearings. The spacers each include a body defining opposite first and second sides, a first substantially concave pocket located at the first side of the body, and a second substantially concave pocket located at the second side of the body. The first and second substantially concave pockets each define a central region having a first radius of curvature about a first center point and an outer region adjacent to the central region that has a second radius of curvature about a second center point. The first and second center points are spaced from one another, and the body includes a portion extending in between at least the respective central regions of the first and second substantially concave pockets.

Separator for bearing assemblies with cyclic loads

A pressure relief device for preventing over pressurization of a propeller hub is disclosed. The pressure relief device is designed to fit within a ball hole opening in the hub arm of the hub. The pressure relief device includes a housing which sealably interfaces with an inner wall of the ball loading hole opening and a diaphragm which sealably interfaces with the housing. The diaphragm is designed to rupture at a design pressure thus venting the hub cavity.

Pressure relief device for a propeller hub

A propeller blade retention assembly for use with a propeller having a hub rotatable about a propeller axis, is disclosed. The assembly includes a blade receiver for mounting the blade to the hub and an internal surface of a hub arm for interfacing the receiver with the hub. The receiver is positioned in the hub arm and is non-integral with the blade and the hub arm internal surface. A retention mechanism is used for retaining the blade receiver to the hub arm while allowing relative rotatable motion therebetween. A preload device is provided for preloading the retention mechanism prior to centrifugal loading during propeller blade operation. The blade is separable from the blade receiver without disturbing the operability of the retention mechanism.

Growing community of inventors

Granby, CT, United States of America

Matthew C Soule