General Electric Company

Bernard Joseph Anderson

Jeffrey Howard Nussbaum

Juan Mario Gomez

Melvin Bobo

A fan blade includes perforated anchor tangs, one with inboard corners and the remainder without. The corners are disposed in a complementary seat in a rotor disk for limiting blade pivoting during assembly.

Corner tang fan blade

A fan blade includes an airfoil having a root and an integral platform. The platform includes forward and aft ends and arcuate first and second sides therebetween. The airfoil root is laterally offset closer to the platform first side than the second side. Impact loads with a trailing blade during a blade-out failure are accordingly distributed for reducing peak loading in the trailing blade and damage thereto.

Conforming platform fan blade

Pairs of cylindrical rolling pin elements are disposed in mating nests between blade dovetails and disk posts in a gas turbine engine rotor assembly. During periods of change of disk rim elastic strain caused by changes in rotor speed, relative movement between the blade dovetails and disk posts is afforded through rolling contact of the pin elements. High pressure load slippage between conventional pressure face portions of dovetails and posts and resultant fretting wear damage is obviated. Multiple pairs of pins and nests and pins of other than cylindrical geometry are also contemplated.

Anti-fretting blade retention means

A gas turbine engine rotor assembly has an inertial damper loosely surrounding a portion of the main rotor shaft. The damper is axially compressed between facing abutment surfaces provided on a nut and bevel gear. The damper has two axially spaced rows of circumferentially spaced slots, with the interrupting web portions of each row being circumferentially staggered with respect to one another. The damper is configured and dimensioned so that the axial force exerted by the damper on the nut and bevel gear, the polar moment of inertia of the damper, and the coefficient of friction between the damper end faces and the abutment surfaces, cooperate to effectively damp the excitation of the fifth-stage blades in response to application of a source of vibrations at a particular frequency to the bevel gear.

Gas turbine engine motor assembly

A fastening device with positive locking means is provided comprising a generally cylindrical threaded portion and a headed portion proximate thereto. An elastically deformable annular ring portion is spaced apart from the threaded portion and includes locking means disposed thereon which are adapted to selectively prevent rotation of the fastening device in accordance with deformation of the ring.

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Danvers, MA, United States of America

Bernard Joseph Anderson