United Technologies Corporation

Perry P Sifford

Jerry Howard Griffin

John C Jones

Joel F Sutton

Richard S Myers

The support structure for the bearing compartment for a gas turbine engine includes eight radial tie bolts connected with the clevis wherein the outer diameter clevis is connected to the mount ring with an accessible bolt for easy assembly and disassembly. The tie bolts, while preloaded in tension, can accept compressive loads during severe loading operation conditions. The turbine exhaust case housing the tie bolts and bearing compartment are designed to facilitate cooling and maintainability at reduced costs.

Bearing compartment support

This invention relates to the construction of a turbine rotor having a rotor disc with a plurality of blades, said blades having roots fitted into slots around the periphery of the disc with each blade engaging a stop means to properly position it, said blades being held in place by a cover plate fixed to the rotor disc and said stop means; a pocket is formed on the front face of each blade while an annular groove on said cover plate is positioned over said circumferential ring of pockets. Each pocket has an outer flat surface placed at an angle so that each surface intersects the outer surface of the annular groove; a stiff solid damper having a rectangular surface is positioned in each pocket so that one end of said surface will be supported by the outer surface of the annular groove while the other end of said surface will be supported by the outer surface of the pocket when the damper is thrown outwardly by centrifugal force.

Blade damper

Effective damping of blade vibratory energy is sought by the apparatus described herein. The concepts relate specifically to what is known as blade to blade damping as is distinguished from blade to ground damping. The dampers employed have a 'T' shaped cross section geometry and are designed to extend circumferentially on an engine rotor between the platform sections of each pair of rotor blades. The dampers are of extreme light weight such that the slipload forces required to generate sliding contact between the damper and the blade platforms is low.

Blade to blade vibration damper

This invention shows a shroud construction located around the tips of the blades on a rotating body in an engine to provide a minimum clearance between the blade tips and the shroud during all conditions of operation-acceleration, steady state and deceleration. This shroud construction provides an arrangement where the internal diameter of the vanes support the shroud member for the tips of the blades. The vane is supported as internal diameter to an internal support while the outer diameter of the vane is permitted radial growth with respect to the turbine casing. While the blade tip shroud can be made integral with the outer shroud of the vanes, it may be connected by means which will permit a small axial misalignment. Means are provided for cooling the shrouds around the tips of the blades.

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Jupiter, FL, United States of America

Perry P Sifford