General Electric Company

Anant Pal Singh

Thomas Ory Moniz

Malcolm John Ashby

Terry Eugene Viel

Larry Jay Sexton

Duane Howard Anstead

Barry Lynn Allmon

Albert Frank Storace

Stephen Anthony Wilton

Donald Ray Bond

Michael Slusher

Daniel M Allen

August H Kramer

James C Austrow

Tony Metz

M Kaleem Ansari

A bearing damper includes: (a) an annular sleeve having spaced-apart grooves formed in a radially-facing surface therein; (b) an annular bearing race received in the sleeve; and (c) a resilient seal ring disposed in each of the grooves, wherein the seal rings cooperate with the sleeve and a radially-facing surface of the bearing race to define a closed annular gap, and further wherein the seal rings are sized so as to urge the bearing race towards a coaxial position relative to the sleeve.

Bearing damper with spring seal

A method for predicting bearing failure of a differential bearing including an inner race, an outer race, and a plurality of rolling elements positioned between the inner and outer race. The method includes coupling a strain gage to the differential bearing, generating a bearing performance model, receiving a signal from the strain gage, and comparing the strain gage signal to the bearing performance model to predict a differential bearing failure.

Bearing assembly and method of monitoring same

A method for predicting bearing failure of a differential bearing including an inner race, an outer race, and a plurality of rolling elements positioned between the inner and outer race, the method includes coupling a measuring apparatus comprising at least one of a strain gage and an accelerometer to the differential bearing, coupling a cable to the measuring apparatus, wherein the cable is adapted for passage through a rotating component, and coupling a transmitter to the cable, wherein the transmitter is configured to transmit a plurality of signals from the measuring apparatus to a remote location to facilitate predicting a failure of the differential bearing.

Telemetry system

A method for predicting bearing failure, wherein the bearing includes an inner race, an outer race, and a plurality of rolling elements between the inner and outer race. The method includes coupling a sensor assembly to the outer race, the sensor assembly including at least one temperature sensor and at least one acoustic sensor, generating a bearing performance model based on an initial signal received from the sensor assembly, receiving a second signal from the sensor assembly, and comparing the second signal to the bearing performance model to predict a bearing failure.

Methods and apparatus for assembling a bearing assembly

An apparatus for scavenging lubricating oil comprises an integrated slinger/runner rotatable with the turbine engine rotor discourages oil seepage out of an oil sump of a forward bearing for a gas turbine engine during all operating conditions of the gas turbine engine from idle to take-off speeds and during static non-operation. The apparatus includes a runner comprising an axially forward section and a frusto-conical aft section, and a slinger joined coaxially integrally to the aft frusto-conical aft section. The apparatus includes a means for blocking flow of oil from the frusto-conical aft section toward the axially forward section.

Apparatus for scavenging lubricating oil

A method for assembling a gas turbine engine that includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first fan assembly, wherein the second fan assembly is configured to rotate in a second rotational direction that is opposite the first rotational direction, coupling a first shaft to the first fan assembly and to a first turbine rotor that is configured to rotate in a first rotational direction, coupling a second shaft coupled to the second fan assembly and to a second turbine rotor that is configured to rotate in a second rotational direction that is opposite the first rotational direction, and coupling a lubrication system to the gas turbine engine such that a lubrication fluid is channeled through the first shaft to lubricate at least one of the first and second fan assemblies.

Counter-rotating turbine engine and method of assembling same

An actuation system which includes apparatus for transferring control signals for varying the blade pitch from a non-rotating member to a rotating member of a gas turbine engine is described. In one embodiment, the engine includes a main disk containing a row of blades, and the disk is coupled to a main shaft which rotates about the engine axis. An actuating disk, or cone, rotates with the main disk, and the torque required to rotate the actuating cone is transmitted through ball splines attached to the main shaft. The ball splines allow transmission of torque between the disk and the cone and at the same time enable the disk and the cone to move axially relative to each other without binding. The actuating cone is supported at one end by the ball splines and at its other end by ball thrust bearings. The ball thrust bearings are pre-loaded to enable the bearings to withstand axial loads in opposite directions. The outer races of the bearings are supported by a ring, and the ring is connected to an actuator through a connecting cone. In addition to the actuating system, a blade support system is provided wherein the load of the blade is transferred from a blade 'button' head to the main disk through a load transfer ring, a bearing inner race support, and a thrust bearing. A nut retains a crank of the actuating system on the blade spindle. To rotate the blade about its radial axis, the ring is moved axially by the actuator. Such axial movement of the ring imparts axial motion to the rotating actuating cone, which rotates a crank attached to the blade. The thrust bearings allow the actuating cone to rotate about the centerline of the actuator and to move axially when actuated.

Actuation system for a gas turbine rotor blade

A non-symmetrical circular row of oil inlets are located in a circular manifold surrounding a squeeze film space in a squeeze film damper. The oil inlets are directed radially inwardly from said manifold to open into the squeeze film space. Certain cluster of inlets provide higher oil pressure to the squeeze film space than other inlets. All inlets are equipped with automatically closing synthetic rubber check valves.

Squeeze film shaft damper oil system

An improved shaft damper bearing utilizing spaced apart piston ring seals to seal off an annular squeeze film space between the rings, includes diagonal surface cross-section ring grooves in the bearing housing with diagonal cross-section rings in the housing grooves adapted to engage a bearing support undergoing radial motion in the housing.

Squeeze film damper seal

Shaft damper bearing utilizing spaced apart piston ring seals to seal off an annular squeeze film space between the rings, includes diagonal surface cross-section ring grooves in the bearing housing with diagonal cross-section rings in the housing grooves adapted to engage a bearing support undergoing radial motion in the housing.

A squeeze film damper employs spaced apart diagonal cross-section piston ring seals in diagonal cross-section grooves in cross-section to cross-section matching and registry relationship with diagonal surfaces directly exposed to the squeeze film space between the rings.

Oil film damper seal ring

A shaft damper bearing utilizing spaced apart piston ring seals to seal off an annular squeeze film space between the rings, includes diagonal cross-section ring grooves in the bearing housing with diagonal cross-section rings in the housing grooves adapted to engage a bearing support undergoing radial motion in the housing.

Growing community of inventors

Cincinnati, OH, United States of America

Anant Pal Singh