General Electric Company

Other

Ge Infrastructure Technology, LLC

Michael Ericson Friedman

Bryan Edward Williams

Paul Lawrence Kalmar

Gang Liu

Thomas Robbins Tipton

John Franklin Ryman

Wei Ning

Stephen Robert Prince

Mark Alan Newton

Brian Patrick Senkiw

Colin Beckwith Spellmeyer

Stephen Paul Wassynger

Dale Robert Lombardo

Andrew Joseph Colletti

John David Dyer

Roberto Anthony Nunez

Minhajuddin Syed

James Purdue Masso

Tushar S Desai

Lynn M Naparty

Mahesh Gopalakrishnan

Premkumar Rajamohan

Madhusudan Rao Pothumarthi

Yong Soon Phua

William Michael Michaud

Lamont Joseph Lum

Christopher Robert Kelly

Jonathan Tilley

A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body and aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body that is smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

Balancing weight entry port for turbine rotor

Protective covers for rotors are disclosed. The protective covers may include a first liner portion contacting and covering a first portion of the rotor, and a second liner portion positioned adjacent and at least partially aligned circumferentially with the first liner portion. The second liner portion may contact and cover a second portion of the rotor. The protective covers may also include an outer casing covering the first liner portion and the second liner portion.

Protective cover for rotor and associated shipping apparatuses

A peening device for treating a component includes a shot media propulsion source configured to propel a quantity of shot media. The device also includes a plurality of treatment enclosures each selectively coupleable to the shot media propulsion source. Each of the treatment enclosures has a shape complementary to a corresponding one of a plurality of portions of the component, such that each treatment enclosure and the corresponding portion cooperate to enclose the shot media.

Apparatus and method for peening of machine components

A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body, aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

A method of assembling a rotor is provided, in which each rotor disk comprising a connecting element. The method includes: (a) applying heat to a localized region of a first rotor disk of a plurality of rotor disks to selectively deflect a first connecting element of the first rotor disk, wherein the first rotor disk is stationary during heating; (b) installing the first rotor disk onto a rotor stack containing at least one rotor disk; and (c) repeating steps (a) and (b) for each rotor disk of the plurality of rotor disks; and (d) allowing the rotor disks, when stacked, to cool. When cooled, the respective connecting element of each rotor disk that has been selectively deflected contracts into an interference fit with an adjacent rotor disk. A system for selectively heating a localized region of a rotor disk is also provided.

System and method for assembling gas turbine rotor using localized inductive heating

A system and method for testing rotor stack assemblies having a plurality of rotor disks is disclosed. A measurement system for measuring at least one electrical characteristic of the plurality of rotor disks is used with a computer electronically connected to the measurement system for capturing data from the measurement system. Software associated with the computer transforms the data into output used to determine flange joint contact topography in the plurality of rotor disks.

Low resistance surface contact topography mapping

Various embodiments include a rotor having a dovetail slot with a bulbous fillet region, and in some cases, recessed inclined bearing surfaces. Various embodiments include methods of forming such a slot in a turbomachine rotor.

Turbomachine rotor having dovetail slot and method of machining

A compressor having a compressor blade with a blade tip portion configured to reduce stresses in the blade tip of the compressor blade is provided. The compressor blade includes a first and second faces extending to the blade tip portion. The blade tip portion includes a blade tip, a first recess extending between the first face and the blade tip, and a second recess extending between the second face and the blade tip.

Compressor having blade tip features

A method of decreasing the operational stresses acting on a target airfoil row in a turbine engine; wherein the target airfoil row is bordered on each side by a first upstream airfoil row and a first downstream airfoil row; the first upstream airfoil row and the first downstream airfoil row having substantially the same number of similar airfoils and both comprising one of a row of rotor blades and a row of stator blades, and the target airfoil row comprising the other; the method comprising the step of: configuring the circumferential position of the airfoils of the first upstream airfoil row and the airfoils of first downstream airfoil row such that at least a portion of the airfoils of the first upstream airfoil row and at least a portion of the airfoils of the first downstream airfoil row comprise a clocking relationship of between 25% and 75% pitch.

Turbine airfoil clocking

An assembly of airfoils in a turbine engine, the assembly comprising: at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row; wherein the first airfoil row and the third airfoil row each comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other; and wherein at least a majority of the mid-channel points of the airfoils in the third airfoil row are positioned circumferentially within +/&#x2212;25% pitch of the third airfoil row with respect to the location at which a wake flow during a selected operating condition from the first airfoil row is determined to enter the third airfoil row.

A rotating assembly. The rotating assembly may include a wheel, a slot positioned about the wheel with the slot having a staking recess positioned therein, a wheel attachment positioned within the slot, and a staking insert positioned within the staking recess. The staking recess axially retains the staking insert and the wheel attachment radially retains the staking insert.

Replaceable staking insert

An axial retention system for restraining axial movement of a first machine component having a dovetail within a complimentary-shaped dovetail slot in a second machine component that includes a first curved groove formed in a bottom surface of the dovetail slot and a second curved groove formed in a bottom surface of the dovetail. The first and second grooves are in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery aperture. A curved locking clip is received within the closed periphery aperture. An optional cover plate may be placed over the ends of the locking clip, with ends of the locking clip deformed by, for example, swaging.

Machine component retention

A safety restraint for securing a dog to the seat of an automotive vehicle includes a one-piece harness having opposing tabs secured to each other by releasable adhesive strips at the chest and beneath the shoulders and flanks of the animal, and permitting freedom of movement but providing a shock distributing shell about the body length of the animal. A pair of rings coupled to the side of the harness in the region of the shoulder and flank of the animal are releaseably coupled to clips mounted on a pair of belts secured about the back of the seat. The clips are individually slidable in upward and downward directions along the lengths of the belts by separate straps which receive the clips and extend along portions of the length of the belts. This permits the animal to stand, sit or lie on the seat while at the same time limiting sideward or forward motion of the animal in the event of a sudden stop or collision. Shocks are partially absorbed within the belt and harness structure, and forces that are not absorbed are uniformly distributed in such manner that there is no injury to the spinal column or localized tightening or restraint.

Growing community of inventors

Simpsonville, SC, United States of America

Michael Ericson Friedman