General Electric Company

Thomas Bradley Beddard

Carlos Alberto Collado

Peter Gaines Cleveland

Paul Stephen DiMascio

Joseph Anthony Weber

David Samuel Pesetsky

Christopher Dean Higgins

Anandraj Sengupta

James Bernard Fehlberg

Kenneth Lorenzo Parks

Patrick C Bowling

Michael Edward Bernard

Scott Matthew Sparks

David Stephen Muench

In one embodiment, a system includes a condition based replacement life (CBRL) approval system configured to receive a turbomachinery component data and to approve a turbomachinery component for CBRL based on the turbomachinery component data. The system further includes a CBRL validation system configured to repair the turbomachinery component into a repaired turbomachinery component, wherein the repaired turbomachinery component is configured to operate in a turbomachinery beyond a service time of the turbomachinery component.

Methods and systems for maintenance of turbomachinery

Disclosed is a method for tracking rotation of a turbomachine component including locating at least one tilt sensor at the turbomachine component and rotating the turbomachine component about a central axis to observe a portion of interest on the turbomachine component. The at least one tilt sensor detects an angle of rotation of the turbomachine component and transmits the angle of rotation from the at least one tilt sensor to a device which converts the angle of rotation to an indicia of the portion of interest. Further disclosed is a rotor including at least one tilt sensor and a system for tracking rotation of a turbomachine component including at least one tilt sensor and a device.

Method and system for rotation tracking of a turbomachine component

A core for use in casting a gas turbine bucket includes a solid, curved upper body portion and a pair of co-planar legs extending downwardly from the solid, curved upper body portions. The pair of legs are separated by an elongated open slot extending from a lower end of the core upwardly more than half a height dimension of the core, into the upper body portion. A pair of axially aligned pegs project in axially opposite directions from opposite sides of the solid, curved upper body portion, perpendicular to and above the elongated slot but spaced from an upper edge of the solid, curved upper body portion. The pair of pegs lie substantially in a plane containing the co-planar legs, and in a radial direction, the pegs are closer to the elongated slot than to the upper edge.

Perimeter-cooled stage 1 bucket core stabilizing device and related method

An airfoil. The airfoil may include a first number of cooling holes and a second number of cooling holes positioned within the airfoil. The first number of cooling holes and the second number of cooling holes each may include a turbulated section and a non-turbulated section.

Airfoil cooling holes

A turbine stage one bucket has an airfoil having a plurality of cooling holes passing through the airfoil from 0% span to 100% span whereby cooling air exits the airfoil tip into the hot gas path. X and Y coordinate values are given in Table I, locating the holes relative to the airfoil profile at airfoil profile sections of 5%, 50% and 90% span, Table I also giving the hole diameters. In this manner, cooling hole optimization for this turbine bucket airfoil is achieved. The cooling holes are also located in relation to the profile of the bucket airfoil given by the X, Y and Z coordinate values of Table II, the two coordinate systems having the same origin.

Perimeter-cooled turbine bucket airfoil cooling hole location, style and configuration

A tip shroud for use with a bucket of a turbine. The tip shroud may include a seal rail with a middle portion and a cutter tooth mounted about the middle portion of the seal rail.

Center located cutter teeth on shrouded turbine blades

Second stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values, from 0.05 to 0.95 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of &#xb1;0.160 inches in directions normal to the surface of the airfoil.

Airfoil shape for a turbine bucket

First stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0.05 span to 0.95 span convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of &plusmn;0.150 inches in directions normal to the surface of the airfoil.

Growing community of inventors

Simpsonville, SC, United States of America

Thomas Bradley Beddard