General Electric Company

Ming Cheng Li

Nicholas Joseph Kray

Christopher Charles Glynn

Ian David Wilson

Jason Wayne Black

Kevin Joseph Barb

Martin C Hemsworth

Susan Marie Hyde

Peter Wayte

Max Robert Farson

Gary D Mercer

Paul Izon

Weiwei Chen

Thomas Charles Mashey

Ronald Richard Wesorick

Bethany Hoogs

Sunil Kumar Sinha

Yi Zhang

Charles R Baum

Systems and methods for performing data anomaly detection and/or removal are usable to accurately assess baseline power consumption. According to one embodiment of the invention, a system can be provided. The system can be operable to receive energy consumption data of a location; select, based at least in part on a collection period of the energy consumption data, an algorithm for detecting anomalies in the energy consumption data; perform the algorithm on the energy consumption data to detect the anomalies in the energy consumption data; and determine an energy consumption baseline for the location based at least in part on a result of the algorithm.

Systems and methods for data anomaly detection

A Ti-6Al-4V-0.2O (Ti64) forged article is fabricated by forging a workpiece to make a forged gas turbine engine component having a thick portion thereof with a section thickness greater than 2&#xbc; inches. The forged article is heat treated by solution heat treating at a temperature of from about 50&#xb0; F. to about 75&#xb0; F. below the beta-transus temperature of the alloy, thereafter water quenching the gas turbine engine component to room temperature, and thereafter aging the gas turbine engine component at a temperature of from about 900&#xb0; F. to about 1000&#xb0; F. The resulting machined gas turbine engine component has a 0.2 percent yield strength of from about 120 ksi to about 140 ksi at its centerline, and a 0.2 percent yield strength of from about 160 ksi to about 175 ksi at a location about &#xbd; inch below a surface thereof.

Method for fabricating a thick Ti64 alloy article to have a higher surface yield and tensile strengths and a lower centerline yield and tensile strengths

A method enables a rotor assembly for a gas turbine engine to be fabricated. The method includes forming a blade including an airfoil extending from an integral dovetail used to mount the blade within the rotor assembly, and extending a projection from at least a portion of the blade, such that the stresses induced within at least a portion of the blade are facilitated to be maintained below a predetermined failure threshold for the blade to facilitate preventing failure of the blade.

Methods and apparatus for facilitating preventing failure of gas turbine engine blades

A tubular connector adapted to extend between two tubular components comprising a tubular body having an internal diameter, a first free end including an annular radial flange having a tapered surface adapted to engage a complementary seating surface on a first of the two tubular components, the internal diameter remaining constant through the first free end; and a second free end having an annular bulbous shape adapted to seat within a cylindrical end of a second of the two tubular components.

Connector tube for a turbine rotor cooling circuit

A measuring system for measuring axial displacement of a tube relative to an axially stationary component in a rotating rotor assembly includes at least one displacement sensor adapted to be located normal to a longitudinal axis of the tube; an insulated cable system adapted for passage through the rotor assembly; a rotatable proximitor module located axially beyond the rotor assembly to which the cables are connected; and a telemetry system operatively connected to the proximitor module for sampling signals from the proximitor module and forwarding data to a ground station.

Rotor component displacement measurement system

The steam cooling circuit for a gas turbine includes a bore tube assembly supplying steam to circumferentially spaced radial tubes coupled to supply elbows for transitioning the radial steam flow in an axial direction along steam supply tubes adjacent the rim of the rotor. The supply tubes supply steam to circumferentially spaced manifold segments located on the aft side of the - spacer for supplying steam to the buckets of the first and second stages. Spent return steam from these buckets flows to a plurality of circumferentially spaced return manifold segments disposed on the forward face of the - spacer. Crossover tubes couple the steam supply from the steam supply manifold segments through the - spacer to the buckets of the first stage. Crossover tubes through the - spacer also return steam from the buckets of the second stage to the return manifold segments. Axially extending return tubes convey spent cooling steam from the return manifold segments to radial tubes via return elbows.

Steam cooling system for a gas turbine

Growing community of inventors

Cincinnati, OH, United States of America

Ming Cheng Li