General Electric Company

General Electric Technology Gmbh

Rebecca Evelyn Hefner

Paul Stephen DiMascio

George Albert Goller

Michael Douglas Arnett

Andrew Scott Kessie

Stephen Gerard Pope

Murali Krishna Kalaga

Jeff P Czapiewski

Kamel Abdelkader Tayebi

Bradford Foulkes

Alston Ilford Scipio

Sanji Ekanayake

Gilbert Otto Kraemer

Rahul Jaikaran Chillar

Victor John Morgan

Ronald Ralph Cairo

Surinder Singh Pabla

Krishnamurthy Anand

Dale Joel Davis

Paul Robert Fernandez

Sundar Amancherla

Guruprasad Sundararajan

Wolfgang Franz Dietrich Mohr

Xiaomo Jiang

John Robert Korsedal

Anthony J Rossi

Maruthi Manohar Jupudi

William Keith Eyers

Christopher Dean Higgins

Richard Todd Everhart

Paul S Dimascio

Anbarasan Viswanathan

Trevor James Dale

Steve David Hiner

Kelsey Elizabeth Beach

Abdurrahman Abdallah Khalidi

Stephen Francis Banks

Cristina Colindres Kraemer

Joerg Pfistner

Robert G Kelly

Anthony M Rossi

Mel Joseph Esmacher

Pablo De Jesus Diaz

Douglas Alan Brown

Sumith Unniyattil

Prashanth Pillai

Muralikrishan R

Jianxiong Chen

Sal Esposito

Kamel Tayebi

Paul Stephen Dimascio

Kelsey E Beach

Mel J Esmacher

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

Turbine system with particulate presence and accumulation model for particulate ingress detection

Air filtration assemblies configured to provide instant detection of particles and/or improve particle filtration are disclosed. The assemblies may include an air inlet duct in fluid communication with a compressor of a gas turbine system. The air inlet duct may include an inlet for receiving intake air including intake air particles, and an outlet positioned opposite the inlet. The assembly may also include a plurality of vane filters at the inlet, an array of fabric filters positioned in the air inlet duct, downstream of the vane filters, and a silencer assembly positioned in the air inlet duct, downstream of the fabric filters. Additionally, the assembly may include an electrostatic component positioned in the air inlet duct, downstream of the fabric filters. The electrostatic component may be configured to charge the intake air particles that pass through the vane filters and the fabric filters.

Air filtration assemblies for gas turbine systems and methods for filtering intake air in gas turbine systems

A control system and method utilizing one or more processors that are configured to determine contaminant loading of blades of a turbomachinery compressor based on one or more environmental conditions to which the turbomachinery compressor is exposed and one or more atmospheric air inlet conditions of the turbomachinery compressor. The one or more processors then determine a corrosion contaminant concentration on the blades of the turbomachinery compressor based on the contaminant loading that is determined and determine an upper limit on or a distribution of potential corrosion of the blades of the turbomachinery based on the corrosion contaminant concentration, at least one of the environmental conditions to which the turbomachinery compressor is exposed, and the corrosion contaminant concentration that is determined.

Control system and method for determining contaminant loading of turbine blades

The present application provides a gas turbine engine. The gas turbine engine may include a compressor, a compressor wash system in communication with the compressor, a condensate or boiler feed water system in communication with the compressor, and a dosing system in communication with the condensate or boiler feed water system.

Systems and methods for compressor anticorrosion treatment

Systems and methods for assessing and quantifying the environmental impact on a mechanical component are provided. In one embodiment, a method can include receiving one or more first set(s) of data from one or more first data acquisition system(s) configured to communicate with an onboard system of an aircraft. The method can further include receiving one or more second sets of data from one or more second data acquisition systems that are remote from the aircraft. The method can include determining an aggregate amount of the environmental condition experienced by a mechanical component of the aircraft based at least in part on the first sets of data and the second sets of data. The method can include predicting a level of distress associated with the mechanical component based at least in part on the aggregate amount of the environmental condition experienced by the mechanical component.

Environmental impact assessment system

A corrosion monitoring system includes at least one corrosion sensor. The corrosion sensor includes a metallic plug having at least one opening, at least one ceramic sheath in the opening of the metallic plug, and a plurality of probes. Each probe has a central portion with a predetermined cross sectional area extending from the metallic plug. The ceramic sheath electrically isolates each first end and each second end of the probes from the metallic plug and the other first ends and second ends. The probes are sized to provide a distribution of predetermined cross sectional areas of the central portions. The corrosion monitoring system also includes a resistance meter measuring an ohmic resistance for at least one of the probes and a computer determining a corrosion rate by correlating a rate of change of the ohmic resistance to the corrosion rate of the probe.

Corrosion sensor, corrosion monitoring system, and method of quantifying corrosion

A control system for a gas turbine includes a processor. The processor configured to access one or more operating parameters of the gas turbine. The operating parameters are configured to specify how the gas turbine operates. The processor is configured to predict a rate of degradation to one or more parts of a compressor of the gas turbine due to one or more effects on the parts by operating the gas turbine according to the one or more operating parameters. The processor is configured to send an alert to an electronic device based at least in part on the rate of degradation of the compressor.

System and method to enhance corrosion turbine monitoring

Methods and compositions are disclosed for inhibiting corrosion on metal surfaces of gas turbine air compressors. The methods comprise contacting the metal surfaces with a corrosion inhibiting composition comprising at least one filming amine.

Compositions and methods for inhibiting corrosion in gas turbine air compressors

A metallic seal assembly, a turbine component, and a method of regulating flow in turbo-machinery are disclosed. The metallic seal assembly includes a sealing structure having thermally-responsive features. The thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change. The turbine component includes the metallic seal assembly. The method of regulating flow in turbo-machinery includes providing the metallic seal assembly and raising or retracting the thermally-responsive features in response to the predetermined temperature change.

Metallic seal assembly, turbine component, and method of regulating airflow in turbo-machinery

A thermally-controlled component and thermal control process are disclosed. The thermally-controlled component includes thermally-responsive features. The thermally-responsive features are configured to modify a flow path to control temperature variation of the thermally-controlled component. The thermally-responsive features deploy from or retract toward a surface of the thermally-controlled component in response to a predetermined temperature change. The thermal control process includes modifying the flow path in the thermally-controlled component to control temperature variation of the thermally-controlled component and/or cooling a region of the thermally-controlled component through the thermally-responsive features deploying from or retracting toward a surface of the thermally-controlled component.

Thermally-controlled component and thermal control process

A method for manufacturing a corrosion sensor includes spraying a non-conductive material on a substrate and spraying a conductive material at discrete locations on the substrate or on the non-conductive material. The method further includes spraying the non-conductive material around the discrete locations of the conductive material.

Method for manufacturing a corrosion sensor

A system includes a catalytic reactor configured to mount to a combustor. The catalytic reactor includes a catalyst configured to reduce emissions associated with combustion in the combustor. The catalytic reactor also includes a first and a second sacrificial coating disposed over the catalyst prior to mounting of the catalytic reactor into the combustor, wherein the first and second sacrificial coatings are removable while the catalytic reactor is mounted to the combustor without damaging the catalyst.

System and method of a catalytic reactor having multiple sacrificial coatings

Aspects of the invention provide an apparatus for cleaning airfoils inside a gas turbine compressor. In one embodiment, an apparatus for cleaning at least one airfoil within a turbine compressor, includes: a hose for applying cleaning material to the at least one airfoil; and an articulation assembly for articulating a nozzle of the hose, the articulation assembly including: a main shaft attached to the hose at a first end; and an articulating trigger for rotating the first end of the main shaft. The apparatus may further include a borescope attached to the articulation assembly and a borescope monitor for viewing the at least one airfoil via the borescope.

Dry ice cleaning apparatus for gas turbine compressor

A components comprising a plurality of tab members formed thereon are provided. The plurality of tab members include at least one dissimilar metallic layer applied to the component. The plurality of tab members are configured to extend away from or retract toward a surface of the component in response to a temperature change.

Components having tab members

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Fountain Inn, SC, United States of America

Rebecca Evelyn Hefner