General Electric Company

Ge Infrastructure Technology, LLC

General Electric Technology Gmbh

David Leach

Ilya Alexandrovich Slobodyanskiy

Berardino Pezzella

Troy Joseph Schroeder

Michael Anthony O'Toole

Kevin Weston McMahan

Geoffrey David Myers

Mark Stewart Schroder

Jason Nathaniel Cook

Stuart Forrest Waldo

Peter Allen Bergendahl

Patrick Benedict Melton

Gilbert Otto Kraemer

Wei A Chen

David William Cihlar

Joel Meier Haynes

Larry W Plemmons

Sarah Lori Crothers

Douglas Frank Beadie

Iain Robertson Kellock

Mark Allan Hadley

Ping Yu

Alexey V Vert

Anthony Wayne Krull

John Joseph Lipinski

Hamid Reza Sarshar

Jayaprakash Natarajan

Garth Curtis Frederick

Brendan F Sexton

Jesse Edwin Trout

Daniel Richard Waugh

Tagir Nigmatulin

Wenjie Wu

Brandon Taylor Overby

Chi Ming Ho

Qingguo Zhang

Samer Aljabari

Suhui Li

Cedric Chow

Valerie Suzanne Vernet

Stephen Randolph Walcott

Jesse Blair Butler

Robert Kim Phelps

Garth Frederick, Ii

Manuel Moises Cardenas

Christan Xavier Stevenson

Brittany Dees

Vinayak Shashikant Godbole

Robert Leroy Smith

Ilya Alexandrovich Slobodyankskiy

Alexey Vert

Anthony Krull

Kevin Weston Mcmahan

Tagir Robert Nigmatulin

A dispatch advisor to assist in selecting operating conditions of a power plant that maximizes operational revenue is described. The dispatch advisor obtains a base load map for operating the power plant to meet base load power demands. The base load map includes a primary base load operating space for attaining target plant power output and efficiency, and an expanded base load portion for attaining higher plant power output and less than optimal efficiency. Both the primary base load operating space and the expanded base load portion associate power output and efficiency values of the power plant that result from a subset of operational parameter values for operating the power plant during base load. The dispatch advisor can transform the flexible base load map into one or more visualizations describing the revenue possibilities associated with operating the power plant based on operating values and attained power output and efficiency.

Dispatch advisor to assist in selecting operating conditions of power plant that maximizes operational revenue

A dispatch advisor for operating a power plant having at least one gas turbine with flexibility is described. The dispatch advisor can generate a representation of a flexible base load map for operating the power plant. The representation can include an aggregation of a primary base load operating space and an expanded portion of the base load operating space. The representation offers a range of operating values for operational parameters of the power plant during base load at various base load settings at predetermined ambient conditions and corresponding power output and efficiency values that are attained while operating the power plant at the range of operating values. This offers an operator of the power plant with flexibility in controlling the plant during base load.

Dispatch advisor for operating power plant with flexibility

A method of operating a rotary machine below a minimum emissions compliance load in a response mode includes reducing a fuel split to zero. The fuel split apportions a total flow of fuel to the combustor between a first combustion zone and a second combustion zone. The method also includes determining a current operating temperature of the first combustion zone using a digital simulation of the rotary machine. The method further includes determining a target operating temperature of the first combustion zone. The target operating temperature enables the rotary machine to operate below a traditional Minimum Emissions Compliance Load (MECL) while still in compliance with emissions standards. The method also includes channeling a first flow of fuel to the first combustion zone. The first flow of fuel decreases the temperature of the first combustion zone to the target operating temperature.

Systems and methods for extended emissions compliant operation of a gas turbine engine

A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided.

Nozzle system and method for starting and operating gas turbines on low-Btu fuels

A system includes a gas turbine combustor configured to combust a fuel and an oxidant, such as Oand Omixtures. The system also includes an aerodynamic peg disposed in the gas turbine combustor. The aerodynamic peg includes a first passage configured to convey a first fluid into the gas turbine combustor and a second passage configured to convey a second fluid into the gas turbine combustor. The first fluid and second fluid are different from one another.

System and method for fuel and steam injection within a combustor

A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.

Gas turbine burner

The present application provides a fuel delivery system for a combustor with reduced coherence and/or reduced combustion dynamics. The combustor can assembly may include a first manifold for delivering a first flow of fuel to a first set of fuel injectors and a second manifold for delivering a second flow of fuel to a second set of fuel injectors. The first flow of fuel may have a first temperature and the second flow of fuel may have a second temperature. The first temperature may be higher than the second temperature.

Combustor can temperature control system

An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough.

Aft frame and method for cooling aft frame

Systems and methods for controlling compressor extraction air flows from a compressor of a turbine system during engine turn down are provided. In one embodiment, a method for controlling compressor extraction air flows from a compressor of a turbine system during turn down includes a control unit monitoring one or more operating parameters of a turbine system associated with an exit temperature of a combustor of the turbine system. The method further includes the control unit detecting one or more operating parameters meeting or exceeding a threshold associated with a decrease in the exit temperature of the combustor. In response to detecting one or more operating parameter meeting or exceeding the threshold, a control signal is transmitted to at least one variable orifice located in the turbine system causing at least one variable orifice to alter at least one extraction air flow from the compressor.

Systems and methods for engine turn down by controlling extraction air flows

In one embodiment, a system includes an engine that includes a combustion chamber and a viewing port into the combustion chamber. The engine also includes a camera configured to obtain an image of a flame in the combustion chamber through the viewing port and a controller configured to adjust a parameter of the engine based on the image of the flame.

System and method for adjusting engine parameters based on flame visualization

An active clearance control system is provided that uses compressor extraction air to manipulate blade tip clearance in an industrial gas turbine and compressor. A stream of air is taken from a cooling and sealing air circuit and redirected to be used for active clearance control. The spent clearance control air is re-introduced into the hot gas path of the gas turbine for cooling and sealing purposes.

Integrated turbine sealing air and active clearance control system and method

A turbine casing alignment tool includes a first section securable to an outer shell of a turbine casing. A second section of the alignment tool is securable to an inner shell of the turbine casing. The alignment tool facilitates adjustment of at least one of the inner shell and the outer shell relative to the other in multiple degrees of freedom to control both co-linearity and concentricity of the outer shell and the inner shell.

Top mounted turbine casing alignment tool with multi-axis maneuverability

A steam gland includes a steam inlet scroll and an extraction scroll axially spaced from one another defining high and low pressure regions. A seal body is disposed between the regions and includes a pair of brush seals axially spaced from one another. Intermediate the brush seals is a honeycomb seal. The hybrid brush seal/honeycomb seal combination minimizes steam leakage between the high and low pressure regions and eliminates the possibility of heat induced damage to the rotor while optimizing seal leakage performance.

Hybrid honeycomb and brush seal for steam gland

Growing community of inventors

Simpsonville, SC, United States of America

David Leach