General Electric Company

Steven William Backman

Robert Joseph Iasillo

Mark Andrew Cournoyer

David William Smith

Kevin Lee Kunkle

Mark Andrew Runkle

Christopher David Miller

David John Chrisfield

Paul David Black

Kevin Andrew Spengler

Daniel D Morrison

Trevor Valder Jones

William Forrester Seely

Matthew John McKeever

David Spencer Ewens

Michael Joseph Alexander

Sanjeev Shyam Heda

Colin Wilkes

Prabhanjana Kalya

Kevin Jon O'Dell

Scott Alan Wood

Christopher Warren Childs

Carlos Andres Hein

Mark Andrew Johnson

Daniel Joseph Flavin

Carlo Angelo Yon

Scott Michael Schaberg

Laura Lea Boes

David J Van Buren

Christopher Childs

Kelly Marie Kurylo

Roger Doyle

Leslie Tong

Steven Rose

Eric Steven Norris

Matthew John Mckeever

Carloa Angelo Yon

A non-transitory computer readable storage medium storing one or more processor-executable instructions wherein the one or more instructions when executed by a processor of a controller, cause acts to be performed is provided. The acts to be performed include controlling a fuel split to a combustor of a gas turbine utilizing automatic tuning and switching control of the fuel split to the combustor of the gas turbine to utilizing an adjusted fixed fuel split schedule instead of automatic tuning. The adjusted fixed fuel split schedule includes a fixed fuel split schedule adjusted via a biasing value, and the biasing value is based on both the fixed fuel split schedule and an automatic tuning based fuel split.

System and method for adjusting combustor fuel split

A method and system for transferring between combustion modes in a gas turbine engine is provided. A processor generates data representative of an initial set of splits for providing at least one of fuel and air to at least one combustor in the gas turbine engine. A gas turbine engine model module generates data representative of at least one engine operating condition. A first split calculation module generates data representative of at least one set of active control splits to control the engine in a first combustion mode, using as an input the initial split data. A second split calculation module generates data representative of at least one set of passive control splits to control the engine in at least a second combustion mode. Transfer between combustion modes may be accomplished via use of at least one of the active control splits and the passive control splits.

Method and system for combustion mode transfer for a gas turbine engine

A system for remote detection of surge in a fleet of turbine engines includes an on-site monitoring device coupled to each turbine engine of the fleet of turbine engines. The on-site monitoring device is configured to continuously receive operating parameter measurements indicative of operational and thermodynamic conditions of the turbine engine. The operational condition includes a compressor exit condition of the turbine engine compressor. The on-site monitoring device is configured to compile and transmit a snapshot of the operating parameter measurements to a remote monitoring unit. The remote monitoring unit is positioned remote from each turbine engine of the fleet of turbine engines. The remote monitoring unit is configured to receive the snapshot of operating parameter measurements from the on-site monitoring device. The remote monitoring unit is further configured to detect surge in the turbine engine based on analysis of the snapshot of operating parameter measurements.

Method and systems for detection of compressor surge

A system includes a water injection system configured to supply water from a pressure regulating valve to a water manifold of a turbine engine. The system also includes a drain valve configured to drain at least a portion of the water from the pressure regulating valve during a start-up period of the water injection system at least until a stable water pressure is achieved downstream of the pressure regulating valve.

System and method for water injection in a turbine engine

A method of operating a fuel system is provided. The method includes removing fuel from at least a portion of the fuel system using a gravity drain process. The method also includes channeling nitrogen into at least a portion of the fuel system to facilitate removing air and residual fuel from at least a portion of the fuel system, thereby mitigating a formation of carbonaceous precipitate particulates. The method further includes removing air and nitrogen from at least a portion of the fuel system during a fuel refilling process using a venting process such that at least a portion of the fuel system is substantially refilled with fuel and substantially evacuated of air and nitrogen. The method also includes removing air from at least a portion of the refilled fuel system using a venting process. The method further includes recirculating fuel within at least a portion of the fuel system, thereby removing heat from at least a portion of the fuel system and facilitating a transfer of operating fuel modes.

Methods and apparatus for a nitrogen purge system

A method of operating a fuel system is provided. The method includes removing fuel from at least a portion of the fuel system using a gravity drain process. The method also includes channeling nitrogen into at least a portion of the fuel system to facilitate removing air and residual fuel from at least a portion of the fuel system, thereby mitigating a formation of carbonaceous precipitate particulates. The method further includes removing air and nitrogen from at least a portion of the fuel system during a fuel refilling process using a venting process, such that at least a portion of the fuel system is substantially refilled with fuel and substantially evacuated of air and nitrogen. The method also includes removing air from at least a portion of the refilled fuel system using a venting process.

Methods and apparatus for a combustion turbine nitrogen purge system

Methods and apparatus for a combustion turbine fuel recirculation system and nitrogen purge system

A method of operating a gas turbine engine is provided. The method includes introducing a fuel into a combustor, detecting a failure of ignition of the fuel, and preventing ignition until the introduced fuel is substantially removed from the gas turbine engine.

System for detecting ignition failure in a gas turbine engine

Method and system for detecting ignition failure in a gas turbine engine

A recirculation system for circulating distillate during gas fuel operation so as to reduce or eliminate distillate carbon formation. The recirculation system keeps the distillate's temperature below the carbon formation limit by circulating the distillate back to a heat sink and/or heat exchanger. The recirculating flow also exercises the flow dividers' gears without having to perform fuel transfers. Further, the system evacuates air from the liquid fuel lines to further decrease the likelihood of carbonaceous residue forming on any interior surfaces that are actually exposed to distillate.

Liquid fuel recirculation system and method

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Simpsonville, SC, United States of America

Steven William Backman