General Electric Company

General Electric Technology Gmbh

Jason Dean Fuller

Justin Allen

Daniel Richard Waugh

Paige Marie Sopcic

William Forrester Seely

Robert Joseph Iasillo

John Carver Maters

Douglas Edward Dean

Jason Nathaniel Cook

Christopher James Wenner

Christopher T Meadows

Gary Michael Itzel

Rahul Jaikaran Chillar

Robert Warren Taylor

Karl Dean Minto

Sarah Lori Crothers

Peter Martin Maly

Derrick Walter Simons

Michael Joseph Alexander

Garth Curtis Frederick

Joell Randolph Hibshman, Ii

Brian Allen Rittenhouse

Maxime Buquet

Louis Veltre

Robert Joseph Loeven, Ii

Noemie Dion Ouellet

Matthew James Findlay

Christian-Anghel Solacolu

Haley Marie Boyd

Steve W Backman

Valerie Suzanne Vernet

Daniel Joseph Flavin

Samuel Ernst-Fortin

Luis M Flamand

Cathy Chiurato

Kelly M Graf

Douglas C Morgan

Luls M Flamand

Robert Joseph Loeven Ii

Valerie S Vernet

A loading/unloading method for a gas turbine system is disclosed. The gas turbine system includes a combustion section featuring a primary combustion stage with a first plurality of fuel nozzles and a downstream, secondary combustion stage with a second plurality of fuel nozzles. For loading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a higher number of at least one of the first or second plurality of fuel nozzles; and for unloading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a lower number of at least one of the first or second plurality of fuel nozzles. During each combustion mode, regardless of whether loading or unloading, a primary combustion stage exit temperature of a combustion gas flow is controlled to be within a predefined target range corresponding to the respective combustion mode.

Gas turbine load/unload path control

A gas turbine engine that includes a stage of guide vanes, a compressor downstream from the stage of guide vanes, and a combustor downstream from the compressor. The combustor includes a primary combustion zone and a secondary combustion zone downstream from the primary combustion zone. The primary combustion zone includes an exit configured to channel combustion gases towards the secondary combustion zone. A controller is communicatively coupled with the stage of guide vanes, the controller configured to monitor a temperature at the exit of the primary combustion zone, and selectively open and close the guide vanes to maintain the temperature within a predefined temperature range.

Gas turbine engine and methods of controlling emissions therefrom

In one embodiment, a turbine system includes a number of sensors, each of the number of sensors disposed in a respective location of the turbine system, and a controller including a memory storing one or more processor-executable routines and a processor. The processor configured to access and execute the one or more routines encoded by the memory wherein the one or more routines, when executed cause the processor to receive one or more signals from the number of sensors during any stage of operation of the turbine system, and convert the one or more signals to audio output.

System for detecting anomalies in gas turbines using audio output

A tangible non-transitory computer readable medium may include instructions to analyze a first signal indicative of a speed of a turbine system and transform the first signal into a second signal. The tangible non-transitory computer-readable medium may also include instructions to transmit the second signal to control a speed of the turbine system by actuating a field device. Actuating the field device may include controlling a fluid level in a torque converter mechanically coupled to the turbine system, and the speed may be below a minimum setpoint of the turbine system.

System and method for controlling turbine speed using torque converter

A method of testing a gas turbine is provided. The gas turbine includes a first compressor and an expansion turbine coupled by a drive shaft. The method includes operating the gas turbine and a second compressor at a first steady load and a first steady drive shaft speed. The second compressor is rigidly coupled to the drive shaft. The method also includes changing a load of the second compressor by a known amount, and measuring a time required for the gas turbine to stabilize at a second steady load and a second steady drive shaft speed in response to the changed load of the second compressor.

System and method for testing a gas turbine

A system includes a controller configured to receive one or more inputs associated with an operation of a turbine system, derive a set of ramp rates for the turbine system based at least in part on the one or more inputs, and to select a ramp rate from the set of ramp rates. The ramp rate includes a variable ramp rate. The controller is further configured to generate an output signal based on the selected ramp rate.

Systems and methods for generating variable ramp rates for turbomachinery

Aspects of the disclosure include apparatuses and program products for recovering speed in a driveline assembly. An apparatus in one embodiment may include: a sensor measuring a shaft speed of a rotatable shaft within a driveline assembly, wherein the driveline assembly includes: a load coupled to the rotatable shaft, a primary power source coupled to the load through the rotatable shaft to deliver a first power output to the load, and a secondary power source coupled to the load through the rotatable shaft to deliver a second power output to the load, wherein the second power output is less than the first power output; and a controller in communication with the secondary power source and the sensor, wherein the controller increases the second power output in response to the shaft speed being less than a minimum speed threshold.

Recovering speed in driveline assembly

A control apparatus for angling guide vanes of a torque converter is provided and includes a modeling unit configured to receive current condition data, to determine a current input power supplied by a starting motor from the current condition data and to output a result of the determination as a control signal and a controller, which is coupled to the modeling unit and thereby receptive of the control signal. The controller is configured to execute a comparison of the current input power with a rating of the starting motor and to angle the guide vanes of the torque converter at an angle in accordance with a result of the comparison.

Control apparatus for angling guide vanes of a torque converter

Embodiments of the disclosure relate to systems and methods for holding target turbomachine compressor pressure ratio constant while varying the shaft speed. In order to characterize a load compressor and validate the compressor design, the speed of the load compressor can be changed while controlling the compressor operating line and holding the inlet guide vanes at a constant angle. Discharge control valves can be dynamically adjusted to maintain the pressure ratio equal to the operating line over a range of speeds.

Systems and methods for holding target turbomachine compressor pressure ratio constant while varying shaft speed

The present invention has the technical effect of reducing the start-up time associated with starting a powerplant machine. An embodiment of the present invention provides a method of starting a powerplant machine, such as, but not limiting of, a turbomachine. An embodiment of the method of the present invention provides a new philosophy for starting a turbomachine. This new philosophy involves testing the turbomachine systems before the start-up process begins.

Method of starting a turbomachine by testing operational support systems during the purging process

A method of managing transient events regularly seen during gas turbine operation that may cause undesirable operation and hardware damage. During certain transient operations, a lag may be seen between reference exhaust temperature and actual turbine exhaust temperature. This lag can result in an under-fired condition within the combustion system of variable magnitude and duration. Either fuel split schedules or a control algorithm can be positioned during these transients to prevent combustion dynamics or loss of flame. Combustion dynamics are known to cause damage that may require hardware replacement. Once the transient has completed, normal control operation is resumed.

Method of mitigating undesired gas turbine transient response using event based actions

A method for controlling a turbomachine exhaust gas recirculation (EGR) system is provided. The EGR system may allow for the removal and sequestration of at least one constituent within the exhaust before the recirculation occurs.

Method for controlling a flowrate of a recirculated exhaust gas

A method and algorithm are provided to operate a gas turbine at baseload in an emission compliant capable mode to avoid combustion dynamics while operating with cold fuel and hot fuel combustion hardware. The method includes performing a gas turbine operational sequence such as a startup to an emission compliant capable mode. A gas fuel temperature is measured. The gas turbine is operated in the emissions compliant capable mode according to a designated fuel split for avoiding combustion dynamics when a temperature for a gas fuel is below a designated value. A determination is made whether a modified wobbe index for the gas fuel is below an emissions compliant value. An alarm is activated if the modified wobbe index is below the emissions compliant value to notify the operator of a potential emissions shift.

Operating a turbine at baseload on cold fuel with hot fuel combustion hardware

A method and system for controlling an exhaust gas recirculation (EGR) system is provided. The method and system may incorporate a device or devices that continuously monitors an exhaust stream for harmful constituents. The method and system may control components of the EGR system based on the concentration of harmful constituents within the exhaust.

Method and system for controlling an exhaust gas recirculation system

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Simpsonville, SC, United States of America

Jason Dean Fuller