General Electric Company

Ge Infrastructure Technology, LLC

Garth Curtis Frederick

Gilbert Otto Kraemer

Anthony Wayne Krull

Geoffrey David Myers

Kenneth Damon Black

Timothy Andrew Healy

Joseph Vincent Citeno

John Charles Intile

Radu Ioan Danescu

Brett Darrick Klingler

Jonathan Dwight Berry

Lewis Berkley Davis, Jr

David Leach

Jason Dean Fuller

Alexey V Vert

John Carver Maters

David Kaylor Toronto

Samer Aljabari

Pierre Beaufrere

Douglas C Morgan

Luls M Flamand

Luis M Flamand

A combined cycle power plant CCPP includes one turbomachine and heat recovery steam generator HRSG that is shutdown (or offline) and a second turbomachine and heat recovery steam generator HRSG that is online. The HRSG supplied duct dampers can provide sealing air therein to ensure no back flow from the online turbomachine to the shutdown turbomachine of the plant. However, as cooling flow is desired, a controlled flow may be implemented to allow cooling flow to the shutdown turbomachine. This solution is valuable to cool CCPP configurations with multiple (e.g., 2) HRSGs discharging into a common exhaust stack without individual flues dedicated to each HRSG, regardless of turbomachine configuration.

System and process for active draft control of power plant

A system and process for restarting a turbomachine includes a shutdown cooldown protection process implemented by a plant level control system or direct control system of the turbomachine. The system and process for restarting ensure rotating components are cooled as expected prior to a unit restart. This system and process for restarting will lockout an ability to restart if an improper cooldown of rotating components is detected. If this lockout is enabled, delaying restart for the rotating components to cool naturally is needed, or the operator could decide to force cool the components.

System and process for restarting a turbomachine

In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, a method for detecting a flame holding condition about a fuel injector. The method may include the steps of: detecting an upstream pressure upstream of the secondary fuel injector; detecting a downstream pressure downstream of the secondary fuel injector; determining a measured pressure difference between the upstream pressure and the downstream pressure; and comparing the measured pressure difference to an expected pressure difference.

Systems and methods for detecting combustor casing flame holding in a gas turbine engine

Optical flame holding and flashback detection systems and methods are provided. Exemplary embodiments include a combustor including a combustor housing defining a combustion chamber having combustion zones, flame detectors disposed on the combustor housing and in optical communication with the combustion chamber, wherein each of the flame detectors is configured to detect an optical property related to one or more of the combustion zones.

Optical flame holding and flashback detection

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

A combustor of a turbine engine having a combustion zone defined therein is provided and includes a fuel nozzle, including two or more burners, each of the burners having a passage defined therein through which combustible materials are permitted to travel toward the combustion zone, a plurality of sensors disposed in relative association with each of the burners to respectively sense static pressures within the passages of each of the burners and to respectively issue sensed static pressure signals accordingly, and a controller, coupled to the sensors and receptive of the signals, which is configured to determine from an analysis of the signals whether any of the burners are associated with a flashback risk and to mitigate the flashback risk in accordance with the determination.

Fuel nozzle flashback detection

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

Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (A), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.

Method and system to determine composition of fuel entering combustor

A method and system for reducing the amount of nitrogen oxides (NO) in a combustion gas waste stream by (1) analyzing the waste stream to determine the amount of NO; (2) determining the stoichiometric amount of ammonia required to reduce the NOconcentration down to a required level or less; (3) determining the flow rate profile of NOcomponents across the combustion gas waste stream upstream of an ammonia injection grid; (4) selecting specific locations within the ammonia injection grid to activate ammonia valves; (5) injecting controlled amounts of ammonia vapor into the gas stream at grid locations corresponding to the location of NOin the gas stream; and (6) treating the gas stream using a selective catalytic reduction unit to reduce the amount of NOdown to acceptable levels.

Growing community of inventors

Greenville, SC, United States of America

Garth Curtis Frederick