General Electric Company

Dean Matthew Erickson

Hua Zhang

Douglas Scott Byrd

David Wesley Ball, Jr

Jason Allen Seale

Korey Frederic Rendo

Timothy Russell Bilton

Kenneth Neil Whaling

Brian Michael Gallagher

Michael Savale

Michael Francis Michalski

Mitch Mircea Orza

Rahul Jaikaran Chillar

Bradly Aaron Kippel

Scott Arthur Day

Jatila Ranasinghe

Douglas Frank Beadie

Carl Gerard Schott

Christina Renee Pompey

Bryan Edward Sweet

Gregory Allan Crum

Diego Fernando Rancruel

George Martin Gilchrist

Joseph Law

David William Smith

Mihir Kumar Lal

Iris Ziqin Hu

John Victor Hains

Kyle Joseph Conger

Leslie Yung-Min Tong

Michael John Mariani

Robert Lester Brooks

Priscilla Childers

Jose Francisco Aguilar

Ravi Praveen Eluripati

Durgaprasad Janapaneedi

Rakesh Sivasankaran

James L Davis

Mica Lee Longwell

Gerald Wilson Grove

Martin Lopez

Daniel B Holcombe

Lane Porter

Carlos Gabriel Roman

Rushi Mahesh Amin

Joseph Robert Law

David Michael Kindel

Byran Edward Sweet

George Martin Iii Gilchrist

Matthew S Kight

David W Smith

Inlet air heating systems for combined cycle power plants and combined cycle power plants including inlet air heating systems are disclosed. The inlet air heating systems may include a plurality of heating coil assemblies partially positioned within an inlet housing of a gas turbine system, and a vent valve in fluid communication with each of the heating coils. The inlet air heating system may also include a supply line in fluid communication with the heating coils to provide water to the heating coils, and a hot water line in fluid communication with the supply line and a component positioned downstream of a condenser of the combined cycle power plant. The hot water line may provide hot water from the combined cycle power plant to the supply line. Additionally, the inlet air heating system may include a drain line in fluid communication with the heating coils and the condenser.

Inlet air heating systems for combined cycle power plants

Embodiments of the present disclosure include methods, systems and program products for controlling a water bath heater for a fuel gas. Methods according to the present disclosure can include: calculating at least one calculable condition of the fuel gas based on a set of conditions of the fuel gas entering the water bath heater and a type of control valve located downstream of the water bath heater; calculating a target temperature differential for the fuel gas based a set of conditions of the fuel gas entering the water bath heater and the at least one calculable condition; and adjusting an operating parameter of the water bath heater to adjust a temperature of the fuel gas leaving the water bath heater by the target temperature differential.

Controlling a water bath heater for fuel gas

The present application and the resultant patent provide a gas turbine engine system. The gas turbine engine system may include a gas turbine engine, a water wash system, and a system controller. The gas turbine engine may include a compressor, a combustor in communication with the compressor, and a turbine in communication with the combustor. The water wash system may be in communication with the gas turbine engine and configured to remove contaminants therefrom. The water wash system may include a number of valves configured to control flows through the water wash system, and a number of sensors configured to measure operating parameters of the water wash system. The system controller may be in communication with the valves and the sensors and operable to automatically control the valves upon receiving operating parameter signals from the sensors in order to perform a wash of the gas turbine engine.

Automated water wash system for a gas turbine engine

A system for heating fuel in a combined cycle gas turbine includes a fuel heat exchanger downstream from a turbine outlet, and the fuel heat exchanger has an exhaust gas inlet, an exhaust gas outlet, a fuel inlet, and a fuel outlet. A first exhaust gas plenum has a first exhaust gas inlet connection between the turbine outlet and a heat exchanger and a first exhaust gas outlet connection upstream from the exhaust gas inlet. A second exhaust gas plenum has a second exhaust gas inlet connection downstream from at least a portion of the heat exchanger and a second exhaust gas outlet connection upstream from the exhaust gas inlet.

System and method for heating fuel in a combined cycle gas turbine

A system for heating combustor fuel includes a turbine exhaust plenum and a heat exchanger downstream from the turbine exhaust plenum. The heat exchanger has an exhaust inlet, an exhaust outlet, a fuel inlet, and a fuel outlet. An exhaust recirculation plenum has a recirculation inlet connection downstream from the exhaust outlet and a recirculation outlet connection upstream from the exhaust inlet. The system further includes structure for controlling a recirculated exhaust flow from the exhaust outlet into the exhaust recirculation plenum.

System and method for heating combustor fuel

A method of operating a fuel heating system is provided. The method includes performing pre-ignition diagnostic checks on a plurality of components of the fuel heating system, wherein at least one inlet damper and at least one outlet damper of an exhaust flow circuit are each in a closed position. The method also includes purging the fuel heating system of unburned hydrocarbons. The method further includes operating the fuel heating system in a normal operating condition. The method yet further includes operating the fuel heating system in a cool down condition, wherein the at least one inlet damper is in the closed position.

Method of operating a fuel heating system

The present application provides a passive control valve actuator cooling system to provide a flow of cooling air to a control valve actuator used with a gas turbine engine. The passive control valve actuator cooling system may include a turbine enclosure with a negative pressure therein, a radiation shield with a number of radiation shield outlets and the control valve actuator positioned therein, and a cooling air line extending from outside of the turbine enclosure to the radiation shield such that the negative pressure within the turbine enclosure pulls the flow of cooling air into and through the radiation shield so as to cool the control valve actuator.

Passive cooling system for control valve actuators within a negative pressure turbine enclosure using ambient cooling air

The present application provides a fuel conditioning system for delivering a flow of fuel to a nozzle in a gas turbine engine. The fuel conditioning system may include a fuel compressor to increase the pressure of the flow of fuel, a pressure reduction valve to decrease the pressure of the flow of fuel, and a heater downstream of the pressure reduction valve. The pressure reduction valve may include a rotary control valve.

Fuel conditioning system

Star shaped exercise platform

An approach for utilizing fuel gas to purge a dormant fuel gas circuit is disclosed. In one aspect, there is a fuel gas supply that supplies fuel to fuel gas circuits. Gas control valves, each coupled to one of the fuel gas circuits control the flow of fuel gas thereto from the fuel gas supply. A fuel purge system selectively purges fuel gas circuits from the fuel gas circuits that are dormant with fuel gas from the fuel gas supply.

Utilization of fuel gas for purging a dormant fuel gas circuit

A impingement cooling system for heavy duty turbines that includes a manifold affixed to a casing of the heavy-duty turbine, wherein the manifold includes a plurality of impingement holes in the surface of the manifold and a blower that provides air flow across the plurality of impingement holes of the manifold to cool the casing of the heavy-duty turbine to control the clearance between a tip of a turbine blade and a shroud of the heavy-duty turbine.

Turbine case impingement cooling for heavy duty gas turbines

A fuel delivery system for a combustion turbine engine, comprising: a fuel line having a fuel compressor and parallel branches downstream of the fuel compressor: a cold branch that includes an after-cooler; and a hot branch that bypasses the after-cooler; a rapid heating value meter configured to measure the heating value of the fuel from the fuel source and transmit heating value data relating to the measurements; means for controlling the amount of fuel being directed through the cold branch and the amount of fuel being directed through the hot branch; and a fuel-mixing junction at which the cold branch and the hot branch converge; wherein the fuel-mixing junction resides in close proximity to a combustor gas control valve.

Methods and systems relating to fuel delivery in combustion turbine engines

A combustion turbine engine that includes: a compressor; a combustor that receives fuel from a fuel line; a turbine; a heat exchange portion comprising a portion of the fuel line in heat transfer relationship with a heat source for heating the fuel; a rapid heating value meter disposed to test the heating value of the fuel that is configured to provide heating value test results within approximately 1 minute; a cold leg bypass comprising a fuel line that bypasses the heat exchange portion, the cold leg bypass being connected to the fuel line at an upstream fork and at a fuel mixing junction; and valves for controlling the fuel being directed through the heat exchange portion and the fuel being direct through the cold leg bypass; wherein the length of fuel line between the fuel mixing junction and the combustor is less than 20 meters.

Systems relating to turbine engine control and operation

A system is provided and includes first and second water supplies at first and second relatively high and low temperatures, respectively, a heat exchanger, coupled to the water supplies, through which fuel and relative amounts of the water supplies at the first and second temperatures flow for fuel heating and a controller, operably interposed between the water supplies and the heat exchanger, to select and/or modulate the relative amounts of the water supplies permitted to flow through the heat exchanger to heat the fuel to a temperature based on a heating requirement to meet a modified wobbe index (MWI) rating.

Fuel heater system including hot and warm water sources

In a gas turbine power plant, pressurized fuel gas undergoes pressure reduction and gas expansion before being provided to a gas turbine. Condensations, which can damage the turbine, can form as the fuel gas cools when the fuel gas undergoes the pressure reduction and expansion. An electric startup heater is used to superheat the fuel gas to substantially prevent the condensations from forming. The electric startup heater includes band heaters wrapped externally to a fuel gas pipe to heat the fuel gas from outside in. Compared to conventional heaters which provide superheating through internal heating elements, the electric startup heater reduces costs and provides increased safety, flexibility, operational efficiency and ability to adapt to varying fuel gas characteristics.

System and method for applying energy externally for fuel gas for dew point heating in gas turbine power plant

Growing community of inventors

Simpsonville, SC, United States of America

Dean Matthew Erickson