General Electric Company

Brian Michael Gallagher

Dean Matthew Erickson

Timothy Russell Bilton

Jonathan Carl Thatcher

Bryan Edward Sweet

Korey Frederic Rendo

John Victor Hains

Ravi Praveen S Eluripati

Priscilla Childers

Douglas Scott Byrd

Scott Arthur Day

Douglas Frank Beadie

David Wesley Ball, Jr

Mihir Kumar Lal

Ravi Praveen Eluripati

Durgaprasad Janapaneedi

Gary Cletus Mobley

Paul Pierre Antoine Drouvot

Rakesh Sivasankaran

Hatim Anwarhusan Khandwavala

David Wesley Ball

John Francis Wodecki

A gas turbine system includes a compressor section, a turbine section, a combustor section. The combustor section is in fluid communication with a fuel supply via a fuel supply line. The water circuit includes a first water line extending between a first feed water supply line and a return water line. The gas turbine system further includes an extraction-air line that extends between an inlet port on the compressor section and an outlet port on the turbine section. A first heat exchanger thermally couples the first water line to the extraction-air line for transferring heat from a flow of extraction-air within the extraction-air line to a flow of water within the water circuit. A second heat exchanger thermally couples the first water line to the fuel supply line for transferring heat from the flow of water within the water circuit to a flow of fuel within the fuel supply line.

Combined cycle power plant having serial heat exchangers

A system includes a gas turbine. The gas turbine includes a first compressor configured to provide a first portion of a discharge air to a combustor. The gas turbine also includes the combustor configured to combust a mixture of the first portion of the discharge air and fuel to generate an exhaust gas and to provide the exhaust gas to a turbine. The gas turbine also includes an exhaust outlet coupled to the turbine and configured to enable the exhaust gas to exit the gas turbine. The system also includes a nitrogen purification system coupled to the gas turbine. The nitrogen purification system includes a membrane nitrogen generator configured to receive a second portion of the discharge air from the compressor or a portion of the exhaust gas from the exhaust outlet, wherein the membrane nitrogen generator is configured to generate nitrogen from the second portion of the discharge air or the portion of the exhaust gas.

System and method for generating nitrogen from a gas turbine

A system includes a custody transfer system configured to transfer a gas fuel from a gas supply to a plurality of gas turbines. The custody transfer system includes a first plurality of flow meters arranged in parallel with each other, wherein each of the first plurality of flow meters is configured to obtain a first measurement of a portion of a flow rate of the gas fuel flowing through the custody transfer system, and a second plurality of flow meters in series with the first plurality of flow meters, wherein each of the second plurality of flow meters is configured to obtain a second measurement of the flow rate of the gas fuel flowing through the custody transfer system, and wherein each of the first and second plurality of flow meters is configured to be blocked or unblocked from receiving the gas fuel based on a number of the plurality of gas turbines in operation.

Custody transfer system and method for gas fuel

An embodiment of the present invention takes the form of a system that uses exhaust from the combustion turbine engine to heat the fuel gas consumed by a combustion turbine engine. The benefits of the present invention include reducing the need to use a parasitic load to heat the fuel gas.

System for heating a fuel

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

The present application provides a gas turbine engine system for combusting a flow of fuel. The gas turbine engine system may include a combustor and a fuel system for providing the flow of fuel to the combustor. The fuel system may include a fuel heat exchanger so as to provide the flow of fuel to the combustor at a substantially constant temperature.

Systems and methods for modified wobbe index control with constant fuel temperature

A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors.

Pressure control method and system to reduce gas turbine fuel supply pressure requirements

Pressure control method to reduce gas turbine fuel supply pressure requirements

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Simpsonville, SC, United States of America

Brian Michael Gallagher