General Electric Company

John Victor Hains

Brian Michael Gallagher

Gary Cletus Mobley

Abhijit Gupta

Dean Matthew Erickson

George Martin Gilchrist

Korey Frederic Rendo

Timothy Russell Bilton

Steven David Stovall

John Francis Wodecki

Sakshi Kapoor

George Martin Gilchrist Iii

Systems for cooling turbine components via fluid filled conduits are disclosed. Various embodiments include a system having: a set of fan systems for cooling a set of conduits, the set of conduits fluidly connected with a turbine component; a temperature sensor operably connected to the turbine component, the temperature sensor for obtaining a temperature indicator of the turbine component; and a control system operably connected to the set of fan systems and the temperature sensor, the control system for modifying a speed of at least one fan system in the set of fan systems across a range of speeds in response to determining the temperature indicator deviates from a predetermined range of temperature values.

Turbine component cooling system

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

A fuel forwarding skid for delivering fuel from a storage area to a plurality of turbines includes at least two pumps for delivering fuel to a skid outlet line. A flow control device is connected to the pumps to control an output of the pumps. A recirculation line is in communication with the skid outlet line and is adapted to return a portion of the fuel in the skid outlet line to the storage area. A flow meter is in communication with the recirculation line to measure a rate of flow in the recirculation line, and the flow control device controls the output of at least one of the pumps in accordance with the rate of flow in the recirculation line.

Multiple gas turbine forwarding system

A method and system for desalting a fuel having a salt therein is disclosed. A jet of superheated steam is provided at a selected pressure and fuel is drawn into the jet of superheated steam to form a mixture of the fuel and the superheated steam. The mixture is injected into a centrifuge to desalt the fuel.

System for desalting fuel oil using a steam jet pump

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.

Growing community of inventors

Simpsonville, SC, United States of America

John Victor Hains