General Electric Company

Steven William Tillery

David August Snider

Mark W Flanagan

William Forrester Seely

Jason Nathaniel Cook

John Edward Sholes, Jr

Mark Robert Osmundsen

The fuel flow rate to a gas turbine is measured using an inert gas. The inert gas is injected into the fuel flow and the concentration of the inert gas in the fuel/inert gas mixture is later measured. The concentration of the inert gas in the fuel/inert gas mixture is then used to calculate the mass flow rate of the fuel.

Gas turbine fuel flow measurement using inert gas

A compressor start bleed system for a turbine system includes a compressor section. Also included is a turbine section disposed downstream of the compressor section. Further included is at least one duct fluidly coupled to the compressor section, wherein the at least one duct is configured to route a start bleed extraction from the compressor section to a location downstream of the turbine section. Yet further included is at least one control device of the at least one duct configured to actively modulate the start bleed extraction during a part speed operation of the turbine system.

Compressor start bleed system for a turbine system and method of controlling a compressor start bleed system

A system and method in a combined cycle power plant includes a processor modeling plant level performance by considering the interrelation between outputs of the gas turbine and the steam turbine. The model can be computational, predictive, or both. The model may be used to control subsystems of the plant (including the gas turbine and the steam turbine) to achieve a target plant performance. The model may also be used to diagnose or maintain subsystems of the combined cycle power plant.

System and method for controlling and diagnosing a combined cycle power plant

A system to mitigate thermal lag of start-up operations of a gas turbine is provided and includes a housing which is disposed upstream from and which is fluidly coupled to a compressor of the gas turbine, a first system coupled to an aft portion of the compressor and to the housing which, when activated, receives a first air supply from the compressor and delivers the first air supply to the housing, and a second system, coupled to the first system, which removes a second air supply from an intermediate portion of the compressor and delivers the second air supply to the first system prior to the activation of the first system.

Inlet bleed heat system thermal lag mitigation using compressor interstage bleeds

The present application provides a compressor clearance control system for a gas turbine engine. The gas turbine engine includes a turbine producing exhaust gases and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and an extraction port for exhaust gases from the turbine. The extraction port is in communication with the casing heat exchanger so as to heat the casing of the compressor with the exhaust gases from the turbine.

Compressor clearance control system using turbine exhaust

The present application provides a compressor clearance control system for a gas turbine engine having an oil recirculation system with a flow of oil therein and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and a conduit in communication with the casing heat exchanger and the oil recirculation system so as to heat the casing of the compressor with the flow of oil from the oil recirculation system.

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Simpsonville, SC, United States of America

Steven William Tillery