Siemens Energy, Inc.

Damien G Teehan

Gary V Hildebrandt

Adam Matthew Foust

Yan Yin

Jatinder P Singh

Satish B Gadde

Chirag B Patel

Danny W Kozachuk

Jack Douglas Moore

Shervin Rodd

Matthew J LaGrow

Chandrashekar Brahmasandra

Janarthanan Venkataraghavan

Christopher J Davila-Aponte

Joseph L Kollar

John T Fetherolf, Jr

Ashok Reddy Gitta

A method of modulating a cooling supply in a gas turbine engine includes providing the engine comprising a compressor section and a turbine section and including a cooling flow circuit, the cooling flow circuit supplying a cooling air flow from a compressor cavity in the compressor section to a blade ring cavity in the turbine section, wherein the cooling flow circuit includes a main line with a full capacity valve, measuring a first pressure in the blade ring cavity, measuring a second pressure in the compressor cavity, adjusting, by a control system, the opening of the full capacity valve to control the cooling air flow through the main line in order to maintain a target pressure ratio, wherein the pressure ratio defined as a ratio of the first pressure to the second pressure. The method is performed in an ambient temperature operating range of the engine.

Method for modulating a turbine cooling supply for gas turbine applications

A starting process for a gas turbine () that holds the turbine speed of rotation at an ignition speed setting during an ignition window (), with the ignition speed setting being based on ambient air conditions to achieve a specified combustor air mass flow rate (). A fuel flow rate may be set based on the fuel type and temperature to achieve a particular air/fuel ratio in a combustor. The fuel flow rate may be adjusted during the ignition window and thereafter based on a combustor inlet air temperature (). Completion of ignition may be determined by a reduction () in a blade path temperature spread (). After ignition, fuel flow is increased to accelerate the turbine to full speed. At any point, the fuel flow may be reduced, or its increase may be slowed, to avoid exceeding a temperature limit in the turbine.

Gas turbine starting process

A gas turbine engine that includes a compressor, a combustion stage, a turbine assembly, a fuel gas feed system for supplying fuel gas to a combustion stage of the gas turbine, and an integrated fuel gas characterization system. The integrated fuel gas feed system can include a buffer tank. The integrated fuel gas characterization system for determining the amount of energy provided by the fuel prior to combustion of the fuel in the combustion stage. The integrated fuel gas characterization system minimizes megawatt swings by adjusting the operating parameters of the gas turbine engine based on the rate of change in fuel gas energy content. The integrated fuel gas characterization system also provides improved turbine engine start-up reliability by tuning the turbine engine operating parameters using fuel gas energy content measurements obtained prior to actual start-up.

Integrated fuel gas characterization system

A power generation system. The exemplary system shown in FIGS.andincludes a gas turbine (), a gasifier () for generating gaseous fuel and a gas combustor () configured to receive the fuel and power the gas turbine (). A drain collection and separation system () is positioned to collect gaseous fuel entrained in liquid and to separate the gaseous fuel from the liquid so the gaseous fuel can be cycled or disposed of separately from the liquid.

System and method for separation and control of entrained gas mixture

A method of controlling fuel flow to a combustor () of a gas turbine engine () during startup of the engine includes determining a relationship between Cand valve position for a flow control valve (e.g.,) in a fuel supply () to the combustor as a function of at least one real time parameter of fuel () in the fuel supply. The method also includes determining a value of the at least one parameter of the fuel before initiating a flow of the fuel to the combustor, and then calculating a first actual Cvalue for the flow control valve at a target flow rate using the determined value of the parameter. The method then includes positioning the flow control valve to a first position corresponding to the actual Cvalue based upon the determined relationship between Cand valve position, and initiating the flow of fuel to the combustor through the flow control valve.

Fuel control for starting a gas turbine engine

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St. Cloud, FL, United States of America

Damien G Teehan