Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Krishna C Miduturi

Walter Ray Laster

Stephen A Ramier

Clifford E Johnson

Werner Krebs

Weidong Cai

David M Ritland

Michael Huth

Danny W Kozachuk

Mark Seifarth

Thomas Primke

Ben Karanja

Yohannes Ghermay

A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air from a shell surrounding the primary and secondary combustion zone. The feeding of the fuel through the air scoop allows atomization of the fuel. The mixture can then enter the secondary combustion zone and mix with the products from the first combustion zone.

Fuel oil axial stage combustion for improved turbine combustor performance

A method, including: operating an industrial gas turbine engine having a plurality of combustor cans arranged in an annular array, each can having burner stages and a pilot burner arrangement having a premix pilot burner and a diffusion pilot burner; operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.

Method of selective combustor control for reduced emissions

A combustor arrangement () including: a pilot burner () having a pilot cone (); a plurality of clockwise () main swirlers interposed among a plurality of counterclockwise () main swirlers and disposed concentrically about the pilot burner; and a base plate () transverse to the main swirlers. Inbound-zones () exist where adjacent portions () of adjacent flows () through main swirlers flow toward the pilot cone, and interposed between the inbound zones outbound zones () exist where adjacent portions of adjacent flows flow away from the pilot cone. The arrangement is configured to preferentially deliver more cooling fluid to the inbound zones than the outbound zones.

Asymmetric baseplate cooling with alternating swirl main burners

A control system and method for a gas turbine engine are provided A controller () is responsive to at least one parameter to control an air-to-fuel ratio. The parameter may be a measured engine exhaust temperature from a temperature sensor (). During a transient, such as a ramping condition of the engine, a measured value of such parameter may have a time lag affecting one or more control settings during the transient condition. The controller is programmed to predictively determine a bias for the measured value of the parameter to correct such control settings and avoid combustion instabilities and high emissions during such transient conditions.

Control system and method for controlling a gas turbine engine during transients

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Oviedo, FL, United States of America

Krishna C Miduturi