Siemens Energy, Inc.

Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Siemens Power Generation, Inc.

Weidong Cai

David Marchant Parker

Clifford E Johnson

Arthur J Harris, Jr

Ching-Pang Lee

Kok-Mun Tham

Timothy A Fox

Walter Ray Laster

Vincent Paul Laurello

Werner Krebs

Abdullatif M Chehab

Michael Huth

Daniel W Garan

Scott M Martin

Yan Yin

Krishna C Miduturi

David A Kemp

Kyle L Landry

Yohannes Ghermay

Thomas Primke

John A Fussner

Bijay K Sultanian

Mark Seifarth

Ben Karanja

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 cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.

External cooling fluid injection system in a gas turbine engine

A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is reduced, wherein the secondary fuel/air injection system provides fuel to a secondary combustion zone downstream from a main combustion zone. A total amount of air provided to the combustor apparatus is reduced, wherein portions of the air are provided to each of the injection systems. Upon reaching operating parameters corresponding to the second operating mode, the amount of fuel provided to the primary fuel injection system is increased, the amount of fuel provided to the secondary fuel/air injection system is reduced, and the total amount of air provided to the combustor apparatus is increased.

Operation of a combustor apparatus in a gas turbine engine

A fuel injector () for alternate fuels (A,B) with different energy densities. Vanes (B) extend radially from a fuel delivery tube structure (B) with first and second fuel supply channels (A,B). Each vane has first and second radial passages (A,B) communicating with the respective fuel supply channels, and first and second sets of apertures (A,B). The first fuel supply channel, first radial passage, and first apertures form a first fuel delivery pathway providing a first fuel flow rate at a given fuel delivery pathway backpressure that is essentially common to both sets of fuel delivery pathway apertures. The second fuel supply channel, second radial passage, and second apertures form a second fuel delivery pathway providing a second fuel flow rate that may be at least 1 about twice the first fuel flow rate at the given fuel delivery pathway backpressure.

Flex-fuel injector for gas turbines

A combustor () for a gas turbine engine is provided comprising a primary combustion chamber () for combusting a first fuel to form a combustion flow stream () and a transition piece () located downstream from the primary combustion chamber (). The transition piece () comprises a plurality of injectors () located around a circumference of the transition piece () for injecting a second fuel into the combustion flow stream (). The injectors () are effective to create a radial temperature profile () at an exit () of the transition piece () having a reduced coefficient of variation relative to a radial temperature profile () at an inlet () of the transition piece (). Methods for controlling the temperature profile of a secondary injection are also provided.

Apparatus and method for controlling the secondary injection of fuel

A thermal shield for reducing thermal stress induced proximate to a first joint formed between adjacent engine casing components in a gas turbine engine. The thermal shield includes a cover structure for covering a radially inner portion of at least one of the engine casing components. The cover structure is disposed proximate to the first joint and attached to the respective engine casing component so as to limit exposure of a covered inner portion of the engine casing component to hot gases in an interior volume defined by the engine casing components. A thermally insulating layer is disposed between the cover structure and the engine casing component for effecting a reduced amount of heat transfer to the covered inner portion of the engine casing component from the hot gases in the interior volume defined by the engine casing components.

Thermal shield at casing joint

A gas turbine combustion system is provided comprising a combustion chamber () having a central axis (), a primary combustion stage () located at a front end () of the combustion chamber () for injecting fuel, air, or mixtures thereof substantially along the central axis (), a plurality of secondary combustion stages (A-D) spaced apart in flow series along a length of the combustion chamber (), wherein each of the plurality of secondary combustion stages (A-D) comprises a plurality of circumferentially-spaced secondary injectors () for injecting fuel, air, or mixtures thereof, toward the central axis (), and wherein an internal diameter of the combustion chamber () decreases from at least a first one of the plurality of secondary combustion stages (AD) to at least a second one of the plurality of secondary combustion stages (A-D).

Multi-stage axial combustion system

A secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a manifold formed integral to, and surrounding a portion of, the transition piece, a manifold inlet port, and a collection of injection nozzles. A flowsleeve augments fuel/diluent flow velocity and improves the system cooling effectiveness. Passive cooling elements, including effusion cooling holes located within the transition boundary and thermal-stress-dissipating gaps that resist thermal stress accumulation, provide supplemental heat dissipation in key areas. The system delivers a secondary fuel/diluent mixture to a secondary combustion zone located along the length of the transition piece, while reducing the impact of elevated vibration levels found within the transition piece and avoiding the heat dissipation difficulties often associated with traditional vibration reduction methods.

Secondary fuel delivery system

An extended flashback annulus () is formed between an exterior surface () of a shroud or casing () associated with a main swirler assembly inner body () or other fuel/air mixing device and the inner surface () of an annulus casting () which are in operational relationship with one another in a gas turbine combustor assembly. The extended flashback annulus () is capable of forming an extended protective cylindrical air barrier () that extends farther into the combustion zone, this barrier being more robust and providing for the reduction or prevention of flashback to the baseplate and other heat-susceptible upstream components.

Extended flashback annulus in a gas turbine combustor

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Oviedo, FL, United States of America

Weidong Cai