Siemens Energy, Inc.

Siemens Westinghouse Power Corporation

Siemens Power Generation, Inc.

Westinghouse Electric Corporation

Siemens Aktiengesellschaft

William Richard Ryan

Robert James Bland

David Marchant Parker

Sanem Berksoy

David James Wiebe

Yevgeniy P Shteyman

Andreas Böttcher

Timothy A Fox

Bernd Prade

Stephen A Ramier

Richard L Thackway

Nancy H Ulerich

Berthold Köstlin

Muzaffer Sutcu

Satish B Gadde

Daniel Vogtmann

Mitchell O Stokes

Michael H Koenig

Richard D Holm

Phillip W Gravett

Robert Watson Spitzer

David D North

John N Strain

Douglas Dean Darling

Thomas J Gordon

Lawrence Lee Ross

Brian D Ottinger

Boris Ferdinand Kock

Nicholas D'Amico

Ernest W Smith

David Dealba North

Ulrich WÖRZ

Lars Terjung

A gas turbine combustor for producing hot gas by burning a fuel in compressed air comprising a combustor central axis and multiple main swirlers with respective swirler axes disposed about and parallel to the combustor central axis, each main swirler delivering an air fuel mixture flowing through it and about its swirler axis, wherein each swirler imparts rotation to the air fuel mixture flowing through it in a direction opposite that of adjacent swirlers. This combustor configuration reduces shear where the outer edges of adjacent flows meet, allowing for greater tuning of the combustion chamber and reduced NOx and CO emissions.

Alternately swirling mains in lean premixed gas turbine combustors

A hot gas path system for a gas turbine including a stepped inlet ring at an intersection between a downstream end of a combustor basket and an upstream end of a transition is disclosed. The heat shield may be positioned downstream from a combustor basket and proximate to an intersection between the collar and the axially extending cylindrical wall. The stepped inlet ring may be coupled to the transition section and may extend upstream from the transition section. An upstream end of the stepped inlet ring may be positioned radially outward from the combustor basket such that at least a portion of the stepped inlet ring overlaps a portion of the combustor basket. A spring clip may be positioned between the combustor basket and the stepped inlet ring such that the spring clip seals at least a portion of a gap between the combustor basket and the stepped inlet ring.

Stepped inlet ring for a transition downstream from combustor basket in a combustion turbine engine

A method and system for controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine. A liquid fuel is conveyed from a single stage fuel supply through a plurality of primary fuel supply lines to a first nozzle stage including a plurality of primary nozzles. A predetermined operating condition of the gas turbine is identified and a signal is produced in response to the identified operating condition. The signal effects actuation of valves located on secondary fuel supply lines extending from each of the primary fuel supply lines to supply fuel to respective secondary nozzles.

Method and system for controlling fuel to a dual stage nozzle

A combustor-to-transition seal () includes a spring clip assembly () and a first spring metal ring () or a ring assembly () that includes the first spring metal ring () and a second spring metal ring (). Such combustor-to-transition seal () provides a first seal () and a second seal () when at a junction of a combustor () and a transition (). In an embodiment, the first spring metal ring () has a plurality of apertures () through the ring () that provide effusion cooling of the ring (). The plurality of apertures () regulates a flow of cooling fluid to maintain an acceptable temperature of the ring (). In an alternative embodiment, the second spring metal ring () has grooves () that regulate a flow of cooling fluid to maintain an acceptable temperature of the ring assembly ().

Low leakage spring clip/ring combinations for gas turbine engine

A fuel injector assembly for use in a turbine engine having a combustion section and a turbine section downstream from the combustion section. The fuel injector assembly includes a flow sleeve defining a pre-mixing passage of the combustion section and including a sleeve wall having a forward end proximate to a cover plate of the combustion section and an opposed aft end. An annular cavity in fluid communication with a source of fuel is formed in the sleeve wall adjacent the aft end. A fuel dispensing structure is associated with the cavity and includes at least one fuel distribution aperture for distributing fuel from the cavity to the pre-mixing passage.

Integral flow sleeve and fuel injector assembly

A combustor assembly in a gas turbine engine is provided. The combustor assembly may comprise a combustor device coupled to a main casing, a transition duct and a flow conditioner. The combustor device may comprise a liner having inlet and outlet portions and a burner assembly positioned adjacent to the liner inlet. The transition duct may comprise a conduit having inlet and outlet sections. The inlet section may be associated with the liner outlet portion. The flow conditioner may be associated with the main casing and the transition duct conduit for supporting the conduit inlet section.

Combustor assembly comprising a combustor device, a transition duct and a flow conditioner

A gas turbine engine fuel heat shield configured to shield fuel from high temperatures of surrounding turbine components to prevent coking of the fuel is disclosed. The gas turbine engine fuel heat shield may be formed from a generally elongated member having a first collar at a first end and a second collar at a second end opposite to the first end. One or more recesses may be positioned in an outer surface of the generally elongated member between the first and second collars. A sleeve is positioned around the generally elongated member and radially outward of the recess to form one or more sealed chambers. The sleeve may be sealed to prevent fuel from entering the recess and coking. Such design, therefore, prevents the formation of carbon particles from the fuel that could clog the fuel injectors.

Self-contained oil feed heat shield for a gas turbine engine

An igniter assembly () of a gas turbine () is presented, including an igniter () disposed within an igniter housing (). The igniter is extendable from the igniter housing through an opening () in a combustion liner () to an extended position, and is retractable from the extended position back through the opening to a retracted position (). The igniter assembly further includes a compressible assembly () disposed between a base () of the igniter housing and the combustion liner to form a sealed interface () with a perimeter () of the opening (). The compressible assembly is configured to restrict an air flow from passing between the igniter housing base and the perimeter of the opening. The compressible assembly is variable in length to accommodate a respective variation in a separation between the igniter housing base () and the opening ().

Igniter assembly for a gas turbine

A support for the first row turbine vanes () in a gas turbine engine, the support including a support framework (). The support framework () includes an outer vane carrier (), and an inner vane carrier () connected to the outer vane carrier () by a plurality of struts (). The outer vane carrier () is mounted to an inner casing () of the engine and the struts () support the inner vane carrier () in cantilevered relation to the outer vane carrier (). An aft outer flange () of each first row vane () is supported on the outer vane carrier () and a forward inner flange () of the vane () is support on the inner vane carrier ().

Cantilevered framework support for turbine vane

A fuel modulation system usable in can-annular combustor systems of turbine engines for more efficiently managing fuel flow to reduce the amount of NOwhile maintaining appropriate combustor flame temperatures. The fuel modulation system controls individual inline modulation valves in cooperation with a overall stage control valve to bring a turbine engine through the startup phase and to maintain operating conditions at a load set point while reducing NOvariability between baskets by using individual combustor dynamic pressure measurements. The fuel modulation system may be managed such that individual inline modulation valves remain within a predetermined range of positions relative to a nominal position to reduce NOvariability.

System for modulating fuel supply to individual fuel nozzles in a can-annular gas turbine

A method and system for controlling combustion in a gas turbine combustor () includes adjusting an amount of a premix fuel portion () of a pilot fuel () provided to a premix burner stage () of a pilot () of the gas turbine combustor. The amount of the premix fuel portion is adjusted from a preset premix fuel portion amount to an adjusted premix fuel portion amount to achieve a desired first operating condition of the combustor. An amount of a diffusion fuel portion () of the pilot fuel provided to a diffusion burner stage () of the pilot is then adjusted from a preset diffusion fuel portion amount to an adjusted diffusion fuel portion amount to achieve a desired second operating condition of the combustor.

Pilot fuel flow tuning for gas turbine combustors

Aspects of the invention relate to a system for attaching a ceramic liner to a non-ceramic combustor head-end component while accommodating different rates of thermal expansion of these components. One end of the liner can be received within a slot formed by the combustor head-end component. The liner can be held in place by a plurality of pins with each pin passing through a pair of aligned openings in the liner and the head-end component. The end of the liner can be spaced from each of the walls of the slot so as to form a series of gaps in fluid communication. The gaps and the pins can accommodate differential thermal expansion between the liner and combustor head-end component. If desired, at least some of the gaps can be tightly controlled so as to regulate air leakage around the end of the liner.

Attachment system for ceramic combustor liner

Aspects of the invention related to a system for providing advance notice of impending contact between a stationary component and a rotating component in a turbine engine. For example, the system can be used to warn of potential contact between a seal holder and a rotor disk in the compressor section of the engine. In one embodiment, a pad or other component can be provided on the stationary seal holder. If the seal holder and the rotor disk approach each other during operation, the pad can contact the rotor disk prior to actual contact between the seal holder and the rotor disk. An optical and/or an acoustic signal can be generated by such contact. The signals can be detected remotely from the point of contact by a signal detection device, thereby avoiding the need to pass wires through the compressor section.

Warning system for turbine component contact

An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal is composed of inner and outer housings and a center sealing member disposed between the inner and outer housings. The center sealing member is flexible and prevents a fluid, such as air, from leaking through the seal. In operation, the center sealing member flexes and is sealed against the outer housing by a pressure differential that is created by the relatively higher pressure on the inner housing side and the relatively lower pressure on the outer housing side.

Turbine spring clip seal

Aspects of the invention relate to resonator assemblies for use in non-uniform flow environments. The resonator assemblies include one or more features, such as a box or a scoop, for substantially equalizing the pressure on the resonator. In the box configuration, a box is attached on top of the resonator. The box has a top plate with a plurality of openings and at least one side wall extending from the entire periphery of the top plate. A plenum is defined between the box and the resonator plate. In the scoop configuration, a scoop is attached to the top of the resonator such that the scoop substantially overhangs the resonator. The scoop includes at least one side wall extending substantially perpendicularly therefrom, except for one side without a side wall so as to provide an opening into a space defined between the scoop and the resonator.

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Oviedo, FL, United States of America

William Richard Ryan