Siemens Aktiengesellschaft

Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Siemens Westinghouse Power Corporation

Siemens Canada Limited

Stephen A Ramier

Daniel W Garan

Timothy A Fox

Charalambos Polyzopoulos

Richard L Thackway

Vinayak V Barve

Andreas Böttcher

Tobias Krieger

Thomas Grieb

Khalil Farid Abou-Jaoude

David James Wiebe

Robert James Bland

Robert H Bartley

Kevin J Spence

Steven Williams

Abhijeet Tiwary

Joseph Scott Markovitz

James Bertoncello

Yadollah Naghian

David P Holzapfel

Mark L Adamson

Walter Ray Laster

William Richard Ryan

Bernd Prade

John L Battaglioli

Samer P Wasif

Jens Kleinfeld

David M Ritland

John Carl Glessner

Anil Gulati

Birgit Grüger

Erick J Deane

Holger Streb

Thomas Hauser

Krishna C Miduturi

Karsten Jordan

Blake R Cotten

Christin Schlensog

Udo Schmitz

J Scott Markovitz

David Kargetta

Stefan Dahlk

Urmi B Dave

Marcus Zurhorst

Vaidyanathan Krishnan

Jürgen Buchheim

Michael C Escandon

Lawrence P Budnick

Andreas BÖTTCHER

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

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

W501D5/D5A DF42 combustion system

A cross-flame duct for connecting adjacent combustors together in a gas turbine to guard against flameout conditions within the combustors, whereby the cross-flame duct includes first and second ducts forming a slip joint to prevent stress from developing within the cross-flame duct is disclosed. The cross-flame duct remains flexible during turbine operation due to the slip joint, thereby preventing damaging thermal and mechanical stresses from developing within the cross-flame duct and enhancing the useful life of the cross-flame duct and associated components. The first and second ducts include cooling chambers positioned between outer sleeves and inner housings and maintained with one or more standoffs to reduce thermal stress and gradients or prevent material loss due to overheating or burning. The cooling chambers are supplied with cooling fluids via one or more fluid ports extending through the outer sleeves enabling air to flow through the cooling chambers and into the combustors.

Cross ignition flame duct

A multi-functional fuel nozzle () for a combustion turbine engine is provided. An annular fuel-injecting lance () may include a first fluid circuit () and a second fluid circuit (). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer () is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice () responsive to the first fluid circuit to form a first atomized ejection cone (), and a second ejection orifice () responsive to the second fluid circuit to form a second atomized ejection cone (). The first and second ejection cones () formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.

Multi-functional fuel nozzle with a dual-orifice atomizer

A multi-functional fuel nozzle () for a combustion turbine engine is provided. A nozzle cap () may be disposed at a downstream end of the nozzle. A heat shield () is mounted onto the nozzle cap. A plurality of cooling channels () is arranged between a forward face of the nozzle cap and a corresponding back side of the heat shield. The plurality of cooling channels may be arranged to discharge cooling air over a forward face of an atomizer assembly in the multi-functional fuel nozzle.

Multi-functional fuel nozzle with a heat shield

A nozzle cap () is disposed at a downstream end of the nozzle. The nozzle cap includes a bore arranged to accommodate a downstream portion of a fluid-injecting lance that extends along a longitudinal axis () of the nozzle. The downstream portion of the fluid-injecting lance includes a centrally-located atomizer () to form a first atomized ejection cone. An array of atomizers () is disposed in the nozzle cap. The array of atomizers is circumferentially disposed about the longitudinal axis of the lance. The array of atomizers may be positioned radially outwardly relative to the centrally-located atomizer to form an array of respective second atomized ejection cones.

Multi-functional fuel nozzle with an atomizer array

An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.

Gas turbine assembly and method therefor

A combustor () for a gas turbine engine () has a circumferentially extending liner () defining at least a portion of an interior combustion chamber () and a hot gas path (). The liner includes a resonator section () including at least one resonator (A,B) having a resonator chamber (A,B) formed on an exterior of the liner. A thermal barrier coating () is disposed along an inner surface of the liner including an inner surface () of the resonator section. The resonator further includes a plurality of apertures () and each aperture extends through the liner and the thermal barrier coating at the resonator section and there is fluid flow communication between the combustion chamber and the resonator chamber.

Combustor resonator section with an internal thermal barrier coating and method of fabricating the same

A fuel nozzle assembly () is presented for a gas turbine engine (). The fuel nozzle assembly () includes a rocket unit () and a swirler () with an aft end () in threaded engagement with a forward end () of the rocket unit (). The fuel nozzle assembly () may include an oil tip () including a clocking feature with a mechanical constraint to orient the oil tip () at a predetermined angular orientation () relative to the swirler (). The fuel nozzle assembly () may include one or more gas stage inlets (), one or more oil stage inlets (), and a flexible hose () to direct the oil to a plurality of rocket units ().

Fuel nozzle assembly with removable components

A combustor apparatus defining a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus comprises an outer wall including a fuel inlet opening for receiving a fuel feed pipe. A coupling assembly is engaged with the fuel feed pipe at the fuel inlet opening to attach the fuel feed pipe to the outer wall. A fuel injection system is located in the interior volume of the outer wall and comprises fuel supply structure including a fuel feed block having a fuel intake passage aligned with the outlet portion of the fuel feed pipe. A coupling fastener is engaged against an exterior outer face of the fuel feed block to create a sealed coupling for containing fuel passing from the fuel feed pipe into the fuel feed block, and to secure the fuel feed block relative to the coupling assembly.

Combustor apparatus in a gas turbine engine

A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall.

A casting () for a support housing (), including: a fuel manifold () comprising an a-stage gas gallery () and a b-stage gas gallery (); a-stage and a b-stage rocket bases () integrally cast with the fuel manifold (), the a-stage gas gallery () in fluid communication with the a-stage stage rocket bases and the b-stage gas gallery () in fluid communication with the b-stage rocket bases; and one oil tube passageway () for each fuel rocket base (), each oil tube passageway () spanning from an upstream end () of the fuel manifold () to an interior () of a respective fuel rocket base (). Each oil tube passageway () is disposed radially inward of an inner perimeter () of the b-stage gas gallery ().

Cast manifold for dry low NOx gas turbine engine

A burner assembly is provided. The burner assembly includes a support housing with a supply manifold, the supply manifold includes a fuel passage system, and fuel nozzles extending from the supply manifold and being supplied with fuel through the fuel passage system of the supply manifold. The supply manifold is sandwiched using at least two subparts.

Burner assembly

A burner arrangement is provided. The burner arrangement includes a support and at least two fuel nozzles attached to the support in the direction of flow, with each fuel nozzle including a support-side section which includes a contact surface on the support side with which it rests on a supporting surface of the support, with at least two fuel nozzle tips embodied in one piece extending out from the support-side section in the direction of flow and the support-side contact surface including at least two extension parts projecting in the direction of the support, with the extension parts each embodying a channel through which fuel is fed in each case to the fuel nozzle tips through passages which are arranged in the support-side contact surface of the support-side section.

Burner arrangement

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

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Fredericton, Canada

Stephen A Ramier