Siemens Aktiengesellschaft

Siemens Energy, Inc.

Siemens Aktiengesell Schaft

Steven Williams

Timothy A Fox

Stephen A Ramier

Abhijeet Tiwary

James Bertoncello

Reinhard Schilp

Daniel W Garan

Ulrich Wörz

Jaap Van Kampen

William F Van Nieuwenhuizen

A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip. A plurality of fuel tubes extend along the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor An outer sleeve surrounds the fuel tubes and defines an annular space in fluid communication with the air passages of the nozzle tip between the outer sleeve and the central body.

Nozzle with multi-tube fuel passageway for gas turbine engines

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 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 port () for axially staging fuel and air into a combustion gas flow pathof a turbine combustor (A). A port enclosure () forms an air path through a combustor wall (). Fuel injectors () in the enclosure provide convergent fuel streams () that oppose each other, thus converting velocity pressure to static pressure. This forms a flow stagnation zone () that acts as a valve on airflow () through the port, in which the air outflow () is inversely proportion to the fuel flow (). The fuel flow rate is controlled () in proportion to engine load. At high loads, more fuel and less air flow through the port, making more air available to the premixing assemblies ().

Self-regulating fuel staging port for turbine combustor

Disclosed is a gas turbine fuel injector and swirler assembly, including: a delivery tube structure arranged on a central axis of the fuel injector and swirler assembly, a first fuel supply channel arranged in the delivery tube structure, a shroud surrounding the delivery tube structure, swirl vanes arranged between the delivery tube structure and the shroud, a radial passage in each swirl vane, communicating with the first fuel supply channel, a set of apertures open between the radial passage and the exterior surface of said each swirl vane, wherein a second fuel supply channel is arranged in the delivery tube structure extending to a downstream end of the delivery tube structure and a mixer with lobes for fuel injection is arranged at the downstream end. Further disclosed is an assembly method for assembling a fuel injector and swirler assembly.

Growing community of inventors

Charlotte, NC, United States of America

Steven Williams