Siemens Aktiengesellschaft

Abhijeet Tiwary

Timothy A Fox

Charalambos Polyzopoulos

Stephen A Ramier

Steven Williams

Miguel Bascones

Erick J Deane

James Bertoncello

Daniel W Garan

Stephen A Raimer

A fuel manifold () configured to form a base support structure () to support a plurality of fuel nozzles () including a pilot fuel nozzle is provided. A restraining element () is arranged in the base support structure () to support the pilot fuel nozzle. Restraining element () is integrally formed with the base support structure. The restraining element being integrally formed with the base support structure is effective to arrange for an incremental thickness () in a portion () of a wall () interposed between the inner diameter () of restraining element () and respective proximate edges () of a number of pilot bolt holes () disposed around the restraining element.

Fuel manifold with integrally formed retainer for a pilot nozzle in a combustor of a gas turbine engine

A casting method and cast manifold are provided. The method allows configuring conduits, such as conduits in a fuel feed boss and/or a base rocket, which are part of the manifold for removing a ceramic core from the cast without forming extraneous holes in the body of the manifold. Absence of such extraneous holes in turn allows eliminating sealing plugs and welds, which otherwise would be needed for sealing the extraneous holes.

Casting method and manifold cast with conduits effective for removing a core from the cast without forming extraneous holes in the body of the manifold

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 ().

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Orlando, FL, United States of America

Abhijeet Tiwary