Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

James Bertoncello

Timothy A Fox

Stephen A Ramier

Mahmut Faruk Aksit

Anthony L Schiavo

Steven Williams

Abhijeet Tiwary

Robert H Bartley

Daniel W Garan

Adam J Weaver

Wojciech Dyszkiewicz

Benjamin G Hettinger

Ali Ihsan Yurddas

Erdem Gorgun

Sadik Hazer

Ertugrul Tolga Duran

Kunyuan Zhou

Markus Raben

Stephen A Raimer

A seal for sealing a gap in a combustion apparatus of a gas turbine between a first side and an opposite second side. The seal includes a steel strap with a flat shape and a first metal web with a flat shape attached to the steel strap on the first side and a second metal web attached to the steel strap on the second side. Thereby the seal has a seal thickness with at least the steel strap plus the first metal web plus the thickness of the second metal web, wherein the seal thickness is at most 0.2-times of width of the seal. The new seal has an Omega shape of the second metal web, which is therefore attached on both sides with a flat shaped portion to the steel strap.

Seal for combustion apparatus

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

Growing community of inventors

Charlotte, NC, United States of America

James Bertoncello