Siemens Aktiengesellschaft

Siemens Energy, Inc.

Siemens Canada Limited

Daniel W Garan

Stephen A Ramier

David James Wiebe

Timothy A Fox

Charalambos Polyzopoulos

Richard L Thackway

Robert H Bartley

Kevin J Spence

Joseph Scott Markovitz

David P Holzapfel

Mark L Adamson

Yadollah Naghian

Andreas Böttcher

David Marchant Parker

Tobias Krieger

David M Ritland

Jens Kleinfeld

Weidong Cai

Thomas Grieb

Vinayak V Barve

Arthur J Harris, Jr

Steven Williams

Erick J Deane

Abhijeet Tiwary

Khalil Farid Abou-Jaoude

James Bertoncello

Blake R Cotten

Marcus Zurhorst

Adam J Weaver

Lashanda N Oliver

Urmi B Dave

Ashtad Kotwal

Vaidyanathan Krishnan

Michael C Escandon

Lawrence P Budnick

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

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 combustion system for a gas turbine engine including a combustor assembly comprising a combustor basket having a downstream terminal end, and a transition duct extending downstream from the combustor basket and having an upstream end located adjacent to the downstream terminal end of the combustor basket. A coupling is provided comprising an inlet ring adapter including a cylindrical sleeve extending downstream of the upstream end of the transition duct in overlapping relation to an inner surface of the transition duct. A spring clip assembly is mounted to the terminal end of the combustor basket. The spring clip assembly extends into engagement with and forms a seal on the cylindrical sleeve.

Gas turbine transition inlet ring adapter

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 secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a manifold formed integral to, and surrounding a portion of, the transition piece, a manifold inlet port, and a collection of injection nozzles. A flowsleeve augments fuel/diluent flow velocity and improves the system cooling effectiveness. Passive cooling elements, including effusion cooling holes located within the transition boundary and thermal-stress-dissipating gaps that resist thermal stress accumulation, provide supplemental heat dissipation in key areas. The system delivers a secondary fuel/diluent mixture to a secondary combustion zone located along the length of the transition piece, while reducing the impact of elevated vibration levels found within the transition piece and avoiding the heat dissipation difficulties often associated with traditional vibration reduction methods.

Secondary fuel delivery system

Growing community of inventors

Chuluota, FL, United States of America

Daniel W Garan