Siemens Aktiengesellschaft

Siemens Energy, Inc.

Siemens Aktiengensellschaft

Vinayak V Barve

Charalambos Polyzopoulos

Stephen A Ramier

Richard L Thackway

Khalil Farid Abou-Jaoude

Timothy A Fox

Robert H Bartley

Daniel W Garan

Kevin J Spence

Jaap Van Kampen

Ulrich Wörz

Joseph Scott Markovitz

David P Holzapfel

Jianfan Wu

Blake R Cotten

Sachin Terdalkar

Urmi B Dave

Vaidyanathan Krishnan

Michael C Escandon

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 fuel burner system () configured to inject a liquid fuel and a gas fuel into a combustor () of a turbine engine () such that the engine () may operate on the combustion of both fuel sources () is disclosed. The fuel burner system () may be formed from a nozzle cap () including one or more first fuel injection ports () in fluid communication with a first fuel source () of syngas and one or more second fuel injection ports () in fluid communication with a second fuel source () of natural gas. The fuel burner system () may also include an oil lance () with one or more oil injection passages () that is in fluid communication with at least one oil source () and is configured to emit oil into the combustor (). The oil lance () may include one or more fluid injection passages () configured to emit air to break up the oil spray and water to cool the combustor (), or both.

Flexible fuel combustion system for turbine engines

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

A method of operating a multi-fuel combustion system is provided. The method includes a first phase and a second phase, wherein the first phase includes providing ignition to a combustor basket to ignite a first type of fuel, where the first type of fuel is supplied to the combustor basket through a first conduit. Also in first phase steam is also supplied to the first conduit in addition to the first type of fuel and steam is supplied to the second conduit after the ignition. In the second phase a second type of fuel is supplied to the combustor basket through the second conduit after ignition of the first fuel through the first conduit, while stopping the supply of the first fuel, and continuing to supply steam through both the first and second conduits.

Method of operating a multi-fuel combustion system

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Oviedo, FL, United States of America

Vinayak V Barve