Other

Ansaldo Energia Switzerland Ag

Power Systems Mfg., LLC

Ansaldo Energia IP UK Limited

General Electric Technology Gmbh

Paul Economo

Peter Stuttaford

Hany Rizkalla

Stephen Wilder Jorgensen

Khalid Oumejjoud

Nicolas Demougeot

Donald Gauthier

Sumit Soni

Kevin B Powell

John Henriquez

Timothy Hui

Justin Bosnoian

Chiluwata Lungu

Max Dufflocq

Peter John Stuttaford

The present invention discloses a fuel nozzle assembly and method for axially staging fuel injection. The fuel nozzle assembly comprises a plurality of vanes connected to a core, with an annular ring connectedly surrounding the plurality of vanes. Fuel is directed through the core and then through the vanes and is injected at different axial planes generally perpendicular to an oncoming air stream to obtain a broad spectrum of gas residence time between the point of fuel injection and the flame.

Fuel nozzle for axially staged fuel injection

The present invention discloses a novel and improved apparatus and method for reducing the emissions of a gas turbine combustion system. More specifically, a combustion system is provided having a first combustion chamber and a premixer positioned proximate an outlet end of a combustion liner for mixing a second fuel/air mixture with hot combustion gases and burning the subsequent mixture to achieve reduced emissions levels. The premixer is positioned generally about the combustion liner and includes a plurality of channels and fuel injectors for introducing a fuel/air mixture, induced with a swirl, into a second, axially staged combustor.

Axially staged gas turbine combustor with interstage premixer

Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.

Gas turbine fuel nozzle having improved thermal capability

An ignition system having improved reliability for a gas turbine combustor is disclosed. The ignition system comprises an outer housing having at least one fuel passage and an electrode extending therethrough forming a generally annular passage for cooling air to pass to a mixing chamber. Fuel and air mix in the mixing chamber to form a combustible mixture that is ignited by the electrode. The outer housing further comprises a plurality of air swirl holes to effectively cool the walls of the mixing chamber as well as to provide improved flame stability.

Tornado torch igniter

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Jupiter, FL, United States of America

Paul Economo