Siemens Energy, Inc.

Scott M Martin

Juan Enrique Portillo Bilbao

Timothy A Fox

Walter Ray Laster

Jacob William Hardes

Robert James Bland

William A Elmer

Steven W Elmer

David M Ritland

Weidong Cai

Arthur J Harris, Jr

Anil Gulati

A cooling system for a fuel system in a turbine engine that is usable to cool a fuel nozzle is disclosed. The cooling system may include one or more cooling system housings positioned around the fuel nozzle, such that the cooling system housing forms a cooling chamber defined at least partially by an inner surface of the cooling system housing and an outer surface of the fuel nozzle. The fuel nozzle may extend into a combustor chamber formed at least in part by a combustor housing. The fuel nozzle may include one or more fuel exhaust orifices with an opening in an outer surface of the fuel nozzle and configured to exhaust fluids unrestricted by the housing forming the cooling system cooling chamber. The cooling system may provide cooling fluids to cool the fuel nozzle within the cooling system cooling chamber regardless of whether the fuel nozzle is in use.

Cooling system for fuel nozzles within combustor in a turbine engine

A secondary fuel stage () of a combustor of a gas turbine engine. The combustor has a main combustion zone () upstream of the secondary fuel stage to ignite working gas The secondary fuel stage includes a nozzle () with dual outlets () oriented with a circumferential component to inject an air-fuel mixture () into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas () such that a peak temperature () of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature () of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle ().

Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine

A combustor () including: a first premix main burner () comprising a first swirler airfoil section (); a second premix main burner () comprising a second swirler airfoil section (); and a supply air reversing region upstream of the premix burners (), (). The first swirler airfoil section () and the second swirler airfoil section () are effective to impart swirl to a first airflow and a second airflow characterized by a same swirl number as the airflows exit respective burners (), (). The combustor () is effective to generate a first airflow volume through the first premix main burner () that is different than a second airflow volume through the second premix main burner ().

Air biasing system in a gas turbine combustor

A pilot burner () for a gas turbine engine delivers an inner non-swirling fuel-oxidant mixture surrounded by an outer swirling fuel-oxidant mixture, thereby providing enhanced mixing with no recirculation zone. At least one fluid-restricting inlet port () provides an oxidant to an inner mixing passage (). The inner mixing passage () includes a plurality of fuel outlets (). An outer annular mixing passage () receives oxidant from an upstream port () surrounding the inner mixing passage and includes at least one swirler element () and fuel outlets ().

Pilot burner for gas turbine engine

A combustor () for a gas turbine engine is provided comprising a primary combustion chamber () for combusting a first fuel to form a combustion flow stream () and a transition piece () located downstream from the primary combustion chamber (). The transition piece () comprises a plurality of injectors () located around a circumference of the transition piece () for injecting a second fuel into the combustion flow stream (). The injectors () are effective to create a radial temperature profile () at an exit () of the transition piece () having a reduced coefficient of variation relative to a radial temperature profile () at an inlet () of the transition piece (). Methods for controlling the temperature profile of a secondary injection are also provided.

Apparatus and method for controlling the secondary injection of fuel

An improved gas turbine combustor () including a basket () and a multiplicity of micro openings () arrayed across an inlet wall () for passage of a fuel/air mixture for ignition within the combustor. The openings preferably have a diameter on the order of the quenching diameter; i.e. the port diameter for which the flame is self-extinguishing, which is a function of the fuel mixture, temperature and pressure. The basket may have a curved rectangular shape that approximates the shape of the curved rectangular shape of the intake manifolds of the turbine.

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Daytona Beach, FL, United States of America

Scott M Martin