Gas Turbine Efficiency Sweden Ab

Siemens Energy, Inc.

Combustion Science & Engineering, Inc.

Beijing Huatsing Gas Turbine & Igcc Technology Co., Ltd

John L Battaglioli

Robert James Bland

Thomas Wagner

Richard J Roby

Michael S Klassen

Adam Bailey

Shanshan Zhang

Richard Joklik

John Barnes

Diwakar Vashishat

Andrew J Hamer

Christopher R Oliveri

Daniel F Woolley

Hilbert H Valdez

Jonathan R Knaust

Lindsay A Early

Robert J Burke

Robert J L Bland

Stephen A Ramier

Anil Gulati

Xiaoehen Zha

Xiaochen Zha

Richard G Joklik

A method of optimizing a premix fuel nozzle for a gas turbine is provided including the step of providing a nozzle that provides, when the gas turbine is in operation, an axial flow field of an air and fuel mixture flows through the burner tube and around the nozzle tip, and at least two recirculation zones with at least two differing radial extents as part of a toroidal vortex generated on the nozzle tip to provide strong flame holding and flame propagation.

Method of optimizing premix fuel nozzles for a gas turbine

A nozzle tip for a premix fuel nozzle includes an outer body having an outer body external face facing the downstream end of the burner tube, the outer body external face having a smaller cross-sectional area than the cross-sectional area of the burner tube; and at least one segment radiating radially outwardly toward the internal wall of the burner tube from the outer body, wherein each segment has a proximal end disposed adjacent to the outer body external face and a distal end disposed in a direction toward the burner tube, wherein each segment has a segment downstream face angled relative to the longitudinal axis of the burner tube towards the downstream end of the burner tube. When the gas turbine is in operation, an axial flow field of an air and fuel mixture flows through the burner tube and around the nozzle tip, and two or more recirculation zones of differing radial extent are generated on the nozzle tip by the segments to provide strong flame holding and flame propagation.

Premix fuel nozzle for a gas turbine and combustor

A compressor wash system for compressor washing includes stages of fluid delivery lines coupled at one end to a pump output and at the other end to a corresponding nozzle set. A control valve is connected to the fluid delivery line between the pump and the nozzle set, selectively supplying fluid between the pump and the nozzle set. Each nozzle of a nozzle set is positioned on an inlet of the compressor to allow the stages to wash a portion of the compressor. Nozzle sets are positioned around a bellmouth assembly and/or around an inlet cone of the compressor inlet, with a nozzle spray tip of each nozzle extending into an inlet air flow path of the compressor. Fluid may be directed to one or more of the stages in a sequencing pattern determined and configured to wash the compressor. Templates and installation guides are utilized to position the nozzles.

Staged compressor water wash system

A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a trailing edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell.

Axial diffusor for a turbine engine

A system and method for providing continuous measurement and control of a combustion device by altering the fuel composition delivered thereto. The system includes devices for sensing combustion characteristics or other device characteristics, and controlling the performance of the combustion device based on the sensed information. Performance control occurs via addition of one or more additives to the fuel to adjust combustion characteristics. Via such sensing and performance control, consistent combustion device performance may be maintained, despite varying fuel characteristics. In one variation,&#x2014;characteristics of the combustion device in operation, such as flame characteristics, are sensed and used to adjust fuel characteristics via iterative addition of one or more additives.

System and method for flame stabilization and control

A burner () of a gas turbine engine () includes a cylindrical basket () comprising an air flow reversal region (). The flow reversal region ends at an air inlet plane () of the basket. The burner also includes a flow conditioner () disposed in the flow reversal region transecting an air flow () flowing non-uniformly through the flow reversal region, the flow conditioner being effective to mitigate variation of the air flow entering the basket across the inlet plane.

Air flow conditioner for a combustor can of a gas turbine engine

A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines a passageway therein having a first side facing the nozzle and a second side facing the combustion chamber. Compressed air is directed into an inlet in fluid communication with the first and second sides of the venturi passageway. The venturi passageway directs the compressed air from the inlet in opposite directions within the first and second sides of the passageway for cooling the venturi.

Venturi cooling system

A secondary nozzle is provided for a gas turbine. The secondary nozzle includes a flange and an elongated nozzle body extending from the flange. At least one premix fuel injector is spaced radially from the nozzle body and extends from the flange generally parallel to the nozzle body. At least one second nozzle tube is fluidly connected to the fuel source and spaced radially outward from the first nozzle tube with a proximal end fixed to the flange. The second nozzle tube has a distal end, spaced from the proximal end, with at least one aperture therein. A passageway extends between the proximal end and the distal end of the second nozzle tube, with the passageway fluidly connecting to the fuel source and the aperture.

Combustor nozzle

A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines an internal passageway therein having a first side facing the nozzle and a second side facing the combustion chamber. Compressed air is directed into an inlet in fluid communication with the first and second sides of the internal passageway. The internal passageway directs the compressed air from the inlet in opposite directions within the first and second sides of the internal passageway for cooling the venturi.

A system and method for providing continuous measurement and control of a combustion device by altering the fuel composition delivered thereto. The system includes devices for sensing related information, such as fuel characteristics, combustion characteristics, or other device characteristics, and controlling the performance of the combustion device based on the sensed information. Performance control occurs via addition of one or more additives to the fuel to adjust combustion characteristics. Via such sensing and performance control, consistent combustion device performance may be maintained, despite varying fuel characteristics. In one variation, sensing occurs for the fuel delivered to the combustion device, and one or more additives are added to the fuel, based on the composition and flow rate for the fuel. In another variation, characteristics of the combustion device in operation, such as flame characteristics, are sensed and used to adjust fuel characteristics via iterative addition of one or more additives.

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Ballston Lake, NY, United States of America

John L Battaglioli