Westinghouse Electric Corporation

Siemens Energy, Inc.

Stephen E Mumford

David Marchant Parker

Jan P Smed

Rajeev Ohri

William L McCarty

Arthur J Harris, Jr

Edward W Tobery

Herbert C Reid

Andrew J Kosinski

Kristian I Wetzl

A fuel/air mixing apparatus, such as a main swirler assembly () comprising a sleeve (), provides for additional air entry around the perimeter of a bore () through which passes a fuel/air mixture. The additional air reduces or eliminates flashback during operation of a gas turbine comprising the assembly (). In some embodiments, a plurality of gaps () exists between spaced apart tabs () along a downstream end () of the sleeve (). During gas turbine operation, air flows through both a flashback annulus () and the gaps (). In other embodiments, a plurality of holes are placed upstream and in line with the tabs () to supplement the air flow through gaps (). In yet other embodiments, rows () of holes () are provided to supplement the airflow. Downstream ends () may interface with a downstream-oriented lip () or with an upstream-oriented lip (). The interfacing may comprise a fit effective to damp vibration and to increase the natural frequency.

Swirler assembly and combinations of same in gas turbine engine combustors

An improved combustion system that is constructed and arranged to be used with a power-generating turbine or the like includes at least one combustion chamber, a fuel supply system for supplying fuel to the combustion chamber, an air supply system for supplying air from a pressurized air source to the combustion chamber, a monitor for monitoring a property of the combustion products from the combustion chamber, a regulator for regulating an air to fuel ratio in the combustion chamber, and a controller, in communication with the monitor and the regulator for controlling the regulator in response to information received from the monitor. According to one novel aspect of the invention, the controller controls the regulator with no direct mechanical linkage therebetween, so that the complexity and expense of the system is kept to a minimum.

System for controlling combustion in a gas combustion-type turbine

Apparatus for retro-fitting low NOx combustors in a conventional gas turbine using the existing openings in the cylinder casing and without any significant alteration of the turbine apparatus. Each one of the low NOx combustors is mounted by a nozzle block to the cylinder casing over an existing opening sized for a conventional combustor, the nozzle block having a plurality of fuel nozzles for spraying fuel into said combustor. The nozzle block has a pilot nozzle aperture and a plurality of annular fuel passages such that when the nozzle block is mechanically connected to the combustor the nozzles are in flow communication with the fuel passages. The nozzle block is sized such that one end can be flushly mounted to the cylinder casing over the existing opening. A fuel supply adapter having a plurality of manifold passages is connected to the nozzle block such that the manifold passages are in flow communication with a supply of fuel and also with the fuel passages such that fuel is supplied to the nozzles through the fuel passages in the nozzle block. A pilot nozzle is in flow communication with a supply of fuel and extends through the pilot nozzle aperture and into the combustor for creating a pilot flame in the combustor.

Low NOx combustor retro-fit system for gas turbines

A method and system for auto-igniting the pilot section of a gas turbine combustor prior to down-loading the turbine from base load operation. A liquid fuel is employed that has an auto-ignition temperature which is less than the temperature of air which enters into the recirculation zone of the pilot section. The liquid fuel is injected into the recirculation zone and auto-ignites, causing natural gas fuel which is also being injected into the pilot section to burst into flame, creating a diffusion flame in the pilot section. This permits operation of the pilot section in a premix mode where natural gas fuel mixes with air without a flame during base load operation, thus providing for low production of NOx emissions, while ensuring maintenance of a flame in the combustor when the flame in the main burn section of the combustor is extinguished to allow for turbine unloading.

Auto-ignition system for premixed gas turbine combustors

Method and apparatus for generating an ignition enabling signal for use with a given combustion turbine having an ignition system which ignites the turbine in response to an enabling signal, wherein a turbine speed signal is given, is shown to include a sensor for generating an ambient air temperature signal, a reference member for generating a reference signal representative of the turbine speed at which optimum air flow exists for ignition, a comparator for comparing the reference signal to an adjusted speed signal and for generating the ignition enabling signal when the adjusted speed signal exceeds the reference signal and for providing the enabling signal to the ignition system. The adjusted speed signal is generated by modifying the turbine speed signal in response to the ambient air temperature signal. Such modification is achieved by summing the turbine speed signal with a bias speed factor. The bias speed factor is representative of the difference between optimum turbine ignition speed and that turbine speed necessary for optimum ignition air flow to exist in said combustion turbine at such ambient temperature.

Gas turbine control system having optimized ignition air flow control

A gas turbine combustion chamber with an inlet and outlet has apertures in the combustion chamber wall and air scoops provided in the apertures, the air scoops having an outer tubular member and coaxially spaced inner tubular member. The spaced tubular members have inner cylindrical portions and outwardly extending flanges, with spacers disposed between and secured to the flanges with cooling air passing therebetween and through the annular air flow passage into the combustion chamber. Preferably, a radially outwardly extending arcuate section on the inner tubular member has a radius at least about one-third of the inner diameter of the inner cylindrical portion thereof.

Gas turbine combustion chamber with air scoops

An improved combustor basket for a land-based combustion turbine comprises a plurality of ring segments joined in telescoping fashion to form a constant diameter basket, the downstream end of each ring segment having an extended lip for improved film cooling of the interior surface of the ring segments, a combustor dome adjoining the upstream end of the combustor basket and having an interior splash plate directing a cooling air film along the interior surface of the dome wall, fuel injecting means, and oval-shaped scoops for directing the flow of compressed air into the combustion zone. Each ring segment, excluding the first, comprises an upstream cylindrical section, a conical section, and a downstream cylindrical section, which geometrical arrangement permits construction of a constant diameter combustor basket. The combined improvements of the present combustor basket result in more efficient and complete combustion, which results in the production of less smoke.

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Longwood, FL, United States of America

Stephen E Mumford