Siemens Westinghouse Power Corporation

Siemens Energy, Inc.

Siemens Power Generation, Inc.

Ramarao V Bandaru

Walter Ray Laster

Robert James Bland

John Carl Glessner

John Luigi Battaglioli

Joan Mae Baer

Sean A Miller

A combustor () for a gas turbine () includes a main burner oxidizer flow path () delivering a first portion () of an oxidizer flow (e.g.,) to a main burner () of the combustor and a pilot oxidizer flow path () delivering a second portion () of the oxidizer flow to a pilot () of the combustor. The combustor also includes a flow controller () disposed in the pilot oxidizer flow path for controlling an amount of the second portion delivered to the pilot.

Controlled pilot oxidizer for a gas turbine combustor

A method and apparatus for detecting a flashback condition in a fuel nozzle () of a gas turbine () are provided. The fuel nozzle is configured to pass a flow of air () to be mixed with a fuel in a premixing zone (). The apparatus includes at least one fuel injecting device () positioned to define a point of fuel injection in the premixing zone. The apparatus further includes an electrode () positioned upstream of the point of fuel injection. The electrode is adapted to sense a flashback condition that can occur in the premixing zone.

Method and apparatus for detecting a flashback condition in a gas turbine

A gas turbine combustor () includes a catalytic combustion stage () receiving a first portion () of a total oxidizer flow () and a first portion () of a total fuel flow () and discharging a partially oxidized fuel/oxidizer mixture () into a post catalytic combustion stage () defined by a combustion liner (). The combustor further includes an injector scoop () having an injector scoop inlet () in fluid communication with an opening () in the combustion liner for receiving a second portion () of the oxidizer flow. A fuel outlet (e.g.) selectively supplies a second portion () of the total fuel flow into the second portion of the oxidizer flow. The injector scoop includes an injector scoop outlet () in fluid communication with the post catalytic combustion stage and discharges a fuel/oxidizer mixture () into the partially combusted fuel/oxidizer mixture at an angle relative to the flow axis to impart a swirl to the fuel/oxidizer mixture as it enters the post catalytic combustion stage.

Catalytic combustor having fuel flow control responsive to measured combustion parameters

Aspects according to the invention relate to a catalytic combustor system for a turbine engine and an associated method. Catalytic combustors are used in connection with turbine engines because they can minimize the formation of oxides of nitrogen during combustion. Despite this emissions advantage, catalytic combustion systems can increase the level of CO in the turbine exhaust. According to aspects of the invention, vortex formation devices includes vortex generators, swirlers and mixers can be placed downstream of each catalytic module surrounding the pilot nozzle so as to form one or more vortices in the otherwise substantially laminar flow exiting the modules. The vortices can create a suction so that a portion of the flow exiting the pilot nozzles is mixed with the flow exiting the catalyst modules. The introduction of the higher temperature pilot flow can accelerate the catalytic reaction time, promoting burnout of the CO formed during combustion.

Catalytic combustion system and method

A catalytic gas turbine includes a compressor, a catalytic combustor, a turbine, and a flow path conducting a bypass portion of the compressed air around the combustor and turbine. A method of operating the catalytic gas turbine to activate a catalyst in the catalytic combustor includes opening an inlet guide vane upstream of the compressor to a position to produce an increased volume of compressed air. The increased volume exceeds a volume of compressed air needed to support combustion. A bypass portion of the compressed air is extracted and directed around the combustor and turbine. The method may also include extracting a recirculation portion of the compressed air and directing the recirculation portion into the inlet of the compressor.

Control of gas turbine for catalyst activation

A pilotless catalytic combustor () including a basket () having a central axis () and a central core region () disposed along a portion of the central axis. Catalytic combustion modules () are circumferentially disposed about the central axis radially outward of the central core region for receiving a fuel flow () and a first portion of an oxidizer flow (), and discharge a partially oxidized fuel/oxidizer mixture () at respective exit ends (). A base plate () is positioned in the central core region upstream of the exit ends of the catalytic combustion modules, the baseplate defining a recirculation zone () near the respective exit ends for stabilizing oxidation in the burnout zone. A method of staged fueling for a pilotless catalytic combustor includes providing fuel to at least one of the modules during start up and progressively providing fuel to other modules as a load on the turbine engine is increased.

Pilotless catalytic combustor

A catalytic combustor includes a frame and catalyst support plate assemblies carried by the frame. A catalyst support plate assembly includes a pair of opposing plates A, B, at least one having ridges A, B that define passageways between the pair of opposing plates. A catalyst is carried by the catalyst support plate assemblies . Both of the opposing plates A, B may have ridges A, B with valleys A, B between adjacent ridges. A pair of opposing plates A, B may be aligned and connected at opposing ridges A, B so that opposing valleys A, B define air passageways having predetermined shapes. The catalyst support plate assemblies may be arranged in back-to-back relation so that adjacent pairs of catalyst support plate assemblies define fuel/air passageways . Adjacent pairs of catalyst support plate assemblies may be offset from one another to define a nested configuration.

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Oviedo, FL, United States of America

Ramarao V Bandaru