Abstract: A combustor (22) for a gas turbine (10) includes a main burner oxidizer flow path (34) delivering a first portion (32) of an oxidizer flow (e.g., 16) to a main burner (28) of the combustor and a pilot oxidizer flow path (38) delivering a second portion (36) of the oxidizer flow to a pilot (30) of the combustor. The combustor also includes a flow controller (42) disposed in the pilot oxidizer flow path for controlling an amount of the second portion delivered to the pilot.

Abstract: A method and apparatus for detecting a flashback condition in a fuel nozzle (8) of a gas turbine (10) are provided. The fuel nozzle is configured to pass a flow of air (20) to be mixed with a fuel in a premixing zone (11). The apparatus includes at least one fuel injecting device (12) positioned to define a point of fuel injection in the premixing zone. The apparatus further includes an electrode (16) positioned upstream of the point of fuel injection. The electrode is adapted to sense a flashback condition that can occur in the premixing zone.

Abstract: A system for dampening combustor dynamics within a turbomachine. The system may include at least one resonator installed adjacent a head-end region of a combustion can. The at least one resonator may include a first side having a plurality of holes forming a cold side hole pattern; a second side having a plurality of holes forming a hot side hole pattern; and a cavity substantially defined by the first side and the hot side. The cold side hole pattern may be oriented such that each of the plurality of holes in the cold side hole pattern allows for a jet of a cooling air to substantially impinge a second side facing surface; and wherein the hot side hole pattern is oriented such that each of the plurality of holes in the hot side hole pattern allows for a jet of a working fluid to substantially impinges a first side facing surface.

Abstract: A gas turbine combustor (23) includes a catalytic combustion stage (22) receiving a first portion (18) of a total oxidizer flow (16) and a first portion (30) of a total fuel flow (29) and discharging a partially oxidized fuel/oxidizer mixture (40) into a post catalytic combustion stage (24) defined by a combustion liner (58). The combustor further includes an injector scoop (54) having an injector scoop inlet (56) in fluid communication with an opening (56) in the combustion liner for receiving a second portion (20) of the oxidizer flow. A fuel outlet (e.g. 64) selectively supplies a second portion (42) of the total fuel flow into the second portion of the oxidizer flow.

Abstract: A method and apparatus for detecting a flashback condition in a fuel nozzle (8) of a gas turbine (10) are provided. The fuel nozzle is configured to pass a flow of air (20) to be mixed with a fuel in a premixing zone (11). The apparatus includes at least one fuel injecting device (12) positioned to define a point of fuel injection in the premixing zone. The apparatus further includes an electrode (16) positioned upstream of the point of fuel injection. The electrode is adapted to sense a flashback condition that can occur in the premixing zone.

Abstract: 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.

Abstract: 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.

Abstract: A pilotless catalytic combustor (10) including a basket (12) having a central axis (14) and a central core region (16) disposed along a portion of the central axis. Catalytic combustion modules (18) are circumferentially disposed about the central axis radially outward of the central core region for receiving a fuel flow (20) and a first portion of an oxidizer flow (22), and discharge a partially oxidized fuel/oxidizer mixture (24) at respective exit ends (26). A base plate (30) is positioned in the central core region upstream of the exit ends of the catalytic combustion modules, the baseplate defining a recirculation zone (32) 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.

Abstract: A catalytic combustor 30 includes a frame 32 and catalyst support plate assemblies 34 carried by the frame. A catalyst support plate assembly 34 includes a pair of opposing plates 36A, 36B, at least one having ridges 38A, 38B that define passageways 40 between the pair of opposing plates. A catalyst 44 is carried by the catalyst support plate assemblies 34. Both of the opposing plates 36A, 36B may have ridges 38A, 38B with valleys 42A, 42B between adjacent ridges. A pair of opposing plates 36A, 36B may be aligned and connected at opposing ridges 38A, 38B so that opposing valleys 42A, 42B define air passageways having predetermined shapes. The catalyst support plate assemblies 34 may be arranged in back-to-back relation so that adjacent pairs of catalyst support plate assemblies 34 define fuel/air passageways 46. Adjacent pairs of catalyst support plate assemblies 34 may be offset from one another to define a nested configuration.

Abstract: A catalytic combustor 30 includes a frame 32 and catalyst support plate assemblies 34 carried by the frame. A catalyst support plate assembly 34 includes a pair of opposing plates 36A, 36B, at least one having ridges 38A, 38B that define passageways 40 between the pair of opposing plates. A catalyst 44 is carried by the catalyst support plate assemblies 34. Both of the opposing plates 36A, 36B may have ridges 38A, 38B with valleys 42A, 42B between adjacent ridges. A pair of opposing plates 36A, 36B may be aligned and connected at opposing ridges 38A, 38B so that opposing valleys 42A, 42B define air passageways having predetermined shapes. The catalyst support plate assemblies 34 may be arranged in back-to-back relation so that adjacent pairs of catalyst support plate assemblies 34 define fuel/air passageways 46. Adjacent pairs of catalyst support plate assemblies 34 may be offset from one another to define a nested configuration.