Abstract: A gasification power plant 10 includes a compressor 32 producing a compressed air flow 36, an air separation unit 22 producing a nitrogen flow 44, a gasifier 14 producing a primary fuel flow 28 and a secondary fuel source 60 providing a secondary fuel flow 62 The plant also includes a catalytic combustor 12 combining the nitrogen flow and a combustor portion 38 of the compressed air flow to form a diluted air flow 39 and combining at least one of the primary fuel flow and secondary fuel flow and a mixer portion 78 of the diluted air flow to produce a combustible mixture 80. A catalytic element 64 of the combustor 12 separately receives the combustible mixture and a backside cooling portion 84 of the diluted air flow and allows the mixture and the heated flow to produce a hot combustion gas 46 provided to a turbine 48. When fueled with the secondary fuel flow, nitrogen is not combined with the combustor portion.

Abstract: A gas turbine engine combustor (26) including a primary combustion chamber (28), a mixer element (34), a mixing chamber (46) and a secondary combustion chamber (48). The primary combustion chamber receives a fuel oxidizer mixture flow (22) and discharges a partially oxidized mixture flow (32). The mixer element includes a plurality of flow channels (36, 38) for separating the partially oxidized mixture from a flow of an oxidizer (24) and producing a plurality of partially oxidized mixture flows interspersed with a plurality of oxidizer fluid flows. The mixer element may include a plurality of tubes (62) retained by an upstream tubesheet (70) and a downstream tubesheet (76). The mixer element may function as a heat exchanger to heat the oxidizer fluid flow and to cool the partially oxidized mixture flow upstream of the post-mixing chamber.

Abstract: A gas turbine engine (10) includes a catalytic oxidation module (28). The catalytic oxidation module includes a pressure boundary element (30); a catalytic surface (32); and an opening (34) in the pressure boundary element to allow premixing of the fluids before the fluids enter a downstream plenum. In an embodiment, the pressure boundary element includes a catalyst-coated tube (58) having holes (68) formed therein to allow mixing across the tube. In another embodiment, the pressure boundary element includes a tubesheet (44) having a first fluid passageway intersecting a second fluid passageway to premix the fluids upstream of the outlet end of the tubesheet. In yet another embodiment, the catalytic oxidation module includes an upstream tubesheet (86) for mounting a tube inlet end (73) and a downstream tubesheet (78) for mounting a tube outlet end (72) so that the tube is slidably contained there between.

Abstract: A gas turbine engine (10) includes a catalytic oxidation module (28). The catalytic oxidation module includes a pressure boundary element (30); a catalytic surface (32); and an opening (34) in the pressure boundary element to allow premixing of the fluids before the fluids enter a downstream plenum. In an embodiment, the pressure boundary element includes a catalyst-coated tube (58) having holes (68) formed therein to allow mixing across the tube. In another embodiment, the pressure boundary element includes a tubesheet (44) having a first fluid passageway intersecting a second fluid passageway to premix the fluids upstream of the outlet end of the tubesheet. In yet another embodiment, the catalytic oxidation module includes an upstream tubesheet (86) for mounting a tube inlet end (73) and a downstream tubesheet (78) for mounting a tube outlet end (72) so that the tube is slidably contained there between.

Abstract: A combustion turbine with a secondary combustor is provided. The secondary combustor is disposed within the turbine assembly of the combustion turbine. The secondary combustor assembly is structured to maintain the working gas at a working temperature within the turbine assembly. The secondary combustor assembly re-heats the working gas by injecting a combustible gas into the working gas. The secondary combustor assembly includes a plurality of openings disposed among the vanes and/or blades in the turbine assembly which are coupled to a combustible gas source. As the combustible gas is injected into the working gas, the combustible gas will auto-ignite. That is, the combustible gas will combust without the need for an igniter or pre-existing flame. Combustion of the combustible gas in the turbine assembly re-heats the working gas.

Abstract: A catalytic combustor includes a plurality of rectangular, tubular subassemblies having the catalyst coating on their outside surfaces. The subassemblies are held in spaced relationship within channels in support walls so that the catalyst coated surfaces of adjacent subassemblies define a catalyst-coated channel, and the interior of the tubular subassemblies defines uncoated channels. This structure permits precise location and support for the various subassemblies, provides wide flexibility in selecting the number and size of catalyst coated subassemblies, and provides for multiple possible flow paths for cooling air and fuel-air mixture through the catalytic combustor.

Abstract: A catalytic combustor includes a plurality of rectangular, tubular subassemblies having the catalyst coating on their outside surfaces. The subassemblies are held in spaced relationship within channels in support walls so that the catalyst coated surfaces of adjacent subassemblies define a catalyst-coated channel, and the interior of the tubular subassemblies defines uncoated channels. This structure permits precise location and support for the various subassemblies, provides wide flexibility in selecting the number and size of catalyst coated subassemblies, and provides for multiple possible flow paths for cooling air and fuel-air mixture through the catalytic combustor.

Abstract: A combustion turbine with a secondary combustor is provided. The secondary combustor is disposed within the turbine assembly of the combustion turbine. The secondary combustor assembly is structured to maintain the working gas at a working temperature within the turbine assembly. The secondary combustor assembly re-heats the working gas by injecting a combustible gas into the working gas. The secondary combustor assembly includes a plurality of openings disposed among the vanes and/or blades in the turbine assembly which are coupled to a combustible gas source. As the combustible gas is injected into the working gas, the combustible gas will auto-ignite. That is, the combustible gas will combust without the need for an igniter or pre-existing flame. Combustion of the combustible gas in the turbine assembly re-heats the working gas.

Abstract: A combustion turbine which produces a reduced amount of NOx is provided. The combustion turbine reduces the amount of NOx produced by utilizing a secondary combustor. By using a secondary combustor the working gas of the combustion turbine does not need to be heated above 2500° F., the temperature at which a substantial amount of NOx begins to form, until the working gas is entering the turbine assembly. The secondary combustor assembly heats the working gas by injecting a combustible gas, or compressed air if the primary combustor produces a fuel rich working gas, into the elevated temperature working gas. This gas combusts and heats the working gas adjacent to the beginning of the turbine assembly. Because the working gas is not raised above 2500° F. until it is about to enter the turbine assembly, the time during which NOx is formed is reduced.

Abstract: An axially elongated candle filter element (28′) is made having an open end, a closed end and porous walls (86) around an axially elongated passageway volume (88) where the walls are of an open metal structure (86), preferably a honeycomb structure, placed at a 90 degree angle to and surrounding the axis (90—90) of the inner volume, where the structure (86) is filled with porous ceramic material (84) through which hot gases can pass to reach the passageway (88).

Abstract: A combustor for burning a mixture of fuel and air in a rich combustion zone, in which the fuel bound nitrogen in converted to molecular nitrogen. The fuel rich combustion is followed by lean combustion. The products of combustion from the lean combustion are rapidly quenched so as to convert the fuel bound nitrogen to molecular nitrogen without forming NOx. The combustor has an air radial swirler that directs the air radially inward while swirling it in the circumferential direction and a radial fuel swirler that directs the fuel radially outward while swirling it in the same circumferential direction, thereby promoting vigorous mixing of the fuel and air. The air inlet has a variable flow area that is responsive to variations in the heating value of the fuel, which may be a coal-derived fuel gas. A diverging passage in the combustor in front of a bluff body causes the fuel/air mixture to recirculate with the rich combustion zone.

Abstract: A low NOx generating combustor in which a first lean mixture of fuel and air is pre-heated by transferring heat from hot gas discharging from the combustor. The preheated first fuel/air mixture is then catalyzed in a catalytic reactor and then combusted so as to produce a hot gas having a temperature in excess of the ignition temperature of the fuel. Second and third lean mixtures of fuel and air are then sequentially introduced into the hot gas, thereby raising their temperatures above the ignition temperature and causing homogeneous combustion of the second and third fuel air mixtures. This homogeneous combustion is enhanced by the presence of the free radicals created during the catalyzation of the first fuel/air mixture. In addition, the catalytic reactor acts as a pilot that imparts stability to the combustion of the lean second and third fuel/air mixtures.

Abstract: A fail-safe back-up filter system for filtering particles from a flow of hot gas in a coal gasifier or the like in the event of a failure of the primary filter system. In the event of a break in one of the primary filter elements of the filtration system, the back-up filters, having a higher porosity than the primary filters, begin to collect particulate matter such that the particulates become embedded in the back-up filter. After a period of time, the back-up filters become clogged and prevent the flow of particle laden gas through the back-up filter and the corresponding primary filter such that the flow of gas is diverted into communication with the remaining, properly functioning primary filters. The back-up filters also provide a thermal regenerator device for heating the flow of cleaning gas before it contacts the primary filter elements during back-flush cleaning in order to avoid the effects of extreme temperature fluctuations on the primary filters.

Abstract: The nuclear reactor control column comprises a column disposed within the nuclear reactor core having a variable cross-section hollow channel and containing balls whose vertical location is determined by the flow of the reactor coolant through the column. The control column is divided into three basic sections wherein each of the sections has a different cross-sectional area. The uppermost section of the control column has the greatest cross-sectional area, the intermediate section of the control column has the smallest cross-sectional area, and the lowermost section of the control column has the intermediate cross-sectional area. In this manner, the area of the uppermost section can be established such that when the reactor coolant is flowing under normal conditions therethrough, the absorber balls will be lifted and suspended in a fluidized bed manner in the upper section.