Abstract: A hybrid combustor, for providing stable high and low levels of operation while minimizing emissions of NOx, CO, and UHCs, includes a casing having a chamber, a catalytic combustor disposed in the chamber, and a non-premixed combustor disposed in the chamber. The hybrid combustor may comprise a fuel nozzle comprising a casing having a chamber, and a body supportable in the chamber to define a passageway between the body and the casing. The passageway has an inlet for receiving a stream of air and an outlet for discharging a stream of fuel and air, and the body includes a tapering downstream portion. Desirably, flow separation of the fuel and air mixture from the body (i.e., recirculation of the fuel and air mixture in the passageway and/or chamber) is inhibited whereby a generally uniform fuel and air mixture is provided.

Abstract: A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decomposing element (26) of an ACS thruster. The ACS decomposing element is operative to decompose the reduced toxicity propellant into hot propulsive gases. In addition the system includes suitable valves and conduits (18) for supplying the reduced toxicity propellant to an axial decomposing element (24) of the axial thruster. The axial decomposing element is operative to decompose the reduced toxicity propellant into hot gases. The system further includes suitable valves and conduits (20) for supplying a second propellant (12) to a combustion chamber (28) of the axial thruster, whereby the hot gases and the second propellant auto-ignite and begin the combustion process for producing thrust.

Abstract: Methods for operating catalytic combustion chambers including first and second catalytic reactors disposed in series with an intermediate chamber therebetween are disclosed, the method including heating the first catalytic reactor to a temperature at least equal to the ignition temperature of the first catalytic reactor, introducing air and fuel mixture to the first catalytic reactor whereby catalytic combustion is initiated in the first catalytic reactor, and increasing the mass flow through the first catalytic reactor whereby combustion of the air and fuel mixture takes place in the gas phase in the intermediate chamber and the end surface of the second catalytic reactor is heated to a temperature at least equal to the ignition temperature of the second catalytic reactor and ignition takes place in the second catalytic reactor.

Abstract: A catalytic combustion chamber is provided with at least two cataleptic combustion zones arranged in flow series, In a first mode of operation fuel is supplied from first fuel injectors, positioned upstream of the first catalytic combustion zone, into the catalytic combustion chamber and is burnt in the first catalytic combustion zone in order to preheat the subsequent catalytic combustion zones. In the second mode of operation the supply of fuel to the first fuel injectors is reduced and fuel is supplied from second fuel injectors positioned between the first catalytic combustion zone and the second catalytic combustion zone into the space between the first catalytic combustion zone and the second catalytic combustion zone. This prevents the first catalytic zone becoming overheated, and reduces the possibility of the second and third catalytic combustion zones becoming overheated and allows the optimum catalyst to be selected for the first catalytic combustion zone.

Abstract: A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decomposing element (26) of an ACS thruster. The ACS decomposing element is operative to decompose the reduced toxicity propellant into hot propulsive gases. In addition the system includes suitable valves and conduits (18) for supplying the reduced toxicity propellant to an axial decomposing element (24) of the axial thruster. The axial decomposing element is operative to decompose the reduced toxicity propellant into hot gases. The system further includes suitable valves and conduits (20) for supplying a second propellant (12) to a combustion chamber (28) of the axial thruster, whereby the hot gases and the second propellant auto-ignite and begin the combustion process for producing thrust.

Abstract: This invention pertains to an apparatus and means to lower emissions of carbon monoxide and nitrogen oxides in lean, pre-mixed gas turbine combustors. Specifically, this invention employs a catalyst deposited on the inner surfaces of the combustor in the region of combustion which oxidizes CO combustion products. Also provided is a means for depositing a catalyst within the thermal barrier coating on the combustor liner walls.

Abstract: A combustion control method for use in a catalytic combustion system having (a) a gaseous mixture inlet port, located at the upstream side of said catalytic combustion system, for the entrance of a fuel-air mixture; (b) an exhaust gas outlet port, located at the downstream side of said catalytic combustion system, for the exit of an exhaust gas; (c) a primary combustion chamber in which a catalyst body is disposed, said catalyst body being formed of a porous base material with numerous communicating holes that supports thereon an oxidation catalyst; (d) a secondary supply port, located downstream of said primary combustion chamber, for the supply of a gaseous mixture or air; and (e) a secondary combustion chamber located downstream of said secondary supply port; comprising such process that an excess air ratio of said primary combustion chamber is initially set above 1 and after the rate of combustion of said secondary combustion chamber exceeds a given level, combustion is made to take place, with the

Abstract: An energy producing system includes a compressor side for compressing an air/fuel mixture, and a turbine side for producing mechanical, electrical, and/or heat energy, and driving the compressor side. A catalytic combustor is disposed upstream of the turbine side for combusting a steady state air/fuel mixture during a steady state operation of the apparatus. During start-up of the system, the catalytic combustor is preheated by being supplied with a preheat air/fuel mixture capable of lighting-off therein at ambient temperature, whereby oxidization of the preheat air/fuel mixture in the catalytic combustor produces heat. The preheat air/fuel mixture is produced on-site, preferably in a reformer which burns natural gas in the presence of insufficient oxygen for complete combustion, thereby producing hydrogen and carbon monoxide.

Abstract: A gas turbine engine (10) combustion chamber (28) comprises a primary combustion zone (36) and a secondary combustion zone(40) in which lean mixtures of fuel and air are burned. Air is supplied to a first mixing duct (50) through a swirler (52). Air is supplied to an additional mixing duct (58) through a swirler (54) and hydrocarbon fuel is supplied to the additional mixing duct (58) through a swirler (66). The hydrocarbon fuel and air is mixed and reacted in a catalytic partial oxidation reaction zone (60) which produces a product gas comprising a mixture of hydrogen, carbon monoxide, carbon dioxide, water and unreacted hydrocarbon fuel. Additional hydrocarbon fuel is supplied from apertures (72) and is mixed with the product gas in a mixing chamber (68) and this mixture is supplied to the first mixing duct (50) and mixes with the air. The first mixing duct (50) supplies a lean mixture of fuel into the primary combustion zone (36).

Abstract: In a catalytic combustor for gas turbines, the dimensions of the preheater and premix duct, the location of the preheater and premix fuel nozzles, and the number and location of air orifices in the combustor can inner liner are configured to result in low NOx production during both preheating combustion and catalytic combustion. Placement of the air orifices helps reduce the potential for autoignition within the premix duct, while enhancing fuel-air mixture uniformity upstream of the catalyst. At the same time, the overall configuration is optimized to result in the relative compactness of the catalytic combustor, making it particularly suitable for applications such as automotive turbine engines and microturbines.

Abstract: A gas turbine system includes a compressor side for compressing an air/fuel mixture, and a turbine side for driving the compressor side. A heat exchanger transfers heat from turbine exhaust gases to the air/fuel mixture from the compressor side. A main catalytic combustor is disposed between the heat exchanger and the turbine side for combusting the air/fuel mixture and supplying the resultant products of combustion to the turbine side. The main catalytic combustor has a volume which is sufficient for oxidizing enough fuel to achieve a predetermined turbine inlet temperature, but insufficient for oxidizing all of the fuel. A secondary catalytic combustor is disposed downstream of the turbine side for combusting at least some of the fuel that was not combusted by the main catalytic combustor. The second catalytic combustor typically operates at a lower temperature than the main catalytic combustor.

Abstract: Described are a gas-turbine construction and a method of operating this gas-turbine construction, having an air compressor, a heat exchanger connected downstream of the air compressor, a combustion chamber, and a turbine which can be driven by hot combustion gases and from which the combustion gases are fed to the heat exchanger for heating the compressed supply air coming from the air compressor. The invention is distinguished by the fact that the heat exchanger and the combustion chamber are integrated in a common unit, and that fuel can be added to the supply air before entry into the unit, which fuel can be ignited catalytically in the form of an air/fuel mixture inside the unit, in which a catalyst is provided.

Abstract: Lean premixed combustion of a hydrocarbon fuel and air is combined with lean direct injection of hydrocarbon fuel and carrier fluid such as air or inert gas or a mixture of air and inert gas into a combustor downstream of the premixed reaction zone in order to achieve extremely low levels of emissions of oxides of nitrogen at the high combustor exit temperatures required by advanced heavy duty industrial gas turbines. One or more premixing fuel nozzles are used to supply a lean mixture of hydrocarbon fuel and air to the main or primary reaction zone of a gas turbine combustor. This lean fuel/air mixture has an adiabatic flame temperature below the temperature that would result in substantial thermal NOx formation.

Abstract: A gas turbine power system for generating energy by means of a gas turbine cycle, wherein heat energy is more effectively used by burning the exhaust gases (109) and the partial oxidation of said exhaust gases (109) is achieved by means of a hypostoichiometric amount of air and steam fed into a catalytic reactor (107) to form a first oxidation stage followed downstream in said turbine (103) by additional oxidation occurring in a power turbine (104) or downstream therefrom, said power turbine being in turn arranged downstream from the catalytic reactor (107). Catalytic partial oxidation may be performed using a supply of an initiating agent, particularly hydrogen. The method is remarkable in that the hydrogen fed into the reactor inlet through an injector (113) is provided by recycling part of the effluent from the reactor, the power turbine or a reforming reactor for reforming part of the fuel gas with a large excess amount of steam for performing catalytic partial oxidation.

Abstract: A catalytic combustor is formed of a plurality of segments which are enclosed within a canister. Each segment includes a metal strip which is folded back and forth upon itself. The strip is coated with catalyst on only one side, and the strip is brazed or welded to the canister only on the uncoated side. The segments of the combustor substantially fill the cross-section of the canister, but these segments are not physically joined to each other. The structure described above makes it possible to make the combustor relatively flat, having a length to diameter ratio of 0.25 or less. The catalytic combustor of the present invention is especially useful in a gas turbine, where space is limited, and where catalytic combustion is useful in preventing the formation of NOx.

Abstract: This invention relates to an apparatus and method for increasing the reactivity of a fuel/air mixture prior to homogenous combustion of the mixture. More specifically, this invention is a pilot for a gas turbine combustor which utilizes the heat of combustion within the pilot to increase the reactivity of a portion of the fuel/air mixture utilized by the pilot.

Abstract: A microturbine power generation system includes an electrical generator, a turbine and a compressor intermediate the generator and the turbine. The turbine, compressor and electrical generator are secured together by a tieshaft. The tieshaft is prestressed such that faces of the turbine, electrical generator and compressor maintain contact during high-speed, high-temperature operation of the system.

Abstract: A support structure for securing a catalyst structure comprising a multiplicity of longitudinally disposed channels for passage of a flowing gas mixture within a reactor, said support structure being comprised of a monolithic open celled or honeycomb-like structure formed by thin strips or ribs of high temperature resistant metal or ceramic which abuts against one end of the catalyst structure, and extends in a direction perpendicular to the longitudinal axis of the catalyst structure to essentially cover an end face (at either the inlet end or outlet end or both) of the catalyst structure with the support structure being secured on its periphery to the reactor wall. The strips or ribs making up the support structure are bonded together to form a unitary structure having cellular openings at least as large as the catalyst structure channel openings.

Abstract: This invention relates to an electrically-heated catalyst (EHC) and a start-up method of a gas turbine engine for combusting a hydrocarbonaceous fuel/oxygen-containing gas mixture using this electrically-heated catalyst. The catalytic structure is electrically heated to a predetermined temperature prior to start up of the turbine so as to reduce emissions during the start-up of the system. The EHC unit is a stacked or spirally wound layering of flat and corrugated thin metal foils which forms a plurality of axially-extending, longitudinal channels. The channels are preferably coated on one surface with a catalytic material, leaving the other surface free from the reaction to act as a heat sink, making the design an IHE (integral heat exchange) catalytic unit. The preferred embodiment of the EHC has electrodes outside of the fuel/oxygen-containing mixture stream, and uses electrical power having a predetermined voltage in the range of 100 to 200 volts to heat the unit.

Abstract: A gas turbine engine combustion chamber comprises a primary combustion zone and a secondary combustion zone downstream of the primary combustion zone. A catalytic combustion zone is arranged downstream of the secondary combustion zone and a homogeneous combustion zone is arranged downstream of the catalytic combustion zone. A pilot injector supplies fuel into the primary combustion zone. At least one primary premixing duct has a plurality of primary fuel injectors to supply a first mixture of fuel and air into the primary combustion zone. A secondary premixing duct has a plurality of secondary fuel injectors to supply a second mixture of fuel and air into the secondary combustion zone. A plurality of temperature sensors are arranged at the intake to the catalytic combustion zone and a processor controls the valves which adjust the supply of fuel the fuel injectors to ensure that the temperature at the intake to the catalytic combustion zone remains in a predetermined temperature range.

Abstract: A unique and useful dynamic control system has been invented for the control of a catalytic combustion system for use on a dynamic plant, preferably, a gas turbine engine. The dynamic control system facilitates the replacement of conventional flame combustion systems with catalytic combustion systems, which produce far less pollutants, by producing acceptable transient performance of the combustion system. A method of controlling the catalytic combustion process comprises the steps of calculating a mass flow of air introduced into the combustor, monitoring a flow of fuel to be combusted within the combustor, monitoring a temperature of the air introduced into the combustor, calculating an inlet temperature set point based on the mass flow and fuel flow, and controlling a pre-burner to heat the air based on the inlet temperature set point, the mass flow, and the temperature of the air. Further, the mass flow may be estimated based on ambient air temperature and pressure, and compressor speed.

Abstract: An efficient, high output, compact catalytic combustor that is low in combustion cost includes a combustion member having a front surface portion and a rear surface portion. The air-fuel mixture passing from the rear surface portion toward the front surface portion is combusted on the front surface portion. The combustion member is made of a material higher in thermal conductivity than alumina and includes a flame-holding unit for geometrically holding the flames formed on the surface of the combustion member. A catalyst oxide is carried on at least the front surface portion of the combustion member.

Abstract: This invention relates to an apparatus and method for increasing the reactivity of a fuel/air mixture prior to homogenous combustion of the mixture. More specifically, this invention is a pilot for a gas turbine combustor which utilizes the heat of combustion within the pilot to increase the reactivity of a portion of the fuel/air mixture utilized by the pilot.

Abstract: A catalytic combustion chamber is provided with at least two catalytic combustion zones arranged in flow series. In a first mode of operation fuel is supplied from first fuel injectors, positioned upstream of the first catalytic combustion zone, into the catalytic combustion chamber and is burnt in the first catalytic combustion zone in order to preheat the subsequent catalytic combustion zones. In the second mode of operation the supply of fuel to the first fuel injectors is reduced and fuel is supplied from second fuel injectors positioned between the first catalytic combustion zone and the second catalytic combustion zone into the space between the first catalytic combustion zone and the second catalytic combustion zone. This prevents the first catalytic zone becoming overheated, and reduces the possibility of the second and third catalytic combustion zones becoming overheated and allows the optimum catalyst to be selected for the first catalytic combustion zone.

Abstract: A cylindrical fuel reforming apparatus covered with a thermal insulating layer 16 comprises a fuel flow passage 1 contoured by a cylindrical contour wall 2 in its central axial direction and a reforming catalyst bed 3 in the middle of the flow passage for reforming gas to be reformed flowing from the upstream of the fuel flow passage 1 into a proper reformed gas. A cooling jacket 10 is arranged in the upstream of the reforming catalyst bed 3 so as to surround the fuel flow passage 1 and to be supplied with steam 11 for cooling the cylindrical contour wall 2. There are provided in the cylindrical contour wall 2 in the upstream of the reforming catalyst bed 3 a plurality of injection nozzles 15 communicating the cooling jacket 10 with the fuel flow passage 1 so that the steam 11 introduced into the cooling jacket 10 is allowed to flow into the fuel flow passage 1.

Abstract: Flashback of flames in premixed combustion systems is avoided by passing premixed fuel and air prior to combustion through a series of two or more nonaligned multi-channel monolith attached in series. The device is useful as a pre-ignition inhibitor, a detonation wave inhibitor and a flashback arrestor protector.

Abstract: A gas turbine and a burner to be used for all gas turbines for the catalytically induced combustion of a fuel, include a flow duct and a main burner having a fuel outlet. A catalytic supporting burner has a fuel outlet in the flow duct upstream of the fuel outlet of the main burner, as seen in the flow direction of the fuel, for stabilizing the main burner along with catalytic combustion of a pilot fuel stream. A marked reduction in nitrogen oxide emission is achieved by replacing a diffusion pilot flame with a catalytic supporting burner.

Abstract: A burner, particularly for a gas turbine, includes a catalytic combustion chamber and a performer/reformer (24). The combustion chamber has an essentially cylindrical extent in a flow direction of a fuel and a catalytically active coating (12) on a wall facing the fuel for oxidation of the fuel. A particularly low nitrogen oxide content of burner exhaust gas is achieved as a result of the catalytically induced combustion of the fuel. At the same time, in contrast to known primary measures for nitrogen oxide abatement, the flow resistance in the burner is not increased by the coating of the wall. Therefore, when the burner is used in a gas turbine, a particularly high efficiency together with a low nitrogen oxide emission can be achieved.

Abstract: In the case of a method for operating a gas turbine group, the gas turbine group essentially consists of a compressor (1), a combustion chamber (5), a turbine (2) and a generator (3). Fuel is mixed in a premixer (18) of the combustion chamber (5), prior to the combustion, with air compressed in the compressor (1), and subsequently burned in a combustion space (19).Compressed air, fed via an air line element (15) , is mixed with fuel fed via a fuel line element (16) and delivered to a reactor (10) having a catalytic coating. The air/fuel mixture is converted in the reactor (10) into a synthesis gas comprising hydrogen, carbon monoxide, residual air and residual fuel and this synthesis gas is injected into the zones of the combustion chamber (5) where the flame is stabilized.

Abstract: A gas turbine can achieve comparatively low emissions of nitrogen oxide. One disadvantage particularly of a catalytic combustion chamber is that, for example for natural gas, the ignition temperature necessary for combustion is in the region of about 400 .degree. C. The use of an auxiliary burner, which constitutes a disadvantageous source of nitrogen oxide, has therefore been heretofore unavoidable. In order to eliminate that disadvantage, a gas turbine for the combustion of a fuel gas, particularly with catalytic combustion of the fuel gas, includes a conduit system for drawing off part of the fuel gas, guiding it through a catalytic preforming stage to convert a hydrocarbon contained in the fuel gas into an alcohol and/or an aldehyde and subsequently feeding it to the fuel gas again in order to lower its ignition temperature. In this way, the comparatively easily igniting fuels alcohol and/or aldehyde are obtained from the fuel gas in the preforming stage.

Abstract: A combustor for a gas turbine includes a diffusion flame combustion zone, a catalytic combustion zone and a post-catalytic combustion zone. At start-up or low-load levels, fuel and compressor discharge air are supplied to the diffusion flame combustion zone to provide combustion products for the turbine. At mid-range operating conditions, the products of combustion from the diffusion flame combustion zone are mixed with additional hydrocarbon fuel for combustion in the presence of a catalyst in the catalytic combustion zone. Because the fuel/air mixture in the catalytic reactor bed is lean, the combustion reaction temperature is too low to produce thermal NO.sub.x. Under high-load conditions, a lean direct injection of fuel/air is provided in a post-catalytic combustion zone where auto ignition occurs with the reactions going to completion in the transition between the combustor and turbine section.

Abstract: A cylindrical fuel reforming apparatus covered with a thermal insulating layer 16 has a fuel flow passage 1 contoured by a cylindrical contour wall 2 in its central axial direction, and a reforming catalyst bed 3 is disposed in the middle of the flow passage for reforming gas, flowing from the upstream end of the fuel flow passage 1, into a proper reformed gas. A cooling jacket 10 is arranged upstream of the reforming catalyst bed 3 so as to surround the fuel flow passage 1 and the cooling jacket is supplied with steam 11 for cooling the cylindrical contour wall 2. There are provided in the cylindrical contour wall 2 upstream of the reforming catalyst bed 3 a plurality of injection nozzles 15 for effecting communication between the cooling jacket 10 and the fuel flow passage 1 so that the steam 11 introduced into the cooling jacket 10 is allowed to flow into the fuel flow passage 1.

Abstract: A combustor for a gas turbine includes a diffusion flame combustion zone, a catalytic combustion zone and a post-catalytic combustion zone. At start-up or low-load levels, fuel and compressor discharge air are supplied to the diffusion flame combustion zone to provide combustion products for the turbine. At mid-range operating conditions, the products of combustion from the diffusion flame combustion zone are mixed with additional hydrocarbon fuel for combustion in the presence of a catalyst in the catalytic combustion zone. Because the fuel/air mixture in the catalytic reactor bed is lean, the combustion reaction temperature is too low to produce thermal NO.sub.x. Under high-load conditions, a lean direct injection of fuel/air is provided in a post-catalytic combustion zone where auto ignition occurs with the reactions going to completion in the transition between the combustor and turbine section.

Abstract: The present invention relates to a catalytic combustion system comprising a casing (1) having an inlet (2) for an oxidizer such as air, several fuel injection means (3, 5; 7) intended for a multistage fuel injection, and at least a first monolithic element (4) that may be covered with a combustion catalyst and situated downstream from a first fuel injection means (3) in relation to the direction of progress of an air-fuel mixture in the system, said first injection means performing a partial fuel injection, and comprising at least a second monolithic element (6) situated downstream from a second injection means (5), said second monolithic element (6) being intended to stabilize the combustion. The second monolithic element (6) can be covered with a combustion catalyst.

Abstract: A hybrid electric drive system is provided having a heat engine, a catalytic converter, and an electric storage device having a state of charge. The drive system also includes a state of charge sensor and a device for heating the catalytic converter in response to the state of charge of the electric storage device being less than a predetermined state of charge.

Abstract: In a method for the operation of a power station installation which essentially comprises a compressor (4), a combustion unit and a turbine (12), the combustion unit comprising a conditioning stage for at least part of the combustion air and a combustion chamber, a portion (13a) of the compressed air (13) from the compressor (4) is passed through the conditioning stage and there first of all mixed with a quantity of fuel (14a). This mixture then passes into a generator (8), in which at least hydrogen is fractionated, this hydrogen then being used in the combustion chamber. The combustion chamber comprises a start-up burner (1), a catalytic stage (2) and a downstream second combustion stage (3). Both the air/fuel mixture (16a) fractionated in the generator (8) and the further compressor air (13) enter the combustion chamber, in which interdependent combustion occurs between the combustion units acting there, relative to the running up of the installation, for the purpose of minimizing pollutant emissions.

Abstract: The present invention is directed to a catalytic combustion system having a gas turbine engine recuperator and an annular catalytic combustor. The annular catalytic combustor includes a pre-burner/pre-mixer which functions as a pre-burner during startup and as a pre-mixer for the fuel and air during catalytic operation. This pre-burner/pre-mixer includes a plurality of primary tangential air-fuel venturis each having a fuel injector, and a plurality of secondary tangential air dilution holes. The pre-burner/pre-mixer is joined to the annular in-line catalytic canister by a transition section which includes a plurality of tertiary air dilution holes which introduce air radially into the transition section from the inner liner thereof. The in-line annular catalyst canister includes a large plurality of microlith catalyst elements positioned between support tings and held at the open end thereof by a plurality of support spokes.

Abstract: The conventional gas turbine combustor is improved by mounting a pilot flame producing torch in a wall of the combustor to project a flame into the combustor as a means of ignition. The torch preferably is a catalytic igniter which will operate over a wide range of air/fuel ratios.

Abstract: The conventional gas turbine combustor is improved by mounting a pilot flame producing torch in a wall of the combustor to project a flame into the combustor as a means of ignition. The torch preferably is a catalytic igniter which will operate over a wide range of air/fuel ratios.

Abstract: Gas phase combustion producing lower emissions in gas turbines is stabilized in a lean pre-mixed combustor, by flow of the fuel/air mixture through a catalyst which is heated by contact with recirculated, partially reacted combustion gases.

Abstract: Flashback of flames in premixed combustion systems is avoided by passing premixed fuel and air prior to combustion through a series of two or more close coupled nonaligned multi-channel monoliths.

Abstract: In a combustion chamber consisting of a first stage (1) and a second stage (2) arranged downstream in the direction of flow, a mixer (100) is arranged on the head side of the first stage (1), which mixer (100) forms a fuel/air mixture (19). Acting on the outflow side of this mixer (100) is a catalyzer (3) in which the said mixture (19) is completely burnt, the mixing being selected in such a way that an adiabatic flame temperature of between 800.degree. and 1100.degree. C. arises. Positioned on the outflow side of this catalyzer (3) are vortex generators (200) which provide for a turbulent flow. Downstream of these vortex generators (200), fuel (9) is injected and self-ignition initiated. A following jump (12) in cross section in the cross section of flow of the combustion chamber, which jump (12) in cross section forms the start of the second stage (2), provides a stabilizing backflow zone of the flame front (21).

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: The method of combusting lean fuel-air mixtures comprising the steps of:a. obtaining an admixture of fuel and air, said admixture having an adiabatic flame above about 900.degree. Kelvin;b. passing least a portion of said admixture into contact with one or more mesolith combustion catalysts operating at a temperature below the adiabatic flame temperature of said admixture thereby producing reaction products of incomplete combustion; andc. passing said reaction products to a thermal reaction chamber;thereby igniting and stabilizing combustion in said thermal reaction chamber.

Abstract: In a method of operating a low-pollution premixing burner (2) stabilized by means of vortex breakdown, in particular a burner of the double-cone type of construction, with gaseous fuels (4, 10), the main fuel gas (4) being fed to the burner (2) via a main gas tube (3) connected in one piece to the burner (2) and the pilot gas (10) being fed to the burner (2) near the axis of the latter via a separate feed line (9) by means of an exchangeably inserted fuel lance (8), and the pilot gas (10) being mixed inside the fuel lance (8) with air (17) fed from a plenum (16) outside the burner hood (6), the pilot-gas/air mixture (25) is fed to a catalyzer (21) arranged inside the fuel lance (8) at the tip of the burner (2) and is ignited and burnt there. The hot gas flow is then mixed with the colder main burner flow in the burner interior space (14).

Abstract: A combustor for supporting the catalytic combustion of gaseous carbonaceous fuel contains a catalyst zone in which is disposed a catalyst body comprising at least one catalyst member, a separator zone comprising a separator body and a downstream zone where homogeneous combustion occurs. The catalyst member contains a carrier and a catalyst material deposited thereon. The catalyst body may, optionally, contain additional catalyst members downstream of the at least one catalyst member. The separator body contains a carrier-type monolith containing ceramic fibers in a matrix. One of the optional additional catalyst members may also contain such a monolith on which the catalyst composition is disposed.

Abstract: This invention is an improved catalyst structure and its use in highly exothermic processes like catalytic combustion. This improved catalyst structure employs integral heat exchange in an array of longitudinally disposed adjacent reaction passage-ways or channels, which are either catalyst-coated or catalyst-free, wherein the configuration of the catalyst-coated channels differs from the non-catalyst channels such that, when applied in exothermic reaction processes, such as catalytic combustion, the desired reaction is promoted in the catalytic channels and substantially limited in the non-catalyst channels. The invention further comprises an improved reaction system and process for combustion of a fuel wherein catalytic combustion using a catalyst structure employing integral heat exchange, preferably the improved structures of the invention, affords a partially-combusted, gaseous product which is passed to a homogeneous combustion zone where complete combustion is promoted by means of a flameholder.

Abstract: This invention is an improved catalyst structure and its use in highly exothermic processes like catalytic combustion. This improved catalyst structure employs integral heat exchange in an array of longitudinally disposed, adjacent reaction passage-ways or channels, which are either catalyst-coated or catalyst-free, wherein the configuration of the catalyst-coated channels differs from the non-catalyst channels such that, when applied in exothermic reaction processes, such as catalytic combustion, the desired reaction is promoted in the catalytic channels and substantially limited in the non-catalyst channels.

Abstract: A support structure for securing a catalyst structure wherein a combustion reactor has a plurality of hollow, internally cooled, elongated support members which are secured to the combustion reactor and which abut the catalyst structure to limit the axial movement of the catalytic structure. The support structure is in fluid communication with a cooling medium which maintains the support structure at a temperature at which its strength properties are retained.

Abstract: Carbon monoxide and unburned hydrocarbon burnout in gas turbine combustors is promoted by a combustor liner having a plurality of vortex generating members or ridges formed therein. The liner includes a substrate having an inner surface and a thermal barrier coating disposed on the inner surface. The vortex generating ridges are formed in the thermal barrier coating and extend transverse to the mean direction of flow through the liner. The thermal barrier coating is capped with a catalytic material which enhances carbon monoxide and unburned hydrocarbon oxidation. The ridges are defined by raised portions of the catalytic material and are of sufficient height to cause mixing between the hot flame products and the cool incompletely-burned flow along the liner wall. Alternatively, the ridges can be defined by forming corrugations in the substrate and disposing a uniform catalytically-active thermal barrier coating over the corrugated substrate.