The invention relates to a premixing method for premixing fuel with air prior to the combustion of a fuel/air mixture to allow burners to be operated at high output and with a good load variation range with stable and reliable operation and low NOx emissions. The method comprises: a) creating a rich fuel/air mixture with a fuel/air ratio above an ignitable fuel/air ratio, b) supplying air to the rich fuel/air mixture to obtain an ignitable fuel/air mixture, and c) swirling the ignitable fuel/air mixture obtained in step a) or b). The invention further relates to a premixing device for performing the method.

A system for use with a fired vessel of production/separators or dehydration equipment that includes a metal box, a main burner, a pilot burner, and a flame arrestor. The main burner and the pilot burner are within the metal box and the first flame arrestor is connected to the metal box.

The present disclosure provides for improving flame propagation in a combustor, particularly in a combustor for use in a power production system and method. At least one stream being passed into the combustor (e.g., a fuel, an oxidant, a diluent, a coolant, a working fluid, water, or steam) can be independently heated to a temperature that is about the autoignition temperature of the fuel or greater. Further, flame stabilization, including promoting ignition, can be improved as described herein through controlled addition of one or more NOx species into the combustor or combustion chamber.

The present disclosure provides for improving flame propagation in a combustor, particularly in a combustor for use in a power production system and method. At least one stream being passed into the combustor (e.g., a fuel, an oxidant, a diluent, a coolant, a working fluid, water, or steam) can be independently heated to a temperature that is about the autoignition temperature of the fuel or greater. Further, flame stabilization, including promoting ignition, can be improved as described herein through controlled addition of one or more NOx species into the combustor or combustion chamber.

A burner and methods of using the burner. The burner utilizes bypass conduits to separate the combustion air that is passed to the primary combustion zone into two or more portions. The two portions are injected into the primary combustion zone at different points so as to reduce the flame temperature. A NOx reducing medium may be mixed with the combustion air in the bypass conduit. The NOx reducing medium may be flue gases from a combustion chamber having the primary combustion zone.

A system and method uses a combustor and gasifier to burn a primary dirty fuel, such as waste materials or high-polluting fossil fuels, and a secondary low-polluting fuel, such as biomass fuels, for co-generation of electricity while reducing harmful emissions. The primary fuel is burned at least partially through the use of an improved burner tube. Dirty exhaust from a combustor is scrubbed by a gasifier by reforming the combustors exhaust gases into a clean-burning producer gas (syn-gas). The secondary fuel and oxygen are added to the dirty exhaust in the gaslifier to create gas, char and ash. The gas powers an engine or turbine that turns a generator, or a boiler, Stirling engine, or Organic Rankine Cycle power plant, and releases a cleaner exhaust.

A multi-fueled impulse initiator that includes a fuel source equipped with a control valve, an air source equipped with a control valve, a removable air flow insert having opposing inlet and outlet faces, an air expansion chamber fluidly connected to both the air source and the inlet face of the removable air flow insert, and an igniter assembly having a sparking tip. The removable air flow insert includes channels traversing from the inlet face to the outlet face of the air flow insert.

An injection system includes a radial swirler defining an axis and including a plurality of radial swirl vanes configured to direct a radially inward flow of compressor discharge air entering swirler inlets between the radial swirl vanes in a swirling direction around the axis. The radial swirler includes an outlet oriented in an axial direction to direct swirling compressor discharge air in an axial direction. An injector ring is included radially outward from of the swirler inlets. The fuel injector ring is aligned with the axis and includes a plurality of injection orifices directed towards the swirler inlets for injecting fuel into the radial swirler.

In a combustor including a plurality of combustion nozzles, and a gas turbine including the same, fuel can be uniformly mixed with compressed air for each combustion nozzle. The combustor includes a plurality of combustion nozzles arranged in a nozzle casing, and each combustion nozzle includes a nozzle shroud for taking in compressed air; an injection cylinder concentrically disposed in the nozzle shroud and configured to be supplied with fuel for mixing with the compressed air; and a plurality of swirlers circumferentially arranged around the injection cylinder and configured to inject the fuel from the injection cylinder into the shroud. The plurality of swirlers divide an interior space of the nozzle shroud into a plurality of fluid flow regions, and include a pair of adjacent swirlers spaced apart from each other by a circumferential distance that differs from a circumferential distance between another pair of adjacent swirlers.

The premixing device includes a first and a second venturi having a pressure reducing portion for air, and a gas supply passage for supplying fuel gas to the venturis, and generates air-fuel mixture by mixing fuel gas with air flowing in the venturi by using a fan and supplies the air-fuel mixture to a burner. A first and a second nozzles for reducing pressure of fuel gas are disposed in the gas supply passage, and the first and the second nozzles are formed in the same nozzle shape as the pressure reducing portion of the first and the second venturis.