A staged, lean pre-mix radiant wall burner having an internal staged fuel discharge tip and an internal flow diverter, and a method of using the radiant wall burner, which allow the combustion of a high hydrogen content fuel without the occurrence of flashbacks and which also provide reduced NO.sub.x emissions and allow a closer spacing of the burners when installed in a wall, floor, or ceiling of a fired heater in a multiple burner arrangement.

A burner includes a primary input port configured to receive hydrogen-containing fuel and primary oxygen-containing gas. A fuel-distribution element comprises a plurality of distribution openings. A flashback arrestor element comprises a plurality of flashback arrestor element channels with a mean width that is smaller than a critical flame quench diameter of the hydrogen-containing fuel. A burner housing can be provided, and the burner housing, fuel distribution element, and flashback arrestor element can be made of plastic and by 3D printing. A combustion element includes a plurality of combustion element apertures configured to cause the burner to produce a flame and/or infrared heat, wherein a mean width of the combustion element apertures is 2-4 times larger than the mean width of the flashback arrestor element channels. A method of heating and a heating system are also disclosed. The combustion element can also be equipped for resistive heating.

A burner includes a primary input port configured to receive hydrogen-containing fuel and primary oxygen-containing gas. A fuel-distribution element comprises a plurality of distribution openings. A flashback arrestor element comprises a plurality of flashback arrestor element channels with a mean width that is smaller than a critical flame quench diameter of the hydrogen-containing fuel. A burner housing can be provided, and the burner housing, fuel distribution element, and flashback arrestor element can be made of plastic and by 3D printing. A combustion element includes a plurality of combustion element apertures configured to cause the burner to produce a flame and/or infrared heat, wherein a mean width of the combustion element apertures is 2-4 times larger than the mean width of the flashback arrestor element channels. A method of heating and a heating system are also disclosed. The combustion element can also be equipped for resistive heating.

An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

A fuel supply system for an aircraft engine, comprises a gaseous fuel source and a fuel nozzle. The fuel nozzle includes a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler is fluidly connected to the gaseous fuel source for directing gaseous fuel to a combustor of the aircraft engine. The fuel swirler defines a gaseous fuel path extending from a fuel inlet to a fuel outlet. The gaseous fuel path includes a plurality of discrete apertures distributed around a circumference of the fuel swirler, each of the plurality of discrete apertures having a cross-sectional area selected to prevent a flame from propagating in an upstream direction through the gaseous fuel path towards the gaseous fuel source.

An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air into a combustion chamber is provided. The injection nozzle includes an inlet portion into which fuel and compressed air are introduced, an outlet portion disposed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion disposed between the inlet portion and the outlet portion and connected obliquely to each of the inlet portion and outlet portion, wherein each of the inlet portion, the outlet portion, and the intermediate portion has a prismatic shape.

An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air into a combustion chamber is provided. The injection nozzle includes an inlet portion into which fuel and compressed air are introduced, an outlet portion disposed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion disposed between the inlet portion and the outlet portion and connected obliquely to each of the inlet portion and outlet portion, wherein each of the inlet portion, the outlet portion, and the intermediate portion has a prismatic shape.

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.

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 low-concentration gas differential combustion device includes a low-concentration gas super-cooling dehydration and demisting device, a gas pretreatment device, a burner, a long-term burning open fire device, a high-energy self-heat dispersion rapid ignition device, a combustion chamber, and a waste-heat utilization device. With the low-concentration gas differential combustion device, the problems of gas escaping, forced direct emission, low heat extraction efficiency, concentration over-limit explosions, increase in equipment volume and increase in investment caused by the reversal process in the existing ventilation air oxidation technology, and the problems of narrow gas adaptation concentration range, small adaptive concentration and pressure change amplitude, poor combustion temperature adjustability, high NOx content, high shutdown rate, and low gas utilization rate in the low-concentration gas internal combustion engine power generation technology are solved.