According to an embodiment, a burner system includes a pilot burner disposed in a furnace at a distal position along a main fuel and combustion air flow axis, and one or more main fuel nozzles disposed at a proximal position along the main fuel and combustion air flow axis. The pilot burner is configured to support a pilot flame and the one or more main fuel nozzles are configured to support a main flame in contact with the pilot flame. The pilot burner is disposed to cause the main fuel and combustion air to be ignited by the pilot flame. The pilot burner may support a diffusion pilot flame or may include a premixing apparatus to support a pre-mixed flame.

A gas burner membrane is provided. The gas burner membrane comprises a plurality of first layers, each first layer comprises at least one inlet formed therein for receiving a combustible gas mixture, and a plurality of second layers. Successive first layers are separated by a second layer, and at least one outlet is formed between successive first layers.

A fuel nozzle includes a shroud; an injection cylinder surrounded by the shroud and configured to supply fuel to a combustion chamber; a swirler disposed between the injection cylinder and the shroud; and a porous disk disposed downstream of the swirler to surround an outer peripheral surface of the injection cylinder in order to prevent a flashback phenomenon occurring due to a reduction in pressure around the swirler. The porous disk includes a disk body to block a flame produced in the combustion chamber, and a plurality of flow holes are formed in the disk body through which the fuel flows. It is possible to prevent flashback by installing the porous disk downstream of the swirler, and to impart linearity and a swirling effect to the fuel passing through the fuel nozzle by forming variously configured flow holes in the porous disk.

Horizontal immersion tube boilers include a plurality of burner nozzles positioned in substantial alignment with a respective plurality of boiler tubes. Fuel-air mixture directed through the burner nozzles are ignited by a pilot flame system positioned proximate to the burner nozzles within a combustion chamber. The burner nozzles and pilot flame system receive air from a secondary air manifold having inlets that provide secondary air into the combustion chamber. The flames extending from the burner nozzles are directed into the respective boiler tubes, which exchange heat from the flame into water within a boiler shell. The secondary air inlets direct air around the burner nozzles and toward the boiler tubes, creating an air blanket around each burner nozzle for reducing turbulence and guide the flames into their respective boiler tubes. An improved flame arrestor within the nozzle prevents flame back-flow when modulating to lower firing rates.

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.

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.

A burner combustion system comprising: a burner casing comprising a first inlet and a first outlet; a combustion substrate disposed in the burner casing, wherein the combustion substrate is porous, and wherein the burner casing first outlet is disposed on an exterior of the combustion substrate; an inlet conduit disposed in the burner casing, the conduit comprising a second inlet and second outlet, wherein the second inlet of the conduit is outside the burner casing, and, wherein the second outlet of the conduit is connected to the burner casing first inlet, and wherein the combustion substrate may have a flat shape and wherein the burner combustion system may further comprise a baffle.

A fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine includes a spray nozzle, a gaseous carrier, a fuel mixing and evaporation chamber and an injector nozzle. During operation, both a liquid fuel and the gaseous carrier are supplied to the fuel mixing and evaporation chamber of the injector through the spray nozzle, where they are mixed and evaporated as a result of elevated temperature, and the mixture reaches the combustion chamber. The gaseous carrier is air or, flue gas, at elevated pressure and temperature and having a composition that prevents the initiation of flame combustion, and the gaseous carrier has an oxygen content low enough to prevent the initiation of combustion, even under conditions of elevated pressure and temperature.

A furnace includes a gas burner exposed to a heat-exchange tube. An inducer is fluidly coupled to the heat-exchange tube and configured to induce draft air through the heat-exchange tube. A regulator is fluidly coupled to the gas burner. A rollout shield is disposed adjacent to the gas burner. A rollout switch is disposed in the rollout shield. The rollout switch is electrically coupled to the regulator. At least one vent is formed through the rollout shield adjacent to the rollout switch. The vent provides a path for a rollout flame to the rollout switch. The at least one vent is disposed on at least two sides of the rollout switch.