An internal combustion burner including a combustion chamber supplied with fuel and with oxidant and at least two combustion devices supplied with oxidant and with fuel. Combining two combustion devices of distinct configurations, which respectively generate two distinct types of flames with a system for cooling the walls of the burner by introducing air along the walls, makes it possible to obtain a burner that supplies a combustion gas temperature of up to 1700 C., while at the same time being easily cooled and occupying very little space so that it can, for example, be housed in an existing installation used in the manufacture of rock wool or glass wool.

In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage therethrough having an outlet in a first plane. A second fuel/air mixer assembly comprises a second fuel injector and a plurality of second mixer elements, and each second mixer element defines an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.

A device to induce a fire tornado with a swirling vortex of flames rising into the air. The device includes a flame element and a series of nozzles that deliver the flow of air into the area of the flame element. The air flow is such that eddy currents are created, which along with the heat of the flames, results in inducing the fire tornado.

A swirler for a burner of a gas turbine engine, having a plurality of vanes extending from an outer radius of the swirler to an inner radius of the swirler and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel, located essentially at an outer radius of the swirler, to a radially inner end of the mixing channel, located essentially at an inner radius of the swirler, at least one main injector for providing fuel for a main flame of the gas turbine engine, the main injector arranged at and/or in at least one of the mixing channels, and at least one pilot injector for providing fuel for a pilot flame of the gas turbine engine. A burner of a gas turbine engine and a gas turbine engine include the swirler.

The invention relates to a stove that operates using liquid fuel of alcohol and water that can be diluted to concentrations as low as 50% alcohol by volume.

A vortex flame device includes a flow guiding mechanism integrated from two half flow guiding mechanisms and with which a fuel reservoir is adapted to connect. Each half flow guiding mechanism includes a wall. The walls are engaged together in a manner movable relative to each other, and each includes a plurality of vanes mounted thereon. Two adjacent vanes include a spiral air passage formed therebetween and in communication with the channel. The two half flow guiding mechanisms selectively change to a first position including a gap between free ends thereof and a second position with the free ends thereof joined. Further, a combustion head is disposed in the channel and has at least one outlet hole that fuel of the connected fuel reservoir flows through. Further, a shield is disposed above the flow guiding mechanism.

A combustion chamber wall for a combustion chamber assembly (100) of a heating device (1) in a vehicle is arranged to form a combustion chamber (8). It comprises a cylindrical circumferential wall (44), which defines a central axis (C) extending in the axial direction (X). At least one structure (22) for introducing an oxidizer into the combustion chamber (8) is formed in the circumferential wall (44). The structure comprises a cutout recess (52) formed in the circumferential wall, which forms an introduction opening, and a worked section (54) formed in the circumferential wall (44), which is deformed in a radial direction (R) towards the central axis (C). In a circumferential direction (P) of the circumferential wall (44), the cutout recess (52) directly adjoins the worked section (52) which is deformed towards the central axis (C).

A fuel injection assembly for a combustor of a gas turbine includes a fuel injector configured to couple to an outer sleeve of the combustor. A boss is configured to couple to a combustion liner of the combustor at a position axially and circumferentially aligned with the fuel injector. An insert is removably coupled to the boss. The insert includes a flange portion and an annular wall portion extending from the flange portion and defining a mixing channel. The insert defines a plurality of partial direct injectors spaced apart from one another and disposed about the mixing channel. A combustor including such a fuel injection assembly is also provided.

A cylindrical burner apparatus and method which produce low noise levels and are not dependent upon a blower, or natural draft, for providing combustion air flow. A flow of combustion air is induced into a rearward end of a burner tube and a swirling flame is produced in the tube by discharging a gas fuel from a plurality of discharge ports located in the tube.

A burner apparatus and a method of operating the burner apparatus can include a housing and an array maintained by the housing. The burner apparatus can function according to an air staged mode of operation. The array can include a group of low-capacity fuel swirlers and low-capacity air swirlers, wherein individual or groups of the low-capacity fuel swirlers and/or low-capacity air swirlers among the array can be turned on or off based on a required burner capacity.