A method and apparatus for combustion of fuel in a combustion chamber with a hydraulic diameter D. Fuel and a primary oxidant are introduced via a burner lance into the combustion chamber, having a certain mean velocity u1 at entry, and a secondary oxidant with a mean velocity of u2 is introduced into the combustion chamber. The burner lance has a position p that has a distance Id1I defined as the smallest distance between p and a combustion chamber centerline.

Embodiments of the present invention include high-temperature staged recirculating burners and radiant tube burner assemblies that provide high efficiency, low NOx and CO emissions, and uniform temperature characteristics. One such staged recirculating burner includes a combustion tube having inside and outside helical fins forming opposing spiral pathways for combustion gases and products of combustion, a combustion nozzle coupled to the combustion tube, a gas tube running axially into the combustion tube, and a staging gas nozzle coupled to the gas tube, where the staging gas nozzle includes radial exit holes into the combustion tube and an axial gas staging tube extending into the combustion nozzle to stage combustion.

High turndown ratio gaseous fuel burner nozzles and the control thereof are provided. High turndown ratio gaseous fuel burner nozzles include a mechanically adjustable nozzle port, such as in the form of an iris port, for expanded turndown control. A nozzle extension longitudinally extending from the mechanical adjustable nozzle port can be included to assist in shaping the flow of combustible gas from the nozzle port. A laminar flow insert can be housed within the nozzle extension to assist in producing laminar flow of the combustible gas flowing therethrough. A burner nozzle controller in control communication with the mechanically adjustable nozzle port can adjust the size of the nozzle port to selectively maintain exit velocity of the gaseous fuel from the nozzle port for one or more of combustion stability and flame stability.

Systems and methods are disclosed that include providing a cooking system that comprises a burner assembly and a heat exchanger, the burner assembly having a high velocity burner configured to provide the necessary high velocity, volumetric flowrate through the heat exchanger having a first fluid circuit having a plurality of compactly-arranged tubes disposed perpendicularly and interstitially to a second fluid circuit having a plurality of compactly-arranged tubes, and the burner assembly also having a low velocity burner configured to significantly reduce and/or substantially eliminate “lift off” that could result from operation of only the high velocity burner.

A torch igniter system for a combustor of a gas turbine engine includes a housing defining a combustion chamber, an ignition source disposed at least partially in the combustion chamber, a fuel injector, a first fluid path connecting a first fuel source to the fuel injector, a second fluid path connecting an air source to the fuel injector, and a third fluid path connecting a second fuel source to the combustion chamber. The fuel injector is configured to inject fuel, air, or a mixture of fuel and air into the combustion chamber and to impinge on the ignition source.

An embodiment of a system for measuring fuel ignition within a torch igniter for a combustor in a gas turbine engine includes a housing surrounding and defining a combustion chamber, a first glow plug received through the housing, and control circuitry. An innermost end of the first glow plug extends into the combustion chamber while an outermost end opposite the innermost end extends away from the combustion chamber. The control circuitry is connected to the outermost end of the glow plug and is configured to measure a temperature of the innermost end of the glow plug based on electrical resistance of the glow plug. The control circuitry is further configured to determine an operational parameter of the torch igniter based on the temperature.

An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.

In a burner of an embodiment, a torch part includes: a torch combustor liner that is provided in a torch part casing and burns a fuel and an oxidant; a torch fuel supply part that supplies a fuel; a torch oxidant supply part that supplies an oxidant; an ignition device that ignites a fuel-air mixture; and a combustion gas pipe that is arranged at the center of the torch part and leads a combustion gas in the torch combustor liner to one end side of the torch part. A main fuel-main oxidant supply part includes: a main fuel supply passage formed in an annular shape on an outer periphery of the torch part; and a main oxidant supply passage formed in an annular shape on an outer periphery of the main fuel supply passage.

Embodiments of the present invention include high-temperature staged recirculating burners and radiant tube burner assemblies that provide high efficiency, low NOx and CO emissions, and uniform temperature characteristics. One such staged recirculating burner includes a combustion tube having inside and outside helical fins forming opposing spiral pathways for combustion gases and products of combustion, a combustion nozzle coupled to the combustion tube, a gas tube running axially into the combustion tube, and a staging gas nozzle coupled to the gas tube, where the staging gas nozzle includes radial exit holes into the combustion tube and an axial gas staging tube extending into the combustion nozzle to stage combustion.

The invention concerns a pulverized solid fuel, in particular coal, nozzle (10) comprising an inlet opening (12) for receiving a stream of coal/air mixture (16) and an outlet opening (14) for discharging said stream (16) into a burner. The inlet opening (12) and the outlet opening (14) are fluidically connected by a flow section (18), and a flow cross section (20) of the flow section (18) varies along a flow direction (22) of the stream of coal/air mixture (16). The flow section (18) comprises a flow constriction (24) with a, preferentially globally, minimal flow cross section (26). The flow constriction (24) is fluidically located between the inlet opening (12) and the outlet opening (14) and the flow section (18) has a flow cross section (20) that, in particular continuously, increases from the flow constriction (24) to the outlet opening (14).