A trapped vortex combustor includes a refractory combustor body defining a combustion volume aligned to receive an air and fuel mixture from an air and fuel source. The trapped vortex combustor includes a trapped vortex channel arranged circumferential to a portion of the combustion volume and/or arranged at or adjacent to a center of the combustion volume. The trapped vortex channel is configured to hold a trapped vortex combustion reaction to provide ignition to the air and fuel mixture. The trapped vortex combustor includes a center body supported near or within the combustion volume.

A double swirl burner including an annular air nozzle, an annular fuel nozzle coaxially disposed within the annular air nozzle, and a central air nozzle coaxially disposed within the annular fuel nozzle. An annular air nozzle may include at least one first inlet port on a peripheral wall of the annular air nozzle, where the first inlet port may be configured to allow for tangentially injecting a first air stream into the annular air nozzle. A first air stream may be tangent to a circular cross-section of the exemplary annular air nozzle, and a first axial inlet that may be configured to allow for axially injecting a second air stream into the annular air nozzle along a centerline of the annular air nozzle.

A combustor having an ion transport membrane therein and an adjustable swirler, which is mechanically connected at an inlet of a combustion zone of the combustor; a combustion system comprising the combustor, a feedback control system adapted to adjust swirler blades of the combustor based on a compositional variation of a fuel stream, and a plurality of feedback control systems to control operational variables within the combustor for an efficient oxy-combustion; and a process for combusting a fuel stream via the combustion system. Various embodiments of the combustor, the combustion system, and the process for combusting the fuel stream are disclosed.

A combustor having an ion transport membrane therein and an adjustable swirler, which is mechanically connected at an inlet of a combustion zone of the combustor; a combustion system comprising the combustor, a feedback control system adapted to adjust swirler blades of the combustor based on a compositional variation of a fuel stream, and a plurality of feedback control systems to control operational variables within the combustor for an efficient oxy-combustion; and a process for combusting a fuel stream via the combustion system. Various embodiments of the combustor, the combustion system, and the process for combusting the fuel stream are disclosed.

A cement kiln burner includes a plurality of columnar or cylindrical flow channels. Outlets of the respective flow channels are disposed on substantially the same plane. A wind velocity adjusting member capable of changing a cross-sectional area at an outlet-side tip-end portion of the flow channel by moving along an axial direction of the flow channel in a state of being in contact with any one of an inner peripheral wall and an outer peripheral wall of the flow channel and not in contact with the other is provided inside at least one of the flow channels.

A burner apparatus and process are described. The burner apparatus includes an inlet chamber in communication with a combustion chamber. The combustion chamber has a cylindrical shape defining a longitudinal axis and a radial direction orthogonal to the longitudinal axis. The combustion chamber has an upstream end and a downstream end, and an air inlet is disposed in the inlet chamber. A pilot, a fuel gas inlet, and a refractory material are disposed in the combustion chamber downstream of the air inlet. A mixed gas inlet is positioned downstream of the fuel gas inlet and the pilot in the combustion chamber. The mixed gas inlet includes a manifold having an inlet, a body, and a plurality of nozzles.

A combustor having an ion transport membrane therein and an adjustable swirler, which is mechanically connected at an inlet of a combustion zone of the combustor; a combustion system comprising the combustor, a feedback control system adapted to adjust swirler blades of the combustor based on a compositional variation of a fuel stream, and a plurality of feedback control systems to control operational variables within the combustor for an efficient oxy-combustion; and a process for combusting a fuel stream via the combustion system. Various embodiments of the combustor, the combustion system, and the process for combusting the fuel stream are disclosed.

The present invention relates to an over fire air arrangement for a furnace (1), the furnace (1) having opposing first wall (4) and second wall (6) and opposing first side wall (5) and second side wall (7) between the first and second walls (4, 6) for forming a furnace enclosure (2). The over fire air arrangement comprising at least one first over fire air port (20) provided to the first wall (4) for supplying a first over fire air flow (40) into the furnace (1) and at least one first additional over fire air port (50) provided to at least one of the first and second side walls (5, 7) in the vicinity of the first wall (4), the at least one first additional over fire air port (50) being arranged to supplying a first additional over fire air flow (60) into the furnace (1) transversely to the first over fire air flow (40).

A lobe lance is disclosed for a gas turbine combustor which includes a plurality of N (N4) lobe fingers, each configured as a streamlined body with two lateral surfaces. A plurality of nozzles for injecting a gaseous and/or liquid fuel mixed with air are provided whereby lobes running between the nozzles are provided for improving the mixing quality and reducing pressure loss in said combustor. The lobes of each lobe finger have one of two opposite orientations with respect to said flow direction, and the lobes of all lobe fingers follow a predetermined pattern of orientation across the lobe fingers at least one pair of neighboring lobe fingers has the same lobe orientation resulting in a grouped lobe arrangement ( . . . LL . . . or . . . RR . . . ) such that at least two of the vortices generated by the lobe shape downstream of the lobe fingers combine.

A swirler includes a swirler body defining a longitudinal axis. A stack of swirler plates is assembled to the swirler body stacked in a direction along the longitudinal axis. Each of the swirl plates defines a vane portion. The swirler plates are mounted rotated circumferentially about the longitudinal axis relative to neighboring ones of the swirler plates so the vane portions form a swirler vane.