Abstract:
A burner has a port facing into a combustion chamber along an axis. A secondary fuel injector structure has secondary fuel injection ports that face into the combustion chamber at locations spaced radially outward from the burner port. A tertiary fuel injector structure has tertiary fuel injection ports that face into the combustion chamber in directions perpendicular to the axis at locations spaced axially downstream from the secondary fuel injection ports.
Abstract:
The invention relates to equipment for heating gas (23) in connection with continuous sintering in gas channels (2, 3, 4) placed above a strand (1), the gas channels comprising at least a wall (6) and at least two gas units (24, 25), the gas coming from the gas units being in contact with the material on the strand (1), whereby at least one burner unit (5, 27, 28, 29) is arranged in at least one of the gas channels (2, 3, 4), being arranged as part of the gas channel, the burner unit comprising at least one separate combustion space (7) arranged on the wall (6) of the gas channel. The invention also relates to a method for heating the gas.
Abstract:
The invention relates to a flat-flame vault burner (10) suitable for being installed in a vault (21) which delimits the combustion chamber (20) of a steel heating furnace, the burner (10) comprising a main metallic hollow cylindrical body (12) , a single duct (13) for the conveyance of fuel gas concentric to the main body (12) , and a central internal nozzle (14) for the injection of a fuel gas. Said burner also comprises at least two nozzles (17) outside said main body (12) for the injection of fuel into the combustion chamber (20) .
Abstract:
L'invention concerne un brûleur pour four à clinker pour la combustion d'un combustible liquide et/ou gazeux comprenant un corps de brûleur (1), un canal longitudinal central d'injection en combustible liquide (6), un premier conduit longitudinal d'injection de combustible gazeux basse pression (7), un premier conduit longitudinal d'injection d'air à flux radial (8), un second conduit longitudinal d'injection de combustible gazeux haute pression (9) et un second conduit longitudinal d'injection d'air à flux axial (10). Selon l'invention, dans la tête d'injection (3), le premier conduit d'injection de combustible gazeux (7) est un conduit disposé autour du canal central (6), le premier conduit d'injection d'air (8) est un conduit disposé autour du premier conduit d'injection de combustible gazeux (7), le second conduit d'injection de combustible gazeux (9) est un conduit disposé autour du premier conduit d'injection d'air (8), et le second conduit d'injection d'air (10) est un conduit disposé autour du second conduit d'injection de combustible gazeux (9).
Abstract:
A burner has a port facing into a combustion chamber along an axis. A secondary fuel injector structure has secondary fuel injection ports that face into the combustion chamber at locations spaced radially outward from the burner port. A tertiary fuel injector structure has tertiary fuel injection ports that face into the combustion chamber in directions perpendicular to the axis at locations spaced axially downstream from the secondary fuel injection ports.
Abstract:
A burner arrangement includes a venturi cluster including a plurality of venturis arranged for parallel flow. The multi venturi arrangement utilizing pressurized fuel as the inducing fluid to induce a flow of air enables the provision of an ultra fuel lean premix of fuel and air. A central burner tube which extends outwardly beyond the delivery end of a primary burner tip and mounts a relatively small capacity nozzle at a substantial distance from the delivery end of the burner tip enabling the ultra fuel lean mixture to expand and slow down such that its linear speed does not exceed the flame speed of the mixture prior to by the flame of the spaced nozzle. A deflector may be positioned adjacent the nozzle to assist in stabilizing the flame after the expansion and slowing process has been completed.
Abstract:
The method includes, providing a series of lower compartments (208) for introducing therethrough air and fuel into the combustion chamber. At least one upper compartment (210) is disposed above the topmost compartment (208TM) at a relative disposition to the topmost compartment (208TM) in a spacing range between a contiguous disposition to a more spaced disposition which is no more than twice the average spacing between any given compartment and an adjacent compartment. Air is injected from the at least one upper compartment (210) generally in opposition to the swirling fireball (RB) along a direction which is offset to the other side of the diagonal (DD) in a manner such that the injected air promotes the evolution of the swirling fireball (RB) into an upward flow in the top half of the furnace (204) characterized by portions thereof flowing upward at differing vertical velocities.
Abstract:
The invention relates to a hybrid burner (1) having a central pilot burner (3) and a main burner (5) surrounding the pilot burner (3). The pilot burner (3) is staggered backwards in relation to the main burner (5) in such a way staged combustion occurs.
Abstract:
A round burner capable of being operated with reduced CO and NOx emissions includes a venturi tube (22) positioned to direct a flow of air through the burner and into a combustion zone (14) in a combustion chamber (16) through an entrance in a wall (20) of the combustion chamber. The venturi tube has inlet (25) and outlet (26) ends and a throat (24). The burner may include a duct system (48) that includes an inlet (52) disposed in fluid communication with the combustion zone and an outlet (50) disposed in fluid communication with the venturi tube adjacent the throat thereof. Alternatively or cumulatively, the burner may include a fuel gas injector arrangement (58) having an injector nozzle (60) extending through the wall at a location adjacent the combustion zone. Also disclosed is a method for operating the burner to reduce CO and NOx emissions.
Abstract:
A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages for pre-mixing primary fuel and air to be supplied to the primary combustion zone. Each of the pre-mixing passages has a circumferential array of swirl vanes. A plurality of primary fuel tube assemblies extend through both pre-mixing passages, with each primary fuel tube assembly located between a pair of swirl vanes. Each primary fuel tube assembly is comprised of two tubular members. The first member supplies fuel to the first pre-mixing passage, while the second member, which extends through the first member, supplies fuel to the second pre-mixing passage. An annular fuel manifold is divided into first and second chambers by a circumferentially extending baffle. The proximal end of the first member is attached to the manifold itself while the proximal end of the second member is attached to the baffle. The distal end of the first member is attached directly to the second member at around its mid-point. The inlets of the first and second members are in flow communication with the first and second manifold chambers, respectively. Control valves separately regulate the flow of fuel to the two chambers and, therefore, to the two members of the fuel tube assemblies, thereby allowing the flow of fuel to the first and second pre-mixing passages to be separately controlled.