Abstract: A premixing burner (X) which consists essentially of at least two hollow partial bodies (1, 2), which are positioned one above the other and whose center lines (1b, 2b) extend offset relative to one another in the longitudinal direction of the partial bodies (1, 2), is employed for hot gas generation, for example in a firing plant. Due to this offset, tangential inlet slots (21, 22) respectively occur through which a combustion airflow (15) flows into the internal space (14) of the premixing burner (X). Venturi mixers (32) with fuel nozzles (36), through which a fuel (31) is introduced into the combustion air (15) flowing past at this point, are arranged in the region of these tangential inlet slots (21, 22).

Abstract: In an apparatus for impingement cooling, in which a cooling surface and a cover surface are disposed parallel to one another, trapezoidal profiles that are open respectively on the narrow side and connected to one another at a constant distance from the cooling surface are disposed crosswise to the flow direction of the cooling air. A side of the trapezoid facing the cooling surface is provided with at least one row of perforations and forms a gap of a constant height with the cooling surface. Open sides of the trapezoid located opposite the cover surface form feed openings for the cooling air, and open sides of the trapezoids located opposite the cooling surface form overflow openings. The feed opening is much larger than the cross-section of a perforation. The cross-section of the return flow conduit is much larger than the overflow opening, and this opening is, in turn, much larger than the cross-section of the gap.

Abstract: A method of establishing part-load operation is proposed for a turbine group. This gas turbine group consists essentially of a compressor unit (1), of an HP combustion chamber (4) downstream of the compressor unit (1), of an HP turbine (5) downstream of this HP combustion chamber (4), of an LP combustion chamber (8) operating by self-ignition and arranged downstream of the HP turbine (5), the hot gases (10) of which LP combustion chamber (8) being admitted to an LP turbine (11). The temperature at outlet from the HP turbine (5) remains essentially the same due to the reduction of the fuel quantity in the LP combustion chamber (8) to zero. Furthermore, the fuel quantity of the HP combustion chamber (4) remains approximately constant during the reduction of the fuel quantity in the LP combustion chamber (8) so that the temperature at inlet to the HP turbine (5) likewise remains constant.

Abstract: A premixing burner on the double-cone principle consists essentially of two hollow conical partial bodies (111, 112) which are interleaved in the flow direction and whose respective center lines (113, 114) are offset relative to one another. The adjacent walls of the two partial bodies form tangential gaps (20) in their longitudinal extent for the combustion air. Gas inlet openings (117) distributed in the longitudinal direction are provided in the walls of the two partial bodies. The air is guided into the tangential gaps (20) via vortex generators (9) of which a plurality are arranged adjacent to one another. The fuel is introduced into the gaps (20) in the immediate region of the vortex generators (9).Using the novel static mixer which the three-dimensional vortex generators represent, longitudinal vortices without recirculation region can be generated in the inlet gap through which flow occurs.

Abstract: In a gas turbine combustion chamber which surrounds the rotor as an annulus and therefore has the shape of an annular combustion chamber, the front wall (10) is equipped with a number of burners whose ends occupy a uniform plane. These burners form a double ring (10b, 10c) on the front wall (10). In each ring, the same direction of rotation is present in the burners and this is opposite to the adjacent ring. In addition, two burners at a time are alternately displaced outwards and inwards in each ring in order to achieve a favorable flow field for combustion. The number of burners on the front wall (10) is divided into a larger quantity of piloting burners (A1, A2 ) and a smaller quantity of piloted burners (B1, B2).

Abstract: In a double-cone burner, at least one row of nozzles (10) for a gaseous fuel containing highly reactive components and having a medium calorific value are arranged on the periphery of the partial conical bodies (1, 2) of the burner near the burner outlet at a distance of approximately 30% of the nominal burner diameter. In addition, there is a fuel conduit (11) and a distributing passage (17), placed in the region of the nozzles (10), for the highly reactive fuel. The gaseous fuel (15) containing highly reactive components is injected at high velocity through the nozzles (10), which have a diameter which is smaller than 1% of the nominal burner diameter, into the zones of high air velocity and the penetration depth and the direction of the fuel jets are matched to one another in such a way that ignition only takes place behind the burner, after mixing has occurred.

Abstract: In a process for low-pollutant combustion in a power station boiler (22) for steam generation, at least one precombustion chamber (24) acts at the boiler itself, which precombustion chamber is operated with at least one burner (25a-c). At least a part of the primary air (26) initially flows through a heat exchanger (24c) , in which a caloric treatment of this air takes place to give combustion air (26a). This combustion air (26a) then flows into the burner (25a-c), where a mixing, and subsequent combustion with fuel (12) or with another mixture takes place. A further air stream as secondary air (27) is injected directly into the precombustion chamber (24), this taking place directly before the actual join of the precombustion chamber (24) to the boiler (22). Downstream of the precombustion chamber (24), a tertiary air stream (29) is fed into the boiler (22). Using this configuration, a process with double air staging is proposed, the boiler (22) being operated with air deficiency.

Abstract: In a burner for premixing-type combustion of a liquid and/or gaseous fuel, which essentially comprises hollow conical part-bodies (1, 2) positioned one upon the other, the center lines of which extend mutually offset in the longitudinal direction, whereupon tangential inlet openings (1b, 2b) are formed on both sides of the burner, a fuel (5a) is admixed to the combustion air (13) flowing into the interior (3) of the burner in that area. This admixture is accomplished via a number of nozzles (9, 10), which act in the region of the inlet openings (1b, 2b). The fuel through these nozzles is injected with a small spray cone angle in the longitudinal direction of the slot. The fuel vaporization takes place essentially only in the inlet openings of the burner, with the result that only a fuel vapor enters the interior (3). A further central nozzle (4) supplied with a liquid and/or gaseous fuel provides assistance in the form of a limit fuel quantity.

Abstract: In premixing-type combustion of liquid fuel in a burner without a premixing section, a conical column (5) of liquid fuel is formed in the interior (14) of the burner, which column widens in the direction of flow and is surrounded by a rotating stream (15) of combustion air which flows tangentially into the burner. Ignition of the mixture takes place at the burner outlet, a backflow zone (6) forming in the region of the burner outlet. The burner itself consists of at least two hollow part-cone bodies (1, 2) which are superposed on one another and have a cone angle increasing in the direction of flow. The part-cone bodies (1, 2) are mutually offset, so that tangential air inlet slots (19, 20) are formed. A nozzle (3) placed at the burner head ensures injection of the liquid fuel (12) into the interior (14) of the burner.

Abstract: In a combustion installation, a mixture of fresh air (D) and exhaust gas (C) is fed to the burner (A) via a mixing/conveying device (EFG). There is provided in the combustion installation a heat exchanger (M), which undertakes the thermal conditioning of the mixture (H) before the latter is fed into the burner (A).

Abstract: This burner arrangement has a main feed channel (2) for a fuel-air mixture, which channel discharges into a combustion chamber (1). A swirler, which is provided with swirl vanes (5), is penetrated by a burner lance (3), and into which exit openings for the fuel feed discharge, is provided in this main feed channel (2). The aim is to create a burner arrangement in which it is impossible for undesired instances of ignition of the fuel-air mixture to occur outside the combustion chamber (1). This is achieved in that the exit openings are constructed as nozzles (9) which discharge into a region between the swirl vanes (5). In this regard, at least one nozzle is provided between two neighboring swirl vanes (5).

Abstract: In an annular combustion chamber (A), a row of premixed burners (B, C) are located in the peripheral direction at the inlet end. The large premixed burners (B), which are the main burners of the annular combustion chamber (A), and the small premixed burners (C), which are the pilot burners of the annular combustion chamber, are located alternately relative to one another and at a uniform distance apart. Both the main burners (B) and the pilot burners (C) enter into a single annular front wall (10).

Abstract: In premixing-type combustion of liquid fuel in a burner without a premixing section, a conical column (5) of liquid fuel is formed in the interior (14) of the burner, which column widens in the direction of flow and is surrounded by a rotating stream (15) of combustion air which flows tangentially into the burner. Ignition of the mixture takes place at the burner outlet, a backflow zone (6) forming in the region of the burner outlet. The burner itself consists of at least two hollow part-cone bodies (1,2) which are superposed on one another and have a cone angle increasing in the direction of flow. The part-cone bodies (1, 2) are mutually offset, so that tangential air inlet slots (19, 20) are formed. A nozzle (3) placed at the burner head ensures injection of the liquid fuel (2) into the interior (14) of the burner.

Abstract: The atomizer nozzle exhibits an internal chamber (1) and an external chamber (2) which surrounds the latter in the form of a jacket, which chambers are provided with several outlet openings (9, 10 and 11, 12) which are in alignment in each case. A proportion of the atomizer air supplied via an air duct (5) flows into the internal chamber (1) and is essentially used there for uniformly distributing a liquid fuel, which is also flowing into the internal chamber (1) from a fuel duct (3), to its outlet openings (9, 10). The remaining greater proportion of the atomizer air flows around the internal chamber (1) through the external chamber (2) and is concentrically mixed in with the coarsely atomized fuel emerging from the outlet openings (9, 10) of the internal chamber (1). This prevents liquid fuel fragments from coming into contact with the walls of the outlet openings (11, 12) of the external chamber (2), and a high atomization quality is achieved.

Abstract: In the method, a process medium (14) is heated in two stages, in which fuel oil and gas premixed with air in a burner device (1) are partially burnt in a preliminary combustion chamber (12) substoichiometrically with an air coefficient (.lambda.) of approximately 0.7. The partially burnt mixture, which is low in nitrogen oxides, reaches a temperature of 1800.degree.-1900.degree. C., heats the process medium (14), which is already preheated to an intermediate temperature, to its final temperature in a heat exchanger (13) with counter-current flow and is cooled to 700.degree.-900.degree. C. In an air injection region (15) of the process heat generator the partially burnt mixture is mixed with quenching air in a stoichiometric ratio with respect to the unburnt fractions and is thereby completely burnt in a secondary combustion chamber (18) during which practically no nitrogen oxides (NO.sub.x) are produced. It reaches a temperature of 900.degree.-1300.degree. C.

Abstract: The present invention relates to a burner system, in particular for a gas turbine, with a main supply channel (2), debouching into a combustion chamber (1), for a fuel/air mixture having a swirler (5) and a burner lance (3) which passes through the swirler (5). To improve the transverse ignition properties between several such burner systems, optionally disposed on the burner chamber (1), and also to increase the flame stability, the burner lance (3) has, on the combustion chamber side with respect to the swirler (5) exit openings (12, 16) for fuel supplied to its interior or for a fuel-rich fuel/air mixture supplied to, or formed in, its interior.

Abstract: The resonance atomizer (4) of the burner facility has, as main components, a resonator ring (16) and a resonator cone (23), which each have an annular groove (25+24, respectively), which together form a resonance chamber (24+25). By a plurality of spacer strips (26) on the resonator ring (16), the resonator ring (16) and the resonator cone (23) are held apart by a distance which creates an annular inflow duct (27) for the oil/atomizing air mixture and outflow ducts (28) on the combustion space side for this mixture atomized in the resonance chamber (24+25). Between the components (16, 23) forming the resonator chamber (24+25) and the oil nozzle (7) there is an atomizing cross (17) with a baffle plate (19).