Abstract: A combustor and a method involving burner mains structurally configured to damp vibrational modes that can develop under high-frequency combustion dynamics are provided. The combustor may include a carrier (12), and a plurality of mains (16) disposed in the carrier. Some of the mains (labeled with the letter X) include a body having a different structural feature relative to the respective bodies of the remaining mains. The mains with the different structural feature may be selectively grouped in the carrier to form at least one set of such mains effective to damp predefined vibrational modes in the combustor.

Abstract: A method for producing a component by selective laser melting, wherein a number of lasers arranged next to one another generate a laser field, as a result of which powdery material can be melted in a selective manner for the purposes of generating contours. In the process, individual lasers of the laser arrangement can be switched on or off in a selective matter in order to irradiate or not irradiate certain regions. Furthermore, a device for carrying out the method is provided.

Abstract: A burner arrangement having a combustion chamber, a multiplicity of mixing ducts discharging into the combustion chamber, in which ducts combustion air and fuel introduced during proper operation are mixed, and at least one resonator which has a defined resonator volume and resonator openings. The mixing ducts have mixing tubes which extend axially through an annular space defined between a tubular outer wall, a tubular inner wall arranged with the radial separation from the outer wall, an annular end plate arranged upstream and an annular end plate arranged downstream, wherein the end plates are provided with through openings which receive and/or prolong the mixing tubes. The resonator openings of the at least one resonator are designed as air ducts that extend through the downstream end plate, and the resonator volume of the at least one resonator is formed by at least one part of the annular space.

Abstract: A burner assembly with a combustion chamber, a plurality of mixing ducts leading into the combustion chamber, where combustion air and introduced fuel are mixed. The mixing ducts are formed by mixing tubes extending axially through an annular space between a tubular outer wall, a tubular inner wall arranged radially at a distance from the outer wall, a ring-shaped end plate arranged upstream and a ring-shaped end plate arranged downstream. The end plates have through-openings, which accommodate and/or extend the mixing tubes, and the end plates have, both radially inside and outside, a circumferential edge extending in the direction of the annular space, with axial bores in the edge of the ring-shaped end plate arranged downstream. The axial bores extend from the annual space into the end plate, and at least one opening is for removing cooling air, the opening branching from the axial bore.

Abstract: A burner having a plurality of pre-mixing chambers each having a fuel nozzle for two fuels, the fuel nozzle has a fuel lance extending in a flow direction, in which fuel lance first outlet openings for a first fuel are introduced. The fuel lance is surrounded by an outer pipe having at least one second outlet opening for a second fuel, the first outlet openings oriented radially and the second outlet opening oriented axially, a flow cross-section is formed between the fuel lance and the inside of the pre-mixing chamber and vortex generators are arranged on the fuel lance. At least one vortex generator is arranged upstream of the first outlet openings and downstream of the second outlet opening. The distance of the first outlet openings from an end of the pre-mixing chamber is at least three times as large as a cross-section of the pre-mixing chamber.

Abstract: An adaptation method for a modelling method in which, by means of target geometry, model geometry, which is derived from the target geometry, is created for an object to be produced by a selective laser melting method is provided. In the adaptation method, adapted model geometry is produced from the derived model geometry by dimension adaptation by means of a correction factor and/or by geometry adaptation by means of correction geometry.

Abstract: A thermocouple system, has a metal feedthrough having a cylindrical portion having an axis of symmetry and a terminal end region arranged thereon, which completely closes the cylindrical portion, and which has at least two passageways, the opening cross-section of which is smaller than the cross-sectional surface vertical to the axis of symmetry through the cylindrical portion. Through one passageway, a thermocouple is guided, and in the region of the passageway, the thermocouple is connected to the end region in a fluid-tight manner by way of a seal.

Abstract: A combustor and a method involving burner mains structurally configured to damp vibrational modes that can develop under high-frequency combustion dynamics are provided. The combustor may include a carrier (12), and a plurality of mains (16) disposed in the carrier. Some of the mains (labeled with the letter X) include a body having a different structural feature relative to the respective bodies of the remaining mains. The mains with the different structural feature may be selectively grouped in the carrier to form at least one set of such mains effective to damp predefined vibrational modes in the combustor.

Abstract: A burner having a pre-mixing passage delimited radially outwardly by a wall, a burner lance and a plurality of fuel injectors arranged in the pre-mixing passage, the injectors extending from the burner lance in the direction of the wall and having fuel nozzles. The fuel supply arrangement has at least one fluidic oscillator that has an interaction chamber, an inlet to the interaction chamber connected to a fuel channel of the fuel supply arrangement, a first outlet channel of the interaction chamber extending at least to a first fuel nozzle and a second outlet channel extending at least to a second fuel nozzle, the fluidic oscillator has one feedback line for each outlet channel, one end of the feedback line terminating into the respective outlet channel downstream of the at least one fuel nozzle, and the other end thereof terminating into an inlet region of the interaction chamber.

Abstract: A burner assembly with a combustion chamber, a plurality of mixing ducts leading into the combustion chamber, where combustion air and introduced fuel are mixed. The mixing ducts are formed by mixing tubes extending axially through an annular space between a tubular outer wall, a tubular inner wall arranged radially at a distance from the outer wall, a ring-shaped end plate arranged upstream and a ring-shaped end plate arranged downstream. The end plates have through-openings, which accommodate and/or extend the mixing tubes, and the end plates have, both radially inside and outside, a circumferential edge extending in the direction of the annular space, with axial bores in the edge of the ring-shaped end plate arranged downstream. The axial bores extend from the annual space into the end plate, and at least one opening is for removing cooling air, the opening branching from the axial bore.

Abstract: A burner having a plurality of pre-mixing chambers each having a fuel nozzle for two fuels, the fuel nozzle has a fuel lance extending in a flow direction, in which fuel lance first outlet openings for a first fuel are introduced. The fuel lance is surrounded by an outer pipe having at least one second outlet opening for a second fuel, the first outlet openings oriented radially and the second outlet opening oriented axially, a flow cross-section is formed between the fuel lance and the inside of the pre-mixing chamber and vortex generators are arranged on the fuel lance. At least one vortex generator is arranged upstream of the first outlet openings and downstream of the second outlet opening. The distance of the first outlet openings from an end of the pre-mixing chamber is at least three times as large as a cross-section of the pre-mixing chamber.

Abstract: A burner arrangement having a combustion chamber, a multiplicity of mixing ducts discharging into the combustion chamber, in which ducts combustion air and fuel introduced during proper operation are mixed, and at least one resonator which has a defined resonator volume and resonator openings. The mixing ducts have mixing tubes which extend axially through an annular space defined between a tubular outer wall, a tubular inner wall arranged with the radial separation from the outer wall, an annular end plate arranged upstream and an annular end plate arranged downstream, wherein the end plates are provided with through openings which receive and/or prolong the mixing tubes. The resonator openings of the at least one resonator are designed as air ducts that extend through the downstream end plate, and the resonator volume of the at least one resonator is formed by at least one part of the annular space.

Abstract: A fuel nozzle (2) for two fuels, with an inner pipe (5) with radially oriented outlet openings (7) for a first fuel and with an outer pipe (6), surrounding the inner pipe (5), with axially oriented outlet openings (10) for a second fuel; an axially extending groove (18) on an outer surface of the inner pipe (5) and a projection (19) inward from the outer pipe which engages in the groove (18) as an anti-torsion device (17) and which is arranged between two axial outlet openings (10). Alternative groove and projection configurations are disclosed.

Abstract: An adaptation method for a modelling method in which, by means of target geometry, model geometry, which is derived from the target geometry, is created for an object to be produced by a selective laser melting method is provided. In the adaptation method, adapted model geometry is produced from the derived model geometry by dimension adaptation by means of a correction factor and/or by geometry adaptation by means of correction geometry.

Abstract: A method for producing a component by selective laser melting, wherein a number of lasers arranged next to one another generate a laser field, as a result of which powdery material can be melted in a selective manner for the purposes of generating contours. In the process, individual lasers of the laser arrangement can be switched on or off in a selective matter in order to irradiate or not irradiate certain regions. Furthermore, a device for carrying out the method is provided.

Abstract: A turbine system including a compressor (3), a combustor arrangement having several combustors (4) fluidicallys connected to receive air from the compressor (3), and a turbine (5) fluidically connected to the combustors (4). Each combustor (4) has an air inlet ring chamber (7) with a flow cross-section defined by an inner tube (10) and an outer tube (11; 17) around the inner tube. The air inlet ring chamber is configured to introduce compressed air from the compressor (3) into the combustor (4). A radial distance (d) between the inner tube (10) and the outer tube (11; 17) of each air inlet ring chamber (7) at least partially varies along the circumference of the air inlet ring chamber (7).

Abstract: A gas turbine combustion chamber (8) surrounded by an inner wall (2) having cooling air bores (17) and an outer wall (9) that is spaced from the inner wall (2). The outer wall (9) likewise has cooling air bores (16) and is formed of a plurality of wall elements (11) that are arranged in the circumferential direction of the gas turbine combustion chamber (8) essentially next to each other. The outer wall elements are arranged on the inner wall (2) by means of a fixed bearing (24) on one narrow side (21) of a wall element and by means of a floating bearing (25) on an opposite narrow side (21) of the element, configured to define a hollow space (10) is formed between the two walls (2, 9).

Abstract: A heat-shield element (14), for lining a combustion-chamber wall (13), the chamber wall has a first wall (17) with a hot side (18) which can be loaded with a hot medium, a cold side (19) which lies opposite the hot side (18), and a circumferential edge (24) which extends on a first (20), a second (21) and a third narrow side (22) of the first wall (17) to a first height (25) beyond the cold side (19), the circumferential edge (24) extends on a fourth narrow side (23) to a second shorter height (26), substantially at the second height (26), a second wall (27) lies opposite the cold side (19) and extends over the width of the fourth narrow side (23) from the fourth narrow side (23) and over a part of the length of the narrow sides (20, 22), which adjoin the fourth narrow side; (23), the second wall (27) has an edge (29) at the end (28) thereof which faces away from the fourth narrow side (23), which edge (29) extends to the first height (25). Furthermore, a combustion chamber and a gas turbine are disclosed.

Abstract: An annular combustion chamber (1) for a gas turbine, the chamber having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine chamber (8), wherein ducts (14) which can be closed, which are oriented substantially parallel to the symmetry axis (2) of the annular combustion chamber (1), and through which final compressor air is guided into the annular combustion chamber (1) are provided in the outer shell (12) in the region of the outlet (7). Ring segments around the outer shell have projections selectively movable to at least partially block and open the ducts. A gas turbine is also disclosed.

Abstract: A fuel nozzle (2) for two fuels, with an inner pipe (5) with radially oriented outlet openings (7) for a first fuel and with an outer pipe (6), surrounding the inner pipe (5), with axially oriented outlet openings (10) for a second fuel; an axially extending groove (18) on an outer surface of the inner pipe (5) and a projection (19) inward from the outer pipe which engages in the groove (18) as an anti-torsion device (17) and which is arranged between two axial outlet openings (10). Alternative groove and projection configurations are disclosed.