Abstract: A burner component of a burner. The burner has a flow channel, in which combustion air flows in a flow direction from upstream to downstream. The burner component includes a wall portion, which adjoins the flow channel; a plurality of injection nozzles, which are arranged in the wall portion; and a plurality of vortex generators, which are arranged on the wall portion. The vortex generators have a concavely curved sloped surface rising in the flow direction to improve the distribution of the fuel in the combustion air.

Abstract: A heat shield with support structure and a number of heat shield blocks secured thereto, having a cold side facing the support structure and a hot side opposite the cold side. At least one recess is arranged in at least one heat shield block circumferential face, connecting the cold to hot side. An opening connecting the recess to the cold side runs in the circumferential face perpendicularly to the cold side. A securing bolt inserted into the opening secures the heat shield block to the support structure. A bolt head protrudes at least partly into the recess. The securing bolt passes through an angled plate having first limb extending substantially parallel to the circumferential face and second limb extending into the recess. The angled plate has a reinforcing device extending beyond the pure angular shape to increase a resistance of the angled plate against bending due to the securing bolt.

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 retaining element (22, 54) for retaining a heat shield tile on a supporting structure: A fastening section (23) fastened to the supporting structure. A retaining section (24) having a retaining head (25), which engages an engagement device on the heat shield tile. The fastening section (23) top side (28) faces the cold side of the heat shield tile when the retaining section engages the heat shield tile. Scaling of the supporting structure due to the entry of hot gas can be avoided particularly effectively by means of the retaining element. At least one cooling-air passage (34, 55) arranged in the fastening section (23) has an inlet opening (35, 68) and at least one outlet opening (37, 38, 62) which is arranged in a lateral surface (32) and/or on the top side (28) of the fastening section.

Abstract: A burner arrangement for a combustion chamber for combustion of fluid fuels has a main burner and pilot burner arranged centrally within the main burner for the ignition and/or stabilization of the combustion of the main burner. The main burner has central fuel feed arrangement arranged around the pilot burner, an annular air duct surrounding the central fuel feed arrangement for the supply of combustion air, first fuel nozzles for injection of substantially gaseous fuel into the annular air duct. The first fuel nozzles are fed from a first fuel distributor in the central fuel feed arrangement, and second fuel nozzles for the injection of a substantially liquid fuel into the annular air duct are fed from a second fuel distributor in the central fuel feed arrangement. Ducts are provided which branch off from at least one of the fuel distributors and issue into the pilot burner.

Abstract: A heat shield with support structure and a number of heat shield blocks secured thereto, having a cold side facing the support structure and a hot side opposite the cold side. At least one recess is arranged in at least one heat shield block circumferential face, connecting the cold to hot side. An opening connecting the recess to the cold side runs in the circumferential face perpendicularly to the cold side. A securing bolt inserted into the opening secures the heat shield block to the support structure. A bolt head protrudes at least partly into the recess. The securing bolt passes through an angled plate having first limb extending substantially parallel to the circumferential face and second limb extending into the recess. The angled plate has a reinforcing device extending beyond the pure angular shape to increase a resistance of the angled plate against bending due to the securing bolt.

Abstract: The present invention relates to a burner system (1) comprising a pilot burner arrangement (2), a main burner arrangement (3) surrounding the pilot burner arrangement (2), a combustion chamber arranged downstream with respect to the pilot burner arrangement (2) and the main burner arrangement (3), and at least one resonator (17), wherein the main burner arrangement (3) defines a ring-shaped air supply (13) outwardly delimited by a burner cone (14) and provided with radially extending swirl vanes (15), wherein a resonator cavity (18) of the at least one resonator (17) is formed at the outside of the burner cone (14), wherein the resonator cavity (18) is provided with a plurality of resonator openings (20) defining a fluidic connection between the resonator cavity (18) and the combustion chamber.

Abstract: A burner incorporating a pilot cone and a mounting insert is provided. The pilot cone is constructed as a pilot cone assembly which is decoupled from the mounting insert. Further, an operating method for increasing the service life of a burner which incorporates a pilot cone assembly and a mounting insert is provided. The pilot cone assembly has a cone side and incorporates at least one further side where the further side is arranged to be essentially parallel to one of the sides of the mounting insert and spaced apart from it, so that between the further side and the side of the mounting insert there is a defined gap. In an operation of the burner, the gap is significantly reduced by the thermal expansion in at least at one point of contact between the further side and the side of the mounting insert. Finally, an assembly method is provided.

Abstract: A retaining element (22, 54) for retaining a heat shield tile on a supporting structure: A fastening section (23) fastened to the supporting structure. A retaining section (24) having a retaining head (25), which engages an engagement device on the heat shield tile. The fastening section (23) top side (28) faces the cold side of the heat shield tile when the retaining section engages the heat shield tile. Scaling of the supporting structure due to the entry of hot gas can be avoided particularly effectively by means of the retaining element. At least one cooling-air passage (34, 55) arranged in the fastening section (23) has an inlet opening (35, 68) and at least one outlet opening (37, 38, 62) which is arranged in a lateral surface (32) and/or on the top side (28) of the fastening section.

Abstract: A heat shield of a gas turbine: a supporting structure (16), to which heat shield tiles are fastened releasably by tile holders (2, 2a, 2b); The heat shield permits cooling of the supporting structure. Each tile has a cold side facing the supporting structure (16) and an opposite hot side that can be acted upon with a hot medium; each tile holder (2, 2a, 2b) has a holding section (3) for fastening to a heat shield tile and a fastening section (4) for fastening to the supporting structure (16). The fastening section (4) is fastenable at a fastening groove (18) running in the supporting structure (16). At least one cooling air duct (9) protects against hot gases. For the cooling purpose, in addition to the fastening grooves (18) at least one cooling air groove (1, 22) arranged in the supporting structure (16).

Abstract: A burner assembly having a fuel distribution ring, number of fuel nozzles which are mounted on the fuel distribution ring in the direction of low is provided. The fuel distribution ring has a ring-shaped surface in the direction of flow and wherein the fuel distribution ring center and an opposite outer outer side and wherein there is at least one slot on the surface between the fuel nozzles and the at least one slot extends on the surface from the outside to the inside. There is at least one recess arranged on the surface and the at least one recess also partially includes the outside of the fuel distributor.

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 burner assembly having a fuel distribution ring, number of fuel nozzles which are mounted on the fuel distribution ring in the direction of low is provided. The fuel distribution ring has a ring-shaped surface in the direction of flow and wherein the fuel distribution ring center and an opposite outer outer side and wherein there is at least one slot on the surface between the fuel nozzles and the at least one slot extends on the surface from the outside to the inside. There is at least one recess arranged on the surface and the at least one recess also partially includes the outside of the fuel distributor.

Abstract: A burner arrangement is provided. The burner arrangement includes a support as well as at least two fuel nozzles, with fuel nozzle tips, attached to the support in the direction of flow and a gas feed system to the fuel nozzle tips extending through the support. Each fuel nozzle includes a support-side section which on the support side includes a contact surface with which the fuel nozzle rests on a supporting surface of the support, at least two fuel nozzle tips formed in one piece running from the support-side section in the direction of flow, the gas feed system including at least one gas feed line and its lead-through through the support, the lead-through being embodied as a fit.

Abstract: A burner incorporating a pilot cone and a mounting insert is provided. The pilot cone is constructed as a pilot cone assembly which is decoupled from the mounting insert. Further, an operating method for increasing the service life of a burner which incorporates a pilot cone assembly and a mounting insert is provided. The pilot cone assembly has a cone side and incorporates at least one further side where the further side is arranged to be essentially parallel to one of the sides of the mounting insert and spaced apart from it, so that between the further side and the side of the mounting insert there is a defined gap. In an operation of the burner, the gap is significantly reduced by the thermal expansion in at least at one point of contact between the further side and the side of the mounting insert. Finally, an assembly method is provided.