Abstract: A combustion chamber assembly group includes a burner seal with a bearing section that extends along a longitudinal axis and has a passage hole for positioning a fuel nozzle at a combustion chamber of an engine, and a heat shield which, when mounted according to the intended use at the combustion chamber of the engine, is located inside the combustion space of the combustion chamber and has a passage hole through which the bearing section of the burner seal extends. The burner seal that is manufactured in an additive manner and the heat shield form a constructional unit in which the heat shield is received at least partially between a radially outwardly pointing opening edge of the burner seal and a radially outwardly extending web of the burner seal, so that any separation of the heat shield from the burner seal along the longitudinal axis is excluded.

Abstract: A nozzle assembly group for a combustion chamber of an engine, with multiple nozzles for introducing fuel into the combustion chamber that are arranged next to each other, wherein each nozzle has a nozzle outlet opening and a fuel channel for conveying fuel in the direction of the nozzle outlet opening. According to the invention, it is provided that at least two different types of nozzles are provided, wherein the nozzles of different types have nozzle outlet openings with an identical cross section, and for predetermining different flow rates of fuel through the fuel channels of the nozzles of different types, a cross section of a fuel channel of one type of nozzle is different from a cross section of a fuel channel of another type of nozzle.

Abstract: The present invention relates to a combustion chamber tile of a gas turbine, where the combustion chamber tile has a plurality of effusion cooling holes and a mixing air hole provided as a flow-guiding element (chute) and projecting over the surface of the combustion chamber tile, characterized in that on the side of the mixing air hole facing away from a flow along the combustion chamber tile at least one supporting element is arranged on the combustion chamber tile and on the mixing air hole. It also relates to a method for its manufacture.

Abstract: A combustion chamber shingle arrangement of a gas turbine, including a combustion chamber shingle, at least one threaded bolt configured for attaching the combustion chamber shingle, and a base body connecting the threaded bolt to the combustion chamber shingle, wherein the base body comprises a platform and a connection area that connects the platform to the combustion chamber shingle, wherein the threaded bolt is arranged at the platform, and wherein a hollow space is embodied between the platform and the combustion chamber shingle.

Abstract: A wall component of a combustion chamber arrangement, including a wall area with a side that is facing towards the combustion chamber and a side that is facing away from the combustion chamber, a plurality of first effusion cooling holes connecting the side that is facing away from the combustion chamber to the side that is facing towards the combustion chamber by means of exactly one through channel, and at least one modified second effusion cooling hole with a main channel and a branching channel, wherein the modified second effusion cooling hole has a common entry opening and a common exit opening.

Abstract: The present invention relates to a combustion chamber for a gas turbine with a combustion chamber head and a heat shield which are designed in one piece, with the heat shield being provided with at least one recess, in which is arranged a burner or an annular sleeve enclosing the burner, with a burner seal being provided between the heat shield and the burner, characterized in that the heat shield is provided in the area of the recess with an annular groove, in which is arranged at least one elastic sealing element forming the burner seal.

Abstract: A combustion chamber of a gas turbine having a head plate and a combustion chamber head, where the head plate is connected to the combustion chamber, and where several heat shields arranged in the interior of the combustion chamber are bolted to the head plate, characterized in that each heat shield and the combustion chamber head are fastened to the head plate by means of joint bolted connections.

Abstract: A gas turbine combustion chamber with an inner combustion chamber wall and an outer combustion chamber wall, which form an annular combustor, is provided. Mixing air holes are formed in the inner combustion chamber wall and the outer combustion chamber wall in a circumferentially distributed manner. The respective combustion chamber wall is bulged in the area of the mixing air holes towards the interior space of the combustion chamber wall and the mixing air hole is arranged inside the bulge. The mixing air hole is formed at an inflow surface of the bulge with respect to the through-flow direction of the combustion chamber.

Abstract: The invention relates to a swirl generator of a fuel nozzle 6 of a gas turbine, with an inner 22 and an outer 21 ring element, wherein the ring elements 21, 22 are arranged so as to be concentric with respect to each other, and an outer annular channel 18a is formed between the inner ring element 22 and the outer ring element 21, having a radial height of h in its axially central area, characterized in that the outer annular channel 18a has a radial height of H at its inflow area 23 and is provided with air guiding elements 11 in the inflow area 23, wherein H>h applies, wherein an inner annular channel (18b) is formed at the radially inner side of the inner ring element (22), with its inflow area (23), which is provided with air guiding elements (11), having a larger radial height than a central area of the inner annular channel (18b), wherein the outer annular channel (18a) has an effective flow surface (A) in the area of the guide elements (11) that is larger than the effective flow surface in the axiall

Abstract: A gas turbine combustion chamber includes first admixing air holes having first inner and outer center points, and second admixing air holes having second inner and outer center points. The first and second inner center points respectively lie on a side of the first and second admixing air holes oriented towards the combustion chamber. The first and second outer center points lie on a side of the first and second admixing air holes facing away from the combustion chamber. An equation L=D2/D1*(D2?D1)/C2 is fulfilled, with L being a distance between the first and second inner center points and/or the first and second outer center points; D1 and D2 being flow diameters of the first and second admixing air holes respectively at an entry and/or exit side to the combustion chamber and C being an average flow rate coefficient of the first and second admixing holes.

Abstract: The present invention relates to a gas-turbine combustion chamber having a head plate as well as an outer and an inner combustion chamber wall, wherein the combustion chamber is formed by segments or partial segments manufactured in one piece by means of a DLD method and welded to one another.

Abstract: A gas turbine combustion chamber with a double-wall embodiment, having an outer cold combustion chamber wall and an inner hot combustion chamber wall which form an intermediate space, with impingement cooling holes in the outer combustion chamber wall, effusion cooling holes in the inner combustion chamber wall, outer mixing holes in the outer combustion chamber wall, and inner mixing holes in the inner combustion chamber wall. Respectively, one tubular mixing element connects the outer mixing hole and the inner mixing hole, wherein the mixing element includes an inflow opening in its area which is arranged inside the intermediate space. The outer mixing hole has a smaller diameter than the inner mixing hole, and the throughflow surface area of the effusion holes that are adjoining the mixing element is reduced by the difference in surface area between the outer mixing hole and the inner mixing hole.

Abstract: The present invention relates to a combustion chamber tile of a gas turbine with a plate-like basic element which is provided with at least one effusion cooling hole extending through the basic element from a surface of one side to the other side, with the effusion cooling hole being designed, from the one side of the basic element and beginning from an inlet opening, substantially at right angles to the surface over part of its length, wherein the effusion cooling hole inside the basic element has a straight section and is then provided with an offset section.

Abstract: A combustion chamber tile of a gas turbine includes a bolt for mounting the combustion chamber tile on a combustion chamber wall, with the combustion chamber tile being designed substantially plate-like and having on one side at least one mounting element, on which the bolt, which is provided as a separate component, is positively anchored.

Abstract: A method for mounting a combustion chamber of a gas turbine engine, wherein an annular outer combustion chamber wall and an annular inner combustion chamber wall are brought in position with respect to one another and are connected to a head plate, and wherein subsequently a combustion chamber head is mounted, characterized in that the head plate is connected to the outer combustion chamber wall and the inner combustion chamber wall by means of rivets that are arranged in a circumferentially distributed manner, and that subsequently the combustion chamber head is brought in position and is screwed together by means of threaded bolts and nuts to the arrangement of head plate, outer combustion chamber wall and inner combustion chamber wall, which is pre-mounted by means of the rivet.

Abstract: An assembly group for a combustion chamber of a gas turbine includes a combustion chamber shingle with a mounting element and a bolt formed as a separate structural component for supporting the combustion chamber shingle at a wall of the combustion chamber. The mounting element has a reception area into which a bolt head of the bolt is inserted transversely with respect to a longitudinal axis of the bolt and anchored therein in a form-fit manner. At the reception area, the mounting element forms an edge area that protrudes substantially radially with respect to the longitudinal axis of the bolt and that at least partially surrounds an edge of the bolt head. The edge of the bolt head does not extend exclusively in a plane that is perpendicular to the longitudinal axis of the bolt.

Abstract: A covering part for a combustion chamber of a gas turbine is configured and provided to guide a fluid flow downstream of a diffuser of the gas turbine at least partially into a flow area outside of a combustion space of the combustion chamber so as to cool a combustion chamber wall that delimits the combustion space and has at least one mounting edge at which at least one attachment site is provided for fixating the covering part at the combustion chamber wall by means of a separate attachment element. At least one guiding element is provided at the covering part in the area of the mounting edge, which during operation of the gas turbine guides the partial flow of the fluid flow to be guided in the direction of the flow area over and above a part of the attachment element that protrudes from the mounting edge.

Abstract: A diffuser component for a gas turbine is provided, where a fluid flow in the direction of a combustion chamber of the gas turbine can be slowed down by the diffuser component, and a flow cross-section of the diffuser component, which is defined by a diffuser wall is widened to do so. The diffuser wall is at least locally braced, in that at least one stiffening element with a lattice-type structure is provided on the diffuser wall.

Abstract: A gas turbine combustion chamber with an outer combustion chamber wall and an inner combustion chamber wall, wherein the outer combustion chamber wall and the inner combustion chamber wall are respectively formed in one piece with an outer or an inner ring-shaped platform that are connected in one piece with turbine inlet guide vanes which are arranged around the circumference, wherein the gas turbine combustion chamber is mounted only by means of a suspension device that is formed in one piece at the outer platform, as well as a method for manufacturing the same.

Abstract: A combustion chamber of a gas turbine, including an external combustion chamber wall as well as an internal combustion chamber wall, wherein the internal combustion chamber wall, at its frontal end area as it appears with respect to the flow direction of the combustion chamber, is supported in a longitudinally slidable manner inside a groove of a base plate that is arranged in the area of a combustion chamber head, and is fixedly attached at the external combustion chamber wall at its back end area.