Abstract: The present invention relates to a method for producing an engine component having a cooling duct arrangement which has a plurality of cooling ducts, each having an inflow opening, the inflow openings being arranged according to a predefined pattern in an inflow surface of the engine component, and each cooling duct opening into a recess in a wall of the engine component, along which wall a cooling film is to be formed. According to the invention, the pattern is formed in at least one subregion of defined size of the inflow surface, from a plurality of identical isosceles triangles, which are defined by a minimum spacing (k) and by a mean diameter (a) of the inflow openings correlating to the minimum spacing (k). This procedure reduces the complexity of the design process.

Abstract: The present invention relates to a method for producing an engine component having a cooling duct arrangement which has a plurality of cooling ducts, each having an inflow opening, the inflow openings being arranged according to a predefined pattern in an inflow surface of the engine component, and each cooling duct opening into a recess in a wall of the engine component, along which wall a cooling film is to be formed. According to the invention, the pattern is formed in at least one subregion of defined size of the inflow surface, from a plurality of identical isosceles triangles, which are defined by a minimum spacing (k) and by a mean diameter (a) of the inflow openings correlating to the minimum spacing (k). This procedure reduces the complexity of the design process.

Abstract: A combustion chamber assembly group, and a mounting method therefor, includes a combustion chamber for an engine that includes a curved combustion chamber wall extending along two spatial directions, and a combustion chamber shingle affixed at an inner side of the combustion chamber wall and having a shingle edge defining the outer contour of the shingle. For an at least sectional abutment of the shingle edge at the combustion chamber wall with a minimum clamping force in an operational state of the engine, the shingle is mounted to the combustion chamber wall in a mounting state in which the shingle at least at one section of the shingle edge has a curvature with respect to at least one of the spatial directions that differs from the curvature of the combustion chamber wall with respect to this spatial direction.

Abstract: A combustion chamber assembly for an engine with at least one tile component, on the cold side of which facing away from a combustion space, a positioning aid with at least two positioning elements, wherein a defined position relative to the combustion chamber component is predefined for the tile component via the contact of the at least two positioning elements on at least one contact face of the combustion chamber component in two spatial axes.

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 combustion chamber assembly for an engine, with a tile component fixed to a combustion chamber component and having a hot side facing a combustion space and a cold side facing away from the combustion space and facing towards the combustion chamber component, wherein the tile component on the cold side has at least four fixing elements each arranged eccentrically on the tile component for fixing the tile component to the combustion chamber component. The four base bodies are here oriented with their respective at least one side passage opening towards a reference point lying on a center line of the tile component, so that a respective cavity of the respective base body is open in the direction of the reference point.

Abstract: A plate-shaped structural component of a gas turbine with a base body that, at least in one edge area, is provided in one piece with a side bar that is embodied to ne substantially rectangular to the surface of the base body, wherein the base body has a different thickness than the side bar, wherein a supporting body, which is connected in one piece with the base body and the side bar and is provided with a substantially triangular cross section, is arranged between the side bar and the base body, being provided with multiple slit-like recesses.

Abstract: The present invention relates, in particular, to an engine component, having at least one cooling duct, which extends from an inlet opening on a first side of the engine component to an outlet opening on a second side of the engine component through the engine component. A second, inner duct wall of the cooling duct has a recess relative to an opposite first, outer duct wall in a region of the cooling duct situated between the inlet opening and the outlet opening, said recess being of V-shaped design in a cross-sectional view through the cooling duct and in a direction of view along a direction of extent of the cooling duct.

Abstract: A combustion chamber assembly for an engine with at least one tile component, on the cold side of which facing away from a combustion space, a positioning aid with at least two positioning elements, wherein a defined position relative to the combustion chamber component is predefined for the tile component via the contact of the at least two positioning elements on at least one contact face of the combustion chamber component in two spatial axes.

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: A combustion chamber assembly group, and a mounting method therefor, includes a combustion chamber for an engine that includes a curved combustion chamber wall extending along two spatial directions, and a combustion chamber shingle affixed at an inner side of the combustion chamber wall and having a shingle edge defining the outer contour of the shingle. For an at least sectional abutment of the shingle edge at the combustion chamber wall with a minimum clamping force in an operational state of the engine, the shingle is mounted to the combustion chamber wall in a mounting state in which the shingle at least at one section of the shingle edge has a curvature with respect to at least one of the spatial directions that differs from the curvature of the combustion chamber wall with respect to this spatial direction.

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 gas turbine combustion chamber with a combustion chamber wall and with at least one shingle that is fastened to the combustion chamber wall at a distance from the same, wherein the shingle has a shingle edge that abuts the combustion chamber wall, wherein the combustion chamber wall and the combustion chamber shingle respectively have at least one mixed air hole, and wherein a tubular fastening element provided with a ring flange is inserted through the mixed air hole of the combustion chamber wall, abutting the side of the combustion chamber wall that is facing away from the combustion chamber shingle with the ring flange, characterized in that, at its exterior side, the fastening element is provided with first snap-in means that are in mesh with second snap-in means that are formed at a tubular snap-in element that braces the combustion chamber shingle against the combustion chamber wall.

Abstract: A plate-shaped structural component of a gas turbine with a base body that, at least in one edge area, is provided in one piece with a side bar that is embodied to ne substantially rectangular to the surface of the base body, wherein the base body has a different thickness than the side bar, wherein a supporting body, which is connected in one piece with the base body and the side bar and is provided with a substantially triangular cross section, is arranged between the side bar and the base body, being provided with multiple slit-like recesses.

Abstract: The invention relates to a combustion chamber shingle of a gas turbine combustion chamber with at least one securing bolt that is configured in one piece with the combustion chamber shingle, characterized in that the securing bolt is provided in one piece with a bolt disc that is arranged at a distance from the combustion chamber shingle, and that a free end area of the securing bolt is provided with a thread, as well as a combustion chamber wall for attaching the combustion chamber shingle by means of a nut.

Abstract: A gas turbine combustion chamber with a combustion chamber wall and with at least one shingle that is fastened to the combustion chamber wall at a distance from the same, wherein the shingle has a shingle edge that abuts the combustion chamber wall, wherein the combustion chamber wall and the combustion chamber shingle respectively have at least one mixed air hole, and wherein a tubular fastening element provided with a ring flange is inserted through the mixed air hole of the combustion chamber wall, abutting the side of the combustion chamber wall that is facing away from the combustion chamber shingle with the ring flange, characterized in that, at its exterior side, the fastening element is provided with first snap-in means that are in mesh with second snap-in means that are formed at a tubular snap-in element that braces the combustion chamber shingle against the combustion chamber wall.

Abstract: A gas turbine combustion chamber with a combustion chamber wall and with at least one shingle that is fastened to the combustion chamber wall at a distance from the same, wherein the shingle has a shingle edge that abuts the combustion chamber wall, wherein the combustion chamber wall and the combustion chamber shingle respectively have at least one mixed air hole, and wherein a tubular fastening element provided with a ring flange is inserted through the mixed air hole of the combustion chamber wall, abutting the side of the combustion chamber wall that is facing away from the combustion chamber shingle with the ring flange, characterized in that, at its exterior side, the fastening element is provided with first snap-in means that are in mesh with second snap-in means that are formed at a tubular snap-in element that braces the combustion chamber shingle against the combustion chamber wall.

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.