Abstract: The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall including a tile carrier, on which wall tiles are mounted at a distance to form an impingement cooling gap, where the tile carrier has impingement cooling holes and the tile is provided with effusion holes, where the tile has on its side facing the tile carrier a surface structure which raises from the surface of the tile and extends in the direction of the tile carrier.

Abstract: A device for cooling a wall of a component of a gas turbine, where a flow passes parallel to the wall, having at least one inflow duct provided in the wall that issues into a recess of the wall for supplying cooling air, wherein a center axis of the inflow duct is aligned to an impact wall of double-convex design inside the recess.

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.

Abstract: A washer of a combustion chamber tile of a gas turbine having a round disk-shaped basic body provided with a central recess and a flat contact surface arranged on a first side of the washer, wherein several groove-like air ducts are provided on a second side that extend from a circumferential rim of the washer radially relative to the center axis of the washer, and in the center area of the washer in the axial direction.

Abstract: A gas turbine combustion chamber, including at least one combustion chamber wall in which mixed air holes are formed in a predefined area that extends around the combustion chamber in a ring-shaped manner with respect to the central axis of the combustion chamber in a central area of the same, characterized in that the combustion chamber wall has a greater thickness in the ring-shaped area of the mixed air holes than in the areas that are not provided with mixed air holes.

Abstract: An auxetic locking structure can be used as a mechanism for securing two or more members in an assembly or other system. The locking structure has void patterns on its exterior surface which permit the locking structure to reduce its outer diameter upon loading in an axial direction. Once the structure has been sufficiently loaded and the diameter has been sufficiently reduced, the locking structure may be positioned within a bore of an article, the axial load is then reduced, thus causing the locking structure to expand and engage the bore of the article. The locking structure and article are now secured to one another creating an improved assembly.

Abstract: A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burners 106 distributed around a circumference of the gas turbine. Several segment-like head segments are arranged over the circumference in equal number to the number of burners and extend in the radial direction between the inner combustion chamber wall and the outer combustion chamber wall and in the circumferential direction between radial planes formed by the burner axes.

Abstract: Void structures, systems and devices with void structures, and methods of fabricating void structures are disclosed. A void structure is disclosed with a repeating elongated-aperture pattern designed to provide negative Poisson's Ratio behavior under macroscopic stress and strain loading. The pattern can include horizontal and vertical elliptically shaped apertures that are arranged on horizontal and vertical lines in a way that the lines are equally spaced in both dimensions. The centers of each aperture is on a crossing point of two of the lines. The vertical and horizontal elliptically shaped apertures alternate on the vertical and horizontal lines such that any vertical aperture is surrounded by horizontal apertures along the lines (and vice versa), and the next vertical apertures are found on both diagonals. The voids can also act as cooling and/or damping holes and, due to their arrangement, also as stress reduction features.

Abstract: A low porosity sheet material comprising an arrangement of elongated void structures, each of the elongated void structures including one or more substructures, a first plurality of first elongated void structures and a second plurality of second elongated void structures, each of the first and second elongated void structures having a major axis and a minor axis, the major axes of the first elongated void structures being perpendicular to the major axes of the second elongated void structures, the first and second pluralities of elongated void structures being arranged in an array of rows and columns, each of the rows and each of the columns alternating between the first and the second elongated void structures, wherein a porosity of the elongated void structures is below about 10%.

Abstract: A combustion chamber head of a gas turbine has a base plate 113 provided with a centric recess 121 in which at least one burner 106 is arranged, with the base plate 113 being connected to walls of the combustion chamber 108 and to a burner seal 116 sealing the burner 106 towards the rim of the recess 121. The burner seal 116 is arranged upstream of the base plate 113 and can be brought into contact with a collar 118 provided on the base plate 113 and forming the rim of the centric recess 121. A holding element 117 of the burner seal 116 is formed as a ring and arranged upstream of the burner seal 116 and engages with at least one projection 114 of the base plate 113 in a tension-free state.

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 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.

Abstract: A washer of a combustion chamber tile of a gas turbine having a round disk-shaped basic body provided with a central recess and a flat contact surface arranged on a first side of the washer, wherein several groove-like air ducts are provided on a second side that extend from a circumferential rim of the washer radially relative to the center axis of the washer, and in the center area of the washer in the axial direction.

Abstract: The present invention relates to a gas-turbine combustion chamber with a combustion chamber wall, on which tiles are arranged, and with a recess for passing through an igniter plug, said recess extending through the combustion chamber wall and a tile, with the tile being provided with a tubular projection surrounding the recess and extending from that side of the tile facing away from a combustion chamber interior.

Abstract: The present invention relates to a gas-turbine combustion chamber having a head plate and an outer and an inner combustion chamber wall, characterized in that the combustion chamber is designed in one piece by means of a DLD method, or is assembled from segments which are welded to one another and manufactured in one piece by means of a DLD method, as well as to a method for manufacturing the gas-turbine combustion chamber.

Abstract: A gas-turbine combustion chamber has a cooling-air supply device delivering cooling air to a combustion chamber wall 6 to be cooled. The cooling-air supply device includes at least one air-supply duct 8 which, in respect of its flow axis, is arranged vertically to the combustion chamber wall 6, with the air-supply duct 8 being flow-connected to at least one cooling duct 9. The air-supply duct 8 forms a throttle and has a smaller diameter than the cooling duct 9. The cooling duct 9 issues at a shallow angle, relative to its flow axis, to the surface of the combustion chamber wall 6 in a recess 10 of the combustion chamber wall 6, with the cooling duct 9 being designed to impart a swirl to the air flowing through it.

Abstract: A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the combustion chamber by a heat shield (5). A base plate (2) is arranged at a certain distance from the heat shield (5) and the base plate (2) is provided with several openings (6) in its rim area for passing the cooling air. Center axes (17) of the openings (6) are inclined at a shallow angle (?) relative to the combustion chamber wall (4).

Abstract: A method for the arrangement of effusion holes and impingement cooling holes in a combustion chamber wall including: distribution of the effusion holes in the surface to be cooled in accordance with pattern, diameter and dimension selections made; distribution of the impingement cooling holes in accordance with pattern, diameter and dimension selections made; checking of the number of matches and their spacing from one another, taking into account the component and assembly tolerances; comparison with the permitted number and their minimum spacing; and, if quality requirements are not met, taking corrective actions, including selecting alternative diameters and patterns.

Abstract: An auxetic locking structure can be used as a mechanism for securing two or more members in an assembly or other system. The locking structure has void patterns on its exterior surface which permit the locking structure to reduce its outer diameter upon loading in an axial direction. Once the structure has been sufficiently loaded and the diameter has been sufficiently reduced, the locking structure may be positioned within a bore of an article, the axial load is then reduced, thus causing the locking structure to expand and engage the bore of the article. The locking structure and article are now secured to one another creating an improved assembly.

Abstract: The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall including a tile carrier, on which wall tiles are mounted at a distance to form an impingement cooling gap, where the tile carrier has impingement cooling holes and the tile is provided with effusion holes, where the tile has on its side facing the tile carrier a surface structure which raises from the surface of the tile and extends in the direction of the tile carrier.