Abstract: The present disclosure refers to a pallet made of plastics that includes a pallet body and a plurality of support feet, the pallet body having a length (l), a width (w) and a height (h1), the height (h1) extending between an imaginary lower plane (p2) and an imaginary upper plane (p1), wherein the pallet body comprises several body parts being arranged alternately in the upper plane (p1) and the lower plane (p2) along the direction of the width (w), thereby forming grooves extending in the direction of the length (l), wherein at least in one of the grooves several ribs extending in direction of the width (w) are arranged.

Abstract: An aerofoil for a turbine blade, having a leading edge onto which a hot gas can flow and from which a suction-side wall and a pressure-side wall extend to a trailing edge of the aerofoil, the aerofoil extending in a direction transverse thereto from a root-side end having an aerofoil height of 0% to a tip-side end having an aerofoil height of 100%, and having at least two rows of cooling holes arranged along the leading edge, which cooling holes are at a mutual spacing which can be measured perpendicularly to the leading edge. In order to provide a turbine blade which can be used, with reduced cooling complexity, for additional reliable cooling of the leading edge in various operating conditions, the at least two rows of cooling holes are arranged at least in part in a wavy line along the leading edge.

Abstract: An aerofoil for a turbine blade, having a leading edge onto which a hot gas can flow and from which a suction-side wall and a pressure-side wall extend to a trailing edge of the aerofoil, the aerofoil extending in a direction transverse thereto from a root-side end having an aerofoil height of 0% to a tip-side end having an aerofoil height of 100%, and having at least two rows of cooling holes arranged along the leading edge, which cooling holes are at a mutual spacing which can be measured perpendicularly to the leading edge. In order to provide a turbine blade which can be used, with reduced cooling complexity, for additional reliable cooling of the leading edge in various operating conditions, the at least two rows of cooling holes are arranged at least in part in a wavy line along the leading edge.

Abstract: A cast turbine blade having a platform and hollow blade airfoil arranged thereon, wherein the blade airfoil has a pressure-side blade wall and a suction-side blade wall that extend, along a centrally arranged curved profile centerline, from a common leading edge to a common trailing edge, and having a transition, with an outer contour profile, between the blade airfoil and the platform. The blade walls each have a locally determined blade wall thickness, wherein the turbine blade has, internally, a contour profile that partially matches the outer contour profile of the transition such that the region of the transition has an essentially constant blade wall thickness. In the transition, the contour profile at a surface section of the blade airfoil facing the leading edge is such that the blade wall thickness is increased there in comparison to the blade wall thickness of the transition away from the leading edge.

Abstract: A cast turbine blade having a platform and hollow blade airfoil arranged thereon, wherein the blade airfoil has a pressure-side blade wall and a suction-side blade wall that extend, along a centrally arranged curved profile centerline, from a common leading edge to a common trailing edge, and having a transition, with an outer contour profile, between the blade airfoil and the platform. The blade walls each have a locally determined blade wall thickness, wherein the turbine blade has, internally, a contour profile that partially matches the outer contour profile of the transition such that the region of the transition has an essentially constant blade wall thickness. In the transition, the contour profile at a surface section of the blade airfoil facing the leading edge is such that the blade wall thickness is increased there in comparison to the blade wall thickness of the transition away from the leading edge.

Abstract: A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant.

Abstract: A hollow blade body for a hollow blade, has a blade wall which has a pressure side which has at least one first blade connection element on the inner side thereof, and a suction side which has at least one second blade connection element diametrically opposite to the first blade connection element on the inner side thereof, wherein the first blade connection element can be engaged with at least one first rib connection element which is arranged on a first longitudinal end of an insertion rib, and the second blade connection element can be engaged with at least one second rib connection element which is arranged on a second longitudinal end of the insertion rib facing away from the first longitudinal end in such a way that the insertion rib is fixed on the hollow blade body and effects a stiffening of the hollow blade.

Abstract: A component which can be subjected to hot gas for a gas turbine, the component having at least one wall, which includes a first surface as far as an edge, the first surface for delimiting a hot gas flow path of the gas turbine, and which includes a second surface, which adjoins the edge and is arranged transversely to the first surface. A groove for receiving a sealing element is arranged in the second surface and extends at least partially along the edge at a distance from the edge. The groove includes a groove base lying opposite the groove opening and two mutually facing side walls which adjoin the groove base and extend along the edge. At least one of the side walls has at least one groove-shaped recess.

Abstract: A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant.

Abstract: An energy absorber for damping the impact upon the body of a motor vehicle includes energy absorbing bodies that include successively arranged support walls with a number of energy absorbing structural elements that are each separately arranged at the support wall and are firmly connected to the support wall. Upon impact, each of the structural elements absorb energy by moving towards an opposite support wall while adjoining neighboring structural element until the structural elements are compacting.

Abstract: An energy absorber for damping the impact upon the body of a motor vehicle includes energy absorbing bodies that include successively arranged support walls with a number of energy absorbing structural elements that are each separately arranged at the support wall and are firmly connected to the support wall. Upon impact, each of the structural elements absorb energy by moving towards an opposite support wall while adjoining neighboring structural element until the structural elements are compacting.