Abstract: The invention relates to a method for determining individual vectors for open-loop and/or closed-loop control of at least one energy beam of a layering apparatus, comprising at least the steps of: providing layer data characterizing at least one component layer of a component to be additively manufactured, on the basis of the layer data, determining individual vectors, according to which at least one energy beam is to be moved relative to a construction and joining zone of the layering apparatus in order to solidify a material powder selectively to the component layer, determining at least one node point of a plurality of individual vectors, and adapting at least one property of at least one individual vector of the at least one node point, the at least one property being selected from a group comprising spatial orientation, radiation sequence in relation to at least one other individual vector, and vector length.

Abstract: The present invention relates to a lever for adjusting an adjustable vane of a turbomachine, wherein the lever has a fulcrum for the rotatable mounting of the lever about an axis of rotation, a first load arm with a first adjusting connection point for at least indirect connection to an adjustable vane and a first force arm with a first actuating connection point for connection to an adjusting device, wherein the lever further has a first strut, which connects the first adjusting connection point and the first actuating connection point to each other and thereby extends in an arc-shaped manner about the axis of rotation.

Abstract: An example hybrid power system includes a mobile platform comprising: a generator set comprising: a reciprocating engine configured to convert natural gas into rotational mechanical energy; and a generator configured to convert rotational mechanical energy sourced from the reciprocating engine into electrical energy; an electrical energy storage system (ESS) configured to store electrical energy; an electrical motor configured to convert electrical energy sourced from a combination of the generator set and the ESS into rotational mechanical energy; and a pump configured to operate using rotational mechanical energy sourced from the electrical motor.

Abstract: A method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.

Abstract: The present invention relates to a guide vane assembly for a turbomachine, having an adjustable vane, which can be adjusted in order to alter an angle of attack, and an adjusting element, by way of which the adjustable vane can be adjusted, wherein the adjustable vane and the adjusting element are connected to each other in a connecting region, and wherein the adjustable vane and the adjusting element adjoin each other in the connecting region at a break edge.

Abstract: The invention relates to a rotor for integration in a turbomachine, with a rotor base body, wherein, on the rotor base body in a rotor outer space of the rotor, at least one blade element or airfoil is mounted, wherein the rotor base body extends in an axial direction of the rotor and comprises a connecting section, which extends in an axial direction of the rotor for connection to at least one further rotor and separates the rotor outer space from a rotor inner space of the rotor, wherein the connecting section comprises, in the axial direction, at a front side, preferably in the axial direction at a downstream-lying front side, a balancing flange, wherein the balancing flange is configured for compensating an imbalance of the rotor and extends in the radial direction in the rotor outer space, at least in sections.

Abstract: An adjustable guide vane for a compressor, in particular a high-pressure compressor, of a gas turbine, in particular an aircraft gas turbine is described, said vane comprising a radially outer storage section, a radially inner storage section, and a vane section, which extends in the radial direction between the outer storage section and the inner storage section, wherein the outer and the inner storage sections are designed in such a way that the adjustable guide vane can be taken up rotatably about a vane axis in the compressor, and wherein the radially inner storage section is designed like a journal (cone-shaped) and has a casing surface that revolves relative to the vane axis, said surface being of convex shape. In this way, it is provided that the radius of curvature of the convex casing surface is at least double the maximum diameter of the storage section.

Abstract: The invention relates to an airfoil as well as to a method for producing an airfoil for a turbomachine, comprising a leading edge and a trailing edge joined to each other by a suction side and a pressure side and which, in at least one region, extends in a curved manner from an airfoil root to an airfoil tip, wherein the airfoil tip has a squealer tip, which is arranged at the airfoil tip.

Abstract: The invention relates to a method and a set of balance weights for balancing a rotor particularly of a turbomachine, on which a plurality of balance weights, which are distributed over the periphery, can be arranged for balancing an imbalance. A set of balance weights, in particular plate-shaped weights, with a predetermined number of groups of balance weights, is used for balancing the rotor. Each of the balance weights of every group of balance weights has an identical weight that is assigned to this group and a shape assigned to this group, which differs in basic shape and/or thickness of the balance weights from the balance weights of the other groups.

Abstract: A gas turbine compressor has a flow duct wall disposed radially opposite to an airfoil tip and has a circumferential groove having an upstream groove edge and a downstream groove edge, the circumferential groove having a web having a radial cutback.

Abstract: The invention relates to an airfoil as well as to a method for producing an airfoil for a turbomachine, comprising a leading edge and a trailing edge joined to each other by a suction side and a pressure side and which, in at least one region, extends in a curved manner from an airfoil root to an airfoil tip, wherein the airfoil tip has a squealer tip, which is arranged at the airfoil tip.

Abstract: The invention relates to a compression system for a gas turbine, in particular for an aircraft gas turbine, wherein the compression system comprises a flow duct. The flow duct includes cross-sectional areas that are aligned perpendicular to the axial direction along the flow duct length and have the respective predetermined sizes, where the inlet cross-sectional area has a size that is 15.3 to 16.1 times a size of the outlet cross-sectional area, and/or a cross-sectional area arranged at a distance of 40% of the flow duct length from the inlet cross-sectional area has a size that is 5.0 to 5.2 times the size of the outlet cross-sectional area.

Abstract: The invention relates to a guide vane assembly as well as to a method for mounting a guide vane assembly of a turbomachine, including a number of adjustable guide vanes, the guide vane platform of which has a guide vane journal that is mounted in a receiving opening of a housing of the turbomachine, wherein a guide vane head of the guide vane has a bearing pin, which is mounted on an inner ring arranged on a rotor of the turbomachine. In the method, a guide vane journal, which is arranged on a guide vane platform of a guide vane, is brought into a receiving opening of a housing, which is arranged radially with respect to a rotor axis of the turbomachine, and an inner ring is provided on a rotor of the turbomachine.

Abstract: The present invention relates to an aircraft having at least one wing, on which at least one propulsion unit is arranged, comprising at least one heat engine, especially a gas turbine, as well as an exhaust gas passage for conducting exhaust gas of the heat engine into and inside the wing.

Abstract: The invention relates to a monitoring system for a gas turbine, in particular for an aircraft engine. The monitoring system comprises at least one borescope device that is able to be mounted in a borescope opening of a gas turbine housing and has a housing, in which at least one optical sensor device for acquiring images of at least one inner region of the gas turbine is arranged, and an evaluation device that is able to be connected to the at least one borescope device in order to exchange data and is designed to inspect the at least one inner region for the presence of a fault on the basis of the at least one image acquired by way of the sensor device. The invention furthermore relates to a borescope device to an evaluation device and to a gas turbine.

Abstract: The invention relates to a seal carrier for a turbomachine, in particular a gas turbine, having a carrier base and at least one seal body, wherein the at least one seal body is connected to the carrier base, and wherein the at least one seal body is formed by a plurality of cavities arranged next to one another, in particular uniformly, in the peripheral direction and in the axial direction, wherein the cavities extend out from the carrier base in the radial direction and are delimited by a cavity wall. According to the invention, the seal body has a plurality of damping portions which are designed to locally damp or disrupt the flow of force in the seal body, wherein the carrier base is continuous in the region of the damping portions.

Abstract: The invention relates to a rotor for a turbomachine, having at least one blade and having at least one rotor main part, which has at least one recess, in which a blade root of the least one blade is interlockingly received, wherein the blade root comprises at least one depression, in which at least one protrusion of the at least one rotor main part which protrusion delimits the at least one recess in regions is received, wherein the at least one depression is delimited by a first delimiting face on the blade root side and the at least one protrusion is delimited by a second delimiting face on the rotor main part side. At least the first delimiting face has at least one elevation which narrows a gap at least in regions, which extends between the first delimiting face and the second delimiting face.

Abstract: A regulating method for a charged internal combustion engine, wherein an operating point of the compressor is adjusted in a compressor map by a compressor position regulator based on a throttle valve regulation deviation in that both a first manipulated variable for actuating the compressor bypass valve as well as a second manipulated variable for actuating the turbine bypass valve are calculated by the compressor position regulator. The operating point of the compressor is corrected by a correction regulator on the basis of an air mass regulation deviation in that both a first correction variable for correcting the first manipulated variable as well as a second correction variable for correcting the second manipulated variable are calculated by the correction regulator.

Abstract: The invention relates to a guide vane ring for a turbomachine comprising at least one guide vane, at least one bearing body, and at least two inner ring segments. The guide vane has a bearing journal that is arranged in a in form-fitting manner in a bearing bush of the at least one bearing body. The at least two inner ring segments have on their respective outer radial faces a guide channel running along a circumferential direction of the guide vane ring for receiving the bearing body, into which project at least two opposite-lying guide projections of the inner ring segments, said projections running along the circumferential direction of the guide vane ring. The bearing bodyis arranged in the guide channel of the inner ring segments, and the at least two guide projections of the inner ring segments engage in at least two guide grooves of the bearing body.