Abstract: The invention relates to a guide vane system for a turbomachine with at least one guide vane, which can be rotatably mounted around an adjustment axis and is arranged with a radially inner end region in a corresponding recess of an inner ring, wherein the arrangement of the guide vane on the inner ring is secured by a securing element in a form-fitting manner. For an especially advantageous securing of this arrangement, it is provided that the securing element is designed as an oblong element, which is arranged at least in a recess and/or through-opening of the radially inner end region of the guide vane directed in the peripheral direction of the turbomachine and is arranged at least in a recess and/or through-opening of the inner ring directed in the peripheral direction of the turbomachine. In addition, the invention relates to a turbomachine, in particular an aircraft engine, and to a method for assembling a guide vane system.

Abstract: An inner ring according to the invention or an inner ring segment according to the invention for an adjustable guide vane assembly comprises a plurality of uptakes, each for the bearing of an adjustable guide vane. The uptakes here each form an essentially ellipsoidally shaped uptake space for a guide vane head of the respective guide vane. A guide vane according to the invention for an adjustable guide vane assembly has a blade body and a guide vane head. The guide vane head is essentially ellipsoidal in shape and is equipped to be accommodated pivotably in an uptake of an inner ring or inner ring segment of the guide vane assembly.

Abstract: The invention relates to a seal (10) for sealing a gap between a stationary component and a moving component, in particular for sealing a radial gap between a rotor and a stator of a turbomachine, comprising at least one sealing segment (12) with an edge zone (14) facing the gap, whereby the seal (10) is produced layer-by-layer by a free-forming method, in particular a generative or additive method. A plurality of pre-defined weak regions (16) is formed in the edge zone (14) of the sealing segment (12). In addition, the invention relates to a method for producing a seal (10) as well as a turbomachine.

Abstract: An inner ring according to the invention or an inner ring segment according to the invention for an adjustable guide vane assembly comprises a plurality of uptakes, each for the bearing of an adjustable guide vane. The uptakes here each form an essentially ellipsoidally shaped uptake space for a guide vane head of the respective guide vane. A guide vane according to the invention for an adjustable guide vane assembly has a blade body and a guide vane head. The guide vane head is essentially ellipsoidal in shape and is equipped to be accommodated pivotably in an uptake of an inner ring or inner ring segment of the guide vane assembly.

Abstract: The invention relates to a guide vane system for a turbomachine with at least one guide vane, which can be rotatably mounted around an adjustment axis and is arranged with a radially inner end region in a corresponding recess of an inner ring, wherein the arrangement of the guide vane on the inner ring is secured by a securing element in a form-fitting manner. For an especially advantageous securing of this arrangement, it is provided that the securing element is designed as an oblong element, which is arranged at least in a recess and/or through-opening of the radially inner end region of the guide vane directed in the peripheral direction of the turbomachine and is arranged at least in a recess and/or through-opening of the inner ring directed in the peripheral direction of the turbomachine. In addition, the invention relates to a turbomachine, in particular an aircraft engine, and to a method for assembling a guide vane system.

Abstract: The present invention relates to a guide vane ring (1) for a turbomachine, having a plurality of rotatable guide vanes (3), and having an inner ring (5), wherein the inner ring (5) has a seal (17) for sealing a radial gap between the inner ring (5) and an opposite-lying rotor segment (7), and wherein the inner ring (5) comprises at least two inner ring segments (11). The inner ring (5) is produced from a material or has a material that has a heat expansion coefficient ? of less than 6*10?6 per Kelvin in a temperature range between at least 20 degrees Celsius and 90 degrees Celsius. In addition, the present invention relates to a turbomachine having at least one guide vane ring (1) according to the invention.

Abstract: The invention relates to a seal (10) for sealing a gap between a stationary component and a moving component, in particular for sealing a radial gap between a rotor and a stator of a turbomachine, comprising at least one sealing segment (12) with an edge zone (14) facing the gap, whereby the seal (10) is produced layer-by-layer by a free-forming method, in particular a generative or additive method. A plurality of pre-defined weak regions (16) is formed in the edge zone (14) of the sealing segment (12). In addition, the invention relates to a method for producing a seal (10) as well as a turbomachine.

Abstract: A method for repairing a guide blade segment fashioned as a twin guide blade segment within a guide blade composite element, the guide blades being formed from a nose segment and a rear edge segment, the method having identification, within a guide blade segment, of a non-repairable guide blade to be separated from the guide blade composite structure; separation of a non-repairable guide blade from a one repairable guide blade in a first plane of division; division of at least one separated guide blade in a second plane of division between the nose segment and the rear edge segment; reconditioning of the at least one repairable nose segment and/or rear edge segment; joining of a reconditioned and/or new nose segment to a reconditioned and/or new rear edge segment to form at least one guide blade; and joining of at least two guide blades to form a guide blade segment.

Abstract: A turbine engine is disclosed. A blade ring is surrounded by a housing wall, the housing wall being configured as an outer ring, and delimits therewith a gap, the gap being adjustable by deformation of the outer ring. The outer ring is concentrically surrounded by an adjusting element, opposite faces of the outer ring and the adjusting element having the contour of a truncated cone, and rolling bodies being positioned between the outer ring and the adjusting element, the rolling bodies being put at an oblique angle in relation to the axial direction in the radial direction and in the peripheral direction, making it possible for the adjusting element to be rotated in relation to the outer ring while simultaneously adjusting the gap.

Abstract: A method for repairing a guide blade segment fashioned as a twin guide blade segment within a guide blade composite element, the guide blades being formed from a nose segment and a rear edge segment, the method having identification, within a guide blade segment, of a non-repairable guide blade to be separated from the guide blade composite structure; separation of a non-repairable guide blade from a one repairable guide blade in a first plane of division; division of at least one separated guide blade in a second plane of division between the nose segment and the rear edge segment; reconditioning of the at least one repairable nose segment and/or rear edge segment; joining of a reconditioned and/or new nose segment to a reconditioned and/or new rear edge segment to form at least one guide blade; and joining of at least two guide blades to form a guide blade segment.

Abstract: A method for producing a blisk (bladed disk) or a bling (bladed ring) of a gas turbine is disclosed. The method includes the following steps: a) producing a turbine blade by joining a blade to an adapter element consisting of a metal material that is suitable for fusion welding, the adapter element being used to form a blade root of the turbine blade, and b) joining the turbine blade to a rotor disk consisting of a metal material that is suitable for fusion welding or to a rotor ring consisting of a metal material that is suitable for fusion welding in such a manner that the turbine blade is arranged on the outer periphery of the rotor disk or of the rotor ring. A component of a gas turbine or of a high-pressure or low-pressure compressor, especially a blisk or bling, and a turbine blade are also disclosed.

Abstract: A turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (20) with radially outwardly positioned ends (18) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins (24) allocated to the housing (20) and penetrating through the housing (20). The guide pins (24) extend at a slant relative to the radial direction and the axial direction of the turbomachine, wherein the ends (26) of the guide pins (24) reaching into the housing engage in forked elements (27) allocated to the radially outer ends (18) of the guide vane rings (11, 12).

Abstract: A turbine engine is disclosed. A blade ring is surrounded by a housing wall, the housing wall being configured as an outer ring, and delimits therewith a gap, the gap being adjustable by deformation of the outer ring. The outer ring is concentrically surrounded by an adjusting element, opposite faces of the outer ring and the adjusting element having the contour of a truncated cone, and rolling bodies being positioned between the outer ring and the adjusting element, the rolling bodies being put at an oblique angle in relation to the axial direction in the radial direction and in the peripheral direction, making it possible for the adjusting element to be rotated in relation to the outer ring while simultaneously adjusting the gap.

Abstract: A rotor of a turbo machine having a rotor base and a plurality of rotor blades. Each rotor blade is anchored in an axial groove of the rotor base body via the blade footing and the rotor blades are secured in the rotor base body by locking plates which are guided in ring grooves of the rotor base body and the rotor blades. The locking plates have a diamond-shaped outline, in particular in the form of a parallelogram or a rhombus such that in an insertion position, the locking plates can be inserted between the rotor base body and the rotor blades, and in an installation position, which is rotated with respect to this insertion position, they can be rotated into the ring grooves of the rotor base body and the rotor blades.

Abstract: The invention relates to a turbomachine, more particularly a gas turbine. The turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (20) with radially outwardly positioned ends (18) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins (24) allocated to the housing (20) and penetrating through the housing (20). According to the invention, the guide pins (24) extend approximately perpendicularly to the housing (20), wherein the ends (26) of the guide pins (24) reaching into the housing engage in forked elements (27) allocated to the radially outer ends (18) of the guide vane rings (11, 12).

Abstract: A rotor of a turbo machine having a rotor base and a plurality of rotor blades. Each rotor blade is anchored in an axial groove of the rotor base body via the blade footing and the rotor blades are secured in the rotor base body by locking plates which are guided in ring grooves of the rotor base body and the rotor blades. The locking plates have a diamond-shaped outline, in particular in the form of a parallelogram or a rhombus such that in an insertion position, the locking plates can be inserted between the rotor base body and the rotor blades, and in an installation position, which is rotated with respect to this insertion position, they can be rotated into the ring grooves of the rotor base body and the rotor blades.