Abstract: The invention relates to a three-dimensional screen printing method for producing a green part from printing material for a powder metallurgical component, wherein the printing material contains a fraction of powder, more particularly metal powder or ceramic powder, and binder or consists of these materials, characterized in that a screen printing mask has a screen printing structure having openings for pressing the printing material through, the openings being partly undulate so that the green part at least partly has a three-dimensional undulate structure and/or undulate edges.

Abstract: A rotor blade assembly group for an engine with at least one blade carrier having at least one rotor blade that is provided with multiple rotor blades along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blade, the carrier section comprises a connection area at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the stiffening element is arranged at a first face side of the blade carrier, and the second stiffening element is arranged at a second face side that is facing away from the first face side. The blade carrier is formed in a ring-segment-shaped or disc-segment-shaped-manner.

Abstract: A rotor blade assembly group for an engine with a ring-shaped or disc-shaped blade carrier having multiple rotor blades that are provided along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blades, the carrier section comprises a connection area, at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the first stiffening element is arranged at a first face side of the blade carrier and the second stiffening element is arranged at a second face side that is facing away from the first face side. The first and second stiffening elements are connected to the connection area of the blade carrier and in addition are connected to each other.

Abstract: A rotor blade assembly group for an engine includes a blade carrier with rotor blades along a circle line about a central axis of the group, wherein the blade carrier has a carrier section extending radially inwards toward a central axis, the carrier section includes a connecting area at which a stiffening structure with a stiffening element is fixedly attached, and the stiffening element is arranged at a face side of the blade carrier. The stiffening element is axially secured at the face side of the blade carrier via a barrier element, that (a) is affixed radially further inside at or to a flange section of the blade carrier, or (b) is formed in front of the blade carrier and engages around the stiffening element with at least one barrier element section.

Abstract: A sealing element for a turbomachine, in particular an aircraft engine, with a housing for the at least one rotating structural component is provided. The sealing element comprises a honeycomb structure for arrangement inside the housing, wherein the honeycomb structure extends in a first direction, wherein support structures are connected to the honeycomb structure in one piece and/or in a pattern-like manner and extend at least partially into the honeycomb structure, and the support structures extend at least partially or completely in a second direction that is different from the first direction. The support structures have planar portions, which are formed by at least one partially or completely closed cell together with the honeycomb structure.

Abstract: A gas turbine drive shaft arrangement, comprising: a hollow compressor drive shaft, a first hollow turbine drive shaft for driving a first turbine stage and a second hollow turbine drive shaft for driving a second turbine stage, wherein the compressor drive shaft has a spline on an internal surface that is meshed with a spline on an external surface of the first hollow turbine drive shaft, the first turbine drive shaft further comprising a spline on an internal surface thereof that is meshed with a spline on an external surface of the second hollow turbine drive shaft.

Abstract: A rotor blade assembly group for an engine with a ring-shaped or disc-shaped blade carrier having multiple rotor blades that are provided along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blades, the carrier section comprises a connection area, at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the first stiffening element is arranged at a first face side of the blade carrier and the second stiffening element is arranged at a second face side that is facing away from the first face side. The first and second stiffening elements are connected to the connection area of the blade carrier and in addition are connected to each other.

Abstract: A rotor blade assembly group for an engine with at least one blade carrier having at least one rotor blade that is provided with multiple rotor blades along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blade, the carrier section comprises a connection area at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the stiffening element is arranged at a first face side of the blade carrier, and the second stiffening element is arranged at a second face side that is facing away from the first face side. The blade carrier is formed in a ring-segment-shaped or disc-segment-shaped-manner.

Abstract: A sealing element for a rotating sealing system of a turbomachine is provided. The sealing element, if installed in the sealing system according to the intended use, can be rotated around a rotational axis of the turbomachine. The sealing element comprises a ring-shaped sealing lip that has a central point through which the rotational axis extends if the sealing element is installed in the sealing system according to the intended use, wherein the sealing lip has at least one recess, and at least one rubbing element that is arranged at the sealing lip, wherein the at least one rubbing element is arranged inside the at least one recess and projects at least partially beyond the outer contour of the sealing lip in the radial and/or the axial direction with respect to the rotational axis. The at least one rubbing element has a plurality of layers of a rubbing material.

Abstract: A sealing element for a turbomachine, in particular an aircraft engine, with a housing for the at least one rotating structural component is provided. The sealing element comprises a honeycomb structure for arrangement inside the housing, wherein the honeycomb structure extends in a first direction, wherein support structures are connected to the honeycomb structure in one piece and/or in a pattern-like manner and extend at least partially into the honeycomb structure, and the support structures extend at least partially or completely in a second direction that is different from the first direction. The support structures have planar portions, which are formed by at least one partially or completely closed cell together with the honeycomb structure.

Abstract: A gas turbine drive shaft arrangement, comprising: a hollow compressor drive shaft, a first hollow turbine drive shaft for driving a first turbine stage and a second hollow turbine drive shaft for driving a second turbine stage, wherein the compressor drive shaft has a spline on an internal surface that is meshed with a spline on an external surface of the first hollow turbine drive shaft, the first turbine drive shaft further comprising a spline on an internal surface thereof that is meshed with a spline on an external surface of the second hollow turbine drive shaft.

Abstract: An arrangement (30, 80) for sealing a shaft (40, 60, 90, 110) in a casing (31, 81) by a hydraulic seal (50, 70, 100, 120) includes at least one essentially annular, radially inwardly open cavity (51, 71, 101, 121) and at least one essentially annular, radially outwardly directed sealing element (54, 74, 102, 122) which projects into the cavity (51, 71, 101, 121). To provide a hydraulic shaft seal, in which swirl and friction losses in the sealing medium are low and no leakage occurs, the hydraulic seal (50, 70, 100, 120) is arranged on the inner side (42, 62, 92) or on the outer side (111) of the shaft (40, 60, 90, 110) and the cavity (51, 71, 101, 121) or the sealing element (54, 74, 102, 122) of the hydraulic seal (50, 70, 100, 120) is connected to a wall (32, 82) of the casing (31, 81).

Abstract: A labyrinth sealing ring for a labyrinth seal of a turbine disk 1 of a gas turbine includes a metallic annular element 3 with at least one annular sealing lip 4. The sealing lip 4 is provided with at least one groove 5 on its circumference which is essentially arranged in the radial direction.

Abstract: A labyrinth sealing ring for a labyrinth seal of a turbine disk 1 of a gas turbine includes a metallic annular element 3 with at least one annular sealing lip 4. The sealing lip 4 is provided with at least one groove 5 on its circumference which is essentially arranged in the radial direction.

Abstract: An arrangement (30, 80) for sealing a shaft (40, 60, 90, 110) in a casing (31, 81) by a hydraulic seal (50, 70, 100, 120) includes at least one essentially annular, radially inwardly open cavity (51, 71, 101, 121) and at least one essentially annular, radially outwardly directed sealing element (54, 74, 102, 122) which projects into the cavity (51, 71, 101, 121). To provide a hydraulic shaft seal, in which swirl and friction losses in the sealing medium are low and no leakage occurs, the hydraulic seal (50, 70, 100, 120) is arranged on the inner side (42, 62, 92) or on the outer side (111) of the shaft (40, 60, 90, 110) and the cavity (51, 71, 101, 121) or the sealing element (54, 74, 102, 122) of the hydraulic seal (50, 70, 100, 120) is connected to a wall (32, 82) of the casing (31, 81).

Abstract: On a hydraulic shaft sealing arrangement for high-temperature applications, a heat protection ring (21) and an air chamber (22) are arranged before the annulus (8) containing the sealing medium (10) for thermal insulation, while spacers (16, 17) for the generation of a pumping action are provided in the annulus continuously supplied with fresh sealing medium (oil) to accelerate liquid transport. The hazard of coking and oil carbon deposition is thereby minimized. A split design of the annulus with an inserted annular ring also provides for an improved hydraulic shaft sealing arrangement optimized for weight, overall height, manufacture and assembly time.

Abstract: On a hydraulic shaft sealing arrangement for high-temperature applications, a heat protection ring (21) and an air chamber (22) are arranged before the annulus (8) containing the sealing medium (10) for thermal insulation, while spacers (16, 17) for the generation of a pumping action are provided in the annulus continuously supplied with fresh sealing medium (oil) to accelerate liquid transport. The hazard of coking and oil carbon deposition is thereby minimized. A split design of the annulus with an inserted annular ring also provides for an improved hydraulic shaft sealing arrangement optimized for weight, overall height, manufacture and assembly time.