Abstract: A bearing chamber housing for supporting a shaft of a turbomachine is provided, the bearing chamber housing including an additively built-up housing wall which bounds an oil chamber of the bearing chamber housing radially outwardly relative to an axis of rotation of the shaft, the housing wall being built up with an oil duct which has an inlet opening toward the oil chamber for admission of oil from the oil chamber into the oil duct, and which has an outlet opening for discharging the oil from the oil duct, the outlet opening being located at a different axial position and at a different circumferential position than the inlet opening, considered relative to the axis of rotation of the shaft, and the oil duct having an extent with both an axial component and a circumferential component, at least over a portion thereof.

Abstract: A bearing chamber housing for supporting a shaft of a turbomachine is provided, the bearing chamber housing including an additively built-up housing wall which bounds an oil chamber of the bearing chamber housing radially outwardly relative to an axis of rotation of the shaft, the housing wall being built up with an oil duct which has an inlet opening toward the oil chamber for admission of oil from the oil chamber into the oil duct, and which has an outlet opening for discharging the oil from the oil duct, the outlet opening being located at a different axial position and at a different circumferential position than the inlet opening, considered relative to the axis of rotation of the shaft, and the oil duct having an extent with both an axial component and a circumferential component, at least over a portion thereof.

Abstract: The invention relates to a turbine blade which comprises at least one cavity that is defined by a wall with one or more surface discontinuities which preferably are selected from elevations, depressions and undercuts and preferably change at least one eigenmode of the blade. The blade may suitably be produced by a generative production method such as selective laser melting (SLM).

Abstract: A sealing ring for a turbomachine, in particular a compressor or turbine stage of a gas turbine is provided, the sealing ring having an, in particular at least partially honeycomb-like and/or integral, seal, in particular an abradable coating (13); a profile cross section of the sealing ring, which is in particular at least partially manufactured by a generative manufacturing process, varying in the circumferential direction, in particular at least in some regions continuously and/or non-continuously at one or more circumferential positions, in particular separation points.

Abstract: The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, comprising an additively built-up housing section and a cover, which, in each case referred to an axis of rotation of the shaft, connects axially to the housing section and has a radially extending collar, which collar axially bounds an oil space of the bearing chamber housing, wherein the cover is assembled with the housing section and is connected therewith via a weld.

Abstract: Disclosed are compounds within the scope of formula (II) or a salt or solvate thereof, medical uses involving them, and methods for their preparation

Abstract: The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, having an additively built-up housing wall and a cover of the oil chamber, wherein, in each case referred to an axis of rotation of the shaft, the housing wall bounds radially outwardly an oil chamber of the bearing chamber housing and the cover of the oil chamber disposed on an axial end of the housing wall axially bounds a region of the oil chamber; the region bounds radially inwardly an inner shell of the bearing chamber housing.

Abstract: Compounds of formula (II) or a pharmaceutically acceptable salt or solvate thereof, the medical uses thereof for diseases or medical conditions where the inhibition of the voltage-gated potassium channel Kv1.3 is beneficial, and methods for their preparation.

Abstract: Compounds of formula (II) or a pharmaceutically acceptable salt or solvate thereof, the medical uses thereof for diseases or medical conditions where the inhibition of the voltage-gated potassium channel Kv1.3 is beneficial, and methods for their preparation.

Abstract: Compounds of formula (II) or a pharmaceutically acceptable salt or solvate thereof, the medical uses thereof for diseases or medical conditions where the inhibition of the voltage-gated potassium channel Kv1.3 is beneficial, and methods for their preparation.

Abstract: A seal segment assembly for a turbomachine, in particular a gas turbine, including a first seal carrier and a second seal carrier, that are adjacently disposed in the circumferential direction, the first seal carrier having a first carrier base and at least one first sealing member that is joined to the first carrier base, and the second seal carrier having a second carrier base and at least one second sealing member that is joined to the second carrier base, the first sealing member and the second sealing member being formed by a plurality of cavities, that are adjacently disposed in the circumferential direction and in the axial direction, in particular evenly spaced, the cavities extending in the radial direction from the particular carrier base. The first carrier base and the second carrier base are intercouplable or are intercoupled in the circumferential direction by a mating connection assembly.

Abstract: The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, having an additively built-up housing wall and a cover of the oil chamber, wherein, in each case referred to an axis of rotation of the shaft, the housing wall bounds radially outwardly an oil chamber of the bearing chamber housing and the cover of the oil chamber disposed on an axial end of the housing wall axially bounds a region of the oil chamber; the region bounds radially inwardly an inner shell of the bearing chamber housing.

Abstract: The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, comprising an additively built-up housing section and a cover, which, in each case referred to an axis of rotation of the shaft, connects axially to the housing section and has a radially extending collar, which collar axially bounds an oil space of the bearing chamber housing, wherein the cover is assembled with the housing section and is connected therewith via a weld.

Abstract: Compounds of formula (II) or a pharmaceutically acceptable salt or solvate thereof, the medical uses thereof for diseases or medical conditions where the inhibition of the voltage-gated potassium channel Kv1.3 is beneficial, and methods for their preparation.

Abstract: A sealing ring for a turbomachine, in particular a compressor or turbine stage of a gas turbine is provided, the sealing ring having an, in particular at least partially honeycomb-like and/or integral, seal, in particular an abradable coating (13); a profile cross section of the sealing ring, which is in particular at least partially manufactured by a generative manufacturing process, varying in the circumferential direction, in particular at least in some regions uniformly and/or non-uniformly at one or more circumferential positions, in particular separation points.

Abstract: A seal carrier (63) for a turbomachine (60) which is assembled from seal carrier segments, is provided. The seal carrier segments each have a seal structure (1a, b) on the radially inward side. These seal structures (1a, b) are either interleaved in the circumferential direction (4) such that a cross-sectional plane containing the longitudinal axis (2) of the turbomachine (60) intersects both the first seal structure (1a) and the second seal structure (1b), or the seal structures (1a, b) rest against each another.

Abstract: The invention relates to a turbine blade which comprises at least one cavity that is defined by a wall with one or more surface discontinuities preferably selected from elevations, depressions and undercuts. The blade may suitably be produced by a generative production method.

Abstract: Disclosed are compounds within the scope of formula (II) or a salt or solvate thereof, medical uses involving them, and methods for their preparation

Abstract: A twist prevention system for turbomachinery is disclosed. The twist prevention system has a first ring segment pair with a first radially inner ring segment and a first radially outer ring segment and a second ring segment pair having a second radially inner ring segment and a second radially outer ring segment. The ring segment pairs have mutually facing faces. A portion of the face of the first radially inner ring segment overlaps a portion of the face of the second radially outer ring segment in the radial direction.

Abstract: A seal segment assembly for a turbomachine, in particular a gas turbine, including a first seal carrier and a second seal carrier, that are adjacently disposed in the circumferential direction, the first seal carrier having a first carrier base and at least one first sealing member that is joined to the first carrier base, and the second seal carrier having a second carrier base and at least one second sealing member that is joined to the second carrier base, the first sealing member and the second sealing member being formed by a plurality of cavities, that are adjacently disposed in the circumferential direction and in the axial direction, in particular evenly spaced, the cavities extending in the radial direction from the particular carrier base. The first carrier base and the second carrier base are intercouplable or are intercoupled in the circumferential direction by a mating connection assembly.