Abstract: The invention relates to a housing system (10) for an axial turbomachine, in particular for an aircraft turbine, comprising a housing (12), at least one guide blade (14), which is fastened to the housing (12) by means of at least one fastening element (18),a scaling element (20) for reducing a leakage flow between the listening element (18) and the housing (12), wherein the sealing element (20) is arranged between a downstream wall (22) of the fastening element (18) with respect to a flow direction (I) of the axial turbomachine and a wall (24) of the housing (12), and a pressing means (36), by means of which an axial force can be applied to the scaling element (20) And the scaling element can be pressed against the wall (24) of the housing (12), at least during the operation of the axial turbomachine. The invention further relates to an axial turbomachine having such a housing system (10).

Abstract: The invention concerns a moving blade system for a moving blade sequence of a continuous-flow machine, in particular a thermal gas turbine with at least two moving blade segments, of which each moving blade segment encompasses at least two moving blades that are disposed, in reference to a rotation axis of the moving blade sequence, at least primarily radially between a radially interior and a radially exterior shroud band and are coupled to the shroud bands, wherein at least the radially exterior shroud bands of the two moving blade segments encompass contact surfaces that correspond to one another, wherein radial equilibrium axes of neighboring moving blades of the at least two moving blade segments are disposed in a tilted manner by respectively axially an angle (?a, ?b) relative to their respective base inclination, wherein the angles (?a, ?b) in regard to the base inclination feature opposite signs.

Abstract: An arrangement for optimizing the running clearance for turbomachines of the axial type, such as turbocompressors, gas turbines, and steam turbines, in particular for compressors of stationary gas turbines, by controlling the inner diameter, which is relevant to the running clearance, of at least one stator structure that surrounds a rotor blade ring, including: the stator structure has a closed, circular inner ring, a circular outer ring that is situated concentric to the inner ring at a radial distance therefrom, and a plurality of links that integrally connect the inner ring to the outer ring, the links being circumferentially inclined at a defined angle (?) to the radial direction and distributed around the circumference of the stator structure, and the arrangement includes an adjustment device for rotating the inner ring relative to the outer ring with elastic modification of the running clearance-relevant inner diameter (D) of the inner ring.

Abstract: A turbomachine, especially a gas turbine, includes a rotor having rotating blades and a stator having a housing and guide blades. The rotating blades form at least one rotating blade ring, which at one radially outward lying end adjoins an inner ring or casing ring of the housing, thereby defining a gap therebetween. The casing ring is connected to a support ring via curved walls, which together with the casing ring and the support ring bound a cavity and form a bellowslike structure. By changing the pressure prevailing in the cavity of the respective bellowslike structure, the gap between the casing ring and the radially outward lying ends of the respective rotating blade ring can be pneumatically adjusted.

Abstract: The present invention relates to a strut for a turbine center frame of a jet engine, in particular a gas turbine, with a first end for disposition on an internal structure of the turbine center frame and a second end opposite the first end for attaching the strut on a housing or an internal boundary wall of the turbine center frame, and on the second end at least one flange-like element with at least one first aperture is removably arranged with at least one first aperture for accommodating or passing through an attachment means. The invention further relates to a turbine center frame for a jet engine, in particular a gas turbine as well as a method for producing a turbine center frame of a jet engine, in particular a gas turbine.

Abstract: The English-language Abstract from the international application is to be retained and is therefore not duplicated in the specification.

Abstract: The invention concerns a moving blade system for a moving blade sequence of a continuous-flow machine, in particular a thermal gas turbine with at least two moving blade segments, of which each moving blade segment encompasses at least two moving blades that are disposed, in reference to a rotation axis of the moving blade sequence, at least primarily radially between a radially interior and a radially exterior shroud band and are coupled to the shroud bands, wherein at least the radially exterior shroud bands of the two moving blade segments encompass contact surfaces that correspond to one another, wherein radial equilibrium axes of neighboring moving blades of the at least two moving blade segments are disposed in a tilted manner by respectively axially an angle (60 a, ?b) relative to their respective base inclination, wherein the angles (?a, ?b) in regard to the base inclination feature opposite signs.

Abstract: The present invention relates to a strut for a turbine center frame of a jet engine, in particular a gas turbine, with a first end for disposition on an internal structure of the turbine center frame and a second end opposite the first end for attaching the strut on a housing or an internal boundary wall of the turbine center frame, and on the second end at least one flange-like element with at least one first aperture is removably arranged with at least one first aperture for accommodating or passing through an attachment means. The invention further relates to a turbine center frame for a jet engine, in particular a gas turbine as well as a method for producing a turbine center frame of a jet engine, in particular a gas turbine.

Abstract: An earth drilling device having a rotary drive and a drilling head connected to the rotary drive via a shaft is disclosed. The shaft runs at least partially axially along a pipe with two pipe ends, the first pipe end of which is connectable to a vacuum source and the second pipe end of which is provided with a pipe opening over which the drilling head at least partially projects. The drilling head is provided with at least two fillet sections connected to the shaft, which are attached to the shaft in radial extension and in projection along the axis of the pipe only partly cover the pipe opening. The fillet sections are each connected to an axially oriented surface section, which contacts the inner wall of the pipe in a gliding manner or contacts an inner wall of a sleeve coaxially connected to the second pipe end when the drilling head rotates. The axially oriented surface sections are each connected to a limb which axially projects over the pipe or the sleeve.

Abstract: An arrangement for optimizing the running clearance for turbomachines of the axial type, such as turbocompressors, gas turbines, and steam turbines, in particular for compressors of stationary gas turbines, by controlling the inner diameter, which is relevant to the running clearance, of at least one stator structure that surrounds a rotor blade ring, including: the stator structure has a closed, circular inner ring, a circular outer ring that is situated concentric to the inner ring at a radial distance therefrom, and a plurality of links that integrally connect the inner ring to the outer ring, the links being circumferentially inclined at a defined angle (?) to the radial direction and distributed around the circumference of the stator structure, and the arrangement includes an adjustment device for rotating the inner ring relative to the outer ring with elastic modification of the running clearance-relevant inner diameter (D) of the inner ring.

Abstract: The invention concerns a turbo engine, especially a gas turbine, with a stator and a rotor, wherein the rotor has rotating blades and the stator has a housing (11) and guide blades (12), wherein the rotating blades at the rotor side form at least one rotating blade ring, and the rotating blade ring or each rotating blade ring at one radially outward lying end adjoins an inner ring or casing ring (17) of the housing at the stator side, by which it is surrounded and with which it bounds a gap, wherein the particular casing ring (17) is connected to a support ring (20) via curved walls (19), which together with the casing ring (17) and the support ring (20) bound a cavity (22) and form a bellows-like structure (21), and wherein by changing the pressure prevailing in the cavity (22) of the respective bellows-like structure (21) the gap between the casing ring (17) and the radially outward lying ends of the respective rotating blade ring can be pneumatically adjusted.

Abstract: The present invention relates to a process for producing cotton warp yarns having an inverse denim effect, which comprises using an indigo dyeing range to perform a dyeing step whereby the cotton warp yarn is through-dyed with indigo in one pass at a dyeing temperature of 30 to 90° C. and an indigo concentration of 5-500 g/l and a subsequent bleaching step whereby the indigo is selectively decolorized on the surface of the cotton warp yarn.

Abstract: The present invention relates to a process for through-dyeing of cotton warp yarns with indigo in an indigo dyeing range, which comprises dyeing in one pass at a dyeing temperature of 30 to 90° C. and an indigo concentration of 10-60 g/l.

Abstract: What is described here is a device for facilitating the locomotion of a person by himself or herself by means of a spring system for removable attachment to both legs of the person, which spring system enables the person, by compression and deflection of at least one spring element, to walk on the ground by jumping step by step. The invention is distinguished by the provisions that the spring element is a leaf spring having an arc-shaped configuration, on the concave side of which a leverage mechanism is provided that is fixedly connected for rotation to the leaf spring via two separate fixing means and a base plate on which the respective foot of the person may be placed and which is connected, on the one hand, via at least one rotary pin bearing and one connecting rod to the first fixing means and, on the other hand, to the other fixing means either directly or via a central support rigidly connected to the base plate.

Abstract: This invention relates to a gas-turbine engine which is provided in the turbine interior with a bearing chamber for a turbine shaft, the bearing chamber being sealed by sealing elements, and with a scavenge line for the lubricating oil which is supplied to the bearing chamber, in particular is sprayed onto the bearing(s) arranged therein. In accordance with the present invention, the single scavenge line, which is connected to a suitable lubricating-oil collecting compartment, features such an ample cross-section and the sealing elements have such a high sealing effect that the pressure in the bearing chamber is essentially equal to the pressure in the lubricating-oil-collecting compartment and maximally half the pressure in the turbine interior.

Abstract: A passive clearance control system is provided in the turbine section of a gas turbine engine in which turbine casing nozzle vanes and rotor blades are provided. The rotor blades are arranged on a rotor and preferably fitted with a shroud. The tips of the blades or shroud are surrounded by shroud segments suspended in the turbine casing, and a clearance between the tips and the shroud segments is formed and has a width which is controlled by a heating-cooling channel system. The channel system is supplied with a stream of air from the compressor section of the gas turbine and bypasses the combustion chamber to reach, via a plurality of metering holes, an annulus bounded by a stator ring. In a preferred aspect of the present invention, a ring-shaped orifice plate interacting with the metering holes is provided within the annulus which closes these metering holes to a varying degree depending on the temperature of the air stream reaching the heating-cooling channel system.

Abstract: A fixed bearing for a radial or diagonal flow compressor is guided in a damping bush whose axial position can be fixed by means of a reconciling plate to establish a desired running gap with respect to the compressor housing. The damping bush has a receiving device for a supporting element which rests against the reconciling plate, such that the supporting element and the reconciling plate are removable when the damping bush is disposed in the compressor housing. When the rotor is mounted, the required thickness of the reconciling disk can be determined and this reconciling disk can then be inserted without removing the rotor or the damping bush for the adjustment of the desired running gap.

Abstract: A sealing device for inner surfaces of hollow bodies such as pipes, containers, or the like which have adhering thereto contaminated or activated material. The sealing device comprises two supporting plates arranged in spaced relationship and substantially parallel to each other while extending in a direction perpendicular to the axis of the hollow body to be sealed. Of these two plates, the outer one is provided with a filling connection and with a discharging connection. The two supporting plates are adapted by means of pull elements to be tightened against a yieldable seal which is positively guided and is arranged along the circumferential rim of the hollow body.

Abstract: A method of and device for quickly and safely shielding a localized source of rays, according to which easily movable frame means are placed around the localized source of rays and shielding means non-penetrable by the rays of the localized source of rays are by remote control inserted into the frame means.