Abstract: Disclosed is a sealing system for a turbomachine, in particular for a gas turbine, the sealing system being formed in an annular space between a flow-limiting wall of the turbomachine and at least one rotor blade tip of a rotor blade or an outer shroud arranged on the rotor blade tip, and comprising at least one sealing point. The sealing point comprises at least one run-in coating arranged on the rotor blade tip or on the outer shroud in the direction of the flow-limiting wall of the turbomachine. The invention furthermore encompasses a gas turbine comprising the sealing system.

Abstract: A blade segment (1) for a fluid flow machine (2), including: a first blade (3); a first shroud (7) attached to the tip of the first blade (3) and having a contact face (11); a second blade (3?); and a second shroud (7?) attached to the tip of the second blade (3?) and having a counter-contact face (12?) for engagement with the contact face (11) of the first shroud (7) in the radial direction (R) in such a way that a friction lock (RF) can be created between the contact face (11) and the counter-contact face (12?).

Abstract: A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed between two end sections of the parent body and defines a center section, running between the two end sections, of the parent body, wherein the two end sections have bearing surfaces running parallel to one another.

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 invention relates to an earth drilling device having a rotary drive and a drilling head connected to the rotary drive via a shaft.

Abstract: An apparatus and method for adjusting a bearing array, specifically for a gas turbine aircraft engine, is disclosed. The bearing array has a first stator-side, or fixed, bearing ring and a second rotor-side, or rotating, bearing ring, where rolling elements are located between the stator-side bearing ring and the rotor-side bearing ring. Transducers are assigned to the stator-side bearing ring to determine the position of the stator-side bearing ring and actuators govern the position of the stator-side bearing ring.

Abstract: An arrangement is provided for a non-hermetical seal between the stator and the rotor of a gas turbine. The arrangement comprises a brush seal which is arranged in a receiving chamber that is formed by at least one spacer or reinforcing element arranged between preferably two cover or guide elements. The brush seal is hub-centered via sliding elements, especially via sliding pads, said sliding elements being integrated into the spacer or reinforcing element.

Abstract: A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed between two end sections of the parent body and defines a center section, running between the two end sections, of the parent body, wherein the two end sections have bearing surfaces running parallel to one another.

Abstract: An arrangement for detachably fixing a guide blade segment that forms part of a transition channel of an aircraft gas turbine comprises high-pressure and low-pressure turbines. The arrangement has a groove-hook-type connection in the front area of the outer platform of the guide blade segment for its radial fixation and at least one pin that penetrates the hook-groove-type connection for securing it against rotation of the guide blade segment.

Abstract: A gas turbine apparatus includes a compressor and/or a turbine, having rotor blades mounted on a rotor that is rotatable relative to a stationary housing, with a clearance gap between the rotor blades and the housing. During operation, external forces tend to deform the housing and the clearance gap. At least two actuators are arranged circumferentially offset from one another about the circumference of the housing. Each actuator is coupled to the housing and adapted to apply onto the housing a rotational moment about a torque axis that is at least approximately parallel to the housing axis. Based on the signal of a sensor that senses the deformation, a regulating unit actuates the actuators so as to counteract or compensate any deformations of the housing that arise during operation of the apparatus.

Abstract: An arrangement is provided for a non-hermetical seal between the stator and the rotor of a gas turbine. The arrangement comprises a brush seal which is arranged in a receiving chamber that is formed by at least one spacer or reinforcing element arranged between preferably two cover or guide elements. The brush seal is hub-centered via sliding elements, especially via sliding pads, said sliding elements being integrated into the spacer or reinforcing element.

Abstract: A gas turbine apparatus includes a compressor and/or a turbine, having rotor blades mounted on a rotor that is rotatable relative to a stationary housing, with a clearance gap between the rotor blades and the housing. During operation, external forces tend to deform the housing and the clearance gap. At least two actuators are arranged circumferentially offset from one another about the circumference of the housing. Each actuator is coupled to the housing and adapted to apply onto the housing a rotational moment about a torque axis that is at least approximately parallel to the housing axis. Based on the signal of a sensor that senses the deformation, a regulating unit actuates the actuators so as to counteract or compensate any deformations of the housing that arise during operation of the apparatus.

Abstract: An arrangement for detachably fixing a guide blade segment that forms part of a transition channel of an aircraft gas turbine comprises high-pressure and low-pressure turbines. The arrangement has a groove-hook-type connection in the front area of the outer platform of the guide blade segment for its radial fixation and at least one pin that penetrates the hook-groove-type connection for securing it against rotation of the guide blade segment.

Abstract: An arrangement for the releasable fastening of struts serving as bearing carriers for the rotor of an aeronautical gas turbine to the casing structure of the aeronautical gas turbine, with stop faces, arranged in the circumferential direction and in the axial direction of the rotor of the gas turbine, at that end of the strut which faces away and acts as a connection head, the stop faces being assigned matching stop faces on the casing structure of the aeronautical gas turbine, and with a screw connection, inclined at an angle, between the casing structure and the connection head of the strut, for the purpose of the positive and non-positive retention of the strut on the casing structure.

Abstract: This invention relates to an arrangement for the cooling of the casing 1 of an aircraft gas turbine with a bypass duct 2 and at least one cooling air tube 3, this cooling air tube 3 having its inlet 4 arranged in the bypass duct 2 and entering at least one cooling air chamber 5 for the supply of cooling air to the casing 1, characterized in that a movable air deflector 6 is arranged in the bypass duct 2 upstream of the inlet 4 of the cooling air tube 3.

Abstract: Turbojet powerplant with at least one compressor (1), at least one combustion chamber (2), a high-pressure turbine (3) and a low-pressure turbine (4), characterised in that a heat exchanger (5) is arranged between the compressor (1) and the combustion chamber (2), in that at least one hot-gas line (6) branches off from an area downstream of the high-pressure turbine (3) and is connected to the heat exchanger (5), and in that at least one cold-gas line (7) connects the heat exchanger (5) with an area upstream of the low-pressure turbine (4).