Abstract: The present invention relates to a seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. The present invention further relates to a turbo machine having a seal configuration (100).

Abstract: Disclosed is process for producing a wear-resistant coating on a component. The process comprises providing an electrolyte which contains Co and/or Ni, dispersing first particles comprising hard material particles and/or slip material particles in the electrolyte, dispersing second particles comprising metal alloy particles in which the metal alloy comprises chromium and aluminum in the electrolyte, providing a component to be coated in a bath of the electrolyte which has first and second particles dispersed therein, and electrodepositing a matrix of Co and/or Ni with incorporated first and second particles on the component. A correspondingly produced wear-resistant coating is also disclosed.

Abstract: Disclosed is a process for producing a wear-resistant layer, in particular on components of gas turbines or aero engines. The process comprises providing a component with a titanium material on at least part of a surface on which the wear-resistant layer is to be produced, applying a solder formed from a cobalt base material to the titanium material, soldering the solder to the titanium material by applying heat and producing at least one diffusion zone between solder and titanium material which comprises intermetallic phases.

Abstract: A component for a turbomachine having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent. The intermetallic material is compacted and/or modified in microstructure by microplasticization at least partially at a surface or interface in a region close to the surface or interface.

Abstract: Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. In the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

Abstract: The invention relates to a torque support for a valve lock (5) in order to prevent a rotation of the lock with respect to the valve (1), wherein a connection housing (8) adjoins the valve lock and at least one boom (9, 9a) carried by the connection housing rests against the valve housing in the pivoted-out end position. Similarly, the torque support can also be connected to the valve housing and the boom can rest against the connection housing, or the connection housing is integrated in the valve lock.

Abstract: The invention relates to a method for producing an inlet lining on a stator-sided component of a turbine engine, in particular, a gas turbine, with at least the following steps: providing a stator-sided component of a turbine engine with an inlet lining; providing a mixture consisting of a solvent, particles of a metallic parent material for the inlet lining, the particles being insoluble in the solvent, and a filler having at least one constituent soluble in the solvent; applying the mixture to the stator-sided component; drying the stator-sided component and the mixture applied to the component while at least partially expelling the solvent to provide a porous green body in the area of the applied and dried mixture; and diffusion heat treating the component for inwardly diffusing aluminum and/or chromium and for forming the intermetallic phases in the resulting inlet lining.

Abstract: A device for use in a method for the galvanic production of a protective layer featuring hard material particles on a component of a turbomachine, particularly a blade tip armoring of a blade tip of a rotor blade, is disclosed. The device includes a pouch-, bag- or sack-like receiving device for receiving the hard material particles and is made of a net-, screen- or non-woven-like material that is pervious to an electrochemical coating solution and has a mesh size smaller than the diameter of the hard material particles. The receiving device is designed such that it can be removably attached with an opening over and around a region of the component to be coated. A method for the galvanic production of a protective layer featuring hard material particles on a component of a turbomachine using a pouch-, bag- or sack-like receiving device filled with hard material particles, is also disclosed.

Abstract: The present invention relates to a method of repairing intake coatings (12), in particular intake coatings for use in compressor and turbine components, wherein the process comprises the following steps: a) filling of a damaged place (10) of the inlet coating (12) with a material (18) whose material composition corresponds to that of the intake coating (12) or is comparable to this or whose materials properties are comparable to the materials properties of the intake coating (12); b) drying of the material (18) introduced into the damaged place (10); c) application of a diffusion donor layer (20) over the region of the damaged place (10) and onto the introduced material (18); and d) heat treatment of the intake coating (12) at least in the region of the damaged place (10) to effect local diffusion of at least one metallic element from the diffusion donor layer (20) into the introduced material (18).

Abstract: A system and method for planning outages for a power generation installation comprising a gas turbine power plant. The system and method utilizes a computer to receive requests from users to create maintenance plans for the power plant by generating templates, applying the templates to a database containing gas turbine data for the power generation installation; and receiving data from users to create maintenance package plans. Users can select either modular or turnkey maintenance plans. Modular maintenance package options enable a user to specifically select and obtain price quote information for parts and technicians who perform the maintenance tasks, and to specify particular shift options for the technicians.

Abstract: A method for producing an abradable coating for a component of a turbo-machine is disclosed. The method includes a) a powdery material is pretreated; b) a processable preliminary product is produced which is to be applied to a component that is to be coated; c) the preliminary product is applied to the component that is to be coated; d) a synthetic binder contained in the preliminary product is burned off; e) the component is sintered; and f) the component is post-processed. The method for producing an abradable coating for a turbo-machine eliminates the drawbacks of the solutions known from the prior art. In particular, the method is inexpensive, can easily be combined with other production process steps, for example, thermal treatments that have to be carried out anyway, and is also suitable as a method for repairs.

Abstract: An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.

Abstract: An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.

Abstract: A component, in particular a rotor blade of a gas turbine, having a blade tip plating, the plating including a cover layer that is formed of abrasive particles embedded in a metallic matrix material, and the cover layer being applied onto a surface of the component with the intermediate situation of a metallic bonding layer, wherein the metallic bonding layer is fashioned as a bonding layer applied to the component by high-speed flame spraying, and that the metallic matrix material of the cover layer is galvanically deposited.

Abstract: The invention relates to a method for producing an inlet lining on a stator-sided component of a turbine engine, in particular, a gas turbine, with at least the following steps: a) providing a stator-sided component of a turbine engine, this component being provided with an inlet lining; b) providing a mixture consisting of a solvent; particles of a metallic parent material for the inlet lining, said particles being insoluble in the solvent; and a filler, this filler having at least one constituent that is soluble in the solvent; c) applying the mixture to the stator-sided component; d) drying the stator-sided component and the mixture, applied to the component, while at least partially expelling the solvent in order to provide a porous green body in the area of the applied and dried mixture; e) diffusion heat treating the component for inwardly diffusing aluminum and/or chromium and for forming the intermetallic phases in the resulting inlet lining.

Abstract: A system and method for planning outages for a power generation installation comprising a gas turbine power plant. The system and method utilizes a computer to receive requests from users to create maintenance plans for the power plant by generating templates, applying the templates to a database containing gas turbine data for the power generation installation; and receiving data from users to create maintenance package plans. Users can select either modular or turnkey maintenance plans. Modular maintenance package options enable a user to specifically select and obtain price quote information for parts and technicians who perform the maintenance tasks, and to specify particular shift options for the technicians.

Abstract: Materials and systems substantially having photoactive properties are produced with a high quality output and without time losses in the fabrication process. To determine the quality of the photoactive material in situ, conductivity is induced in the material by exciting charge carriers through irradiation, and an electromagnetic field influenced thereby is measured, with the result of the measurement being evaluated by a computer with a corresponding control of actuating members such as valves and controllers. Optimum process parameters are thus found and used for the process.