Abstract: The invention relates to a shaft-grounding ring which is used to remove induced voltages or electric charges from a first machine element (68), preferably from a shaft, into a second machine element (69) and has an annular housing (1), which consists of electrically conductive material and is conductively connected to the one machine element (68, 69) and has an electrically conductive connection to at least one discharging element (8). The discharging element consists of an electrically conductive material and has an electrically conductive connection to the other machine element. The discharging element (8) is a disk-shaped discharging body that extends at least over part of the circumference thereof.

Abstract: The invention relates to a shaft-grounding ring which is used to remove induced voltages or electric charges from a first machine element (68), preferably from a shaft, into a second machine element (69) and has an annular housing (1), which consists of electrically conductive material and is conductively connected to the one machine element (68, 69) and has an electrically conductive connection to at least one discharging element (8). The discharging element consists of an electrically conductive material and has an electrically conductive connection to the other machine element. The discharging element (8) is a disk-shaped discharging body that extends at least over part of the circumference thereof.

Abstract: 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. A turbo machine having a seal configuration (100) is also provided.

Abstract: A crankshaft seal flange has a support made at least partially of a plastic material. The support has a passage with an inner wall. The support has at least one dynamic seal that extends about a circumference of the inner wall of the passage. At least one sensor is provided that detects crankshaft rotary speed and crankshaft position. The at least one sensor encompasses an electronic component group that is integrated into the plastic material of the support.

Abstract: A crankshaft seal flange has a support made at least partially of a plastic material. The support has a passage with an inner wall. The support has at least one dynamic seal that extends about a circumference of the inner wall of the passage. At least one sensor is provided that detects crankshaft rotary speed and crankshaft position. The at least one sensor encompasses an electronic component group that is integrated into the plastic material of the support.

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: 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: 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.