Patent application number | Description | Published |
20130084166 | SEGMENTED COMPONENT - A component, in particular for a gas turbine, is disclosed. The component has at least two component segments which are arranged relative to one another leaving a gap and are sealed against each other by a sealing device. The sealing device includes at least one brush seal. Also disclosed is a gas turbine, in particular an aircraft engine, having such a component. | 04-04-2013 |
20130136619 | BLADING - A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades. | 05-30-2013 |
20130136621 | BLADING - A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades. | 05-30-2013 |
20130149165 | ROTATING BLADE HAVING A RIB ARRANGEMENT WITH A COATING - The present invention relates to a rotating blade ( | 06-13-2013 |
20130149551 | DIFFUSION COATING METHOD AND CHROMIUM COAT PRODUCED THEREWITH - A method for producing a coating made of metal or a metal alloy on a substrate ( | 06-13-2013 |
20130171343 | Method for repair of a component of a turbomachine and a component repaired according to this method - A method is disclosed for the repair of a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with blades taken up in at least one groove and with at least one support region for limiting a blade tilt angle, whereby at least one segment, which has been subjected to wear, of the support region of the component is removed, and a coating that can be introduced in the unit on at least one supporting surface of at least one blade is formed on the component for limiting the blade tilt angle. In addition, a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with at least one such repair site is disclosed. | 07-04-2013 |
20130187061 | METHOD FOR NONDESTRUCTIVE TESTING OF WORKPIECE SURFACES - A method for nondestructive testing of workpiece surfaces by a fluorescent penetration test is disclosed. An embodiment of the method includes a) cleaning the area of the workpiece surface that is to be inspected; b) applying a fluorescent liquid penetrant to the area of the workpiece surface that is to be inspected, where the penetrant penetrates into possible recesses in the workpiece surface; c) removing the excess penetrant from the workpiece surface; d) applying a developer to the area of the workpiece surface that is to be inspected; e) bleaching the fluorescent penetrant by a beam of light in the layer formed by applying the developer to the workpiece surface; and 0 visual evaluation of the fluorescent penetrant remaining in the recesses present in the workpiece surface. | 07-25-2013 |
20130189085 | TURBOMACHINE SEAL ARRANGEMENT - The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells ( | 07-25-2013 |
20130193000 | ELECTRODE AND INSTALLATION FOR ELECTROCHEMICAL MACHINING AND METHOD THEREFOR - Disclosed is an electrode arrangement for the defined rounding or deburring of edges of electrically conductive components, in particular turbine components, by means of electrochemical machining with at least one working electrode ( | 08-01-2013 |
20130195611 | Unknown - A method for vibration damping of at least one blade of a turbomachine, wherein initially at least one damping element is arranged on the blade such that it can move in the axial direction, employs a damping element having a larger permeability constant than the blade (μ | 08-01-2013 |
Patent application number | Description | Published |
20130156562 | TURBOMACHINE AND TURBOMACHINE STAGE - A turbomachine stage including guide vanes, radially inner and/or radially outer airfoil platforms, which together form a guide vane cascade, and further including rotor blades, radially inner and/or radially outer airfoil platforms, which together form a rotor blade cascade adjacent to the guide vane cascade. Radially outer airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies, in particular periodically, in the radial and/or axial direction around the circumference. | 06-20-2013 |
20130156563 | TURBOMACHINE AND TURBOMACHINE STAGE - A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference. A maximum extent of this contour in the radial direction toward the spoke-like pattern is circumferentially spaced from an airfoil edge of this cascade by no more than 50% of the cascade pitch, a maximum variation in the radial direction being no more than 50% of the cascade pitch and/or a maximum extent in the axial direction away from the spoke-like pattern is circumferentially spaced from an airfoil edge of this cascade by no more than 50% of the cascade pitch, a maximum variation in the axial direction being no more than 50% of the cascade pitch. | 06-20-2013 |
20130167375 | APPARATUS AND METHOD FOR PROCESSING A SEALING ELEMENT LOCATED WITHIN THE HOUSING OF A GAS TURBINE - A machining or processing apparatus ( | 07-04-2013 |
20130189111 | ROTOR FOR A TURBOMACHINE - A rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades ( | 07-25-2013 |
20130202444 | BLADE CASCADE AND TURBOMACHINE - A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed. | 08-08-2013 |
Patent application number | Description | Published |
20130189086 | SEAL ASSEMBLY, METHOD AND TURBOMACHINE - A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed. | 07-25-2013 |
20130189108 | BLADE RIM SEGMENT FOR A TURBOMACHINE AND METHOD FOR MANUFACTURE - The present invention relates to a blade rim segment for a turbomachine with at least one shroud band which extends along a segment of a circle and is connected in single-piece fashion with at least three blades, which extend radially from the shroud band and are configured to be hollow with at least one channel, wherein the blade rim segment is manufactured in a single piece by casting and directional solidification, and wherein at the outlet openings of the channels of the blades, the shroud band exhibits first reinforcement ribs that surround the opening and run axially, as well as at least one second reinforcement rib between at least the first reinforcement ribs, as well as a corresponding method for manufacturing a blade rim segment. | 07-25-2013 |