Patent application number | Description | Published |
20090263239 | Ring structure with a metal design having a run-in lining - A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt. | 10-22-2009 |
20110225822 | ASSEMBLY MECHANISM COMPRISING A TENSION ANCHOR AND CORRESPONDING METHOD FOR A ROTOR SYSTEM OF AN AXIAL TURBO ENGINE - The invention relates to a device ( | 09-22-2011 |
20110290861 | METHOD FOR PRODUCING A BLADE PLATING ON A BLADE FOR A TURBOMACHINE - The invention relates to a method for producing a blade tip plating ( | 12-01-2011 |
20120045313 | FLOW DEVICE COMPRISING A CAVITY COOLING SYSTEM - A flow device having a cooling-air injection system for injecting cooling air into cavities ( | 02-23-2012 |
20140044526 | STATIONARY BLADE RING, ASSEMBLY METHOD AND TURBOMACHINE - Disclosed is an adjustable stationary blade ring of a turbomachine, whose stationary blades are each supported in a bearing body onto which an inner ring, which is divided into two half rings and acts as a seal carrier, is pushed without deformation, viewed in the circumferential direction, as well as a method for assembling a stationary blade ring of this type and a turbomachine having a stationary blade ring of this type. | 02-13-2014 |
20150139811 | Blade-disk assembly, method and turbomachine - Disclosed is a blade-disk assembly of a turbomachine, the blade-disk assembly having a plurality of adjacent rotor blades and a closure blade which are tilted into an anchoring groove, and at least one circumferential retention element which interlockingly cooperates with at least one blade, as well as a plurality of tilt-out prevention elements which are disposed between the groove base and the root portions and which, in the rest state, space the blades from the groove base when in the upper position. The blade-disk assembly further has a locking element, a portion of which is located between the groove base and the root portions and which, in the rest state, spaces the closure blade from the groove base when in the upper position. Also disclosed are a method for assembling such a blade-disk assembly, as well as a turbomachine. | 05-21-2015 |
20150275683 | Guide vane ring ,guide vane, inner ring and turbomachine - An adjustable guide vane ring of a turbomachine having an inner ring, the guide vanes of which each have a radially inner vane disk with disk thickness increasing in the direction of flow and acting as a bearing pin; a guide vane, as well as an inner ring for such a guide vane ring, as well as a turbomachine are disclosed. | 10-01-2015 |