Patent application number | Description | Published |
20100232952 | TURBO COMPRESSOR IN AN AXIAL TYPE OF CONSTRUCTION - A turbo compressor in an axial type of construction is disclosed. The turbo compressor having a bladed stator and a bladed rotor, and having a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially within their aerofoil on an inner ring belonging to the stator. The inner ring is split, i.e., segmented, at at least two points of its circumference. Furthermore, the inner ring has for each guide blade at least one bearing bush which can be inserted radially into an opening from inside. | 09-16-2010 |
20110255973 | DAMPING ELEMENT AND METHOD FOR DAMPING ROTOR BLADE VIBRATIONS, A ROTOR BLADE, AND A ROTOR - A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine is disclosed. A damping element is guided on a support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with a lower platform area of a rotor blade. A circumferential contact surface is formed by an elevation on the lower platform area, where the circumferential contact surface is a limit stop for a movement of the damping element. | 10-20-2011 |
20110255991 | INTEGRALLY BLADED ROTOR DISK FOR A TURBINE - An integrally bladed rotor disk ( | 10-20-2011 |
20110265328 | METHOD FOR MOUNTING AN INTEGRAL INNER RING OF A TURBOCOMPRESSOR STATOR - A method for mounting an integral inner ring ( | 11-03-2011 |
20120057988 | ROTOR FOR A TURBOMACHINE - The invention relates to a rotor ( | 03-08-2012 |
20120121384 | ROTOR AND METHOD FOR MANUFACTURING A ROTOR FOR A TURBO MACHINE - The invention relates to a rotor for a turbo machine, having rotating blades ( | 05-17-2012 |
20120121435 | ROTOR FOR A TURBO MACHINE - The invention relates to a rotor ( | 05-17-2012 |
20120121436 | ROTOR FOR A TURBO MACHINE - The invention relates to a rotor ( | 05-17-2012 |
20120121437 | ROTOR FOR A TURBO MACHINE - The invention relates to a rotor ( | 05-17-2012 |
20120224969 | COUPLING ELEMENT FOR MECHANICALLY COUPLING BLADES AND A ROTOR - A coupling element | 09-06-2012 |
20120224972 | METHOD AND DEVICE FOR PRODUCING AN INTEGRALLY BLADED ROTOR AND ROTOR PRODUCED BY MEANS OF THE METHOD - A method for producing an integrally bladed rotor, in particular a gas turbine rotor, by means of joining, comprises the following steps:—Providing a blade ( | 09-06-2012 |
20120230825 | GAS TURBINE BLADE FOR A TURBOMACHINE - The invention relates to a gas turbine blade ( | 09-13-2012 |
20120280021 | METHOD FOR PRODUCING AN INTEGRALLY BLADED ROTOR USING ARCUATE FRICTION WELDING, DEVICE FOR CARRYING OUT SAID METHOD, AND ROTOR PRODUCED BY MEANS OF SAID METHOD - A method for producing an integrally bladed rotor, in particular a gas turbine rotor, comprises the following steps:—Providing a blade ( | 11-08-2012 |
20120282088 | INNER RING FOR FORMING A GUIDE BLADE RING, AND GUIDE BLADE RING AND TURBOMACHINE - An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring. | 11-08-2012 |
20120282098 | SEALING DEVICE, INTEGRALLY BLADED ROTOR BASIC BODY, AND TURBOMACHINE - A sealing device for an integrally bladed rotor basic body of a turbomachine to suppress a gas exchange between a hot gas stream and a cooling air stream in the radial direction in contact areas of adjacent moving blades, including a plurality of sealing elements activatable by centrifugal force, which may be situated in the area of channels which extend from a high-pressure side to a low-pressure side and are peripherally delimited by the moving blades, an integrally bladed rotor basic body having such a sealing device, and a turbomachine having such an integrally bladed rotor basic body. | 11-08-2012 |
20120282109 | Blade, Integrally Bladed Rotor Base Body and Turbomachine - A blade for a turbomachine is disclosed. At least one cooling channel is configured in the blade neck, whose inlet is disposed near a platform projection on the high-pressure side and whose outlet is disposed in the region of a platform projection on the low-pressure side. An integrally bladed rotor base body having a plurality of these types of blades as well as turbomachine with such a rotor base body is also disclosed. | 11-08-2012 |
20130343900 | PROCESS FOR PRODUCING A RUN-IN COATING - Disclosed is a process for producing a run-in coating ( | 12-26-2013 |
20140044550 | Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine - A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed. | 02-13-2014 |
20140105725 | FISH MOUTH SEAL CARRIER - A fish mouth seal carrier for a guide vane arrangement of a gas turbine comprises a first half-shell element and a second half-shell element bonded to it, which together form a box profile with two axial arms and two radial arms. A sealing element is arranged on one of the axial arms of the box profile. At least one of the two half-shell elements has an integrally formed axial flange for forming, with a guide vane platform, a fish mouth seal accommodating an axial flange of an adjoining moving blade radially between the guide vane platform and the axial flange of the seal carrier. | 04-17-2014 |
20140161590 | COVER DEVICE, INTEGRALLY BLADED MAIN ROTOR BODY, METHOD AND TURBOMACHINE - A covering device for an integrally bladed rotor base body of a turbomachine for preventing or reducing a cooling air stream that flows from a high-pressure side to a low-pressure side through channels that are formed between adjacent rotor blades, a plurality of cover elements being provided that are individually insertable into the channels and have at least one peripheral sealing surface. Also an integrally bladed rotor base body having a covering device of this kind, a method for producing such an integrally bladed rotor base body, as well as a turbomachine having such an integrally bladed rotor base body. | 06-12-2014 |
20140246835 | COMPONENT - A component is disclosed. The component includes a base body with a first end section and a second end section. The first end section has a first locking protrusion with a first guide surface and a first guide section with a first support surface. The second end section has a second guide section with a second guide surface and a second locking protrusion with a second support surface. The first guide surface is contactable with the second guide surface with respect to a guide plane and the first support surface is contactable with the second support surface with respect to the guide plane such that the first locking protrusion is engageable with the second locking protrusion in a locked position. | 09-04-2014 |
20140301854 | SECUREMENT SYSTEM AND METHOD FOR SECURING AN ATTACHMENT PORTION OF AT LEAST ONE ROTOR BLADE OR ROTOR BLADE SEGMENT IN A MOUNTING SITE OF A ROTOR BASE - A securement system for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base. The securement system has at least one holder element and a second holder element, each of which has a holding portion and a connecting portion. The connecting portions can be introduced into the mounting site so as to establish a clip connection and can be locked together in the mounting site. The holding portions are configured so as to fasten the attachment portion of the at least one rotor blade or of the rotor blade segment in the mounting site in the locked state of the connecting portions. Further disclosed is a method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base and a rotor having a securement system. | 10-09-2014 |
20140348639 | TURBOMACHINE BLADE | 11-27-2014 |
20140348657 | TURBOMACHINE BLADE | 11-27-2014 |
20150061228 | SEALING ARRANGEMENT IN AN AXIAL TURBOMACHINE - A sealing arrangement ( | 03-05-2015 |