Patent application number | Description | Published |
20080206043 | Rotor for a turbomachine - The invention refers to a rotor for a turbomachine, wherein the rotor has a vibration reduction device which is formed in such a way that it damps vibrations of the rotor which emerge during operation of the turbomachine. The damping is achieved by means of a rolling body inside the vibration reduction device, wherein the rolling body is arranged with capability of movement along a track surface. | 08-28-2008 |
20090016889 | Locking Sub-Assembly for Closing The Remaining Gap Between The First and The Last blade of a Blade Ring Which Are Inserted in a Circumferential Groove of a Turbomachine, and Corresponding Turbomachine - The invention relates to a closing assembly for closing the gap remaining between the first and the last blade of a blade ring that is inserted in a peripheral groove of a turbo machinery, said assembly consisting of at least two lateral parts, at least one of which can be hooked onto a projection that forms an undercut in said peripheral groove and at least one securing element, which secures the parts from coming detached from the peripheral groove. To provide a particularly reliable closing assembly, the securing element is configured as a pin, joining the parts of the closing assembly in a non-positive fit. | 01-15-2009 |
20090220345 | Closing Assembly for a Blade Ring of Turbomachinery - The invention relates to a closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into a peripheral groove of turbomachinery. Said assembly comprises at least two parts each of which can be hooked onto projections that form an undercut in said peripheral groove and comprises a securing element, which secures the parts from becoming detached from the peripheral groove. To provide a closing assembly for closing the remaining gap, which can be simply and cost-effectively detached and which reliably withstands high mechanical stress, the securing element is mounted to rotate about its longitudinal axis between the two parts and has a key head and a web. The web of the securing element can be positioned by rotation is such a way that to fit the parts in the peripheral groove, said parts can be displaced in relation to one another and to secure the parts from being detached from said groove, the web of the securing element can be placed against at least one lateral face of one of the parts. | 09-03-2009 |
20090302696 | Oscillation Damping System for a Stator of an Electrical Machine - An oscillation damping system for stator windings is provided which includes a supporting component of an end winding. The supporting component is equipped with damping elements, which are arranged asymmetrically in the circumferential direction in order to suppress excited natural oscillations. Masses or springs and screw-type restraints which connect the supporting component to the stator housing are suitable as damping elements. | 12-10-2009 |
Patent application number | Description | Published |
20090324414 | BLADE FASTENING MEANS OF A TURBINE - A turbine-blade locking device having a wedge movable in an axial direction is disclosed. The wedge is movable in the axial direction by a tensioning device, as a result of which a force is produced in the axial direction. The force in the axial direction causes the turbine blade to be pressed against the blade holder. | 12-31-2009 |
20100278636 | MAGNETIC DEVICE FOR DAMPING BLADE VIBRATIONS IN TURBOMACHINES - An arrangement for damping blade vibrations in a turbomachine is provided. The blade vibrations are due to an arrangement made of magnets and multiple induction plates and the undesired vibrations of the blade are damped by creating turbulent flows, wherein the induction plates are directed parallel to the rotation axis, and the magnetic field caused by the magnets is formed homogenously in the circumferential direction. | 11-04-2010 |
20110299989 | Blade union of a turbo machine - A damping system for damping the vibrations of a blade union is provided. The blades arranged in a neighboring manner are coupled to one another via a coupling element, wherein the coupling element is arranged fixed in a first blade and extends into the second blade, wherein the coupling element is not arranged in the second blade but rather solely contacts there such that, as a consequence of centrifugal forces, a free end of the coupling element presses against the second blade and a friction force thus occurs, leading to an energy dissipation and vibrations being thus damped. | 12-08-2011 |
20120020793 | Turbine blade system - A turbine blade system including a first turbine blade and a second turbine blade being arranged adjacent to each other shall be suited to allow a particularly secure and reliable operation of a turbine. To this end, the turbine blades are in contact in a first surface area and separated from each other in a second surface area, wherein the first turbine blade includes a pocket containing a damping piece in the second surface area. | 01-26-2012 |
20120224971 | TURBINE BLADE FASTENING FOR A TURBO ENGINE - A turbine blade fastening is provided. The turbine blade fastening include a blade root implemented in a fir tree design, which includes anchoring teeth implemented toward the blade casting tip such that the height of the anchoring teeth is reduced toward the blade casting tip. The anchoring teeth are designed for fitting into corresponding recesses in a rotor. | 09-06-2012 |
20150063985 | GUIDE BLADE RING FOR AN AXIAL TURBOMACHINE AND METHOD FOR DESIGNING THE GUIDE BLADE RING - A method for designing a stage for an axial turbomachine having a guide blade ring and a rotor blade ring arranged downstream of the guide blade ring is provided. The method includes: profiling a guide blade ring having guide blades arranged regularly over the circumference of the guide blade ring in accordance with basic aerodynamic and mechanical conditions; moving at least one profile section of at least one of the guide blades in the circumferential direction in such a way that the pitch angle for the at least one guide blade and a guide blade arranged adjacent thereto varies over the blade height in such a way that during operation of the axial turbomachine the departing flow formed downstream of the guide blade ring is irregularly formed over the circumference of the axial turbomachine, such that the vibration excitation of the rotor blades of the rotor blade ring is low. | 03-05-2015 |