| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 029889230 | Shaping integrally bladed rotor | 14 |
| 20090144981 | Method for the manufacture of integrally designed rotor wheels for compressors and turbines - In the manufacture of integrally designed rotor wheels (BLISKs), the natural frequency of each blade is measured after forming by conventional shaping methods and the respective blade mass and its divergence from the smallest blade mass is calculated therefrom. The mass of each blade exceeding the smallest blade mass is removed by means of an etchant, so that all blades have essentially corresponding thickness, chord length, mass and natural frequency and are evenly loaded in operation. BLISKs manufactured in this way feature a long service life. | 06-11-2009 |
| 20090282680 | Method for the fabrication of integrally bladed rotors - With the fabrication of integrally bladed rotors or stators (blisks) for gas-turbine engines, where the space confined by the pressure and suction side as well as the annulus surface is shaped by cutting and machining from the solid material, starting at the periphery of a ring or disk, a stiffness-optimized pre-machining contour is cut out in a cutting process at a certain distance from the pressure and suction side along straight control surfaces at a cutting angle varying in correspondence with the blade twist and along a conical surface extending at a certain distance from the annulus surface as well as along transition surfaces between the conical and the control surfaces, and subsequently finish machined by finish milling to produce the final contour of the blade, annulus and transition surfaces. The method reduces tool wear and is cost-effective. | 11-19-2009 |
| 20100199495 | PROCESS FOR PREPARING ROTORS OR STATORS OF A TURBOMOLECULAR PUMP - The invention relates to a process for preparing rotors or stators of a turbomolecular pump with rotor blades made of a specific aluminum alloy. | 08-12-2010 |
| 20100199496 | TURBINE BLADE HAVING MATERIAL BLOCK AND RELATED METHOD - A turbine blade including a root section at an end of the turbine blade, a first airfoil section adjacent to the root section, and a tip section adjacent to the airfoil section and including a material block that is incongruous with the airfoil section. A midspan section may also include a material block. Each material block can be selectively machined to customize the length of the turbine blade and the position of a tip shroud connection or midspan connection. The turbine blade can be sized for retrofitting last stage blades of older turbines. A radial position of the root mounts for the turbine blade may also be adjusted to provide further customization. | 08-12-2010 |
| 20100212158 | METHOD FOR THE MILLING MACHINING OF COMPONENTS - A method for the milling machining of components is disclosed. The method produces recesses with one or more lateral walls, in particular for the production of integrally bladed rotors for gas turbines, the recesses forming flow channels and the lateral walls forming blade surfaces of an integrally bladed rotor. The component to be machined by milling is clamped in a locating device for the milling machining. To adjust the vibrational properties of the component to be machined by milling, areas of the component are embedded in and/or filled with a machinable plastic. | 08-26-2010 |
| 20110041334 | PROCESS FOR MANUFACTURING A SINGLE-PIECE BLISK WITH A TEMPORARY BLADE SUPPORT RING REMOVED AFTER A MILLING FINISHING STEP - A process for manufacturing a single-piece blisk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material forming a connecting mechanism between at least two directly consecutive blade preforms; then milling on the blade preforms so as to obtain profiled blade blanks; then a finishing by milling of the blade blanks, so as to obtain blades with a final profile; then removing the connecting mechanism. | 02-24-2011 |
| 20110067240 | MACHINE TOOL, PARTICULARLY FOR MILLING A TURBOCHARGER COMPRESSOR IMPELLER - The present invention relates to a machine tool and a corresponding method for machining, in particular for turning and milling, a workpiece having a central bore, said machine tool comprising a tool holder for holding a tool, a work rest for seating the workpiece, a work mounting for holding the workpiece in place, and a drive means for rotating the workpiece about a central rotation axis, wherein the work rest has an arbor for attaching the workpiece, such that a section of the arbor projects into the central bore on a first side of the workpiece, and wherein the work mounting has a counter-holder movable in the direction of the bore axis of the central bore for applying a contact pressure, acting in the direction of the bore axis, to the workpiece on a second side opposite the first side. | 03-24-2011 |
| 20130000121 | SPHERICAL CUTTER AND METHOD FOR MACHINING A CURVED SLOT - A spherical cutter includes a spherically shaped body having open and closed ends defining a central cavity, multipoint cutting edges disposed along a circular rim at the open end, and the spherically shaped body generally defined by a radius and an origin. The cutting edges may be provided on cutting inserts removably attached to support teeth circumferentially disposed along the rim. The spherical cutter may be mounted to a rotatable spindle of a multi-axis computer numerically controlled machine with the radius and the origin located along a rotational axis of the spindle. The machine may be used for machining a cylindrical blank to form a plurality of circumferentially spaced apart integral rotor blades extending radially outwardly from a hub by machining each of the slots along a spherical surface defined by the radius and the origin. | 01-03-2013 |
| 20130086805 | ROTOR DISC AND METHOD OF BALANCING - A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life. | 04-11-2013 |
| 20130199042 | MACHINE TOOL, PARTICULARLY FOR MILLING A TURBOCHARGER COMPRESSOR IMPELLER - The present invention relates to a machine tool and a corresponding method for machining, in particular for turning and milling, a workpiece having a central bore, said machine tool including a tool holder for holding a tool, a work rest for seating the workpiece, a work mounting for holding the workpiece in place, and a drive mechanism for rotating the workpiece about a central rotation axis, wherein the work rest has an arbor for attaching the workpiece, such that a section of the arbor projects into the central bore on a first side of the workpiece, and wherein the work mounting has a counter-holder movable in the direction of the bore axis of the central bore for applying a contact pressure, acting in the direction of the bore axis, to the workpiece on a second side opposite the first side. | 08-08-2013 |
| 20160059365 | ROTORS WITH STALL MARGIN AND EFFICIENCY OPTIMIZATION AND METHODS FOR IMPROVING GAS TURBINE ENGINE PERFORMANCE THEREWITH - Methods are provided for improving performance of a gas turbine engine comprising a component having a rotor mounted in a rotor casing and having rotor blades. A tip sweep is applied to a leading edge of one or more rotor blades each having a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between the leading edge and a trailing edge. One or more blade geometric design parameters are adjusted. A rotor casing treatment is applied to the rotor casing over at least one of the one or more rotor blades. The applying and adjusting steps are performed during design of the rotor and cause a measured stall margin to substantially match a required stall margin with an increase in efficiency of the component. | 03-03-2016 |
| 20160175983 | METHOD OF PRODUCING AN INTEGRALLY BLADED ROTOR FOR A TURBOMACHINE | 06-23-2016 |
| 20160176000 | METHODS OF ROUGHING AND FINISHING ENGINE HARDWARE | 06-23-2016 |
| 20160184940 | METHOD FOR MANUFACTURING TURBINE ROTOR BLADE - The present invention addresses the problem of providing a method for manufacturing a turbine rotor blade wherein warping, bending and twisting of the entire rotor blade, which is provided with an excess thickness portion after a forging step, can be suppressed. In the forging step in a process for manufacturing a rotor blade ( | 06-30-2016 |
