EP2730370A1 - Procédé et appareil pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine - Google Patents
Procédé et appareil pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine Download PDFInfo
- Publication number
- EP2730370A1 EP2730370A1 EP12192401.3A EP12192401A EP2730370A1 EP 2730370 A1 EP2730370 A1 EP 2730370A1 EP 12192401 A EP12192401 A EP 12192401A EP 2730370 A1 EP2730370 A1 EP 2730370A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- grinding
- blade
- grinding device
- blades
- turbomachine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 38
- 239000000428 dust Substances 0.000 claims abstract description 18
- 238000003754 machining Methods 0.000 claims abstract description 18
- 238000011065 in-situ storage Methods 0.000 claims abstract description 6
- 239000012809 cooling fluid Substances 0.000 claims description 6
- 239000002390 adhesive tape Substances 0.000 claims description 4
- 239000002245 particle Substances 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 2
- 238000000605 extraction Methods 0.000 abstract 2
- 239000000284 extract Substances 0.000 abstract 1
- 238000012216 screening Methods 0.000 abstract 1
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000007781 pre-processing Methods 0.000 description 2
- 238000004904 shortening Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000011109 contamination Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B49/00—Measuring or gauging equipment for controlling the feed movement of the grinding tool or work; Arrangements of indicating or measuring equipment, e.g. for indicating the start of the grinding operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
- B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B55/00—Safety devices for grinding or polishing machines; Accessories fitted to grinding or polishing machines for keeping tools or parts of the machine in good working condition
- B24B55/06—Dust extraction equipment on grinding or polishing machines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
Definitions
- the present invention relates to a method for setting a predetermined radial gap of arranged in a housing of a turbomachine blades.
- Blades of turbomachines are subject during operation to a very high material stress and a correspondingly large wear. For this reason, the blades are usually replaced by new blades during maintenance work after a predetermined period of operation.
- the operating time is advantageously chosen such that the exchanged blades can still be repaired.
- the turbine blades, the turbine vanes and the guide segments are replaced.
- the original radial blade clearance must also be achieved in the new turbine blades.
- the blade tips of the new blades are machined accordingly prior to their assembly. Since the radial gap dimension depends not only on the manufacturing tolerances of the new blades but also on other influencing factors, the final radial blade gap results only after complete replacement of all blades.
- Factors influencing this are, for example, the contour of the new guide vanes, the contour of the new guide rings, the coating of the new vanes and guide rings, the change in the position of the new vanes relative to the position of the replaced old vanes, and the like.
- the finally adjusting gap dimension is correspondingly difficult in advance and can only be calculated within a fairly broad tolerance band.
- the machining of the blade tips of new blades to adjust the radial gap is usually done in the context of grinding. This is always carried out away from the turbomachine, since otherwise there would be a risk that the turbomachine is affected by the resulting during processing sanding dust.
- the blades can be machined using a conventional grinding system mounted on the original wheel disc state, including the runner must be unstacked in advance, which is associated with a lot of effort.
- a so-called dummy wheel disc can be used, which eliminates the unstacking of the rotor.
- the use of such a dummy wheel disc is in turn associated with a lower machining accuracy, which can adversely affect the performance of the turbomachine. It is also possible to machine the blades without wheel disc with a so-called single blade grinding, which is associated with further losses in terms of machining accuracy.
- an object of the present invention to provide a method of the type mentioned above and a grinding apparatus for performing the method, with which setting a predetermined radial gap of arranged in a housing of a turbomachine blades in the context of a grinding of Shovel tips easy, fast and convenient with very high machining accuracy feasible without endangering the proper operation of the turbomachine.
- the present invention provides a method of the type mentioned, comprising the steps of: a) removing a housing part with at least partial exposure of the blades to be machined; b) placing a grinding device portion of a blade to be machined such that the tip of the blade can be processed with a grinding wheel of the grinding device; c) shielding the processing area by disposing a shielding device configured to oppose leaving of grinding dust from the shielded processing area; d) providing a suction such that it sucks sanding dust from the shielded processing area; and e) grinding the bucket tip of the bucket in situ to produce the predetermined radial gap.
- the inventive method is characterized in particular by the fact that the shielding of the processing area and the suction prevent fouling of the turbomachine by grinding dust, whereby machining in situ on a mounted in the intended condition blade is made possible.
- the processing of the blades in situ is on the one hand to the advantage that a very high, the known methods superior machining accuracy is achieved, so that not only maintaining an original performance of the turbomachine but also optimize the performance by adjusting the radial gap can be done.
- a destacking of the rotor is not required for carrying out the method, whereby time and cost can be saved.
- the blades may be, for example, those of a compressor or a turbine.
- step e the grinding device and a further blade are aligned with each other, after which again steps c) to e) are performed.
- steps c) to e) are performed.
- step e) is carried out on a blade with an already ground blade tip.
- the pre-grinding of the blade tip for example, in a state in which the blade is fixed to a dummy wheel disc as described above, or using a Einzelschaufelschleifvorraum.
- the final or fine machining is then carried out in the intended mounted state of the blade using the method according to the invention, which then highest machining accuracies and a correspondingly optimal performance of the turbomachine can be achieved.
- the shielding device is preferably formed by a brush arrangement provided on the grinding device and encircling the grinding wheel in an annular manner.
- the use of a brush arrangement as a shielding device is advantageous in that the flexible brushes are sealingly applied to the component to be processed, so that gaps are eliminated by which the grinding dust can escape from the shielded processing area.
- the dimensions of the grinding device used are matched to the distances between axially adjacent blade arrangements of the turbomachine, that the blades of all blade assemblies can be edited collision-free with the grinding wheel of the grinding device. Accordingly, for example, the blades of all stages of a turbine can be machined with a single grinder, thereby avoiding changeover times.
- cooling fluid bores provided on the rotor blade are at least partially closed before the implementation of step e). In this way it can be prevented that during the processing resulting grinding dust within the shielded processing area clogs existing cooling fluid bores. Also, clogging of the cooling fluid bores is counteracted if abrasive dust should leave the shielded processing area despite the shielding means and the suction.
- the closing of cooling air holes is advantageously carried out using adhesive tape and / or wax. Tape becomes preferred at those locations that do not come into contact with the shielding device.
- the use of wax is particularly suitable in the area of the blade tips, since wax is normally not dissolved upon contact with the shielding device.
- the grinding device is held movably on a cross slide arranged on a base plate in two mutually perpendicular directions. Accordingly, the grinding wheel can be moved appropriately for machining the blade tip.
- the base plate is attached in step b) to the housing of the turbomachine. Accordingly, unwanted relative movements between the grinding wheel and the blade to be machined can be excluded and thus a proper work result can be ensured.
- the present invention further provides a grinding apparatus, in particular for carrying out the method described above, which comprises a grinding wheel, a grinding wheel enclosing shielding device, which is designed such that it shields the processing area during normal operation of the grinding device, and a suction device, which is designed such that it sucks abrasive particles from the shielded processing area during the normal operation of the grinding device.
- the shielding device is provided in accordance with an embodiment of the grinding device according to the invention in the form of a grinding wheel annularly enclosing brush assembly. With such a brush arrangement very good results were achieved.
- the grinding device is preferably arranged on a cross slide arranged on a base plate in two relative to one another vertical directions held movable.
- a fastening device is provided, which is designed such that the base plate is detachably fastened to a housing of a turbomachine.
- FIG. 1 shows a grinding apparatus 1 according to an embodiment of the present invention.
- the grinding device 1 comprises a grinding wheel 2, which is rotationally driven by a drive 3.
- the grinding wheel 2 is annularly bordered by a shielding device, which in the present case is formed by a brush arrangement 4.
- the brush assembly 4 comprises a plurality of flexible bristles projecting outwardly over the grinding wheel 2 so as to come into contact with a workpiece to be machined during normal operation of the grinding apparatus 1.
- the grinding device 1 comprises a suction device 5 arranged underneath the grinding wheel 2, which during the normal operation of the grinding device 1 draws off abrasive particles from the shielded processing region of the grinding device 1, which is defined by the brush arrangement 4.
- the drive of the grinding wheel 2 and the suction 5 are coupled to one another such that the drive is switched off automatically in case of failure of the suction 5.
- the grinding device 1 is held movably on a cross slide 7 arranged on a base plate 6 in two mutually perpendicular directions in the plane of the base plate 6.
- the movement of the grinding device 1 is realized via a drive unit not shown in detail and an associated control.
- the dimensions and the weight of the grinding device 1 are chosen overall such that they can be easily packaged and transported to the operating location of turbomachines.
- the grinding device 1 is designed to be portable.
- FIG. 2 is a flow chart of a method according to an embodiment of the present invention, which is performed using the methods of FIG. 1 Grinder 1 shown is performed. The method is used to optimize a predetermined radial gap of arranged in a housing of a turbomachine blades and, accordingly, to optimize the performance of the turbomachine.
- the starting point of this process variant according to the invention is a turbomachine whose radial gap or power was already set by shortening the blades with one of the known methods described above by shortening the blades. Due to the fact that the blades are processed in the disassembled state in all of these methods, the adjustment of the radial gap and correspondingly the performance of the turbomachine can be further optimized, according to the invention, the following steps are carried out:
- FIG. 3 shows an example of a partial view of a turbomachine 8 after performing step S1.
- the turbomachine 8 comprises a two-part housing with a lower housing shell 9 and an upper housing shell, which is placed on the lower housing shell 9 and screwed in the proper condition along a parting line 10 with this.
- the upper housing shell is lifted so that the blades 11 of the present three stages 12, 13 and 14 having turbomachine are freely accessible.
- cooling fluid bores of the individual rotor blades 11 are closed using adhesive tape 15 and / or wax in order to prevent the grinding dust from clogging the cooling fluid bores during the execution of a subsequent grinding operation in step S6.
- Adhesive tape 15 is used at those locations that do not come into contact with the brush assembly 4 in the course of grinding. In all other places, especially in the area of the blade tips, however, wax is used, since this does not detach even when in contact with the brush assembly 4.
- step S3 the grinding device 1 is arranged in the region of a blade 11 to be machined of the step 12 such that the tip of the blade with the grinding wheel 2 of the grinding device 1 can be edited. More specifically, the base plate 6, on which the grinding device 1 is mounted, is fastened to the parting line 10 of the lower casing shell 9 of the turbomachine 8 by using screws 16, as shown in FIG FIG. 4 is shown schematically. Accordingly, the grinding wheel 2 can be moved in the direction of the arrows 17 and 18 using the cross slide 7 for machining the blade 11.
- step S4 the working region is shielded in such a way that it leaves during grinding sanding dust from the shielded processing area is counteracted. It should be noted that in FIG. 4 the upper row of brushes of the brush assembly 4 is not shown to release the view of the grinding wheel 2.
- the suction 5 is automatically provided in accordance with step S5 such that it sucks during the grinding grinding dust from the shielded processing area.
- a further step S6 the blade tip of the blade 11 is now ground in situ to produce the predetermined optimized gap dimension. Thanks to the fact that the grinding is performed on the blade 11 in the intended mounted state, this highest machining accuracies are achieved.
- the grinding dust is prevented by the brush assembly 4 from leaving the shielded processing area, and removed using the suction 5 from the processing area. In this way, contamination of the turbomachine by grinding dust is effectively counteracted. If the suction 5 fails during grinding, the drive of the grinding wheel 2 is automatically switched off, since lack of suction pollution-free machining can not be guaranteed.
- step S7 the step 12 is rotated such that the tip of another blade 11 can be processed with the grinding wheel 2 of the grinding device 1, whereupon the steps S4 to S6 are carried out again. This process is repeated until all blades 11 of stage 12 have been optimally processed with respect to the gap dimension.
- the grinding wheel 2 can be moved in the direction of the arrow 17 to the step 13 as a function of the width of the base plate 6 or of the length of the cross slide 7.
- the base plate 6 can naturally also be displaced manually along the parting line 10 of the turbomachine 8.
- the dimensions of the grinding device 1 are matched to the distances between the individual stages 12, 13 and 14 such that the moving blades 11 of all stages 12, 13 and 14 can be machined without collision with the grinding wheel 2 of the grinding device 1.
- the width of the grinding device 1 is selected such that when processing a blade 11 of the stage 12, a collision of the grinding device 1 with the radially above the blades 11 of the stage 12 projecting blades 11 of the stage 13 is not to be feared.
- a machining of the blades 11 of the stage 13 is possible without the grinding device 1 colliding with the blades 11 of the stage 14.
- FIG. 5 is a flowchart of a method according to another embodiment of the present invention for replacing worn blades. FIG to reset the original gap with new blades.
- Method steps of this second variant the method steps of referring to FIG. 2 correspond to the first method variant described are in FIG. 5 for simplicity, provided with identical reference numerals. A further explanation of these mutually corresponding method steps will be omitted below.
- step S1 a housing part of a turbomachine is removed with at least partial exposure of blades to be machined of the turbomachine, so that, for example, an arrangement according to FIG. 3 results.
- step S9 new blades are provided which replace the worn blades.
- step S10 the blade tips of the new blades provided in step S9 are pre-machined in an abrasive machining process.
- This preprocessing can be done, for example, using a dummy wheel disc or a single blade grinding device, as has already been described in connection with the methods known in the prior art.
- step S11 the pre-machined blades are installed to replace the blades removed in step S8.
- step S10 The preprocessing of the new blades in step S10 when disassembled takes place primarily against the background that the amount of grinding dust accumulated in step S6 is to be reduced to a minimum.
- step S10 basically also omitted and the entire grinding of the blade tips can be performed in step S6.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Grinding And Polishing Of Tertiary Curved Surfaces And Surfaces With Complex Shapes (AREA)
- Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Grinding-Machine Dressing And Accessory Apparatuses (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12192401.3A EP2730370B1 (fr) | 2012-11-13 | 2012-11-13 | Procédé pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine |
EP13003934.0A EP2730371B1 (fr) | 2012-11-13 | 2012-11-13 | Appareil pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine |
TW102138581A TWI655994B (zh) | 2012-11-13 | 2013-10-25 | 設定渦輪機轉子葉片之預定徑向間隙寬度的方法及裝置 |
US14/073,942 US9969055B2 (en) | 2012-11-13 | 2013-11-07 | Method and device for setting a predetermined radial gap width for rotor blades of a turbomachine |
KR1020130135685A KR102192838B1 (ko) | 2012-11-13 | 2013-11-08 | 터보 기계의 로터 블레이드의 사전 결정된 반경 방향 갭 폭을 설정하기 위한 방법 및 장치 |
JP2013233795A JP2014098389A (ja) | 2012-11-13 | 2013-11-12 | ターボ機械のロータブレードについて所定のラジアル方向間隙幅に調整するための装置及び方法 |
CN201310571643.7A CN103802005B (zh) | 2012-11-13 | 2013-11-13 | 用于设定流体机械的转子叶片的预定的径向间隙量的方法和设备 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12192401.3A EP2730370B1 (fr) | 2012-11-13 | 2012-11-13 | Procédé pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine |
Related Child Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13003934.0A Division EP2730371B1 (fr) | 2012-11-13 | 2012-11-13 | Appareil pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine |
EP13003934.0A Division-Into EP2730371B1 (fr) | 2012-11-13 | 2012-11-13 | Appareil pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2730370A1 true EP2730370A1 (fr) | 2014-05-14 |
EP2730370B1 EP2730370B1 (fr) | 2015-10-14 |
Family
ID=47552738
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12192401.3A Active EP2730370B1 (fr) | 2012-11-13 | 2012-11-13 | Procédé pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine |
EP13003934.0A Active EP2730371B1 (fr) | 2012-11-13 | 2012-11-13 | Appareil pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13003934.0A Active EP2730371B1 (fr) | 2012-11-13 | 2012-11-13 | Appareil pour régler un jeu prédeterminé à l'extrémité d'une aube d'une turbomachine |
Country Status (6)
Country | Link |
---|---|
US (1) | US9969055B2 (fr) |
EP (2) | EP2730370B1 (fr) |
JP (1) | JP2014098389A (fr) |
KR (1) | KR102192838B1 (fr) |
CN (1) | CN103802005B (fr) |
TW (1) | TWI655994B (fr) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
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DE102014215441A1 (de) * | 2014-08-05 | 2016-02-11 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Verfahren zur Herstellung eines Rotors einer Ladeeinrichtung |
EP2998061A1 (fr) * | 2014-09-22 | 2016-03-23 | Rolls-Royce Deutschland Ltd & Co KG | Procede et dispositif d'usinage des extremites d'aube d'un rotor de compresseur d'une turbine a gaz |
DE102016207141A1 (de) | 2016-04-27 | 2017-11-02 | Siemens Aktiengesellschaft | Schleifvorrichtung zum Schleifen von Laufschaufelspitzen |
EP3312387A1 (fr) * | 2016-10-21 | 2018-04-25 | Siemens Aktiengesellschaft | Système et procédé d'usinage de pointe |
EP2960009B1 (fr) * | 2014-06-24 | 2020-05-13 | Rolls-Royce plc | Fabrication de pale de rotor |
DE102019102480A1 (de) * | 2019-01-31 | 2020-08-06 | Rolls-Royce Deutschland Ltd & Co Kg | Schutzvorrichtung zum Schutz der Laufschaufeln eines Verdichters vor Funken und/oder Partikeln bei einer Bearbeitung der Schaufelspitzen |
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GB2491398B (en) * | 2011-06-03 | 2013-11-27 | Rolls Royce Plc | An apparatus and a method of shaping an edge of an aerofoil |
DE102013211047B4 (de) * | 2013-06-13 | 2015-04-30 | MTU Aero Engines AG | Verfahren zum Verschließen von Kühlluftbohrungen |
DE102015220883A1 (de) * | 2015-10-26 | 2017-04-27 | Siemens Aktiengesellschaft | Dummy-Radscheibe und Verfahren zum Bearbeiten von Schaufeln |
DE102016216857A1 (de) * | 2016-09-06 | 2018-03-08 | Siemens Aktiengesellschaft | Bearbeitungsvorrichtung und Verfahren zur Bearbeitung eines in einem unter Bildung einer Teilfuge zweigeteilten Turbinengehäuse angeordneten Rotors sowie Verfahren zur Reparatur und/oder Nachrüstung einer Turbine |
CN113001260A (zh) * | 2019-12-19 | 2021-06-22 | 中国航发商用航空发动机有限责任公司 | 防尘罩件、磨削装置、防尘方法以及叶尖磨削方法 |
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EP2590781A1 (fr) * | 2010-07-09 | 2013-05-15 | Eltronic A/S | Agencement d'abrasion pour abraser une surface d'objet et procédé d'utilisation correspondant |
US8820148B2 (en) * | 2010-11-17 | 2014-09-02 | General Electric Company | External casing functional access port |
GB201101909D0 (en) * | 2011-02-04 | 2011-03-23 | Rolls Royce Plc | A method of tip grinding the blades of a gas turbine rotor |
US8684669B2 (en) * | 2011-02-15 | 2014-04-01 | Siemens Energy, Inc. | Turbine tip clearance measurement |
-
2012
- 2012-11-13 EP EP12192401.3A patent/EP2730370B1/fr active Active
- 2012-11-13 EP EP13003934.0A patent/EP2730371B1/fr active Active
-
2013
- 2013-10-25 TW TW102138581A patent/TWI655994B/zh not_active IP Right Cessation
- 2013-11-07 US US14/073,942 patent/US9969055B2/en active Active
- 2013-11-08 KR KR1020130135685A patent/KR102192838B1/ko active IP Right Grant
- 2013-11-12 JP JP2013233795A patent/JP2014098389A/ja active Pending
- 2013-11-13 CN CN201310571643.7A patent/CN103802005B/zh active Active
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US5704826A (en) * | 1995-10-18 | 1998-01-06 | Danobat, S. Coop. Ltda. | Machine for grinding rotor blades provided with a multiwheel head |
DE29804858U1 (de) * | 1998-03-18 | 1998-07-30 | Stolpe, Johannes, Dipl.-Ing., 38106 Braunschweig | Schleifmittelträger zum Bearbeiten gewölbter und profilierter Flächen unter Verwendung elektrischer Handschleifmaschinen |
DE19908708A1 (de) * | 1998-09-09 | 2000-03-16 | Rieter Ag Maschf | Schärf- bzw. Schleifeinrichtung und Zustelleinrichtung |
DE102008037429A1 (de) * | 2007-10-12 | 2009-04-16 | General Electric Co. | Einrichtung und Verfahren zur Beeinflussung des Toleranzspielraums von Turbinenlaufschaufelspitzen |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2960009B1 (fr) * | 2014-06-24 | 2020-05-13 | Rolls-Royce plc | Fabrication de pale de rotor |
DE102014215441A1 (de) * | 2014-08-05 | 2016-02-11 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Verfahren zur Herstellung eines Rotors einer Ladeeinrichtung |
US9970309B2 (en) | 2014-08-05 | 2018-05-15 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Method for producing a rotor of a charging apparatus |
US10076816B2 (en) | 2014-09-22 | 2018-09-18 | Rolls-Royce Deutschland Ltd & Co Kg | Method and device for machining the blade tips of a compressor rotor of a gas turbine |
EP2998061A1 (fr) * | 2014-09-22 | 2016-03-23 | Rolls-Royce Deutschland Ltd & Co KG | Procede et dispositif d'usinage des extremites d'aube d'un rotor de compresseur d'une turbine a gaz |
DE102016207141A1 (de) | 2016-04-27 | 2017-11-02 | Siemens Aktiengesellschaft | Schleifvorrichtung zum Schleifen von Laufschaufelspitzen |
EP3312387A1 (fr) * | 2016-10-21 | 2018-04-25 | Siemens Aktiengesellschaft | Système et procédé d'usinage de pointe |
CN109844266A (zh) * | 2016-10-21 | 2019-06-04 | 西门子股份公司 | 顶端加工方法和系统 |
WO2018073210A1 (fr) | 2016-10-21 | 2018-04-26 | Siemens Aktiengesellschaft | Procédé et système d'usinage de pointe |
RU2726303C1 (ru) * | 2016-10-21 | 2020-07-13 | Сименс Акциенгезелльшафт | Способ и система механической обработки вершины |
US10989061B2 (en) | 2016-10-21 | 2021-04-27 | Siemens Energy Global GmbH & Co. KG | Tip machining method and system |
DE102019102480A1 (de) * | 2019-01-31 | 2020-08-06 | Rolls-Royce Deutschland Ltd & Co Kg | Schutzvorrichtung zum Schutz der Laufschaufeln eines Verdichters vor Funken und/oder Partikeln bei einer Bearbeitung der Schaufelspitzen |
WO2020156889A1 (fr) * | 2019-01-31 | 2020-08-06 | Rolls-Royce Deutschland Ltd & Co Kg | Dispositif de protection pour la protection des aubes d'un compresseur contre des étincelles et/ou des particules lors du traitement des pointes d'aubes |
DE102019102480B4 (de) | 2019-01-31 | 2023-10-19 | Rolls-Royce Deutschland Ltd & Co Kg | Schutzvorrichtung zum Schutz der Laufschaufeln eines Verdichters vor Funken und/oder Partikeln bei einer Bearbeitung der Schaufelspitzen |
Also Published As
Publication number | Publication date |
---|---|
US9969055B2 (en) | 2018-05-15 |
TWI655994B (zh) | 2019-04-11 |
EP2730371B1 (fr) | 2016-05-18 |
JP2014098389A (ja) | 2014-05-29 |
CN103802005A (zh) | 2014-05-21 |
US20140134926A1 (en) | 2014-05-15 |
KR102192838B1 (ko) | 2020-12-18 |
EP2730370B1 (fr) | 2015-10-14 |
EP2730371A1 (fr) | 2014-05-14 |
TW201427795A (zh) | 2014-07-16 |
CN103802005B (zh) | 2018-07-17 |
KR20140061252A (ko) | 2014-05-21 |
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