EP1135578B1 - Dispositif d'appui pour pales de groupes moteurs - Google Patents

Dispositif d'appui pour pales de groupes moteurs Download PDF

Info

Publication number
EP1135578B1
EP1135578B1 EP99944367A EP99944367A EP1135578B1 EP 1135578 B1 EP1135578 B1 EP 1135578B1 EP 99944367 A EP99944367 A EP 99944367A EP 99944367 A EP99944367 A EP 99944367A EP 1135578 B1 EP1135578 B1 EP 1135578B1
Authority
EP
European Patent Office
Prior art keywords
support
arrangement
clamping
set forth
support rings
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.)
Expired - Lifetime
Application number
EP99944367A
Other languages
German (de)
English (en)
Other versions
EP1135578A2 (fr
Inventor
Heinz-Jürgen MEYER
Gerd LÜNSMANN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
ETN Prazisionstechnik GmbH
Original Assignee
ETN Prazisionstechnik GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by ETN Prazisionstechnik GmbH filed Critical ETN Prazisionstechnik GmbH
Publication of EP1135578A2 publication Critical patent/EP1135578A2/fr
Application granted granted Critical
Publication of EP1135578B1 publication Critical patent/EP1135578B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49863—Assembling or joining with prestressing of part

Definitions

  • the invention relates to a device for supporting blades of axial flow machines, especially of turbo air jet engines.
  • Axial flow machines are machines that are axially driven by a fluid, for example a gas such as air. Such machines have at least a rotor equipped with blades, which either over the blades Releases energy to the fluid and thus as a compressor (compressor) or pump acts, or on the blades of which the fluid does work, then it is around a turbine. Both compressors (compressors) and turbines are in the Usually structured in several stages. Each stage of such multi-stage axial flow machines is formed by a variety of rotor blades, which usually are arranged projecting radially outward around a central shaft. A Such an arrangement of rotor blades is called a playpen. A multi-stage Compressors or a multi-stage turbine have several playpens. Both between the individual grids of a compressor or a turbine as in front of the first playpen and behind the last playpen are also common Baffle provided, each of a plurality of radially extending, however, fixed guide vanes are formed.
  • Turbo air jet engines such as those used to power aircraft, usually have both a multi-stage compressor and a multi-stage Turbine on. Air enters the jet engine from the compressor or compressor sucked in and compressed. It flows through the compressor in the essentially in the axial direction and gets into one or in the compressed state several combustion chambers. There the compressed air is mixed with fuel and the fuel burned. This leads to a further pressure increase in the Combustion chamber. The gases flow out of the combustion chamber into a turbine in which they relax and release their energy to the rotor blades of the playpen.
  • the Turbine playpens are connected to a turbine shaft and drive this on.
  • the turbine shaft transfers its energy to the shaft of the compressor and furthermore, if necessary, to an air screw, a blower or a other consumers of mechanical energy. Also the turbine of a turbo air jet engine is flowed through essentially axially and parallel to the turbine shaft.
  • gaps are provided, so that the fixed guide vanes are not moving parts and the rotating rotor blades have no fixed parts of the compressor or the Touch the turbine.
  • the dimension of this column is a decisive criterion for the operating behavior and the overall efficiency of the turbine or the compressor. Large gap dimensions or different gap dimensions for the individual blades of the guide grille or the playpen have a negative effect.
  • the Buckets are typically attached to the housing or rotor in a manner are, which allows a slight mobility of the blades, they must for the Finishing can be brought into a stable position after assembly.
  • the Finishing consists in that the assembled blades are fixed and ground become. In order to achieve a functional blade position, the individual blades during the final grinding.
  • the air guide vanes one-piece compressor housings of jet engines to cast using a hardening wax, thereby fixing and then edit.
  • the time spent waxing and removing of the wax amounts to more than 30 hours for five stages one Housing. With housings with more stages, the effort is correspondingly greater.
  • DE 34 02 066 also discloses a device for fixing rotor blades known, which is characterized in that the blades of a playpen can be biased by means of a printing medium and those of the printing medium generated biasing force is assigned to each blade of the playpen.
  • Such one Uniform distribution of the pretensioning force generated by the pressure medium is given by achieves the known uniform distribution of the hydrostatic pressure in a fluid.
  • the use of compressed air as a fluid is described. It has been shown that the fluid undesirably tends to vibrate when grinding to be transferred from one blade to the other blades. The device thus does not meet the requirement for vibration-free grinding the blade ends. Even worse is that an uncontrollable - itself lighter - pressure drop leads to grinding errors and an unusable one Result of work with the corresponding high costs.
  • the aim of the present invention is to provide a device for supporting blades Specify in particular a jet engine that is as cheap as possible Fixing engine blades to be machined enables and the disadvantages of Avoid prior art as far as possible.
  • This aim is achieved according to the invention with a device of the type mentioned at the beginning Type achieved by at least one pair axially opposite each other and mutually adjustable support rings for mounting between Guide or rotor blades of adjacent compressor or turbine stages.
  • one of these support rings lies, for example, on the end edges all blades of a guide or moving grille of a turbine or a compressor while the other support ring on the nose edges of all blades one Guide or moving grids of the adjacent stage of the turbine or the compressor is applied.
  • the Laufoder located between the neighboring guide or play grids The guide grill has been removed.
  • the two support rings are supported in axial direction against each other with adjustable force and clamp on this Way the blades of the neighboring guide or playpen with adjustable force in front.
  • the support rings are preferably segmented in the circumferential direction. In this way the support rings can be dismantled and can be used in particular in one-piece compressor housings can be easily assembled.
  • the support rings are preferably supported by several over the circumference of the Support rings of distributed support elements adjustable against each other.
  • Any support element For this purpose preferably comprises at least one clamping bolt each two clamping pieces, the distance between them adjustable by means of the clamping bolt is.
  • the clamping pieces preferably each have two at an angle to one another running, flat bevels on and the support rings preferably each laterally limited counter slopes, against which the tension slopes are supported.
  • the clamping elements can then be arranged so that the clamping pieces approach when tightening the bolt connecting them and at the same time over their Spread the two opposite support rings using the Tension bevels of the tension pieces on the corresponding counter bevels of the Slide the support rings along and push the support rings apart.
  • At least some segments of a support ring are on its The blades facing the side are provided with an elastic coating that Damage to the blades is prevented and tolerances are compensated if necessary.
  • the fasteners are preferably round bolts, the holes in the opposite Segments are included. Prevent the fasteners a falling apart of the opposite segments and thus facilitate the Assembling the support rings.
  • the free ends of guide or rotor blades of axial flow machines Help of the support devices according to the invention, according to which the blades together of a housing or rotor carrying it is inserted into a receiving device and the support rings between the guide vanes or rotor blades are adjacent Compressor or turbine stages and before their first stage and their last Mount the stage so that those caused by the support devices Supporting forces are absorbed by the receiving device.
  • the housing Preferably the housing to be machined or the rotor to be machined vertical central axis inserted into the receiving device.
  • the receiving device and Support device preferably preassembled and after preassembly of all support rings first the lowest support ring and then continuing upwards all other support rings set to a desired support force.
  • the method is particularly in its preferred embodiment variants Particularly suitable for fast and precise support for everyone to ensure machining blades.
  • the support device 10 shown in FIG. 1 includes two support rings 12 and 14, of which the second support ring 14 from the first support ring 12 in the drawing is essentially hidden and can only be seen in the area of detail X. is because the first support ring 12 is shown there cut in the drawing. Both support rings 12 and 14 have the same dimensions and are mirror images built up to each other. Both support rings 12 and 14 each consist of three Segments 82, 84, 86, recognizable by the dividing lines 16 between the segments.
  • each clamping element 20 comprises two clamping pieces 22nd and 24, with each other via a screw bolt 26 serving as a clamping bolt are connected.
  • the externally threaded shaft 28 of the bolt 26 engages in an internal thread in the clamping piece 22.
  • the countersunk head 30 is with an engagement for a hex key Turn the bolt 26 provided.
  • Both clamping pieces 22 and 24 are each with two clamping slopes 32, 34, 36 and 38 provided. These bevels 32, 34, 36 and 38 are each planar Surfaces executed and are based on appropriately inclined counter-slopes 40, 42, 44 and 46 on the support rings 12 and 14. If the bolt 26 tightened a clamping element 20, the two clamping pieces 22 and 24 of this tensioning element 20. The tension slopes 32, 34, 36 and 38 slide here the clamping pieces 22 and 24 on the corresponding counter slopes 40, 42, 44 and 46 of the two support rings 12 and 14 along and simultaneously press the two support rings 12 and 14 due to the corresponding inclination of the clamping and the opposite surfaces apart.
  • level training of the clamping and Counter slopes are particularly advantageous compared to, for example, a conical one Execution because the flat surfaces contribute significantly to the spreading apart the support rings as far as possible when tightening the bolts runs in parallel and beyond that no measures to prevent rotation the clamping pieces 24 are required.
  • FIG. 2 shows the manner in which opposing segments 82, 82 ' of the two support rings 12 and 14 are loosely connected to one another so that they are in the Montage do not fall apart, but still their for adjustment by means of Retain clamping elements 20 necessary relative mobility.
  • Both tension rings 12 and 14 have through bores through which a connecting bolt 60 protrudes.
  • the connecting bolt 60 ends on both sides in corresponding recesses 62 and 64 of the support rings 12 and 14.
  • Two snap rings 66 and 68 - One at each end of the connecting bolt 60 - prevent the Ends of the connecting bolt 60 through the through holes in the support rings 12 and 14 slip out of the recesses 62 and 64 can.
  • the connecting pin 60 is in the through holes in the support rings 12 and 14 freely movable, so that the support rings 12 and 14 through the connecting bolts 60 are not prevented from getting anywhere.
  • the connecting bolt 60 is mounted, the support rings 12 and 14 can be but do not fall apart entirely.
  • Fig. 5 shows how the support device 10 between projecting radially inwards Guide vanes 80 of the guide grids of two adjacent stages of a compressor is assembled.
  • the two support rings 12 and 14 shown only partially lie with their respective levels provided with the elastic coating 54 and 56 Outer surfaces on the leading or trailing edges of the guide vanes 80. In In this position, they are clamped with the help of the clamping elements 20. To do this the two clamping pieces 22 and 24 of a clamping element 20 positioned so that their bevels 32, 34, 36 and 38 on the corresponding counter bevels 40, 42, 44 and 46 of the support rings 12 and 14 rest.
  • 5 shows that the counter bevels 40, 42, 44 and 46 are not circumferential but for each Clamping element 20 are limited laterally, so that the position of each clamping element 20 is precisely specified. In this way it becomes even Distribution of the clamping elements 20 over the circumference of the support rings 12 and 14 ensured. 5 is in the manner of a Exploded view shown. Therefore, the two clamping pieces 22 and 24 and the screw bolt 26 shown individually. In addition, the thread is in to recognize the clamping piece 22 forming threaded insert 31. This thread insert 31 is self-locking.
  • a first support device is then formed of a pair of support rings 12 and 14 between the bottom of the cradle and the bottom playpen of the compressor and the bolts 26 of these first two support rings slightly tightened so that the support device the guide vanes of this moving grille against the bottom of the receiving device supported.
  • additional pairs of support rings are used from bottom to top and the clamping elements 20 slightly biased. Also on the top guide grill put a pair of support rings.
  • This uppermost pair of support rings is supported upwards against an end ring of the receiving device, which after insertion of the compressor housing is mounted in the receiving device.
  • the end ring of the receiving device runs plane-parallel to the bottom of the receiving device. In this way, the support forces generated by the support devices at the inlet and outlet of the compressor from the cradle be included.
  • the support devices After the pre-assembly of all support devices and the support device, the support devices by further and defined tightening of the bolts of their clamping elements to a target tension brought. It starts with the lowest support device and with the continue above until the top support device is tensioned. In this way, an even pre-tensioning of all to be machined Buckets guaranteed.
  • the top and bottom support rings have the blades to be machined facing away from the bottom or the end ring of the receiving device no elastic coating on the facing side, since there is no damage are to be feared.
  • a handle 70 is shown, the a ball 72 to touch by Hand, a shaft 74 and a threaded portion at the free end of this shaft 76 has. Shaft 74 and ball 72 are not shown firmly connected.
  • a segment 82 ' of the support ring 14 is provided with bores 78, 79 which have a radial course have with respect to the support ring and in which the gain section 76 each one Handle 70 is screwed.
  • the support devices When using the support devices, they are usually so in the machining compressor housings used that they lie in horizontal planes. For these cases, it is preferably provided that the bores 78, 79 are in one Segment of the respective lower support ring of a support device; in the illustrated 5 would be the support ring 14.
  • Fig. 6 shows the two screwed into the segment 82 'of the support ring 14 Handles 70, 70 '. They protrude radially inwards into the support device 10, namely in the plane of the support ring 14. Since the blades of the Compressor or the turbine in the view of Figures 1 and 6 above or lie below the visible support ring and the shafts 74 of the handles 70, 70 'have a sufficient length, the support ring can be held on the ball 72, 72' and be positioned in the housing.
  • FIG. 6 shows the position of the through holes already mentioned 88, 90, 92, which are provided in each of the superimposed segments in FIG. 6 are. It can be seen that there are two through holes nearby the dividing lines 16 are provided and there is a third through hole is located approximately in the middle of each support element. All of these holes run perpendicular to the paper plane of FIG. 6 and thus perpendicular to the plane of the support rings 12.14.
  • FIG. 8 Another preferred variant is shown in FIG. 8.
  • Pair of clamping pieces 22, 24 together with bolts 26 The shaft 28 of the Bolt 26 is from its free end with a central threaded bore 100, into which an Allen screw 102 with countersunk head 104 is screwed in.
  • Countersunk 104 has a larger diameter than the shaft 28. If you imagine that the screw bolt 26 (to the right in Fig.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (15)

  1. Dispositif d'appui pour pales de turbomachines à écoulement axial, en particulier de groupes moteurs à turboréaction,
       caractérisé par au moins une paire de bagues d'appui (12, 14) opposées l'une à l'autre et s'appuyant l'une contre l'autre de manière réglable destinées à être montées entre des pales directrices ou de rotor d'étages de compresseur ou de turbine voisins.
  2. Dispositif selon la revendication 1, caractérisé en ce que les bagues d'appui sont segmentées dans le sens de la circonférence.
  3. Dispositif selon la revendication 1 ou 2, caractérisé en ce que les bagues d'appui (12, 14) s'appuient l'une contre l'autre de manière réglable au moyen de plusieurs éléments d'appui (20) répartis sur la circonférence des bagues d'appui (12, 14).
  4. Dispositif selon la revendication 3, caractérisé en ce que les éléments d'appui (20) comportent chacun au moins un boulon tendeur (26) ainsi que deux tendeurs (22, 24) dont l'écartement l'un par rapport à l'autre est réglable au moyen du boulon tendeur (26).
  5. Dispositif selon la revendication 4, caractérisé en ce que les tendeurs (22, 24) comportent chacun deux inclinaisons de serrage (32, 34, 36, 38) décrivant un angle l'une par rapport à l'autre et formées de surfaces plates.
  6. Dispositif selon la revendication 5 et l'une des revendications précédentes, caractérisé en ce que les bagues d'appui (12, 14) comportent chacune des contre-inclinaisons (40, 42, 44, 46) plates et limitées latéralement qui, lorsque les tendeurs (22, 24) sont en place, sont parallèles aux inclinaisons de serrage (32, 34, 36, 38) de ceux-ci et se rapprochent l'une de l'autre avec un intervalle décroissant par rapport au centre des bagues d'appui (12, 14).
  7. Dispositif selon l'une des revendications précédentes, caractérisé par un revêtement élastique (54, 56) sur le côté d'au moins un segment de bague d'appui, côté prévu pour être appliqué sur les pales.
  8. Dispositif selon l'une des revendications précédentes, caractérisé par des éléments de liaison (60) qui relient l'un à l'autre de manière mobile deux segments opposés d'une paire de bagues d'appui.
  9. Dispositif selon la revendication 8, caractérisé en ce que les éléments de liaison sont des boulons ronds (60) et que les segments d'une paire de bagues d'appui opposés l'un à l'autre comportent des trous pour loger les éléments de liaison.
  10. Dispositif selon l'une des revendications précédentes, caractérisé en ce qu'au moins un des segments (82, 84, 86) d'au moins une des deux bagues d'appui (12, 14) du dispositif d'appui (10) est pourvu d'une poignée (70, 70') qui permet de saisir manuellement le dispositif d'appui (10) à partir du centre de celui-ci.
  11. Dispositif selon la revendication 10, caractérisé en ce que la poignée (70, 70') peut être vissée depuis le côté radialement intérieur du dispositif d'appui (10) dans au moins une des bagues d'appui (14) et est composée de deux éléments.
  12. Dispositif selon l'une des revendications 1 à 11, caractérisé en ce que chacun des boulons tendeurs (26) réalisés sous forme de boulons filetés et reliant une paire de tendeurs (22, 24), dépasse du tendeur (22) muni d'un filet avec l'extrémité libre de sa tige (28), en ce qu'un alésage fileté central (100) est pratiqué dans l'extrémité libre de la tige (28) et qu'une vis (102) est vissée dans cet alésage fileté, dont la tête (104) ou une rondelle ou autre élément similaire fixé(e) par celle-ci présente un diamètre supérieur à celui de la tige filetée (28) et en ce que la partie de la tête, de la rondelle ou autre élément similaire, dépassant radialement de la tige, se situe contre le tendeur (24) lorsque l'on dévisse le boulon fileté (26) de l'extérieur et évite une séparation des deux tendeurs (22, 24).
  13. Procédé d'usinage des extrémités libres de pales directrices ou de rotor de turbomachines à écoulement axial, à l'aide de dispositifs d'appui selon l'une des revendications 1 à 9, caractérisé en ce que les pales sont fixées dans un dispositif de réception avec un boítier ou rotor les portant, et que les bagues d'appui entre les pales directrices ou de rotor d'étages voisins de compresseur ou de turbine, ainsi qu'avant leur premier et après leur dernier étage, sont montées de telle sorte que les forces d'appui provoquées par les dispositifs d'appui sont absorbées par le dispositif de réception.
  14. Procédé selon la revendication 13, caractérisé en ce que le boítier à usiner ou le rotor à usiner est inséré dans le dispositif de réception avec son axe central à la verticale.
  15. Procédé selon la revendication 14, caractérisé en ce que le dispositif de réception et le dispositif d'appui sont en premier lieu prémontés et légèrement précontraints et, après montage préalable de toutes les bagues d'appui, tous les éléments tendeurs de la bague d'appui la plus basse, puis, en continuant séquentiellement vers le haut, les éléments tendeurs de chaque bague d'appui suivante, sont réglés à une force d'appui souhaitée.
EP99944367A 1998-08-12 1999-08-12 Dispositif d'appui pour pales de groupes moteurs Expired - Lifetime EP1135578B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19836400 1998-08-12
DE19836400 1998-08-12
PCT/EP1999/005856 WO2000009861A2 (fr) 1998-08-12 1999-08-12 Dispositif d'appui pour pales de groupes moteurs

Publications (2)

Publication Number Publication Date
EP1135578A2 EP1135578A2 (fr) 2001-09-26
EP1135578B1 true EP1135578B1 (fr) 2004-06-16

Family

ID=7877214

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99944367A Expired - Lifetime EP1135578B1 (fr) 1998-08-12 1999-08-12 Dispositif d'appui pour pales de groupes moteurs

Country Status (5)

Country Link
US (1) US6513781B1 (fr)
EP (1) EP1135578B1 (fr)
AU (1) AU5732899A (fr)
DE (1) DE59909767D1 (fr)
WO (1) WO2000009861A2 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10344381A1 (de) * 2003-09-23 2005-05-04 Hauni Maschinenbau Ag Fördertrommel mit Spanneinrichtung
ITBO20030693A1 (it) * 2003-11-19 2005-05-20 Gd Spa Tamburo perfezionato per macchine confezionatrici di
US7008170B2 (en) * 2004-03-26 2006-03-07 Siemens Westinghouse Power Corporation Compressor diaphragm with axial preload
US7494317B2 (en) * 2005-06-23 2009-02-24 Siemens Energy, Inc. Ring seal attachment system
US7765658B2 (en) 2005-10-17 2010-08-03 Pratt & Whitney Canada Corp. Blade tip grinding tooling
US7758307B2 (en) * 2007-05-17 2010-07-20 Siemens Energy, Inc. Wear minimization system for a compressor diaphragm
DE102007060030B4 (de) * 2007-06-01 2013-10-31 Airbus Operations Gmbh Luft- oder Raumfahrzeug mit einer Vorrichtung zur Halterung von Systemen
DE102011055895A1 (de) * 2011-11-30 2013-06-06 Grammer Ag Fahrzeugsitz mit seitlichem Stützelement
US8998335B2 (en) * 2011-11-30 2015-04-07 Grammer Ag Vehicle seat and commercial vehicle
EP2599661B1 (fr) 2011-11-30 2016-10-05 Grammer Ag Siège de véhicule et véhicule utilitaire
FR2996289B1 (fr) * 2012-10-01 2018-10-12 Turbomeca Chambre de combustion comprenant un tube a flamme fixe au moyen de trois elements de centrage.
US8978262B2 (en) * 2012-11-29 2015-03-17 General Electric Company Inlet guide vane alignment apparatus and method
DE102013110448B8 (de) 2013-06-26 2018-11-29 Grammer Ag Fahrzeugsitz und Nutzkraftfahrzeug mit einem Fahrzeugsitz
DE102013106721B3 (de) 2013-06-26 2014-10-30 Grammer Ag Fahrzeugsitz und Nutzkraftfahrzeug mit wenigstens einem Fahrzeugsitz
DE102013110445B3 (de) 2013-06-26 2014-12-18 Grammer Ag Fahrzeugsitz und Nutzkraftfahrzeug mit einem Fahrzeugsitz
DE102013110416B3 (de) 2013-06-26 2014-12-18 Grammer Ag Fahrzeugsitz und Nutzkraftfahrzeug mit einem Fahrzeugsitz
CN104561892B (zh) * 2014-12-04 2016-11-23 深圳市华星光电技术有限公司 Oled材料真空热蒸镀用掩膜板
FR3041376B1 (fr) * 2015-09-17 2017-11-17 Snecma Interface et dispositif de support pour carter moteur
CN108150231B (zh) * 2018-01-31 2023-06-16 华电电力科学研究院有限公司 一种安装找中用假瓦及找中方法

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1551342A (en) * 1924-02-25 1925-08-25 Gen Electric Method of manufacturing turbine wheels, nozzle diaphragms, and the like
DE3402066A1 (de) 1984-01-21 1985-08-01 Klöckner-Humboldt-Deutz AG, 5000 Köln Verfahren zur aussendurchmesserfeinbearbeitung von laufradschaufeln
US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
DE19711337B4 (de) 1997-03-18 2004-07-15 ETN Präzisionstechnik GmbH Spannvorrichtung zum Spitzenschleifen für in einem Maschinengehäuse eingebaute Statorschaufeln einer Axial-Strömungsmaschine
US6164903A (en) * 1998-12-22 2000-12-26 United Technologies Corporation Turbine vane mounting arrangement

Also Published As

Publication number Publication date
AU5732899A (en) 2000-03-06
DE59909767D1 (de) 2004-07-22
EP1135578A2 (fr) 2001-09-26
WO2000009861A2 (fr) 2000-02-24
WO2000009861A3 (fr) 2001-07-12
US6513781B1 (en) 2003-02-04

Similar Documents

Publication Publication Date Title
EP1135578B1 (fr) Dispositif d'appui pour pales de groupes moteurs
DE60318147T2 (de) Turbinenschaufel mit Schaufelfusskerbe
DE102011054589B4 (de) Rotationsmaschine mit Abstandhaltern zur Steuerung der Fluiddynamik
DE2952023C2 (fr)
EP0906514B1 (fr) Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor
DE19518203C2 (de) Einrichtung zur Aufnahme eines inneren Leitschaufelendes in einem Axialverdichter
DE954835C (de) Gehaeusering fuer Kreiselradmaschinen, insbesondere fuer Gasturbinen
EP1394364B1 (fr) Turbosoufflante et son anneau de guidage
DE2627702A1 (de) Axialstroemungsmaschine
CH652456A5 (de) Kopfflanschbefestigungsvorrichtung fuer eine turbomaschine.
CH708768A2 (de) Verriegelnde Abstandshalteranordnung zur Einführung in einen umlaufenden Befestigungsschlitz zwischen Plattformen benachbarter Laufschaufeln.
EP1470320A1 (fr) Dispositif de fixation pour un turbocompresseur
DE60300600T2 (de) Auswuchtvorrichtung und -verfahren für Rotorwellenflansch
EP1076184B1 (fr) Dispositf de fixation
EP1619354A1 (fr) Dispositif pour fixer une aube à un disque rotorique de turbomachine, turbomachine et procédé pour le montage et démontage d'une aube au disque rotorique d'une turbomachine
DE69919459T2 (de) Befestigung eines Schaufelblattes an einem Rotor
EP3176386B1 (fr) Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
EP3287608A1 (fr) Bague intérieure d'une couronne d'aubes directrices d'une turbomachine
EP3236011A1 (fr) Rotor comprenant un porte à faux sur les pales pour un élément de sécurité
EP3336319B1 (fr) Dispositif de réglage destiné au réglage d'aubes directrices multiples d'un groupe propulseur
DE102021200813B4 (de) Turbinenrad mit einem ausgleichsgewicht, das in der nut angeordnet ist
DE102008048261B4 (de) Axialturbomaschinenrotor mit einem Schaufelschloss und Verfahren zum Herstellen desselben
WO2008023034A1 (fr) Diffuseur de compresseur radial
DE60204486T2 (de) Doppelte Schaufelblatthalterung
DE2120472A1 (de) Feststellvorrichtung fur die Schau fein einer Turbinenanlage

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20000405

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB IT LI NL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20040616

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20040616

Ref country code: GB

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20040616

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040616

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

XX Miscellaneous (additional remarks)

Free format text: DERZEIT SIND DIE WIPO-PUBLIKATIONSDATEN A3 NICHT VERFUEGBAR.

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 59909767

Country of ref document: DE

Date of ref document: 20040722

Kind code of ref document: P

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: GERMAN

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040831

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040831

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20041015

Year of fee payment: 6

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20040616

NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
GBV Gb: ep patent (uk) treated as always having been void in accordance with gb section 77(7)/1977 [no translation filed]

Effective date: 20040616

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20050317

EN Fr: translation not filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050301