EP1314856A1 - Vorrichtung zur Sicherung von Laufschaufeln in einer Nut einer Rotorscheibe - Google Patents

Vorrichtung zur Sicherung von Laufschaufeln in einer Nut einer Rotorscheibe Download PDF

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Publication number
EP1314856A1
EP1314856A1 EP02292896A EP02292896A EP1314856A1 EP 1314856 A1 EP1314856 A1 EP 1314856A1 EP 02292896 A EP02292896 A EP 02292896A EP 02292896 A EP02292896 A EP 02292896A EP 1314856 A1 EP1314856 A1 EP 1314856A1
Authority
EP
European Patent Office
Prior art keywords
groove
screw
screw head
locking element
radial
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
Application number
EP02292896A
Other languages
English (en)
French (fr)
Other versions
EP1314856B1 (de
Inventor
Bruno Antunes
Laurent Dezouche
Jean-Pierre Paul Henri Caubet
Nicolas Smirr
Alain Jean Charles Chatel
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1314856A1 publication Critical patent/EP1314856A1/de
Application granted granted Critical
Publication of EP1314856B1 publication Critical patent/EP1314856B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides

Definitions

  • the invention relates to a device for blocking the blades in the peripheral groove of a turbomachine disk, said blades with hammer-type feet likely to be introduced into said groove through a loading window and held in said groove by form cooperation with the side walls of the latter, said blocking device being capable of being introduced in said groove by said loading window and comprising a locking element arranged in the space separating two blade roots consecutive and capable of being reassembled in a lock housing formed in the side walls of said groove under the action of a screw radial operation, the head of which rests on the bottom of the groove, a radial clearance being provided between the bottom of the groove and the underside of the dawn feet.
  • the screw head which is wider than the barrel accommodates in an imprint made in the bottom of the groove to the right of the corresponding lock housing. Because the screw head is wider that the barrel, the screw is made captive.
  • the locking element consists of a protrusion formed on the upper face of a body which is in the locking position of the device and in abutment against the side walls of the groove in the vicinity of the groove groove. This body has a lower base which, in device locking position, away from the screw head, in order to allow said body to slide in the groove during blade assembly. Indeed to allow this sliding, the protuberance formed on the body must be in the groove, the base of the body is then supported on the screw head and located in the vicinity of the bottom of the groove.
  • the one-piece part constituted by the body and its protrusion does not include positive guiding means during sliding in the groove during assembly.
  • the screw head can therefore be improperly positioned in its imprint during tightening, which may result in a subsequent displacement of the screw head during the operation of the turbomachine and by a loss of the bracing effect. Tightening the incorrectly positioned screw can also lead to seizure of the thread, which can maintain the protuberance in the latch housing, but which subsequently causes difficulties in dismantling the device during maintenance operations.
  • the element of locking device is axially sliding in a radial opening a body having a section adapted to the section of the groove and fixed radially and the head of the screw is trapped between the bottom of the groove and the base of the body.
  • Means are provided to limit the reassembly of the locking element.
  • the body is guided when it slides in the groove, which ensures precise radial direction of the axis of the screw and prevents seizures.
  • the screw head is radially immobilized with respect to the body, and the action of centrifugal forces on the element of locking, in the event of partial loosening of the screw, prevents it from turn, because the screw head is then in positive support against the base from the body.
  • the body is arranged between the feet of a pair of blades and has a section adapted to the section of said groove. It has a base lower located above the bottom of the groove and a radial opening through of non-circular section in which the element of Lock is slidably mounted under the action of the operating screw.
  • the screw head is dimensioned so as to remain trapped between the bottom of the groove and the base of the body.
  • the section of the body in a plane perpendicular to the axis of the operating screw is greater than the cross section of the locking element in the same plane, and the section of the screw head is also greater than the cross section of the locking element so that the face upper part of the screw head can come to bear on the base of the body.
  • This technology is therefore not suitable for certain turbine disks due to lack of space between the feet of two blades consecutive.
  • the object of the invention is to propose a blocking device which overcomes this drawback and which can accommodate in a space circumferential reduced.
  • the diameter of the screw head is greater than the distance between the two blade feet adjacent.
  • the blocking device then comprises two parts: the element locking bolt and operating screw.
  • a intermediate plate is interposed between the screw head and the element locking, the ends of said plate being arranged under the two adjacent dawn feet.
  • the plate has means for preventing its rotation relative to the locking element.
  • These means consist, for example, of radial tabs which allow the element to rise locking during assembly.
  • the plate also includes means to immobilize the screw head in rotation.
  • These means consist of preferably by radial tabs pressing on the sides of the head quote. These tongues are flexible to allow rotation of the screw, during assembly, during the ascent of the locking element.
  • the element of locking has a greater protrusion in the vicinity of the end of the screw which comes to lodge in the orifice made in the platforms of the two adjacent blades.
  • This sleeve serves as a visual indicator of reassembly of the locking element.
  • Figure 3 shows in section a wheel disc 1 of turbomachine which has at its periphery a groove 2 intended for maintain the hammer-type dawn feet.
  • This groove 2 delimited by side walls 3a and 3b of curvilinear section, opens outwards by a groove 4 which has a dimension, in the direction of the axis of rotation of the wheel, less than the dimension of the cavity 5 formed in the bottom of groove 2.
  • the feet of the blades have a section according to the plan radial passing through the axis of rotation of the disc 1 adapted to the section of the groove 2 in order to be held there by form cooperation.
  • FIG. 1 is a top view of part of the disc 1.
  • the side walls 3a and 3b have opposite a first pair of radial notches 6a and 6b which constitute a loading window, allowing the introduction feet 7 of the vanes 8 in the groove 2 during the mounting of these vanes 8, as well as a second pair of radial notches 9a, 9b which constitute a housing for the lock of an object blade locking device of the invention.
  • the second pair of notches 9a, 9b is offset angularly with respect to the first pair of notches 6a, 6b of a distance equal to the angle formed by two consecutive blades or by a multiple of this angle.
  • the same wheel disc 1 can include several locking devices according to the invention.
  • FIG. 2 shows the same disc part 1 fitted with its blades 8.
  • Each blade 8 has, between its foot 7 and its aerodynamic part 10, a platform 11 which covers the periphery of the disc 1, all of the platforms 11 of the vanes 8 delimiting internally the gas flow vein.
  • each blade 8 is successively introduced in the groove 2 by the window formed by the first pair notches 6a, 6b and the blade 8 is made to slide in the direction of the arrow F until its platform 11 abuts against the platform of dawn previously introduced.
  • vanes 8 are identical except for the penultimate climb, referenced 8a, and the last climb, referenced 8b, which have on the adjacent edges of their platforms 11a and 11b notches 12a and 12b which constitute an orifice 13 whose function will be explained later in this memo.
  • a blocking device 14 is introduced through the window loading in the groove 2, then we position the foot 7 of the last blade in the loading window between the last blade 8a mounted and the first dawn climbed and we slide all of the blades 8 in the direction and arrow F, at an angle corresponding to the half measure the angle between two consecutive vanes, so that the platforms 11a and 11b of the first dawn mounted 8a and of the last dawn rise 8b be contiguous according to the median plane and the window of loading constituted by the first pair of notches 6a and 6b.
  • the locking device 14 disposed between the feet 7 of the blades 8a and 8b is located opposite the second pair of notches 9a and 9b.
  • the notches 9a and 9b have axial dimensions and peripheral lower than those of the notches 6a and 6b of the window of loading the vanes 8, to prevent the vanes from escaping 8 when they pass in front of these notches 9a and 9b.
  • Figures 3 to 5 show a first embodiment of the blocking device 14 which consists of two parts, namely a locking element 16 and an operating screw 17.
  • the locking element 16 has a section along a radial plane passing through the axis of rotation of the disc 1, which is drawn in such a way so that the locking element 16 can slide in the groove 2 during assembly. It has a radial thread fitted with a thread 31 intended to cooperate with the thread of the barrel 40 of the operating screw 17.
  • the operating screw 17 comprises a large screw head 41 which accommodates in the annular space 21 delimited by the bottom 15 of the feet blade 7 and the bottom of groove 2. The diameter of this head 41 is greater than the distance separating the two blade roots 7a and 7b adjacent, as seen in Figure 4.
  • the peripheral part of the upper face 42 of the screw head 41 can therefore come to bear against the undersides 15 of these two dawn feet 7a and 7b, which limits the possible radial displacement of the screw head 41.
  • the circumferential dimension of the notches 9a and 9b is advantageously less than the distance separating the two blade roots consecutive 7a and 7b.
  • the circumferential dimension of the base 23 of the locking element 16 is substantially equal to or less than the distance between the two adjacent blade roots 7a and 7b, while the circumferential dimension of the upper part of the element locking is substantially equal to the circumferential dimension of notches 9a and 9b, at least in the zones 22a, 22b which must accommodate in these notches 9a and 9b, after the element of the lock 16.
  • zones 22a and 22b are arranged in the cavity 5 of the groove 2, when the element of lock is in the lowered position. It is the same for the base 23 of the locking element 16, the lower face 24 of which is then little distance above the upper face 42 of the screw head.
  • the underside 24 of the locking element 16 is remote from the head quote.
  • the side walls 25a and 25b of the base 23 are then in abutment against the side walls 3a and 3b of the groove 2 in the vicinity of the notches 9a and 9b.
  • the forces centrifugal forces exerted on the locking element 16 tend to push the latter and the operating screw outwards.
  • the side walls 25a and 25b of the base 23 are then in positive support against the side walls 3a and 3b of the groove 2, and in the event of loosening of the operating screw 17, displacement of the screw head 41 will be limited, because the peripheral portion of the screw head 17 is retained by the adjacent blade roots 7a and 7b.
  • the head screw 17 may rest on the bottom of the groove 2, but the portions 22a and 22b of the locking element 16 will remain trapped in the notches 9a and 9b.
  • the references 26a and 26b designate radial outgrowths, parallel to the axis of the operating screw 17, which extends radially outward above the top of the element lock 16, and the vertices of which are arranged in the orifice 13 of the platforms 11a and 11b, when the locking element 16 is reassembled, to serve as a visual witness to the correct ascent of the locking element 16, during assembly, or during visits maintenance.
  • the first embodiment of the invention described above requires the diameter of the screw head 41 to be greater than the spacing between the two adjacent blade roots 7a and 7b. This requires that the axial dimension of the underside 15 of a blade root is greater than the distance separating the two adjacent blade roots 7a and 7b.
  • Figures 6 to 12 show a second embodiment of the invention which can be applied to any type of bladed disc of the type hammer attachment.
  • the element lock 16 is almost identical to that described above and will not not described further. Only the optional variants will be described.
  • the operating screw 17, according to the second embodiment of the invention has a screw head 41, of small diameter and preferably non-circular. This diameter is for example less than the distance separating the two adjacent blade roots 7a and 7b.
  • an intermediate plate 50 is interposed between the screw head 41 and the locking element 16.
  • This intermediate plate 50 which has a oblong shape, has a central orifice 51 crossed by the barrel 40 of the operating screw 17, and its circumferential dimension is such that its ends 52a and 52b are arranged under the two blade roots adjacent 7a and 7b.
  • the upper face 42 of the screw head 17 bears on the underside of the intermediate plate 50, of which the ends 52a and 52b come to bear on the undersides 15 of the two adjacent blade roots, which limits the radial movement of the head screw 41.
  • the intermediate plate 50 which is produced preferably from a sheet by cutting and folding, which is shown in detail in FIGS. 9 to 11, comprises two radial tongues 53a and 53b which extend outwards and which are housed in radial grooves 54a and 54b formed on two opposite faces of the element lock 16, as shown in Figure 12.
  • Cooperation tabs 53a and 53b with grooves 54a and 54b prevent the plate intermediate 50 to rotate relative to the locking element 16, while allowing the locking element 16 to slide by relative to the intermediate plate 50, during the ascent or the lowering of the locking element.
  • the grooves 54a and 54b are preferably arranged on the faces of the locking element 16 which are opposite the faces adjacent to the two blade roots 7a and 7b.
  • the intermediate plate 50 also includes and preferably two elastic tabs 55a and 55b which extend radially inward and which are intended to prevent loosening of the operating screw 17, the head 41 of the latter then comprising sections, six in number for example, on which the tongues 55a and 55b are in support.
  • the elasticity of the tongues 55a and 55b is calculated so as to allow the rotation of the screw head 17 when a torque is exerted predetermined on the end 43 of the operating screw 17, during the raising or lowering of the locking element 16, and is sufficient to prevent rotation of the screw head 17 in the absence of this torque.
  • FIG. 9 shows the development of the intermediate plate 50, before folding the tabs 53a, 53b, 55a and 55b. We notice that the orifice 51 is not circular.
  • the centering of the intermediate plate 50 relative to the screw maneuver 17 is achieved by the cooperation of the tongues 53a and 53b with the grooves 54a and 54b of the locking element 16.
  • the orifice 51 is however dimensioned in such a way that the screw head 41 is in pressing against the underside 55 of the intermediate plate 50.
  • the locking element 16 does not need the radial grooves 54a and 54b described above, which are used to prevent rotation of the plate intermediate 50.
EP02292896A 2001-11-22 2002-11-22 Vorrichtung zur Sicherung von Laufschaufeln in einer Nut einer Rotorscheibe Expired - Lifetime EP1314856B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0115095 2001-11-22
FR0115095A FR2832455B1 (fr) 2001-11-22 2001-11-22 Dispositif de blocage des aubes dans une rainure d'un disque

Publications (2)

Publication Number Publication Date
EP1314856A1 true EP1314856A1 (de) 2003-05-28
EP1314856B1 EP1314856B1 (de) 2005-01-26

Family

ID=8869657

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Application Number Title Priority Date Filing Date
EP02292896A Expired - Lifetime EP1314856B1 (de) 2001-11-22 2002-11-22 Vorrichtung zur Sicherung von Laufschaufeln in einer Nut einer Rotorscheibe

Country Status (9)

Country Link
US (1) US6752598B2 (de)
EP (1) EP1314856B1 (de)
JP (1) JP4043922B2 (de)
CA (1) CA2411688C (de)
DE (1) DE60202738T2 (de)
ES (1) ES2233784T3 (de)
FR (1) FR2832455B1 (de)
RU (1) RU2239070C2 (de)
UA (1) UA73767C2 (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2964692A1 (fr) * 2010-09-13 2012-03-16 Snecma Dispositif de blocage circonferentiel d'aubes marteau pour turbomachine, a deploiement radial ameliore
FR2965008A1 (fr) * 2010-09-16 2012-03-23 Snecma Disque a aubes pour rotor de turbomachine, et turbomachine equipee d'un tel disque
FR2973067A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
FR2973066A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
FR2973068A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
WO2012131227A1 (fr) * 2011-03-21 2012-10-04 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
EP2669478A1 (de) * 2012-05-31 2013-12-04 Hitachi, Ltd. Verdichter
EP2719866A1 (de) * 2012-10-12 2014-04-16 Techspace Aero S.A. Riegel für Laufradschaufeln einer Rotortrommel in einer Umlaufrille des Rotors
CN104481594A (zh) * 2014-10-28 2015-04-01 哈尔滨汽轮机厂有限责任公司 用于压气机周向环状燕尾型叶根的锁紧装置
EP3696380A1 (de) * 2019-02-04 2020-08-19 Rolls-Royce plc Adapter zur positionierung eines bearbeitungswerkzeugs zwischen zwei tragflügeln

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7435055B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Locking spacer assembly for a turbine engine
FR2886336B1 (fr) * 2005-05-26 2007-08-24 Snecma Moteurs Sa Perfectionnement a une roue aubagee de rotor pour renforcer le verrouillage des aubes
US8206116B2 (en) * 2005-07-14 2012-06-26 United Technologies Corporation Method for loading and locking tangential rotor blades and blade design
EP1801355B1 (de) * 2005-12-23 2015-02-11 Techspace Aero Laufschaufelschloss für eine Turbomaschinenrotorscheibe
US8608446B2 (en) * 2006-06-05 2013-12-17 United Technologies Corporation Rotor disk and blade arrangement
JP4886735B2 (ja) * 2008-05-26 2012-02-29 株式会社東芝 タービン動翼組立体および蒸気タービン
FR2940354B1 (fr) * 2008-12-23 2015-01-09 Snecma Dispositif de fixation d'aubes a attache marteau et disque de compresseur adapte.
US8182230B2 (en) * 2009-01-21 2012-05-22 Pratt & Whitney Canada Corp. Fan blade preloading arrangement and method
GB0908502D0 (en) * 2009-05-19 2009-06-24 Rolls Royce Plc A balanced rotor for a turbine engine
US8523529B2 (en) * 2009-11-11 2013-09-03 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
CH703997A1 (de) * 2010-10-27 2012-04-30 Alstom Technology Ltd Schaufelanordnung, insbesondere Leitschaufelanordnung.
JP5730085B2 (ja) * 2011-03-17 2015-06-03 三菱日立パワーシステムズ株式会社 ロータ構造
US8932023B2 (en) * 2012-01-13 2015-01-13 General Electric Company Rotor wheel for a turbomachine
US20140286782A1 (en) * 2012-08-07 2014-09-25 Solar Turbines Incorporated Turbine blade staking pin
US9341071B2 (en) * 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
DE102013223583A1 (de) 2013-11-19 2015-05-21 MTU Aero Engines AG Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine
DE102015203290A1 (de) * 2015-02-24 2016-09-29 MTU Aero Engines AG Sicherungselement und Strömungsmaschine
CN105065065A (zh) * 2015-08-07 2015-11-18 山东青能动力股份有限公司 一种枞树型叶根动叶片锁紧装置及其装配工艺

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Publication number Priority date Publication date Assignee Title
GB659592A (en) * 1948-09-17 1951-10-24 Sulzer Ag Improvements relating to rotors for turbines or axial flow compressors
US3088708A (en) * 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device
FR1402507A (fr) * 1963-10-24 1965-06-11 Gen Electric Dispositif de verrouillage des ailettes d'un rotor
US3955898A (en) * 1974-08-13 1976-05-11 Motoren- Und Turbinen-Union Munchen Gmbh Locking device for the rotor blades of a flow machine
GB2156908A (en) * 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine
USH1258H (en) * 1992-09-16 1993-12-07 The United States Of America As Represented By The Secretary Of The Air Force Blade lock screw

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2810366B1 (fr) * 2000-06-15 2002-10-11 Snecma Moteurs Dispositif de blocage d'aubes a attaches marteau sur un disque

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB659592A (en) * 1948-09-17 1951-10-24 Sulzer Ag Improvements relating to rotors for turbines or axial flow compressors
US3088708A (en) * 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device
FR1402507A (fr) * 1963-10-24 1965-06-11 Gen Electric Dispositif de verrouillage des ailettes d'un rotor
US3955898A (en) * 1974-08-13 1976-05-11 Motoren- Und Turbinen-Union Munchen Gmbh Locking device for the rotor blades of a flow machine
GB2156908A (en) * 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine
USH1258H (en) * 1992-09-16 1993-12-07 The United States Of America As Represented By The Secretary Of The Air Force Blade lock screw

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2964692A1 (fr) * 2010-09-13 2012-03-16 Snecma Dispositif de blocage circonferentiel d'aubes marteau pour turbomachine, a deploiement radial ameliore
US8858181B2 (en) 2010-09-13 2014-10-14 Snecma Circumferential blocking device of clamp vanes for turbine engine, with improved radial deployment
FR2965008A1 (fr) * 2010-09-16 2012-03-23 Snecma Disque a aubes pour rotor de turbomachine, et turbomachine equipee d'un tel disque
FR2973067A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
FR2973066A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
FR2973068A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
WO2012131227A1 (fr) * 2011-03-21 2012-10-04 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
EP2669478A1 (de) * 2012-05-31 2013-12-04 Hitachi, Ltd. Verdichter
EP2719866A1 (de) * 2012-10-12 2014-04-16 Techspace Aero S.A. Riegel für Laufradschaufeln einer Rotortrommel in einer Umlaufrille des Rotors
US10066487B2 (en) 2012-10-12 2018-09-04 Safran Aero Boosters Sa Drum blade lock in a circumferential rotor groove
CN104481594A (zh) * 2014-10-28 2015-04-01 哈尔滨汽轮机厂有限责任公司 用于压气机周向环状燕尾型叶根的锁紧装置
EP3696380A1 (de) * 2019-02-04 2020-08-19 Rolls-Royce plc Adapter zur positionierung eines bearbeitungswerkzeugs zwischen zwei tragflügeln

Also Published As

Publication number Publication date
RU2239070C2 (ru) 2004-10-27
US20030123986A1 (en) 2003-07-03
JP2003193801A (ja) 2003-07-09
US6752598B2 (en) 2004-06-22
DE60202738T2 (de) 2006-03-30
UA73767C2 (uk) 2005-09-15
CA2411688C (fr) 2010-04-27
JP4043922B2 (ja) 2008-02-06
CA2411688A1 (fr) 2003-05-22
FR2832455B1 (fr) 2004-04-02
DE60202738D1 (de) 2005-03-03
EP1314856B1 (de) 2005-01-26
FR2832455A1 (fr) 2003-05-23
ES2233784T3 (es) 2005-06-16

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