EP1801355A1 - Laufschaufelschloss für eine Turbomaschinenrotorscheibe - Google Patents

Laufschaufelschloss für eine Turbomaschinenrotorscheibe Download PDF

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Publication number
EP1801355A1
EP1801355A1 EP05292779A EP05292779A EP1801355A1 EP 1801355 A1 EP1801355 A1 EP 1801355A1 EP 05292779 A EP05292779 A EP 05292779A EP 05292779 A EP05292779 A EP 05292779A EP 1801355 A1 EP1801355 A1 EP 1801355A1
Authority
EP
European Patent Office
Prior art keywords
groove
lock
disk
turbomachine
latch
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
EP05292779A
Other languages
English (en)
French (fr)
Other versions
EP1801355B1 (de
Inventor
Philippe Ernst
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 Aero Boosters SA
Original Assignee
Techspace Aero 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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP05292779.5A priority Critical patent/EP1801355B1/de
Publication of EP1801355A1 publication Critical patent/EP1801355A1/de
Application granted granted Critical
Publication of EP1801355B1 publication Critical patent/EP1801355B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/3023—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts

Definitions

  • the invention relates to a locking device used on a turbomachine disk carrying vanes.
  • a locking device used on a turbomachine disk carrying vanes.
  • Such a device serves to block said blades in the circumferential direction of the disk.
  • This device is housed in a circumferential groove of the disc, the blades being retained by their foot in this groove.
  • the invention also relates to a turbomachine disk and a turbomachine, equipped with such a locking device.
  • FIG. 1 An example of a disk equipped with a known locking device is shown in FIG. 1.
  • the device 101 comprises a lock 105 and a screw 103 passing through the lock.
  • the disk 107 has a circumferential groove 106 in which the lock 105 is housed.
  • the groove 106 is delimited, in its upper part, by first and second lips 109, 111.
  • the screw 103 is tightened.
  • the latter then bears against the bottom 108 of the groove 106 and forces the lock 105 to go up against the lips 109, 111 of the groove. More precisely, they are radial bearings 117, 122 projecting from opposite lateral faces 119, 121 of the lock which abut against said lips 109, 111.
  • the lock 105 thus moves in a translation movement, along the axis S of the screw.
  • This device has the disadvantage of being difficult to lock when the screw is not properly oriented inside the groove. This is the case, for example, when the axis S of the screw is oriented in the direction D shown in dotted line in FIG. 1. In such a situation, one of the radial bearing surfaces 117, 122 of the lock comes into abutment before the other, and the device tends to hang. To lock the device correctly, it is then necessary to increase the tightening torque, with the risk of damaging the threading of the screw 103 and / or the internal threading of the lock 105.
  • the wrong orientation of the screw 103 may cause the release of the lock, that is to say the output of one of the bearings 117, 122 outside the groove 106.
  • the invention aims to provide a device easy to lock, especially when the lips of the groove in which it is housed are not at the same distance from the axis of rotation of the disc.
  • the invention relates to a device of the aforementioned type comprising a lock passing from an unlocked position to a locked position under the action of pushing means resting on the bottom of the groove, this lock having a first and second opposite lateral faces, characterized in that the first lateral face of the latch has a bearing surface in rotation, and in that said latch is able to move in rotation around said bearing surface, in a plane perpendicular to the circumferential direction of the disk (that is to say a radial plane, containing the axis of rotation of the disk), to move from its unlocked position to its locked position.
  • said support surface is locked in the groove and activates the thrust means which generally comprise a screw cooperating with a threaded hole passing through the lock.
  • the thrust means which generally comprise a screw cooperating with a threaded hole passing through the lock.
  • the lock remains in support on this surface.
  • the locking of the device is obtained not by translation of the lock, but by rotation (or pivoting) thereof.
  • the first lateral face of the lock is curved and constitutes said bearing surface in rotation.
  • the curvature of the first side face facilitates rotation guidance.
  • the side face being devoid of projections (it has neither tenon nor radial bearing), its manufacture is simple and the cost price of the lock is low, compared to that of known locks.
  • the lock has on its second side face a pin or other means for preventing the circumferential movement of the latch when the latter is in its locked position.
  • This stud is protruding from the second side face and adapted to be housed in a notch formed in a lip of the groove, when the lock goes into its locked position.
  • the lock has on its second side face a radial bearing or other means for preventing the radial displacement of the latch, when the latter is in its locked position.
  • This scope is projecting relative to the second side face and is adapted to abut against a lip of the groove, when the lock passes into its locked position.
  • the radial direction is defined with respect to the axis of rotation of the disk (a radial line is perpendicular to the axis of rotation and intersects this axis).
  • the invention also relates to a turbomachine disk having a circumferential groove in which blades are capable of being retained by their feet, this groove being delimited, in its upper part, by first and second lips, the disk comprising a blocking device, as previously described, for blocking the blades in the circumferential direction of the disk.
  • the disc has a housing, between the upper edge of the first lip and the bottom of the groove, adapted to receive the bearing surface in rotation of the latch and whose shape is substantially complementary to that of the bearing surface. This improves the rotation guidance of the lock.
  • the bearing surface is formed by the first lateral face of the latch, the whole of this lateral face is located under the upper edge of the first lip of the groove and the upper part of the first lateral face abuts against this first lip, at least when the lock is in the locked position.
  • the subject of the invention is also a turbomachine rotor drum and, more generally, a turbomachine comprising a disc of the aforementioned type.
  • turbojet turbojet
  • turboprop land gas turbine
  • rotor of the low pressure compressor of this turbojet consists of a drum formed of a stack of disks on the periphery of which are fixed blades, whose head remains free.
  • FIG. 2 there is shown (see Figure 2) a disc 7 carrying vanes 13 forming part of the drum of such a rotor.
  • This drum is constituted by several disks 7 of this type and each disk carries at its periphery a plurality of vanes 13 (see FIG. 3).
  • the blades 13 are retained in a groove 6, extending circumferentially to the outer surface of the disk 7.
  • a blade 13 comprises at its base a platform 16 and a blade root 18, said to "hammer clip", which is extends under said platform 16 over part of the width thereof.
  • the blade root 18 is engaged and retained in said groove 6 of the disk 7. In FIG. 3, the position of the blade root 18 in the groove 6 appears in phantom.
  • the groove 6 is delimited in its upper part, by a first lip, or upstream lip 9, and by a second lip, or downstream lip 11.
  • the upstream and downstream are defined relative to the normal direction the circulation of gases through the turbomachine.
  • the platform 16 of a blade 13 comes to cover a sector of the groove 6. Once all the blades 13 are in place, the platforms 16, side by side, reconstruct an annular surface which externally delimits a portion of the conical flow of the compressor. inside which the gases circulate.
  • the mounting of the blades 13 requires at least one insertion slot 30 to be made on one of the annular lips 9, 11 of the groove 6, in this case the two lips have an insertion notch 30.
  • This notch 30 makes it possible to engage the dawning feet 18 one after the other in the groove 6.
  • Each locking device 1 comprises a latch 5 traversed by a screw 3.
  • the latch has two opposite upstream side faces 21 and downstream 21 opposite. Once the lock 5 in the groove 6, the upstream side faces 19 and downstream 21 respectively face the upstream lips 9 and downstream 11 of this groove.
  • the radial span 17 extends substantially over the entire width of the side face 21, while the pin 15 extends over only a portion of this width.
  • the pin 15 is intended to be housed in a notch 23 formed in the downstream lip 11 of the groove 6 and the radial bearing 17 is intended to abut against the downstream lip 11 when the latch 5 is in the locked position (see FIG. ).
  • the upstream side face 19 of the lock is devoid of tenon or radial bearing. This face 19 is curved and constitutes a rotating bearing surface around which the latch 5 pivots to move from its unlocked position to its locked position (or vice versa). The change of position is made during the screwing (or unscrewing) of the screw 3.
  • the upstream side face 19 of the lock 5 is housed between the upper edge of the upstream lip 9 of the groove 6 and the bottom 8 of this groove.
  • the wall of the housing receiving the upstream side face of the latch 5, is also curved. The shape of this wall and that of the upstream side face 19 correspond to promote the guiding of the latch 5 during its pivoting.
  • the downstream lateral face 21 of the lock 5 has, in regions where there is neither the tenon nor the radial bearing surface 17, a curvature such that the clearance J between the face 21 and the downstream lip 11 of the groove remains substantially constant during the rotation of the latch.
  • An example of a face 21 of this type is shown in FIGS. 3 and 4.
  • the face 21 is part of an arc of circle C of appropriate diameter, centered at the point O which belongs to the rotating support surface formed by the side face 19. Note that a point on the face 21 substantially describes part of the arc C when the latch 5 pivots.
  • downstream side face 21 is substantially flat. This simplifies the machining of the lock, but the assembly clearance between the lock 5 and the disc 7 varies during the rotation of the lock (so be careful that this game is not too high).
  • the locking device according to the invention is interesting when the lips 9 and 11 of the groove 6 are offset, that is to say located at different distances, D and d, of the axis of A rotation of the disc (see Figure 3).
  • FIG. 3 shows the average plane P passing through the lower faces of the lips 9, 11 against which the upper part of the upstream lateral face 19 and the radial bearing 17 respectively abut in the locked position of the lock 5.
  • the plane P is inclined at an angle with respect to the axis A of rotation of the disk, which also corresponds to the axis of the turbomachine.
  • the angle a is greater than or equal to 25 °, it is preferable to use a locking device according to the invention because the use of known devices, in which the lock is mounted in translation along the axis of the screw, gives very poor results in terms of locking.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP05292779.5A 2005-12-23 2005-12-23 Laufschaufelschloss für eine Turbomaschinenrotorscheibe Active EP1801355B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05292779.5A EP1801355B1 (de) 2005-12-23 2005-12-23 Laufschaufelschloss für eine Turbomaschinenrotorscheibe

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05292779.5A EP1801355B1 (de) 2005-12-23 2005-12-23 Laufschaufelschloss für eine Turbomaschinenrotorscheibe

Publications (2)

Publication Number Publication Date
EP1801355A1 true EP1801355A1 (de) 2007-06-27
EP1801355B1 EP1801355B1 (de) 2015-02-11

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Family Applications (1)

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EP05292779.5A Active EP1801355B1 (de) 2005-12-23 2005-12-23 Laufschaufelschloss für eine Turbomaschinenrotorscheibe

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EP (1) EP1801355B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2971542A1 (fr) * 2011-02-16 2012-08-17 Snecma Dispositif de blocage circonferentiel d'aubes pour turbomachine, a deploiement radial par mouvement de rotation d'un organe du dispositif
EP2719866A1 (de) 2012-10-12 2014-04-16 Techspace Aero S.A. Riegel für Laufradschaufeln einer Rotortrommel in einer Umlaufrille des Rotors
EP2333243A3 (de) * 2009-11-19 2014-06-18 United Technologies Corporation Rotor mit Umfangsnut, zugehöriges Schloss, Scheibe und Montageverfahren
EP2873808A1 (de) 2013-11-19 2015-05-20 MTU Aero Engines GmbH Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine
EP2602435A3 (de) * 2011-12-07 2017-04-05 United Technologies Corporation Strömungsmaschinenrotor und zugehöriges Montageverfahren

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3165294A (en) * 1962-12-28 1965-01-12 Gen Electric Rotor assembly
US3721506A (en) * 1971-05-25 1973-03-20 Gen Electric Split-nut blade locking assembly
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
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
US5584658A (en) * 1994-08-03 1996-12-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbocompressor disk provided with an asymmetrical circular groove
US20030123986A1 (en) * 2001-11-22 2003-07-03 Snecma Moteurs Device for immobilizing blades in a slot of a disk

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2097480B (en) * 1981-04-29 1984-06-06 Rolls Royce Rotor blade fixing in circumferential slot
FR2810366B1 (fr) * 2000-06-15 2002-10-11 Snecma Moteurs Dispositif de blocage d'aubes a attaches marteau sur un disque
FR2857405B1 (fr) * 2003-07-07 2005-09-30 Snecma Moteurs Amelioration de la capacite de retention d'une aube a attache marteau dissymetrique
FR2886336B1 (fr) * 2005-05-26 2007-08-24 Snecma Moteurs Sa Perfectionnement a une roue aubagee de rotor pour renforcer le verrouillage des aubes

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3165294A (en) * 1962-12-28 1965-01-12 Gen Electric Rotor assembly
US3721506A (en) * 1971-05-25 1973-03-20 Gen Electric Split-nut blade locking assembly
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
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
US5584658A (en) * 1994-08-03 1996-12-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbocompressor disk provided with an asymmetrical circular groove
US20030123986A1 (en) * 2001-11-22 2003-07-03 Snecma Moteurs Device for immobilizing blades in a slot of a disk

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2333243A3 (de) * 2009-11-19 2014-06-18 United Technologies Corporation Rotor mit Umfangsnut, zugehöriges Schloss, Scheibe und Montageverfahren
FR2971542A1 (fr) * 2011-02-16 2012-08-17 Snecma Dispositif de blocage circonferentiel d'aubes pour turbomachine, a deploiement radial par mouvement de rotation d'un organe du dispositif
WO2012110735A1 (fr) * 2011-02-16 2012-08-23 Snecma Dispositif de blocage circonferentiel d'aubes pour turbomachine, a deploiement radial par mouvement de rotation d'un organe du dispositif
EP2602435A3 (de) * 2011-12-07 2017-04-05 United Technologies Corporation Strömungsmaschinenrotor und zugehöriges Montageverfahren
US10107114B2 (en) 2011-12-07 2018-10-23 United Technologies Corporation Rotor with relief features and one-sided load slots
US10704401B2 (en) 2011-12-07 2020-07-07 Raytheon Technologies Corporation Rotor with relief features and one-sided load slots
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
EP2873808A1 (de) 2013-11-19 2015-05-20 MTU Aero Engines GmbH Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine
DE102013223583A1 (de) 2013-11-19 2015-05-21 MTU Aero Engines AG Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine
US10041363B2 (en) 2013-11-19 2018-08-07 MTU Aero Engines AG Blade-disk assembly, method and turbomachine

Also Published As

Publication number Publication date
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