EP1760258A2 - Blockierungsvorrichtung einen axialen Retentionsring einer Schaufel - Google Patents

Blockierungsvorrichtung einen axialen Retentionsring einer Schaufel Download PDF

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Publication number
EP1760258A2
EP1760258A2 EP06119579A EP06119579A EP1760258A2 EP 1760258 A2 EP1760258 A2 EP 1760258A2 EP 06119579 A EP06119579 A EP 06119579A EP 06119579 A EP06119579 A EP 06119579A EP 1760258 A2 EP1760258 A2 EP 1760258A2
Authority
EP
European Patent Office
Prior art keywords
hook
immobilization
slot
ring
cleat
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
EP06119579A
Other languages
English (en)
French (fr)
Other versions
EP1760258A3 (de
EP1760258B1 (de
Inventor
Erick Jacques Boston
Alain Marc Lucien Bromann
Pierre Debeneix
Frédéric Paul Eichstadt
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 SAS
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 SAS filed Critical SNECMA SAS
Publication of EP1760258A2 publication Critical patent/EP1760258A2/de
Publication of EP1760258A3 publication Critical patent/EP1760258A3/de
Application granted granted Critical
Publication of EP1760258B1 publication Critical patent/EP1760258B1/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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to the technical field of rings for axial retention of the blades of a rotor of a turbomachine, in particular an aircraft engine.
  • It also relates to a retaining ring of the blades of a turbomachine rotor, and a rotor comprising such a device for immobilization in rotation.
  • turbomachine for example an aircraft engine, comprising such a device for immobilizing rotation.
  • axial refers to the axial direction of the turbomachine.
  • a turbomachine rotor is equipped with a disk and vanes carried by the disk, as well as with a retention ring to prevent movement of the vanes in the axial direction, as described in the document FR 2 729 709-A1 .
  • Figure 1 illustrates such a blade retention ring of a rotor, known from the prior art.
  • a disk 10 of a rotor has a disk body 11 and teeth 12 which extend radially from the disk body 11 and are distributed around the circumference thereof.
  • the space between two successive teeth 12 forms a cell 13 oriented axially.
  • Each tooth 12 is provided with at least one hook 6 projecting in an axial direction, which defines on this tooth an elementary groove opening radially inwards.
  • the teeth 12 are provided with an upstream hook 6 and a downstream hook 6.
  • FIG. 2 illustrates a root 14 of a blade 16 inserted into such a cell 13.
  • the two teeth 12 make it possible to contain this blade 16 circumferentially and radially.
  • a retention ring 20 is placed in a groove 22, discontinuous, which corresponds to the succession of elementary grooves.
  • the presence of the retaining ring 20 in the groove 22 makes it possible to prevent axial displacement of the blades 16.
  • the retaining ring 20 is opened by a slot 24 which separates the two ends or strands 26 thereof.
  • the slot 24 of the retaining ring 20 is located at one of the teeth 12 and not between two adjacent teeth 12, in order to prevent the ends of the retention ring 20 from coming out. of the groove 22.
  • each contact face 32 of the respective cleats 30 is in abutment against one of the lateral faces 44 of the abutment hook 60.
  • the slot 24 becomes is located under the hook stop 60 and the retaining ring 20 is prevented from rotating, so that the retaining ring 20 can not spontaneously exit the groove 22 during operation of the turbomachine. It follows that the vanes 16 can not escape from the cells 13 into which their feet 14 are inserted.
  • the present invention proposes a device for immobilization in rotation of a retention ring rotor blades of a turbomachine, which is an alternative to the prior art rotation immobilizer described above.
  • the invention relates to an immobilization device in rotation of a blade retention ring on a rotor disk of a turbomachine in a substantially axial direction of said turbomachine, said rotor disk being provided with hooks distributed around its circumference and defining a groove for receiving said retention ring, including a first and a second successive locking hooks, and said retention ring being provided with a slot, and at least one cleat disposed on one side thereof near said slot.
  • the position of said at least one stopper on said retention ring is such that, when said retention ring is in place in said groove, said at least one stop abuts against said first immobilization hook, and the slot is covered by said second immobilization hook.
  • immobilization hook covers two functions that fill one and / or the other of these two hooks: a stop function for a cleat and a recovery function of the slot.
  • said first immobilization hook is provided with a locking face on its side which is opposite the second hook.
  • said cleat of the retaining ring is provided with a contact face oriented towards its side which is opposite the opposite side of said slot, and said locking face cooperates with said contact face for a setting abutment of said cleat against said first immobilization hook.
  • the positions of said first and second tabs on the retention ring are such that, when said retention ring is in place in said groove, said first and second tabs abut against said first hook of immobilization, on each side thereof, and said slot is covered by said second immobilization hook.
  • said first immobilization hook is provided with a locking face on its side which is opposite said second immobilization hook and another locking face on its opposite side
  • said stops of said retention ring are each having a contact face, the contact face of said second cleat being on its side facing said slot, and the contact face said first cleat being on its side which is opposite its side facing said slot, and said locking faces cooperate with said contact faces for an abutment of said cleats against said first immobilization hook.
  • said first immobilization hook is provided with a locking face on its side which is opposite said second immobilizing hook
  • said second immobilizing hook is provided with a locking face on its side which is opposite said first immobilization hook
  • said cleat of said retaining ring is provided with two contact faces, one of said contact faces being on its side which is opposite said slot, and the other of said contact faces being on its opposite side, and said locking faces cooperate with said contact faces for abutting said first and second locking hooks against said stopper.
  • the groove has two walls, an inner wall closest to the rotor disc and an outer wall farthest from the rotor disc, characterized in that each locking face is located on said corresponding immobilizing hook, and extends in the axial direction from the free surface of said immobilizing hook to the inner wall of said groove.
  • each locking face is oriented in a radial plane of said rotor disk.
  • each locking face is oriented in an oblique plane with respect to a radial plane of said rotor disk.
  • the invention relates to a retaining ring of the blades of a turbomachine rotor, intended to be associated with a rotor disc provided with hooks distributed over its circumference, including a first immobilization hook and a second successive immobilizing hook, said first immobilizing hook being provided with a blocking face on its side which is opposite said second immobilization hook and another blocking face on its opposite side to its side which is opposite said second immobilization hook, said ring having a slot and two tabs, arranged on one side of this ring.
  • said two cleats are arranged on the same side of said slot, so that they can respectively abut against one of said two locking faces of said first immobilization hook.
  • the invention relates to a retaining ring of the blades of a turbomachine rotor, intended to be associated with a rotor disc provided with hooks distributed over its circumference, including a first immobilization hook and a second successive immobilization hook, said first immobilization hook being provided with a locking face on its side which is opposite said second immobilization hook, and said second immobilization hook being provided with a face of blocking on its side which is opposite said first immobilization hook, said ring having a slot.
  • said ring further comprises a single cleat, disposed on one side thereof on one side of said slot near it, so that said single cleat can be in abutment against the locking face of said first immobilization hook and the locking face of said second immobilization hook.
  • the invention relates to a disk / ring assembly, having a retention ring provided with a slot, and having a rotor disc provided with hooks distributed around its circumference and defining a groove for receiving said retention ring, characterized in that said rotor disk has a first immobilization hook and a second immobilization hook successive, in that said retaining ring has at least one cleat disposed on one side thereof near said slot, and in that the position of said latch on said retention ring is such that, when said retention ring is in place in said groove, said cleat is abutting against said first immobilization hook, and the slot is covered by said second immobilization hook.
  • said first immobilization hook is provided with a blocking face on its side which is opposite the second immobilization hook
  • said at least one stopper of the retention ring is provided with a contact face. on its side which is opposed to its side opposite said slot, and said locking face cooperates with said contact face for an abutment of said latch against said first immobilization hook.
  • said retaining ring comprises first and second tabs disposed on one side thereof on the same side of said slot, said first tab being closer than said second cleat of said slot.
  • the positions of said first and second tabs on the retention ring are such that, when said retention ring is in place in said groove, said first and second cleats abut against said first immobilization hook, on each side thereof, and said slot is covered by said second immobilization hook.
  • said first immobilization hook is provided with a locking face on its side which is opposite said second immobilization hook and another locking face on its opposite side
  • said cleats of said retaining ring are each provided with a contact face, the contact face of said second cleat being on its side which is opposite said slot, and the contact face of said first cleat being on its side which is opposite its side facing said slot, and said locking faces cooperate with said contact faces for an abutment of said latches against said first immobilization hook.
  • said retention ring comprises a single cleat disposed on one side thereof near said slot.
  • the position of said cleat on said retention ring is such that, when said retaining ring is in place in said groove, said single cleat abuts against said first immobilization hook and against said second hook immobilization, and said slot is covered by said second immobilization hook.
  • said first hook of immobilization is provided with a locking face on its side which is opposite said second immobilizing hook
  • said second immobilizing hook is provided with a locking face on its side which is opposite said first hook of immobilization
  • said cleat of said retaining ring is provided with two contact faces, one of said contact faces being on its side which is opposite said slot, and the other of said contact faces being on its opposite side, and said locking faces cooperate with said contact faces for abutment of said first and second locking hooks against said stopper.
  • the invention relates to a turbomachine rotor comprising an immobilization device according to the first aspect of the invention and / or a retention ring according to the second aspect of the invention and / or a disk assembly. ring according to the third aspect of the invention.
  • the invention relates to a turbomachine, for example an aircraft engine, comprising an immobilization device according to the first aspect of the invention and / or a retention ring according to the second aspect of the invention.
  • a turbomachine for example an aircraft engine
  • an immobilization device according to the first aspect of the invention and / or a retention ring according to the second aspect of the invention.
  • invention and / or a disk / ring assembly according to the third aspect of the invention.
  • FIGS. 3 and 4 The two embodiments of the rotational immobilization device according to the invention, illustrated in FIGS. 3 and 4, will only be described for their differences with the rotation immobilization device according to the prior art, illustrated in FIG. 2.
  • identical references designate identical characteristics.
  • the retention ring will simply be called “Ring”
  • the first and second immobilization hooks will simply be called “first hook” and “second hook” respectively.
  • a disc 10 of a rotor has teeth 12 which extend radially from its circumference and are distributed on this circumference.
  • the space between two successive teeth 12, 222, 224 forms an axially oriented cavity 13 in which is inserted a foot 14 of a removable blade 16.
  • These two successive teeth 12 have shapes and dimensions which make it possible to contain circumferentially and radially the blade 16 installed between them in the cell 13.
  • the teeth 12 have a protruding portion 4 protruding from the disk 10 in the upstream axial direction and / or a projecting portion 4 protruding from the disk 10 in the downstream axial direction.
  • each projecting portion 4 is formed an elementary groove opening radially inwards, the free end of each projecting portion 4 beyond the elementary groove with respect to the disk body 11 forming a hook 6 oriented radially. towards the inside.
  • Each elementary groove has two walls, an inner wall closest to the rotor disk 10 and an outer wall furthest from the rotor disk 10.
  • the succession of the elementary grooves forms a groove 22, discontinuous, in which the ring 20 is arranged.
  • the ring 20 in the groove 22 constitutes an axial abutment which makes it possible to prevent axial displacement. 16.
  • this ring 20 is opened by a slot 24 which separates its two ends 26 from one another.
  • the hooks 6 are successively a first hook 162 and a second hook 164.
  • the second hook 164 has a geometry similar to the geometry of the hooks 6 of the prior art.
  • the first hook 162 has a modified geometry compared to that of the hooks 6. It has a front face 142 which is the face of its free surface and two side surfaces 144 which are substantially perpendicular to the front surface 142. Each of these two side faces 144 extends from the front face 142 of the first hook 162 to the inner wall of the elementary groove of this first hook 162. Preferably, the two lateral faces 144 are obtained by machining on each lateral side of the first hook 162, that is to say on the side opposite the second hook 164 and on the side opposite this side facing the second hook 164. In other words, the corresponding tooth 12 ends with a hook 162 which has two lateral faces 144, these lateral faces being circumferentially recessed.
  • the lateral faces 144 are oriented along a radial plane of the rotor disk 10.
  • the ring 20 has a slot 24 and two tabs 302, 304 positioned on its face opposite its face facing the rotor disc 10.
  • each cleat 302, 304 is made in the following manner. Two cuts are made on the ring 20, so as to remove a ring sector having a given dimension in the circumferential direction of said ring 20 and the same dimension as the rest of the ring 20 in the axial direction. The removed sector is replaced by a part having the same dimension in the axial direction and the same dimension in the circumferential direction, but having a greater thickness. This piece is fixed to the rest of the ring 20 by welding so as to reconstitute a closed ring 20. Then the cleat 302, 304 is machined in said piece of greater thickness than the remainder of the ring 20. Such a procedure allows precise machining of the cleats 302, 304, ensuring their dimensions and their position on the ring 20.
  • the slot 24 is formed on the ring 20 after the two tabs 302, 304 have been made. It is positioned in such a way that the two catches 302, 304 are arranged on the same side of the slot 24, towards one of the ends 26. of the ring 20.
  • the first cleat 302 is closer to the slot 24 than the second cleat 304.
  • Each cleat 302, 304 has a contact face 32.
  • the contact face 32 of the second cleat 304 is oriented towards the slot 24.
  • the contact face 32 of the second cleat 304 is oriented on the opposite side.
  • each cleat 302, 304 is in abutment against one of the side faces 144 of the first hook 162.
  • the side faces 144 are locking faces of the first hook 162, which cooperate with the respective contact faces 32 of the two tabs 302, 304 of the ring 20.
  • the two ends 26 of the ring 20 and the slot 24 are then under the second hook 164.
  • the position of the two tabs 302, 304 on the ring 20 is suitably set, preferably depending on the dimensions and distances of the first and second hooks 162, 164 of the rotor disc 10.
  • the position of the first tab 302 is defined so that the slot 24 is under the second hook 164 while the contact face 32 of the first catch 302 is against the locking face 144 of the first hook 162.
  • the position of the second stop 304 is defined by the distance between the two cleats 302, 304, which is substantially equal to the distance between the two locking faces 144 of the first hook 162.
  • the ring 20 is prevented from turning in the groove 22. As a result, it can not escape from the groove 22 during the operation of the turbomachine. It follows that the vanes 16 can not escape in the direction of the cell 13 in which they are inserted.
  • the two tabs 302, 304 are located near the slot 24, which reduces the risk that the end 26 of the ring 20 located on the same side as the two tabs 302 , 304 does not escape from the groove 22.
  • the two tabs 302, 304 are located upstream of the slot 24 in the direction of rotation of the rotor, which is designated by the reference numeral 80 in FIG. 3. With this direction of rotation 80, it is the blocking face 144 of the first hook 162 which is opposite the second hook 164 which plays mainly a blocking function, in cooperation with the first catch 302 of the ring 20.
  • hooks 6 are successively a first hook 262 and a second hook 264.
  • the two hooks 262, 264 have a modified geometry compared to that of the hooks 6.
  • Each hook 262, 264 has a front face 142 which is the face of its free surface, and a lateral face 144 which is substantially perpendicular to the front face 142 and facing the other hook 264, 262.
  • the lateral face 144 of the first hook 262, respectively of the second hook 264 extends from the front face 142 of said hook 262, 264, to the inner wall. of the elementary groove of said hook 262, 264.
  • the lateral face 144 of the first hook 262 is obtained by machining on its lateral side which is opposite the second hook 264.
  • each of the corresponding teeth 12 ends with a hook 262, 264 which has a side face 144 on its side opposite the other hook 264, 262, said lateral face being circumferentially recessed.
  • the lateral faces 144 are oriented in a radial plane of the rotor disc 10.
  • the ring 20 has a slot 24 and a single lug 306 positioned on its face opposite its face facing the rotor disk 10.
  • the cleat 306 is preferably made by a method similar to that described for the production of the cleats 302, 304 of the first embodiment of the immobilizer.
  • the slot 24 is made on the ring 20 after the embodiment of the catch 306. It is positioned in such a way that the catch 306 is disposed on one side of the slot 24 and close to it, towards one of the ends 26 of the ring 20.
  • the cleat 306 has two contact faces 32. One of the contact faces 32 of the cleat 306 is oriented on the side of the slot 24 and the other contact face 32 is oriented on the opposite side.
  • each contact face 32 of the cleat 306 is in abutment against the face lateral faces 144 of the first hook 262 and against the lateral face 144 of the second hook 264.
  • the lateral faces 144 of the first hook 162 and the second hook 164 are locking faces which cooperate with the respective contact faces 32 of the cleat 306 of the 20.
  • the two ends 26 of the ring 20 and the slot 24 are then under the second hook 264.
  • the position of the cleat 306 on the ring 20 and the circumferential width or dimension of the cleat 306 are suitably set, preferably depending on the dimensions and distances of the hooks 262, 264 of the rotor disk 10.
  • the distance between the cleat 306 and the slot 24 is defined so that the slot 24 is under the second hook 264 while one of the contact faces 32 of the catch 306 is against one of the two respective locking faces 144 of the two hooks 262, 264
  • the width of the catch 306 is substantially equal to the distance between the locking face 144 of the first hook 262 and the locking face 144 of the second hook 264.
  • the ring 20 is prevented from rotating in the groove 22. As a result, it can not escape the groove 22 during operation of the turbomachine. It follows that the vanes 16 can not escape in the axial direction of the cell 13 in which they are inserted.
  • the cleat 306 is located near the slot 24, which reduces the risk that the end 26 of the ring 20 located on the same side as the cleat 306 escapes. throat 22.
  • the cleat 306 is located upstream of the slot 24 in the direction of rotation of the rotor, which is designated by the reference 80 in FIG. 4. With this direction of rotation 80, it is the locking face 144 of the first hook 262 which plays mainly a blocking function, in cooperation with the cleat 306 of the ring 20.
  • the invention which has just been described thus makes it possible to prevent the ring 20 from rotating in the groove 22. It has the advantage that the slot 24 of the ring 20 is positioned under a hook and not between two hooks.
  • the actual immobilization function (by abutting the contact faces 32 of the catches against the locking faces 144 of the hooks 162, 262, 264 ) and the overlap function of the slot 24 is not provided by a single disk hook as was the case with the immobilizer of the prior art.
  • An advantage of the immobilization device of the ring 20 according to the invention lies in the fact that it is possible to dissociate the width of the slot 24, that is to say the clearance between the two ends or strands 26 of the ring 20, the clearance necessary for mounting the ring 20 between the faces in cooperation, namely at least one of the faces of contact 32 and at least one of the locking faces 144.
  • the first cleat 302 alone would fulfill the immobilization function in rotation of the ring 20, taking into account the direction of rotation represented by the arrow 80.
  • the second cleat 304 allows, in addition, maintain the opening of the slot 24 between the two strands 26, and prevent these two strands 26 come into contact.
  • the immobilization function in rotation of the ring 20 is filled by the abutment of one of the contact faces 32 of the catch 306 with the locking face 144 of the first immobilization hook. 262, taking into account the direction of rotation represented by the arrow 80.
  • the abutment of the other of the contact faces 32 of the cleat 306 with the locking face 144 of the second immobilization hook 264 allows, moreover, to control the position of the strand 26 carrying the cleat 306 relative to the other strand 26, to maintain the opening of the slot 24 between the two strands 26, and to prevent them from coming into contact.
  • the abutment of the cleat 306 against the first hook 262 and against the second hook 264 is achieved by controlling the circumferential dimension of said cleat 306.
  • the control of the circumferential clearance that is to say the opening of the slot 24 between the two strands 26 of the ring 20 has the effect of improving the maintenance of these two. strands 26 in the groove 22, and thus the retention of the ring 20 in the groove 22.
  • the slot 24 is perpendicular to the circumferential direction of the ring 20, but it could be oblique, without departing from the scope of the invention.
  • the locking faces are oriented along a radial plane of the rotor disk, but they could be oriented in an oblique plane with respect to a radial plane of the rotor disk, without departing from the frame. of the invention.
  • the cells 13 into which the feet 14 of the vanes 16 are inserted are oriented axially, but the invention also applies to configurations in which the direction of the cells forms an angle with the direction axial axis of the turbomachine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pile Receivers (AREA)
EP06119579A 2005-08-31 2006-08-25 Blockierungsvorrichtung für einen axialen Retentionsring einer Schaufel Active EP1760258B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0552635A FR2890104A1 (fr) 2005-08-31 2005-08-31 Dispositif d'immobilisation d'un anneau de retention axiale d'une aube, disque de rotor et anneau de retention associes et rotor et moteur d'aeronef les comportant

Publications (3)

Publication Number Publication Date
EP1760258A2 true EP1760258A2 (de) 2007-03-07
EP1760258A3 EP1760258A3 (de) 2007-08-01
EP1760258B1 EP1760258B1 (de) 2008-10-15

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EP06119579A Active EP1760258B1 (de) 2005-08-31 2006-08-25 Blockierungsvorrichtung für einen axialen Retentionsring einer Schaufel

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US (1) US7290988B2 (de)
EP (1) EP1760258B1 (de)
CA (1) CA2557765C (de)
DE (1) DE602006003155D1 (de)
FR (1) FR2890104A1 (de)

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FR2951224A1 (fr) * 2009-10-13 2011-04-15 Turbomeca Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque
FR2974142A1 (fr) * 2011-04-14 2012-10-19 Snecma Dispositif d'immobilisation en rotation d'un anneau de retention d'aubes
FR3000763A1 (fr) * 2013-01-04 2014-07-11 Snecma Disque de rotor muni d’une pluralite de crochets
FR3029962A1 (fr) * 2014-12-11 2016-06-17 Snecma Blocage axial des aubes dans une roue de turbomachine
EP2722484A3 (de) * 2012-10-18 2017-09-27 General Electric Company Systeme und Verfahren zum axialen Festhalten von Schaufeln

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FR2890105A1 (fr) * 2005-08-31 2007-03-02 Snecma Dispositif d'immobilisation d'un anneau de retention axiale d'une aube, disque de rotor et anneau de retention associes et rotor et motor d'aeronef les comportant
US20090264785A1 (en) * 2008-04-18 2009-10-22 Brainscope Company, Inc. Method and Apparatus For Assessing Brain Function Using Diffusion Geometric Analysis
FR2930603B1 (fr) * 2008-04-24 2010-04-30 Snecma Dispositif de retention axiale d'aubes mobiles sur un disque de rotor
FR2955904B1 (fr) * 2010-02-04 2012-07-20 Snecma Soufflante de turbomachine
US9790803B2 (en) * 2013-03-08 2017-10-17 United Technologies Corporation Double split blade lock ring
US10024183B2 (en) * 2013-03-14 2018-07-17 United Technologies Corporation Gas turbine engine rotor disk-seal arrangement
US10125619B2 (en) 2015-11-19 2018-11-13 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US10145249B2 (en) * 2016-02-23 2018-12-04 Mechanical Dynamics & Analysis Llc Turbine bucket lockwire anti-rotation device for gas turbine engine
JP7213835B2 (ja) * 2020-02-10 2023-01-27 三菱重工業株式会社 タービンホイール

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US5320492A (en) * 1992-07-22 1994-06-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Sealing and retaining device for a rotor notched with pin settings receiving blade roots
FR2729709A1 (fr) * 1995-01-25 1996-07-26 Snecma Dispositif d'etancheite et de retention des aubes de rotor de turbomachine
US6234756B1 (en) * 1998-10-26 2001-05-22 Allison Advanced Development Company Segmented ring blade retainer
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US5320492A (en) * 1992-07-22 1994-06-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Sealing and retaining device for a rotor notched with pin settings receiving blade roots
FR2729709A1 (fr) * 1995-01-25 1996-07-26 Snecma Dispositif d'etancheite et de retention des aubes de rotor de turbomachine
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EP1443179A2 (de) * 2003-01-30 2004-08-04 ROLLS-ROYCE plc Rotor sowie seine Schaufelhalteplatte

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2951224A1 (fr) * 2009-10-13 2011-04-15 Turbomeca Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque
WO2011045520A1 (fr) * 2009-10-13 2011-04-21 Turbomeca Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque
RU2550226C2 (ru) * 2009-10-13 2015-05-10 Турбомека Рабочее колесо турбины и газотурбинный двигатель
US9163520B2 (en) 2009-10-13 2015-10-20 Turbomeca Turbine wheel fitted with an axial retaining ring that locks the blades relative to a disk
FR2974142A1 (fr) * 2011-04-14 2012-10-19 Snecma Dispositif d'immobilisation en rotation d'un anneau de retention d'aubes
EP2722484A3 (de) * 2012-10-18 2017-09-27 General Electric Company Systeme und Verfahren zum axialen Festhalten von Schaufeln
FR3000763A1 (fr) * 2013-01-04 2014-07-11 Snecma Disque de rotor muni d’une pluralite de crochets
US9689278B2 (en) 2013-01-04 2017-06-27 Snecma Rotor disk including a plurality of hooks
FR3029962A1 (fr) * 2014-12-11 2016-06-17 Snecma Blocage axial des aubes dans une roue de turbomachine

Also Published As

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CA2557765A1 (fr) 2007-02-28
DE602006003155D1 (de) 2008-11-27
US20070048141A1 (en) 2007-03-01
FR2890104A1 (fr) 2007-03-02
US7290988B2 (en) 2007-11-06
EP1760258A3 (de) 2007-08-01
EP1760258B1 (de) 2008-10-15
CA2557765C (fr) 2013-07-02

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