EP1969206B1 - Ensemble de verrouillage pour verrouiller l'interstice restant entre la premiere et la derniere aube d'une couronne d'aubes placees dans une rainure peripherique d'une turbomachine et turbomachine correspondante - Google Patents

Ensemble de verrouillage pour verrouiller l'interstice restant entre la premiere et la derniere aube d'une couronne d'aubes placees dans une rainure peripherique d'une turbomachine et turbomachine correspondante Download PDF

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Publication number
EP1969206B1
EP1969206B1 EP06841633A EP06841633A EP1969206B1 EP 1969206 B1 EP1969206 B1 EP 1969206B1 EP 06841633 A EP06841633 A EP 06841633A EP 06841633 A EP06841633 A EP 06841633A EP 1969206 B1 EP1969206 B1 EP 1969206B1
Authority
EP
European Patent Office
Prior art keywords
assembly
locking
circumferential groove
parts
sub
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.)
Not-in-force
Application number
EP06841633A
Other languages
German (de)
English (en)
Other versions
EP1969206A1 (fr
Inventor
Joachim Krützfeldt
Markus Kunze
Silvio-Ulrich Martin
Stefan Mutke
Kang Qian
Christoph Richter
Oliver Schneider
Peter Schröder
Michael Schwarz
Ulrich Waltke
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP06841633A priority Critical patent/EP1969206B1/fr
Priority to PL06841633T priority patent/PL1969206T3/pl
Publication of EP1969206A1 publication Critical patent/EP1969206A1/fr
Application granted granted Critical
Publication of EP1969206B1 publication Critical patent/EP1969206B1/fr
Not-in-force 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the invention relates to a closing assembly for closing the remaining gap between the first and the last used in a circumferential groove of a turbomachine blade of a blade ring, consisting of at least two side parts, of which at least one can be hooked with an undercut forming a projection of the circumferential groove and at least one securing element , which secures the parts against detachment from the circumferential groove.
  • Both end assemblies essentially consist of two side parts, which are inserted into the remaining space between the first and the last blade of a blade ring. Since each side part in each case interlocks with a projection of the circumferential groove forming the undercut, and thus both side parts can be introduced into the intermediate space, both side parts together - viewed in the axial direction - are narrower than the intermediate space to be filled up and closed. After the assembly of the two side parts in turn remains a space between them free, which must be filled with an intermediate part.
  • the intermediate part secures the two side parts against an axial displacement which releases the respective entanglement and thus against detachment from the circumferential groove.
  • this is equipped with two lip-like webs, which are each inflected by plastic deformation in a provided on each side panel bag.
  • the intermediate part is positively locked with each side part, which also causes the two Side parts are kept in the circumferential groove.
  • the US 2002 / 0127105A1 also proposes that the intermediate part is hooked via a dovetail with the first and the last blade of the blade ring, whereas according to the EP 1 457 642 A1 each side part of the final assembly is hooked to the first and the last blade of the blade ring. Thereby, a gap formation and enlargement between adjacent blades and the final assembly in the circumferential direction is substantially prevented.
  • a screw is provided in the middle, conically shaped in cross-section intermediate part.
  • the screw which is supported on the groove base can lift the intermediate part in the direction of the slot opening. Due to arranged on the side parts, corresponding to the intermediate part inclined side surfaces, these can be hooked securely each with the circumferential groove by lifting the intermediate part.
  • a rotor closure for rotors of thermal turbomachines which consists of two end halves.
  • the two end halves are connected by a dovetail attachment when installed.
  • the elements of the dovetail suspension are formed on the two halves in such a way that the dovetail suspension is produced by a displacement of the two halves directed towards one another in the circumferential direction.
  • the rotor closure of DE 103 10 431 A1 There is a further remaining space between the blades used, which, however, can be distributed along the circumference of the circumferential groove.
  • the parts are successively inserted into the circumferential groove and then releasably connected together by means of a pin-like securing element.
  • a pin-like securing element So far, in the prior art designed as an intermediate part securing element was positively held between the side parts, so that the final assembly was secured as a whole against detachment from the circumferential groove.
  • the invention is based on the knowledge that contrary to the usual Conceived a detachable connection of the parts of the final assembly solves the task reliable.
  • the final assembly can be detached from the circumferential groove non-destructively by also removing the securing element used with a suitable tool.
  • all already used parts can be reused, which saves manufacturing costs.
  • the releasable connection can be made by a locking screw.
  • the invention for the first time also specifies a first embodiment in which only the first part inserted into the circumferential groove, for example the front side part, can be hooked with a projection of the circumferential groove.
  • the second inserted, the rear side part of the end assembly is used to cover the remaining opening of the gap after insertion of the first side part.
  • the second side part prevents a displacement of the first side part, which could solve its entanglement.
  • the force acting on the two side parts of the final assembly centrifugal load is taken in total by the projection, which is hooked to the first side part. Consequently, the hooked with the projection first side member prevents the detachment of the final assembly as a whole from the circumferential groove.
  • a dovetail guide In order to prevent an axially directed gap formation between two adjoining parts due to a game formation or due to the parts pressing apart parts securing element, these are positively interlocked with each other via a dovetail guide.
  • the dovetail guide thus allows an entanglement of two adjacent parts of the final assembly, which ensures a detachable and, depending on the requirements, a particularly reliable frictional connection of the parts of the final assembly by means of the securing element. An unwanted release of the fuse element by moving away from each other Securing element encompassing parts is thus safely avoided.
  • the dovetail guide is arranged in such a way on the parts of the final assembly, that engage in the radial insertion of the last part, the elements of the dovetail guide into one another. During the insertion of the last part of this is hooked together with the already used part or with the parts already used.
  • This has the advantage that the closing assembly completely, that is to say in the circumferential direction, completely encloses the space to be filled of the circumferential groove. can fill without play. A displacement of the blades used in the circumferential groove both after assembly of the final assembly and during operation of the turbomachine can be safely avoided.
  • the closing assembly comprises an intermediate part which can be inserted between the two lateral parts which can now be hooked up with the circumferential groove. Since each side part can be hooked in each case with a protruding on a side wall of the circumferential groove and protruding in the axial direction projection, and the two side parts are successively inserted into the circumferential groove, between these another space, which is filled by the subsequently inserted intermediate part. The filling of the further space prevents the displacement of the side parts in the axial direction, so that their secure entanglement remains ensured.
  • the securing element is arranged such that both the two side parts as well as the intermediate part of the closing assembly located therebetween are detachably connected to one another. The individual parts of the final assembly and these as a whole are then secured against detachment from the circumferential groove.
  • each fuse element connects only two of the three parts of the end assembly together, whereby the mechanical load of each fuse element with respect to the configuration with only one securing element is lower.
  • the two adjoining side parts or each side part is adjacent to each other at the intermediate part in a contact plane, wherein the securing element or the securing elements extends or extend longitudinally within the contact plane.
  • the fuse element is therefore arranged in half in the contact plane and connects two adjacent parts releasably together.
  • the securing element or the securing elements can extend transversely through the contact plane, through one of the two or both contact planes.
  • a detachable final assembly can be achieved in particular advantageously with a non-positive connection.
  • the force acting on the two frictionally interconnected side parts of the final assembly centrifugal load is taken in total by the projection or the projections, which is or which is hooked to the side part or the side parts.
  • a particularly easily detachable final assembly can be specified with a further embodiment in which the securing element is a locking screw.
  • the locking screw connects at least two parts of the securing element frictionally with each other.
  • At least one threaded section for the locking screw is provided in each part of the final assembly.
  • the aligned threaded sections take a common locking screw for possibly frictionally connecting the parts, so that the locking screw extends transversely through the contact plane at which the two parts abut each other.
  • the thread can be divided over its entire height into two threaded halves, each half of the thread being disposed on one of the parts of the end assembly.
  • each thread of the thread is divided into two halves, one half being provided at a first of two abutting parts in a contact plane and the other half of each thread being disposed at the second of the two abutting parts.
  • the halves are designated as such, they do not have to be the same size.
  • a locking screw By using a locking screw a particularly reliable and again releasable and possibly non-positive connection of the parts of the final assembly is given, which reliably prevents a detachment of the parts of the final assembly from the circumferential groove even with a force acting on the final assembly centrifugal load.
  • the locking screw itself is secured against loosening due to the increased frictional forces due to the centrifugal force.
  • the provision of the dovetail guide reliably prevents moving away from each other, the two threaded halves, whereby the release of the encompassed locking screw is reliably prevented.
  • the locking screw is designed as a grub screw so that the necessary for screwing and unscrewing approach for a turning tool requires no additional space.
  • each part can be applied to a side wall, the one of the undercut forming projection of the circumferential groove is formed. This prevents the entire end assembly as a unit from twisting within the circumferential groove as the clearance between the first and last blades of the blade ring increases in the circumferential direction for unpredictable reasons. Even for this case, the proposed development provides a particularly reliable and secure against detachment from the circumferential groove final assembly.
  • the securing element can additionally be mechanically secured against loosening, for example by means of an attachment.
  • the closing assembly is provided for closing the gap of a circumferential groove, which is arranged in a rotor of a turbomachine.
  • FIG. 2 . 5 and FIG. 6 each show a section of a plan view of a circumferential groove 10, in which blades 12a, 12b of an axial compressor of a gas turbine are used.
  • the invention could also be used in a steam turbine or in a turbine unit of the gas turbine.
  • the endless circumferential groove 10 is provided on an outer surface 11 of the rotor of the compressor.
  • the circumferential groove 10 could also be provided on an annular inner housing of the compressor, are mounted in the guide vanes.
  • the circumferential groove 10 has seen in the axial direction of the rotor a front side wall 16 and a rear side wall 18, on each of which extending in the circumferential direction and extending in the axial direction projections 20, 22 are arranged, each having a front and a rear undercut 24, 26th form ( FIG. 1, FIG. 3 and FIG. 4 ).
  • blades 12a, 12b are used, which have to the undercuts 24, 26 corresponding executed, hammer-shaped blade roots.
  • the blades 12a, 12b inserted into the circumferential groove 10 and then so far, for example, rotated by 45 ° or 60 ° until the hammer-shaped blade roots, the projections 20, 22 engage behind.
  • the first, in 1 and FIG. 2 shown embodiment of the invention is characterized essentially by the fact that the final assembly comprises only a front side part 30 and a rear side part 32, wherein only the front side part 30 is hooked to the projection 20 of the circumferential groove 10.
  • the front side part 30 is seen in cross-section ( FIG. 1 ) C-shaped and has an outer arm 50 and an inner arm 52, which are interconnected via a radially extending web 54.
  • the inner arm 52 engages the undercut 24, which is formed by the projection 20. Consequently, the arm 52 abuts the projection 20 and prevents it from falling out of the circumferential groove 10.
  • the rear side member 32 closes the opening of the gap 28 after the front side member 30 has been inserted into the space 28 of the circumferential groove 10.
  • the first embodiment of the invention is characterized in particular by the fact that the rear side part 32 viewed in cross-section is only L-shaped and not, like the front side part 30, C-shaped.
  • the rear side part 32 does not engage in the undercut 26 and is not hooked to the projection 22.
  • the front side part 30 is how FIG. 2 shows, with the rear side portion 32 via a dovetail guide 46 positively interlocked.
  • the dovetail guide 46 comprises two elements, a recess with undercuts and a corresponding thereto designed extension, which can engage behind the undercuts of the recess.
  • One of each of the elements is provided on one of the dovetail guide parts.
  • Both the recess with the undercuts and the extension have an outline in the form of a dovetail seen in cross-section - ie perpendicular to the guide direction.
  • the dovetail guide 46 of the end assembly 33 is so aligned, that during the radial insertion of the rear side part 32 in the circumferential groove 10 this is hooked with the already inserted front side part 30.
  • the dovetail guide 46 prevents possible gap formation between the two side parts 30, 32.
  • the front side part 30 and the rear side part 32 are in a contact plane 48 to each other.
  • a bore 62 having an internal thread 61 is provided, in which the securing element 36 designed as a securing screw 64 is screwed.
  • the internal thread 61 is arranged in half in the front side part 30 and in the rear side part 32. Half means that one half of each thread of the internal thread 61 on the front side part 30 and the other half of each thread on the rear side part 32 is formed.
  • the two side parts 30, 32 are releasably connected to each other again.
  • the grub screw can be clamped in the expiring internal thread 61 to form a particularly high frictional engagement. Due to the axial gap formation between the two parts 30, 32 prevented by the dovetail guide 46, the locking screw 64 is reliably screwed into the internal thread 61, although this is formed by two separate parts 30, 32.
  • the assembled closing assembly 33 is held over the entanglement of the front side part 30 with the projection 20 as a whole in the circumferential groove 10 and thus secured against detachment from the circumferential groove 10.
  • the rear side part 32 is securely held in spite of a lack of entanglement with the projection 22 in the circumferential groove, since the force acting on the rear side part 32 centrifugal forces are transmitted by means of the locking screw 64 on the front side part 30, so that the rear side part 32 indirectly also by the projection 20, which serves as an abutment for the interlocked inner arm 52 is worn.
  • FIG. 3 shows a second embodiment of the invention, in which the closing assembly of three, can be inserted into the space 28 parts 130, 131, 132 consists.
  • the two lateral, in cross-section C-shaped side parts 130, 131 are inserted one after the other in the circumferential groove 10 and axially displaced so that their respective inner arms 52 are hooked to the projections 20 and 22, respectively, by each arm 52 in one of the Undercuts 24, 26 engages.
  • the remaining space between these two side parts 130, 131 space is filled by the insertion of an intermediate part 132, which secures the two side parts 130, 131 against axial displacement and prevents the release of the entanglement.
  • the intermediate part 132 has an axially extending width B, which corresponds at least to the dimension a, with which the projection 20 or 22 projects into the circumferential groove 10 in the axial direction.
  • the parts 130 and 132 lie in a contact plane 148 and the parts 131 and 132 in a contact plane 149 to each other.
  • a bore 162 extends obliquely through the contact planes 148 and 149.
  • a pin-like securing element 136 is provided, which can be inserted into the bore 162.
  • the bore 162 extends along an axis 140, which obliquely penetrates the contact surfaces 148, 149 and the three parts 130, 132, 131.
  • an internal thread 161 is provided, in which formed as a locking screw 164 fuse element 136 can be screwed.
  • the three parts, 130, 131, 132 which each have a threaded portion, releasably connected to each other, whereby the intermediate piece 132 and the end assembly 133 are secured as a whole against detachment from the circumferential groove. It is even possible that only that intermediate part 132 has the internal thread 161 and the locking screw 164 is supported on the groove bottom of the circumferential groove 10 in order to secure the end assembly 133 as a whole. In addition, instead of a support on the groove bottom of the circumferential groove and a screw head provided with a locking screw 164 the side parts 130, 132 and this force-locking with each other.
  • the parts 130, 131 132 of the end assembly 133 may be hooked together with a dovetail guide according to the first embodiment.
  • the three parts 130, 132, 131 could also be secured by two securing elements which are axially offset from one another.
  • the securing element 136 would merely frictionally interconnect the side part 131 with the intermediate part 132 and another, not shown, also obliquely extending securing element only the two parts 130 and 132.
  • a dovetail guide the parts 130, 132, and 131, 132 interconnect are also obliquely extending securing element only the two parts 130 and 132.
  • a third embodiment of the invention shows FIG. 4 in a cross-sectional view and FIG. 5 in a top view.
  • the successive insertable into the circumferential groove 10 side parts 230, 231 are each hooked with one of the projections 20 and 22 respectively.
  • the two side parts 230, 231 are formed in cross-section substantially C-shaped and each have an outer arm 250 which partially closes the gap 28 to the outside partially, and an inner arm 252 which hooks with the projections 20, 22 is.
  • the inner arms 250 are connected to the outer arms 252 by a web 254, respectively.
  • an intermediate part 232 is provided, which secures the two side parts 230, 231 against axial displacement and thus against loosening the entanglement.
  • the intermediate part 232 has an axially extending width B, which corresponds at least to the dimension a, with which each projection 20 or 22 projects into the circumferential groove 10 in the axial direction. If this condition is not fulfilled, the second part 130 or 131 to be inserted into the groove can not be used.
  • FIG. 5 shows the top view of the third embodiment of the invention according to FIG. 4 ,
  • the intermediate part 232 abuts in a contact surface 248 on the front side part 230 and is hooked thereto via a first dovetail guide 246.
  • a dovetail-shaped projection and the front side part 230, the corresponding corresponding receptacle is formed on the intermediate part 232.
  • the rear side part 231 is hooked to the intermediate part 232, wherein these lie in a contact surface 249 against each other.
  • the dovetail-shaped extension is provided on the rear side part 231 and the correspondingly shaped recess on the intermediate part 232.
  • the second dovetail guide 247 viewed in the circumferential direction can be made narrower than the first dovetail guide 246 to allow axial insertion of the narrower dovetailed extension in the larger recess during assembly of the second side member 231 or 230 and maximizing this to reach the centrifugally stressed cross sections of the webs 254.
  • a pin-like Secured element 236 is provided, which is designed as a locking screw 264.
  • at least one bore 262 is provided in each contact plane 248, 249.
  • Each bore 262 is provided with an internal thread 263, which are each arranged in half in two parts 230, 231 and 231, 232.
  • the pin-like securing elements 236 designed as securing screws 264 can be screwed into these internal threads 263 for frictionally and / or positively locking the parts 230, 231, 232 of the end assembly 233.
  • each internal thread 263 is arranged in half each in two parts 230, 232 and 231, 232, a reliable and secure against loosening screw is possible because the two each female thread 263 forming parts 230, 232 and 231, 232 by means of the respective dovetail guide 246th , 247 are not axially displaced apart.
  • FIG. 6 shows the top view of a variant of the third embodiment.
  • the dovetail guide 247 between the parts 232 and 231, based on FIG. 5 Conversely formed.
  • Both dovetail-shaped extensions are arranged on the intermediate part 232 and each side part 230, 231 has in the corresponding contact surfaces 248, 249 a recess for receiving the respective extension.
  • a locking screw 64, 164, 264 could also be a pin-like bolt in the bore 62, 162, 262 are used, which secured by a press fit against loosening is. To remove the end assembly this would only have to be drilled out.
  • a screw head provided with a locking screw 64, 164, 264 could be screwed into each lock assembly 33, wherein the recessed into one or more of the parts 30, 32, 130, 131, 132, 230, 231, 232 screw head biased against this ,
  • a device for closing the remaining gap between the first and the last inserted in a circumferential groove blades of a blade ring can be specified, which can be easily assemble and disassemble. Since the assembly of the final assembly no.plastic deformation of the components requires, but proposes the non-positive connection of the parts, they can be solved by disassembled steps performed and disassembled. All components of the final assembly can be reused. In addition, the simple design allows a relatively low production cost.

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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)
  • Threshing Machine Elements (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Loading And Unloading Of Fuel Tanks Or Ships (AREA)

Claims (12)

  1. Ensemble ( 33, 133, 233 ) de verrouillage, pour fermer l'espace ( 28 ) intermédiaire restant entre la première et la dernière aube ( 12a, 12b ) d'une couronne d'aubes, insérées dans une rainure ( 10 ) périphérique d'une turbomachine,
    constitué d'au moins deux parties ( 30, 32, 130, 131, 132, 230, 231, 232 ) latérales,
    dont l'une au moins peut s'accrocher avec une saillie ( 20, 22 ), formant une contredépouille ( 24, 26 ), de la rainure ( 10 ) périphérique et
    au moins un élément ( 36, 136, 236 ) de sécurité du type à broche, qui empêche les parties ( 30, 32, 130, 131, 132, 230, 231, 232 ) de se détacher de la rainure ( 10 ) périphérique et qui les assemble entre elles d'une manière amovible,
    caractérisé en ce que
    les deux parties ( 30, 32 ) latérales sont assemblées entre elles par respectivement par un assemblage ( 146, 147, 246, 247 ) à queue d'aronde.
  2. Ensemble ( 33, 133, 233 ) de verrouillage suivant la revendication 1,
    dans lequel l'assemblage ( 46, 146, 147, 246, 247 ) à queue d'aronde est disposé sur les parties ( 30, 32, 130, 131, 132, 230, 231, 232 ) de façon à ce que, lorsque l'on insère radialement la dernière partie ( 32, 132, 232 ), les éléments de l'assemblage ( 46, 146, 147, 246, 247 ) à queue d'aronde s'interpénètrent.
  3. Ensemble ( 133, 233 ) de verrouillage suivant la revendication 1 ou 2,
    qui comprend la pièce ( 132, 232 ) intermédiaire et un autre élément ( 136, 236 ) de sécurité du type à broche, dans lequel chaque partie ( 130, 131, 230, 231 ) latérale est bloquée avec la partie ( 132, 232 ) intermédiaire au moyen de respectivement l'un des deux éléments ( 136, 236 ) de sécurité du type à broche.
  4. Ensemble ( 33, 133, 233 ) de verrouillage suivant la revendication 1, 2 ou 3,
    dans lequel les deux parties ( 30, 32 ) latérales côte à côte ou chaque partie ( 130, 131, 230, 231 ) latérale s'appliquent dans un plan ( 48 ) de contact à la partie ( 132, 232 ) intermédiaire ou s'appliquent l'une à l'autre dans un plan ( 148, 149, 248, 249 ) de contact,
    l'élément ( 36 ) de sécurité ou les éléments ( 136, 236 ) de sécurité s'étendant le long à l'intérieur du plan ( 48, 148, 149, 248, 249 ) de contact.
  5. Ensemble ( 33, 133, 233 ) de verrouillage suivant l'une des revendications 1, 2 ou 3,
    dans lequel la ou les deux parties ( 30, 32 ) latérales côte à côte ou chaque partie ( 130, 131, 230, 231 ) latérale s'appliquent l'une à l'autre dans un plan ( 48 ) de contact à la partie ( 132, 232 ) intermédiaire ou s'appliquent l'une à l'autre dans un plan ( 148, 149, 248, 249 ) de contact,
    l'élément ( 36 ) de sécurité ou les éléments ( 136, 236 ) de sécurité s'étendant transversalement au plan ( 48, 148, 149, 248, 249 ) de contact.
  6. Ensemble ( 33, 133, 233 ) de verrouillage suivant l'une des revendications précédentes,
    dans lequel l'élément ( 36, 136, 236 ) de sécurité assemble entre elles à complémentarité de force les parties ( 30, 32, 130, 131, 132, 230, 231, 232 ).
  7. Ensemble ( 33, 133, 233 ) de verrouillage suivant l'une des revendications précédentes,
    dans lequel l'élément ( 36, 136, 236 ) de sécurité est une vis ( 64, 164, 264 ) de sécurité.
  8. Ensemble ( 33, 133, 233 ) de verrouillage suivant la revendication 7,
    dans lequel la vis ( 64, 164, 264 ) de sécurité est constituée sous la forme d'une vis sans tête.
  9. Ensemble ( 33, 133, 233 ) de verrouillage suivant l'une des revendications précédentes,
    dans lequel chaque partie ( 30, 32, 130, 131, 230, 231 ) peut s'appliquer à une paroi ( 58 ) latérale qui est formée par une saillie ( 20, 22 ) de la rainure ( 10 ) périphérique, saillie qui forme la contredépouille ( 24, 26 ).
  10. Ensemble ( 33, 133, 233 ) de verrouillage suivant l'une des revendications précédentes,
    dans lequel l'élément ( 36, 136, 236 ) de sécurité est empêché de se desserrer.
  11. Turbomachine ayant un rotor,
    qui a au moins une rainure ( 10 ) périphérique, qui a une contredépouille ( 24, 26 ) et dans laquelle sont fixées des aubes ( 12a, 12b ) mobiles,
    l'espace ( 28 ) intermédiaire restant entre la première et la dernière aube ( 12a, 12b ) mobile, insérées dans la rainure ( 10 ) périphérique, est enfermé complètement par un ensemble ( 33, 133, 233 ) de verrouillage suivant l'une des revendications précédentes.
  12. Turbomachine suivant la revendication 11,
    constituée en turbine d'une turbine à gaz, en compresseur ou en turbine à vapeur.
EP06841633A 2006-01-02 2006-12-27 Ensemble de verrouillage pour verrouiller l'interstice restant entre la premiere et la derniere aube d'une couronne d'aubes placees dans une rainure peripherique d'une turbomachine et turbomachine correspondante Not-in-force EP1969206B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06841633A EP1969206B1 (fr) 2006-01-02 2006-12-27 Ensemble de verrouillage pour verrouiller l'interstice restant entre la premiere et la derniere aube d'une couronne d'aubes placees dans une rainure peripherique d'une turbomachine et turbomachine correspondante
PL06841633T PL1969206T3 (pl) 2006-01-02 2006-12-27 Podzespół zamykający do zamykania odstępu pozostającego między pierwszą a ostatnią łopatką wieńca łopatkowego osadzoną na rowku obwodowym maszyny przepływowej i odpowiednia maszyna przepływowa

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06000025A EP1803900A1 (fr) 2006-01-02 2006-01-02 Ensemble de fermeture pour clore l'interstice restant entre la première et la dernière des aubes d'un anneau aubagé disposées dans la rainure circonférencielle d'une turbomachine, et turbomachine correspondante
EP06841633A EP1969206B1 (fr) 2006-01-02 2006-12-27 Ensemble de verrouillage pour verrouiller l'interstice restant entre la premiere et la derniere aube d'une couronne d'aubes placees dans une rainure peripherique d'une turbomachine et turbomachine correspondante
PCT/EP2006/070226 WO2007077183A1 (fr) 2006-01-02 2006-12-27 Ensemble de verrouillage pour verrouiller l'interstice restant entre la premiere et la derniere aube d'une couronne d'aubes placees dans une rainure peripherique d'une turbomachine et turbomachine correspondante

Publications (2)

Publication Number Publication Date
EP1969206A1 EP1969206A1 (fr) 2008-09-17
EP1969206B1 true EP1969206B1 (fr) 2009-06-17

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EP06000025A Withdrawn EP1803900A1 (fr) 2006-01-02 2006-01-02 Ensemble de fermeture pour clore l'interstice restant entre la première et la dernière des aubes d'un anneau aubagé disposées dans la rainure circonférencielle d'une turbomachine, et turbomachine correspondante
EP06841633A Not-in-force EP1969206B1 (fr) 2006-01-02 2006-12-27 Ensemble de verrouillage pour verrouiller l'interstice restant entre la premiere et la derniere aube d'une couronne d'aubes placees dans une rainure peripherique d'une turbomachine et turbomachine correspondante

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EP06000025A Withdrawn EP1803900A1 (fr) 2006-01-02 2006-01-02 Ensemble de fermeture pour clore l'interstice restant entre la première et la dernière des aubes d'un anneau aubagé disposées dans la rainure circonférencielle d'une turbomachine, et turbomachine correspondante

Country Status (9)

Country Link
US (1) US8157530B2 (fr)
EP (2) EP1803900A1 (fr)
JP (1) JP4926186B2 (fr)
CN (1) CN101351620B (fr)
AT (1) ATE434115T1 (fr)
DE (1) DE502006004038D1 (fr)
PL (1) PL1969206T3 (fr)
RU (1) RU2392445C2 (fr)
WO (1) WO2007077183A1 (fr)

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US8523529B2 (en) * 2009-11-11 2013-09-03 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
CH703997A1 (de) 2010-10-27 2012-04-30 Alstom Technology Ltd Schaufelanordnung, insbesondere Leitschaufelanordnung.
US8875870B2 (en) 2011-03-31 2014-11-04 Benetech, Inc. Conveyor belt cleaner scraper blade and assembly
EP2562356A1 (fr) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
US8979484B2 (en) 2012-01-05 2015-03-17 Pratt & Whitney Canada Corp. Casing for an aircraft turbofan bypass engine
EP2719866B1 (fr) * 2012-10-12 2018-12-05 Safran Aero Boosters SA Roue de turbomachine avec un verrou de blocage d'aubes
US9341071B2 (en) 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
US9518471B2 (en) 2013-10-16 2016-12-13 General Electric Company Locking spacer assembly
US9464531B2 (en) 2013-10-16 2016-10-11 General Electric Company Locking spacer assembly
US9416670B2 (en) 2013-10-16 2016-08-16 General Electric Company Locking spacer assembly
US9512732B2 (en) * 2013-10-16 2016-12-06 General Electric Company Locking spacer assembly inserted between rotor blades
EP3054098A1 (fr) * 2015-02-05 2016-08-10 Siemens Aktiengesellschaft Bloc de fermeture destiné à fermer une couronne d'aube sur un support d'aube d'une turbomachine
KR101884712B1 (ko) * 2016-12-21 2018-08-03 두산중공업 주식회사 로터 블레이드용 로킹 스페이서
KR101920070B1 (ko) * 2016-12-23 2018-11-19 두산중공업 주식회사 로터 블레이드용 로킹 스페이서
US10465699B2 (en) 2017-01-26 2019-11-05 DOOSAN Heavy Industries Construction Co., LTD Compressor blade locking mechanism in disk with tangential groove
US10519970B2 (en) * 2017-02-09 2019-12-31 DOOSAN Heavy Industries Construction Co., LTD Compressor blade locking mechanism in disk with tangential groove
US11359501B2 (en) * 2018-03-28 2022-06-14 Siemens Energy Global GmbH & Co. KG Locking spacer assembly, corresponding blade assembly, method for installing a locking spacer
CN112780351A (zh) * 2019-11-07 2021-05-11 中国航发商用航空发动机有限责任公司 航空发动机转子和航空发动机
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Also Published As

Publication number Publication date
DE502006004038D1 (de) 2009-07-30
PL1969206T3 (pl) 2009-11-30
CN101351620A (zh) 2009-01-21
RU2008131932A (ru) 2010-02-10
EP1969206A1 (fr) 2008-09-17
US8157530B2 (en) 2012-04-17
JP2009522483A (ja) 2009-06-11
US20090016889A1 (en) 2009-01-15
ATE434115T1 (de) 2009-07-15
WO2007077183A1 (fr) 2007-07-12
JP4926186B2 (ja) 2012-05-09
RU2392445C2 (ru) 2010-06-20
CN101351620B (zh) 2012-06-13
EP1803900A1 (fr) 2007-07-04

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