EP2933433A1 - Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés - Google Patents

Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés Download PDF

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Publication number
EP2933433A1
EP2933433A1 EP14164718.0A EP14164718A EP2933433A1 EP 2933433 A1 EP2933433 A1 EP 2933433A1 EP 14164718 A EP14164718 A EP 14164718A EP 2933433 A1 EP2933433 A1 EP 2933433A1
Authority
EP
European Patent Office
Prior art keywords
rotor
sleeve
axially
support sleeve
section
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.)
Withdrawn
Application number
EP14164718.0A
Other languages
German (de)
English (en)
Inventor
Sascha Dungs
Harald Hoell
Karsten Kolk
Marc Lange
Peter Schröder
José Manuel Torres Gutiérrez
Vyacheslav Veitsman
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 EP14164718.0A priority Critical patent/EP2933433A1/fr
Priority to PCT/EP2015/056398 priority patent/WO2015158513A1/fr
Publication of EP2933433A1 publication Critical patent/EP2933433A1/fr
Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • 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
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2260/02—Transport and handling during maintenance and repair
    • 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
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the present invention relates to a method for assembling and / or disassembling a rotor section of a turbomachine, in particular the turbine-side rotor section of a gas turbine, which has a plurality of rotor disks with a central Buchankerötechnik, which are penetrated axially by a tie rod to form an intermediate annulus and axially clamped together are. Furthermore, the invention relates to a mounting device for carrying out the method. Finally, the invention relates to a rotor disk which is designed for carrying out the method.
  • Gas turbines basically include an air inlet, a compressor section, a combustion chamber and a turbine section.
  • the compressor section may be formed from axial or radial compressors.
  • Axial compressors usually consist of several impellers with compressor blades in an axial arrangement, these usually being subdivided into low-pressure and high-pressure compressor stages.
  • By the compressor section receives the incoming air mass by means of supplied kinetic energy in the diffuser-shaped spaces of the compressor blades pressure energy.
  • a complete compressor stage of an axial compressor thus consists of a rotor stage, in which both pressure and temperature, as well as the speed increase, and a stator stage, in which the pressure increases to the detriment of the speed.
  • the compressed and heated due to the compression of air is mixed with a fuel, and the resulting fuel-air mixture is burned. Due to the exothermic reaction, the temperature increases again strongly, and the gas expands. This creates a hot gas that is expanded in the subsequent turbine section, with thermal energy converting to mechanical energy, which is used in part to drive the compressor section, and is otherwise used to drive a generator or the like.
  • the rotating parts of the rotor stages of the compressor section and of the turbine section are collectively referred to as a rotor or as a rotor, which comprises a compressor section and a turbine section.
  • the runner is operationally exposed to high mechanical and thermal loads.
  • the rotor components are heavily stressed. Nevertheless, in order to be able to ensure operational safety on the one hand and to keep the manufacturing costs of the rotor within acceptable limits on the other hand, a large number of design options for such turbine rotors have been proposed in the past.
  • One of these design possibilities is to assemble the rotor from individual rotor or rotor disks.
  • the rotor disks are aligned coaxially with one another and clamped together axially via a so-called tie rod, which axially passes through the rotor disks.
  • the mutually pressed rotor discs are positively connected to one another via frontally provided Hirth toothings in order to transmit rotational forces acting on them.
  • Such gas turbine runners are brought to disassembly by means of a suitable device from its horizontal mounting position in a vertical position to then with Help of a Krahns and a trailer crown the rotor disks individually from the tie rod to pull up.
  • the object of the invention is therefore to provide a method with which the rotor section of a turbomachine, in particular the turbine-side rotor section of a gas turbine, can be easily assembled or disassembled.
  • the invention is thus based on the idea of mounting a plurality of rotor disks forming a rotor section on a carrier sleeve, so that the rotor section can be assembled or disassembled as a unitary module.
  • a carrier sleeve is used whose outer diameter corresponds to the inner diameter of the carrier, so that the carriers are supported radially on the carrier sleeve.
  • the carrier sleeve expediently has an inner diameter which corresponds to the outer diameter of the tie rod, so that the carrier sleeve in turn is radially positioned and supported on the tie rod.
  • the rotor discs are clamped against the retaining projection which is provided at the front end region of the carrier sleeve.
  • corresponding clamping means are provided on the opposite, rear axial end region.
  • the clamping means may comprise an external thread on which a clamping element, in particular a clamping nut is screwed.
  • the rotor disks are initially secured against radial movement.
  • the rotor disks of the rotor section to be dismantled can be braced with further rotor disks of the rotor.
  • the axial strain of the rotor disks is released on the tie rod, so that the support sleeve can be inserted axially into the annular space formed between the tie rod and the rotor disks.
  • the rotor disks are clamped and fixed to one another on the carrier sleeve so that the carrier sleeve with the rotor disks held thereon can be pulled off the tie rod.
  • the rotor module dismantled in this way can be put aside as a tensioned package for servicing.
  • a rotor section To mount a rotor section is provided that the support sleeve is pushed axially with the rotor disks held on the tie rod, the rotor disks are secured against radial movement, and then solved the connection between the rotor disks and the support sleeve and the support sleeve from between the tie rod and The annulus formed the rotor disks is withdrawn.
  • the retaining projection may be formed according to an embodiment of the invention at the front end portion of the support sleeve, so that it after pushing the support sleeve on the tie rod by rotating the support sleeve about its longitudinal axis with a corresponding retaining projection in the insertion direction the last rotor disk of the rotor section can be brought to engage behind this.
  • a plurality of radial retaining projections are formed at the front end portion of the support sleeve, which are uniformly spaced from each other in the circumferential direction of the support sleeve and in particular formed as in the circumferential direction of the support sleeve extending retaining webs.
  • the rotor disk body of the rotor disk is provided with corresponding holding projections, which are designed in particular as holding webs extending in the circumferential direction and project into the tie rod opening of the rotor disk body.
  • the holding projections on the carrier sleeve on the one hand and the rotor disk on the other hand form a kind of bayonet closure and are designed so that the holding projections of the carrier rod between the holding projections the rotor disk can be axially performed and engage behind the holding projections of the rotor disk after rotating the support sleeve about its longitudinal axis in a locking position ,
  • the wall of the support sleeve is axially penetrated by at least two holes, in each of which a support rod is rotatably supported about its longitudinal axis, wherein the support rods protrude with their axial end portions of the support sleeve and at its front End regions each carrying a retaining projection in the form of a locking element, wherein the locking elements are adjustable by rotation of the support rods about their longitudinal axes between an extended locking position and an inner release position.
  • the locking elements on the support sleeve are movable, namely held pivotally about the axes of the support rods, so that they can be adjusted by rotation of the rotary rods between the locking position and the release position.
  • the free end of the locking element projects beyond the outer circumference of the carrier sleeve to the outside, to a corresponding retaining projection the last rotor disk of a rotor section to be assembled / disassembled to engage behind and thus be engaged with this.
  • on the inner surface of the rotor disk body extending in the circumferential direction of the rotor disk holding groove may be formed, in which engage the locking elements in their locking position.
  • the locking elements may be formed in particular in the form of circular ring segments, which are fixed at its one end portion to the associated support rod.
  • the inner diameter of the circular ring segments in particular corresponds to the inner diameter of the carrier sleeve, so that the circular ring segments abut against the tie rod in the release position and engage in the retaining groove in the locking position.
  • the arrangement is preferably made such that the outer diameter of the circular ring segments corresponds to the diameter of the retaining groove on the groove base and thus the circular ring segments come into abutment with their outer surface on the groove base.
  • each support rod is a locking element in the form a circular ring segment which extends approximately over half the circumference of the support sleeve, wherein between the front ends of the two circular ring segments so much space remains that a pivoting movement of the locking elements is possible.
  • This embodiment has the advantage that the locking elements on diametrically opposite sides come into engagement with the rotor disks and thus the rotor disks of the rotor section are supported axially uniformly on the support sleeve, and in addition the free ends of the locking elements in their locking position in the radial direction of maximum the carrier sleeve are positioned at a distance.
  • securing means are provided to secure the holding position in its locking position.
  • FIG. 1 a section of a rotor of a gas turbine is shown. Specifically, the shows FIG. 1 the turbine-side rotor section of the gas turbine, wherein on the left edge of the picture nor a clamping screw 1 of the compressor-side rotor section can be seen.
  • the turbine-side rotor section comprises a plurality - in the illustrated embodiment three - rotor disks 2, 3, 4, which are axially penetrated by a tie rod 5 and are clamped together axially via the tie rod 5.
  • the rotor disks 2, 3, 4 central Werner 2a, 3a, 4a, which are penetrated axially by the tie rod 5, wherein between the tie rod 5 and the inner surfaces of the rotor disks 2, 3, 4, an annular space 6 is formed.
  • the rotor disk 2, which is positioned closest to the compressor-side rotor section, is located axially on the clamping screw 1 of the compressor-side rotor section, which is fastened to the tie rod 5.
  • a tensioning screw 7 is screwed onto the tie rod 5, which presses against the one rotor disk 4 which is furthest away from the compressor side to press the rotor disks 2, 3, 4 against the clamping screw 1 of the compressor side rotor section and axially clamped together in this way.
  • the pressed together Rotor disks 2, 3, 4 connected in a form-fitting manner to one another via Hirth gears provided on the front side in order to transmit rotational forces acting on them.
  • the invention provides, for example, to deduct the rotor disks 2, 3, 4 of the turbine-side rotor section for maintenance purposes via a special mounting device M in the horizontal direction as a package from the tie rod 5.
  • a special mounting device M in the horizontal direction as a package from the tie rod 5.
  • the rotor discs 2, 3, 4 initially secured against radial movement by being connected by corresponding, not shown in the drawing securing means with a housing of the rotor.
  • the clamping screw 7 of the turbine-side rotor section is removed from the tie rod 5 so as to release the tension of the rotor disks 2, 3, 4.
  • the carrier sleeve 8 has an inner diameter which corresponds to the outer diameter of the tie rod 5, so that the carrier sleeve 8 is radially supported on the tie rod 5. Furthermore, the carrier sleeve 8 has an outer diameter which corresponds to the inner diameter of the rotor disks 2, 3, 4, so that the rotor disks 2, 3, 4 are in turn supported radially on the carrier sleeve 8.
  • a plurality of retaining projections in the form of retaining webs 9 are formed, which are distributed uniformly along the circumference of the support sleeve 8 and spaced from each other and extending in the circumferential direction of the support sleeve 8.
  • the holding webs 9 protrude from the outer peripheral surface of the support sleeve 8 at the front end portion to the outside.
  • corresponding holding webs 10 are formed according to projecting inside the tie rod opening 2a and distributed uniformly along the circumference of the rotor disk 2 and spaced from each other.
  • the holding webs 9, 10 of the support sleeve 8 and the rotor disk 2 together form a bayonet closure and are for this purpose designed so that the retaining webs 9 of the support sleeve 8 can be performed axially in a release position of the support sleeve 8 between the support webs 10 of the rotor disk 2, and after rotation the carrier sleeve 8 engage behind its longitudinal axis X in a locking position, the holding webs 10 of the rotor disk 2, as shown in the FIG. 2 is shown.
  • the support sleeve 8 clamping means include an external thread 11, on which a clamping element in the form of a clamping nut 12 can be screwed to press the rotor disks 2, 3, 4 against the retaining webs 9 at the front end portion of the support sleeve 8 and so axially to clamp.
  • the support sleeve 8 forms with the clamping nut 12 and the rotor disks 2, 3, 4 fixed thereto a tensioned package or module which can be pulled off horizontally from the tie rod 5 as a structural unit.
  • the module formed is pushed onto the tie rod 5 in the reverse manner. Subsequently, the rotor disks 2, 3, 4 secured against radial movement on the housing of the rotor before the clamping nut 12 is released on the support sleeve 8. Subsequently, the support sleeve 8 is moved about its longitudinal axis X in the release position and withdrawn axially from the tie rod 5. Finally, the rotor disks 2, 3, 4 again clamped axially by a corresponding clamping screw 7 is screwed onto the tie rod 5, before finally the backup of the rotor disks 2, 3, 4 is removed on the housing.
  • FIG. 7 another embodiment of a mounting device M according to the present invention is shown.
  • This in turn comprises a carrier sleeve 8, which a the Diameter of Werner 2a, 2b, 2c of the rotor disks 2, 3, 4 corresponding outer diameter and has an outer diameter of the tie rod 5 corresponding inner diameter.
  • the support sleeve 8 is axially penetrated by two support rods 13 which protrude at their opposite axial ends of the support sleeve 8 and are rotatably held in corresponding holes 14 which are formed on diametrically opposite sides of the support sleeve 8.
  • the holding rods 13 each carry a retaining projection 9, which is designed as a locking element in the form of a circular ring segment.
  • the locking elements 9 are fixed at its one end portion to the associated support rod 13 and extend approximately over half the circumference of the support sleeve 8, wherein between the mutually facing front ends of the two locking elements 9 so much space remains that a pivoting movement of the locking elements 9 by a Rotation of the support rods 13 about the longitudinal axes is possible.
  • the inner diameter of the circular ring segments 9 is chosen so that it corresponds to the outer diameter of the tie rod 5, so that the circular ring segments 9 in their release position, which in the FIGS. 7 .
  • the tie rod 5 abut the outside and can be pivoted by a rotation of the support rods 13 from this release position to the outside in a locking position, so as to form a corresponding retaining projection 10, here in the form of a along the inner circumference of the rotor disc 2 extending paragraph is to grasp, as this particular in the FIG. 8 is recognizable.
  • the retaining projection 10 is part of a retaining groove 15 which is formed on the inner surface of the rotor disk 2 and in which engage the locking elements 9 in their locking position.
  • an external thread 11 is again provided, via which a clamping nut, counter plate 12 or the like can be fixed to the support sleeve 8.
  • the support rods 13 After insertion of the support sleeve 8, the support rods 13 are rotated about their longitudinal axes to pivot the locking elements 9 from its release position to its locking position outwards, so that their free end portions come into engagement with the retaining groove 15, which on the inner surface of the insertion direction the carrier sleeve 8 last rotor disk 2 of the rotor section is formed.
  • the locking elements 9 are secured by the holding rods 13 are fixed in the corresponding rotational position on the tie rod 5 by means of suitable terminals 16.
  • the counter plate 12 is screwed onto the external thread of the support sleeve 8 in order to press the rotor disks 2, 3, 4 axially against the locking elements 9 and thus to clamp them together.
  • the package or module thus formed can be withdrawn horizontally from the tie rod 5, after the backup of the rotor discs 2, 3, 4 has been solved on the housing.
  • the module with the carrier sleeve 8 and the rotor disks 2, 3, 4 fixed thereto is pushed back onto the tie rod 5, and the rotor disks 2, 3, 4 are counteracted a radial movement secured to the housing.
  • the counter plate 12 and the terminals 16 are released to secure the support rods 13, before the locking elements 9 are pivoted back by rotating the support rods 13 about their longitudinal axes in their release position to finally pull the support sleeve 8 axially from the tie rod 5.
  • the rotor disks 2, 3, 4 again clamped axially together by the clamping screw 7 is screwed onto the tie rod 5 and the fuses of the rotor disks 2, 3, 4 are released on the housing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14164718.0A 2014-04-15 2014-04-15 Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés Withdrawn EP2933433A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14164718.0A EP2933433A1 (fr) 2014-04-15 2014-04-15 Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés
PCT/EP2015/056398 WO2015158513A1 (fr) 2014-04-15 2015-03-25 Procédé de montage et/ou de démontage d'une partie de rotor d'une turbomachine, dispositif de montage et disque de rotor associés

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14164718.0A EP2933433A1 (fr) 2014-04-15 2014-04-15 Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés

Publications (1)

Publication Number Publication Date
EP2933433A1 true EP2933433A1 (fr) 2015-10-21

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EP14164718.0A Withdrawn EP2933433A1 (fr) 2014-04-15 2014-04-15 Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés

Country Status (2)

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EP (1) EP2933433A1 (fr)
WO (1) WO2015158513A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3647537A1 (fr) * 2018-10-30 2020-05-06 Siemens Aktiengesellschaft Appareil de sécurité pour attraper la libération d'energie dans un tirant d'ancrage d'un agencement de rotor et procédé associé

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107091156B (zh) * 2017-06-30 2018-12-28 西安中工动力能源有限公司 一种微型燃气轮机转子及装配方法
CN112177692B (zh) * 2019-07-03 2022-12-27 中国航发商用航空发动机有限责任公司 一种低压涡轮转子的组装工具及组装方法
CN113640114B (zh) * 2021-08-09 2024-04-26 重庆长江预应力有限公司 拉杆静载试验系统

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3722058A (en) * 1971-09-30 1973-03-27 Gen Electric Fastening device and cooperating tool means
DE2643886B1 (de) * 1976-09-29 1977-06-16 Kraftwerk Union Ag Gasturbinenlaeufer in scheibenbauart
US5267397A (en) * 1991-06-27 1993-12-07 Allied-Signal Inc. Gas turbine engine module assembly
EP1970530A1 (fr) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Rotor d'une turbomachine thermique et turbomachine thermique
GB2452932A (en) * 2007-09-19 2009-03-25 Siemens Ag Turbine or turbomachine with axial shaft-mounted compressor and turbine blades
EP2474707A2 (fr) * 2011-01-11 2012-07-11 United Technologies Corporation Protection thermique multifonction pour moteur de turbine à gaz

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3722058A (en) * 1971-09-30 1973-03-27 Gen Electric Fastening device and cooperating tool means
DE2643886B1 (de) * 1976-09-29 1977-06-16 Kraftwerk Union Ag Gasturbinenlaeufer in scheibenbauart
US5267397A (en) * 1991-06-27 1993-12-07 Allied-Signal Inc. Gas turbine engine module assembly
EP1970530A1 (fr) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Rotor d'une turbomachine thermique et turbomachine thermique
GB2452932A (en) * 2007-09-19 2009-03-25 Siemens Ag Turbine or turbomachine with axial shaft-mounted compressor and turbine blades
EP2474707A2 (fr) * 2011-01-11 2012-07-11 United Technologies Corporation Protection thermique multifonction pour moteur de turbine à gaz

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3647537A1 (fr) * 2018-10-30 2020-05-06 Siemens Aktiengesellschaft Appareil de sécurité pour attraper la libération d'energie dans un tirant d'ancrage d'un agencement de rotor et procédé associé
WO2020088811A1 (fr) * 2018-10-30 2020-05-07 Siemens Aktiengesellschaft Appareil de sécurité et procédé correspondant pour contenir une libération d'énergie à partir d'un goujon de tension d'un ensemble rotor
CN112955630A (zh) * 2018-10-30 2021-06-11 西门子能源环球有限责任两合公司 用于容纳来自转子组件的张力螺柱的能量释放的安全装置和对应方法
US11519301B2 (en) 2018-10-30 2022-12-06 Siemens Energy Global GmbH & Co. KG Safety apparatus and corresponding method for containing an energy release from a tension stud of a rotor assembly

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Publication number Publication date
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