WO2008012195A1 - Procédé pour dévisser une moitié annulaire d'un distributeur de forme globale annulaire hors d'une moitié inférieure de boîtier d'une turbomachine stationnaire à écoulement axial, dispositif de montage, assemblage de dispositif de montage et demi-secteur annulaire auxiliaire - Google Patents

Procédé pour dévisser une moitié annulaire d'un distributeur de forme globale annulaire hors d'une moitié inférieure de boîtier d'une turbomachine stationnaire à écoulement axial, dispositif de montage, assemblage de dispositif de montage et demi-secteur annulaire auxiliaire Download PDF

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Publication number
WO2008012195A1
WO2008012195A1 PCT/EP2007/056959 EP2007056959W WO2008012195A1 WO 2008012195 A1 WO2008012195 A1 WO 2008012195A1 EP 2007056959 W EP2007056959 W EP 2007056959W WO 2008012195 A1 WO2008012195 A1 WO 2008012195A1
Authority
WO
WIPO (PCT)
Prior art keywords
ring
lower housing
auxiliary
mounting
housing
Prior art date
Application number
PCT/EP2007/056959
Other languages
German (de)
English (en)
Inventor
Armin Hülfenhaus
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2008012195A1 publication Critical patent/WO2008012195A1/fr

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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

Definitions

  • the invention relates to a method for unscrewing a ring half of a total annular guide from a lower half of an axially flow-through, stationary flow machine, in which after lifting an upper half of a lower housing half of the turbomachine and the release and lifting of the upper
  • Ring half of a total annular nozzle which is to be removed in the lower half of the housing arranged lower ring half of the nozzle. Furthermore, the invention relates to devices which are required for carrying out the method.
  • Stationary gas turbines and their structural design are well known. They have along the machine axis housing sections, which are each divided in half in a so-called parting plane and there are flanged together. With reference to the dividing plane, each housing section has a lower housing half and an upper housing half.
  • the guide vanes are fastened within the associated housing section to a generally annular guide, which in turn comprises at least two parts: an upper ring half and a lower ring half, which also abut one another in the dividing plane.
  • the rotor of the gas turbine or a portion of the rotor is the
  • Gas turbine arranged. Its axis of rotation coincides concentrically with the central axis of the distributor.
  • the assembly of the stationary gas turbine is known to occur by placing the lower housing half on a foundation and inserting the lower nozzle half, after which the rotor of the gas turbine can be inserted. Thereafter, the upper halves of the turbine nozzles and, if present, the compressor are slipped over the rotor and secured to the lower half of the nozzle. Subsequently, the upper half of the housing is placed on the lower half of the housing and connected to each other via a plurality of Flanschverschraubache.
  • the monitored components include, for example, the vanes of the turbine of the gas turbine. If one or more vanes of the turbine are to be replaced, due to defects or when the maximum anticipated service life has been reached, the turbine must be uncovered by lifting the upper half of the casing. If the turbine vane to be removed is located in the upper half of the housing, the lifting of the upper ring half of the overall annular vane exposes the turbine vane connected to the latter and removes it from the diffuser.
  • the accessibility of this turbine guide vane is associated with an increased installation effort. Either the entire upper half of the gas turbine is to dismantle, so that the rotor of the gas turbine is removed as a whole. After removal of the rotor of the gas turbine then the accessibility to the turbine housing located in the lower half of the turbine would be present. Or it is possible with the aid of the rotor and an auxiliary device, a so-called Hilfjobrings, unscrew the lower half of the annular guide from the lower half of the gas turbine engine without having to take other housing sections or even the rotor of the gas turbine.
  • an auxiliary ring is to be mounted on the lower half of the distributor, whereby at the same time the still inserted rotor of the gas turbine is clamped by both ring halves. Subsequently, the attachment of lower ring half of the nozzle and lower half of the housing is achieved by a lower ring half is supported on the lower half of the housing supporting rigid connection. Thereafter, by turning the rotor by an angle of 180 °, the previously in the lower
  • Manifold are separated from the auxiliary ring, after which the vanes of the turbine can be removed from the nozzle.
  • To install the lower ring half of the overall annular nozzle with inserted rotor is moved in the reverse manner.
  • the object of the invention is therefore to provide a method for unscrewing a ring half of a total annular guide from a lower housing half an axially flow-through, stationary flow machine, which is feasible when located in the lower half of the rotor housing and which can be done without the use of the rotor.
  • Another object of the invention is to provide a mounting device, a
  • the object related to the method is achieved by a method according to the features of claim 1.
  • the objects directed to the mounting devices are solved by the subject matters of claim 11, claim 15 and claim 16, respectively.
  • the invention is based on the finding that the
  • Pivoting the lower ring half of the nozzle to the machine axis not only due to a radially inner support and guidance by conditioning the rotor of the gas turbine is possible, but that required during the pivoting centering of the ring half - based on their radial extent - also possible due to an external guide is.
  • the invention requires that the lower ring half of the distributor has a radially outside - that is shell side - provided tread and that several mounting devices are to be introduced into the space between the lower ring half of the distributor and the lower half of the housing, which is attached to the lower half of the housing lower ring half can be supported on rollers, the rollers are on the one hand in contact with the tread and the axes of rotation, on the other hand, are aligned parallel to the machine axis of the turbomachine. Further, an auxiliary half-ring on the lower half-ring of the nozzle for completing the provided on the lower half-ring of the nozzle coat-side tread for an endless circulating
  • the lower Ring half of the nozzle during unscrewing from the lower housing half no longer, as before, via a radially inwardly disposed guide, namely the rotor, centered and supported, but via a radially outwardly provided guide, which includes a plurality of mounting devices, which secured in the lower housing half are and have roles to support the half-shell shell-side on the tread. Consequently, the method according to the invention comprises a total of four work steps according to the steps a to d of claim 1.
  • Diameter is touched or even rotates. Consequently, the lower ring half of the distributor can be pivoted out of the lower half of the housing without the rotor of the gas turbine must rotate or must be used as an auxiliary element for disassembly of the ring half of the nozzle. As a result, improved and more accurate sealing concepts between the rotor and stator are possible.
  • the mounting device for disassembly and assembly of a ring half of the nozzle of an axially permeable, stationary flow machine from a lower or in a lower half of the housing, which is to introduce into the space between the lower half of the nozzle and the lower half of the housing according to the aforementioned method, is for attachment to the inner wall of the lower
  • Housing half provided and has a role or a group of roles.
  • the mounting device for performing the method it is possible to support the lower ring half of the distributor during the entire Auswindvorgangs respectively screwing while maintaining the centricity of the mounting ring with respect to the machine axis of the turbomachine by an external guide - based on the diffuser itself -.
  • an auxiliary half-ring is required for carrying out the method, which shell side has a semi-annular running surface which can form an endlessly circulating circular running surface in conjunction with a lower ring half of the guide apparatus which can be fastened to the auxiliary half-ring.
  • the lower nozzle part via rollers or rolling stock, which are fixed to the housing, and screwed.
  • the rotor of the turbomachine is not used as an aid and does not rotate during the pivoting process.
  • the auxiliary half-ring replaces the upper part of the distributor and has no connection to the rotor during the turning process.
  • the method is particularly advantageous, since a complete disassembly of the gas turbine above the dividing plane, in which all upper housing halves of all housing sections be removed, can be avoided. Likewise, the rotor can remain in the housing half, whereby a total of unnecessary unnecessary maintenance work is avoided, which significantly increases the overall availability of the turbomachine and maintains.
  • the application of the rollers provided on the mounting device to the running surface can already take place during the introduction of the respective mounting device into the intermediate space.
  • the diffuser be supported by means of the mounting devices not only at an axial position, but is supported on at least two axial positions.
  • the mounting devices in each case a plurality, preferably four mounting devices are inserted between the lower half-ring of the distributor and the lower half of the housing.
  • Mounting devices can either be introduced through the manhole in the gap or, due to the revealed gas turbine, through the opening of the gap at the parting plane.
  • the mounting devices are rigidly attached to the lower half of the housing.
  • an auxiliary half-ring on the lower half of the diaphragm to complete each of a shell-side provided tread to an endlessly revolving tread to attach.
  • auxiliary half rings are rigidly interconnected via connecting struts. This makes it possible to increase the rigidity of the auxiliary half-rings in connection with the lower ring half of the distributor. This measure promotes the maintenance of the centricity and the circular configuration of the tread and the surface of the nozzle opposite the rotor.
  • the introduction of the necessary force to rotate the mounting ring takes place in the mounting ring on the shell side with the rotor located in the lower half of the housing. Accordingly, the rotor is not used as an aid for unscrewing the lower ring half. The rotor can thus dwell rigidly in its bearings during the turning process.
  • the method for screwing the lower half of a ring annular overall apparatus in a lower half of the axial flow-through, stationary flow machine with inserted rotor includes the
  • the method for screwing the lower ring half of the distributor in the lower housing half and the method steps according to claims 2 to 8 in reverse order with inverse directions of action are preferably, the method for screwing the lower ring half of the distributor in the lower housing half and the method steps according to claims 2 to 8 in reverse order with inverse directions of action.
  • Mounting device provided rolling groups or rollers designed as a rolling, since they are particularly suitable to store high weights rotatably. According to a particular embodiment of the mounting device, this is rigidly attachable to the lower housing half and / or its role or its role group can be applied by means of a clamping device to a provided on the lower half of the guide nozzle tread.
  • the clamping direction can be expediently designed as a hydraulic or a screw device.
  • a mounting device assembly according to any one of claims 11 to 14 is proposed according to the invention, which are connected to each other in a chain-like manner via a cable connection or a rod connection.
  • the auxiliary half-ring used in carrying out the method has on the shell side a semi-annular running surface which, in conjunction with a lower ring half of the guide apparatus which can be fastened to the auxiliary half-rings, forms an endlessly revolving running surface.
  • a flange connection for flange-like screwing to the lower ring half of the guide tube is provided at its two ends.
  • FIG. 1 shows a turbomachine according to the invention in a longitudinal part cross-section
  • FIG. 2 shows the plan view of a lower housing section with inserted lower half of a guide ring
  • FIG. 3 shows the cross section through a turbomachine with removed upper housing part and removed upper half of the ring of a distributor at a first axial position
  • FIG. 4 shows the same article as FIG. 3, but at an axial position
  • FIG. 5 shows a mounting device for disassembling a ring half of a distributor of an axial flow-through, stationary flow machine
  • a stationary gas turbine 1 is shown in a longitudinal part cross-section as stationary turbomachine, wherein the lower half of the representation, which is below the dash-dotted machine axis 9, the exterior of the housing of the gas turbine 1 together with their supports 3 and 4 represents. Above the dotted line 9, the interior of the gas turbine is to be seen in cross section, wherein the cross-sectional plane is selected parallel to the plane of the drawing.
  • the gas turbine 1 generally comprises a compressor 2, a centrally arranged combustion chamber 5 and, subsequently, a turbine unit 6 and an inner rotor 8 extending along the machine axis 9.
  • the rotor 8 has both rotor-side and turbine-side rings of rotor blades 12 provided, which are rigidly fixed to the rotor 8 rotatable with this.
  • the rotor 8 is mounted in not shown here camps both the compressor input side and turbine output side. Wreaths of vanes 14 are provided between the rings of rotor blades 12 both on the compressor side and on the turbine side, which are each connected directly or indirectly rigidly to the housing of the gas turbine 1.
  • Combustion chamber 5 the compressed air is supplied to the burners 10.
  • a fuel of the compressed air is mixed in, resulting in a hot working medium M is formed by combustion, the rotor 8 due to its turbine blading 12, 14 offset by the annular, diverging in the direction of flow annular channel 20 in rotation and thereby also for the compression of the ambient air necessary energy supplies.
  • “Lower half” or “upper half” respectively refer to a plane perpendicular to the plane of the drawing in which the machine axis 9 lies. This plane coincides with the division plane 40 and is also parallel to the horizontal plane on which the gas turbine is placed 1.
  • the reference numerals if necessary, with the suffix “o” for “upper half” and with the Suffix “u” extended for “lower half", if this is useful for clarity.
  • the gas turbine 1 has a plurality of housing sections 30, 32, 34, which are in each case designed to be annular overall and in each case consist of an upper housing half and a lower housing half.
  • the lower and the upper housing halves of the housing sections 30, 32, 34 are in the dividing plane 40 to each other in a flange and can over
  • Flange fittings are connected to each other gas-tight. Also, a flange 37 between the second housing portion 32 and the third housing portion 34 is shown in abstract.
  • housing is to be understood as meaning the housing section 34, but of course it is also conceivable to use the subsequently recorded methods and the devices described below on the compressor side, ie in the housing section 30 and / or 32 , provided at this point also a diffuser is provided.
  • the gas turbine 1 has, in the axial section of the housing section 34, a guide blade carrier 42, which, equipped with guide vanes 14 on the inside, is also designated as a guide device 44.
  • the diffuser 44 is substantially conical and composed in an analogous manner as the housing portion 34 of two ring halves, a lower ring half 44u and an upper ring half 44o.
  • the overall annular and in the flow direction of the hot gas M conically expanding diffuser 44 is rigidly supported on the housing 34 by means of several components. These components are distributed over the circumference and essentially comprise so-called center centering 46 and height adjustments 47.
  • the center centering devices 46 are in each case at top dead center and bottom dead center of the housing 34. whereas the height adjustments 47 on both sides close, but below the dividing plane 40, respectively. Machine axis 9 lie. Both the height adjustments 47 and the centering 46 are accessible from outside the housing 34.
  • the axial position of the centering 46 and the height adjustments 47 are chosen so that they are close to the position of the axial center of gravity S of the nozzle 44.
  • a gap 52 is present, which can be divided by sealing plates 50 into subspaces for different cooling air pressure levels.
  • the sealing plates 50 are usually formed from two 180 ° large circle segments.
  • the gap 52 is accessible via a provided in the lower half of the housing 34u manhole 54 for fitters.
  • the cover of the manhole 54 is to be removed, so that a fitter can get into the intermediate space 52.
  • a fitter can remove the vanes of the first turbine stage, if necessary.
  • the flange connections between the lower half 34u and the upper half 34o are released.
  • the upper casing half 34o is lifted from the lower casing half 34u so that the upper ring half 44o of the nozzle 44 is accessible from above.
  • FIG. 2 shows the plan view of the lower housing half 34u of the revealed gas turbine 1 in the section 34.
  • FIG. 2 thus shows a view of the flange connection surfaces of the lower ring half 44u and the lower housing half 34u.
  • the division plane 40 coincides with the plane of the drawing.
  • the rotor 8 is blanked out for the sake of clarity, but also the guide vanes inserted into the grooves 60 at the lower guide apparatus 44u.
  • the lower ring half 44u of the distributor 44 is on the shell side, that is provided on its outer circumference, with a total of two semi-annular raceways 62, which are each formed parallel to the machine axis 9 and lie on a concentric circular path.
  • the running surfaces 62 are - viewed in the axial direction - complained to each other. They are thus at two axial positions, which are designated III and IV.
  • the turbine inlet-side tread 62 lies on a smaller radius Rl and the turbine outlet side tread 62 on a larger radius R2.
  • bores 64 are provided, by means of which the two Ring halves 44u, 44o are screwed to a total annular guide 44.
  • the openings 64 provided in the flange connection surfaces of the lower housing half 34u serve to screw the lower housing half 34u to the upper housing half.
  • the distributor 44 has a smaller inner diameter in the turbine input side region of the distributor 44 than in the turbine output side region of the distributor 44. At least one ridge 82 is provided on the inside of the housing 34.
  • FIG. 3 shows the first axial position III in cross-section, FIG. 3 additionally showing an auxiliary ring 70 fixed to the lower ring half 44u of the distributor 44, which is missing in FIG.
  • an outer guide is provided for this one, based on the ring half. The guidance is carried out by means of several first and several second
  • FIG. 3 four first mounting devices 80 arranged in the intermediate space 52 are shown. Each of the mounting devices 80 is by means of three
  • first mounting devices 80 are connected by means of a rod 84.
  • Each of the first mounting devices 80 comprises a roller or a roller group 86 which can be applied to the running surface 62 provided on the shell side of the lower ring half 44u of the guide apparatus 44.
  • the auxiliary half-ring 70 which is screwed to the lower ring half 44u by way of a flange connection 72, likewise has a running surface 74 provided on the shell side, which with the running surface 62 of the lower ring half 44u has a total endlessly circulating surface circular tread 88 forms.
  • two different auxiliary half rings 70 are thus provided with running surfaces on different radii, which in each case the radii Rl resp. R2 correspond.
  • the second support is resp. Guiding the lower ring half 44u provided on the housing 34u.
  • the section according to IV-IV is shown in FIG 4 and shows the second support of the lower ring half 44u on the inside of the lower half of the housing 34u. Only a single one of the second mounting devices 90, which can be fastened to the inside of the inner housing wall of the housing 34 u, is shown by way of example in the radially narrow narrow space 52. In the shown
  • each mounting device 80, 90 designed as a roller carriage roller group 86.
  • the rollers are particularly able to accommodate the high weight of the nozzle 44.
  • a total of four, distributed along the circumference positions are provided on which a support of the lower ring half 44u is provided by rolling.
  • the auxiliary half-rings can still be connected to one another at the points 78 by struts.
  • the first mounting device 80 comprises a main body 81 in which, for example, three bores 83 are provided.
  • the holes 83 are used to accommodate screwing, with which the first mounting device 80 at the housing-side web 82 can be fastened.
  • 81 laterally arranged bores 85 are provided in the base body, in which the connecting rods 84 can be stored.
  • the main body 81 further comprises a central recess 87, in which a hydraulically actuated cylinder 89 is fixed, the piston rod carries a roller group 86, for example, the roller carriage.
  • a roller group 86 for example, the roller carriage.
  • roller group 86 - based on the installed state of the first mounting device 80 in the gas turbine 1 - is adjustable in the radial direction.
  • FIG. 6 and FIG. 7 show the detail Y of FIG. 4 both in a longitudinal section and in a cross section.
  • the turbine output side provided support according to FIG 4 by means of the second embodiment 90 of mounting devices.
  • the hydraulic cylinders are mounted outside and at the lower half of the housing 34u so that their piston rods can extend through the housing or through the housing wall.
  • rolling carriages 86 are inserted from the dividing plane, which can be pressed by the piston rods of the hydraulic cylinder 89 against the running surface 62 of the lower ring half 44u.
  • a screw device can be provided, by means of which the rolling carriages 86 can be adapted to the running surface 62.
  • the procedure for unscrewing the lower ring half 44u of the overall annular nozzle 44 from the lower half 34u of the housing proceeds as follows: after cooling the gas turbine 1, the upper half 34u of the gas turbine 1 is released from the lower half 34u and lifted off a heavy duty crane. After that, several
  • the second mounting devices 90 which via a
  • Cable connection or are connected by a rod connection chain-like are introduced from the dividing plane forth in the radially very narrow gap 52 at this point. After reaching their predetermined position, these are pressed against the running surface 62 of the lower ring half 44u by hydraulic cylinders 89 fastened externally to the housing half 34u. The mounting devices 80, 90 are then applied to the lower ring half 44u and are able to perform this exactly when unscrewing from the outside.
  • auxiliary half ring 70 is attached to the lower ring half 44u.
  • the unit of lower ring half 44u of the nozzle 44 with auxiliary half-rings 70 attached thereto is referred to below as a mounting ring 77.
  • the auxiliary half-ring 70 likewise has a running surface 74 which has the same radius as the running surface 62 with respect to the machine axis 9. Both running surfaces 74, 62 then form an endlessly running running surface 88 as a whole.
  • Mounting rings 77 take place. The introduction of force took place on the shell side, for example by a mounting ring 77 completely encompassing pull rope.
  • the pull rope preferably wraps around the mounting ring 77 at least more than once.
  • the auxiliary half-ring 70 is in the lower half of the housing 34u and the former lower ring half 44u above the dividing plane 40.
  • the rotation of the mounting ring 77 takes place with the rotor inserted, without this during rotation of the mounting ring 77 rotates or is touched by the mounting ring 77.
  • pressure transducers can additionally be provided on the roller carriages.
  • the pressure sensors detect the respective pressure and make their measured values available to an evaluation unit, which determines therefrom the center of the mounting ring 77. If a shift of the center point of the mounting ring 77 can be determined from the machine axis 9, the radial position of the rolling elements can be corrected by means of the hydraulic to compensate for this shift.
  • All mounting devices 80, 90, resp. the auxiliary half rings 70 and the drive for rotating the mounting ring 77 are collectively referred to as RoIl-in and roll-out device and allow the rapid removal of the lower nozzle 44u and the lower vanes of the Turbine unit 6 from a gas turbine 1, without that the rotor 8 can be seen.
  • Parts of the steps are parallelizable or can be performed in different orders.
  • the assembly of the auxiliary half-rings 70 may also take place prior to the assembly of the first and second mounting devices 80, 92 or simultaneously with them. It is also conceivable to carry out the screwing of the auxiliary half ring 70 with the lower ring half 44u simultaneously with the release of the rigid connection between the lower ring half 44u and the lower half of the housing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé pour dévisser une moitié annulaire (44u) d'un distributeur de forme globale annulaire (44) hors d'une moitié de boîtier inférieure (34u) d'une turbomachine stationnaire à écoulement axial, et des dispositifs de montage (80, 90) nécessaires à cet effet ainsi qu'un demi-secteur annulaire auxiliaire (70). Afin de dévisser la moitié annulaire inférieure (44u) du distributeur (44) hors de la moitié de boîtier inférieure (34u), sans devoir enlever pour cela le rotor (8) de la turbomachine (1) ou devoir l'utiliser en tant que moyen auxiliaire, on utilise deux configurations différentes de dispositifs de montage avec lesquelles on peut supporter la moitié annulaire inférieure (44u) contre le côté interne de la moitié de boîtier inférieure (34u). Le support de la moitié annulaire (44u) s'effectue par un groupe de rouleaux (86) prévu sur le dispositif de montage. Du fait du montage d'un demi-secteur annulaire auxiliaire (70) sur la moitié annulaire (44u), on peut obtenir une surface de roulement circonférentielle sans fin (88) sur laquelle l'anneau peut tourner sous l'effet d'une force s'appliquant tangentiellement. Le demi-secteur annulaire auxiliaire (70) est dans ce cas vissé depuis sa position supérieure dans la moitié de boîtier inférieure (34u), et en même temps la moitié annulaire inférieure (44u) est dévissée de la moitié de boîtier inférieure (34u). Ensuite, la moitié annulaire inférieure (44u) est desserrée du demi-secteur annulaire auxiliaire (70), après quoi les aubes directrices de turbine (14) fixées au distributeur (44) sont librement accessibles.
PCT/EP2007/056959 2006-07-24 2007-07-09 Procédé pour dévisser une moitié annulaire d'un distributeur de forme globale annulaire hors d'une moitié inférieure de boîtier d'une turbomachine stationnaire à écoulement axial, dispositif de montage, assemblage de dispositif de montage et demi-secteur annulaire auxiliaire WO2008012195A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006034674 2006-07-24
DE102006034674.2 2006-07-24

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WO2008012195A1 true WO2008012195A1 (fr) 2008-01-31

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Cited By (18)

* Cited by examiner, † Cited by third party
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EP2107219A1 (fr) * 2008-04-03 2009-10-07 Siemens Aktiengesellschaft Segment de couronne d'aubes directrices et support de couronne pour un boîtier de turbomachine divisé horizontalement
EP2194236A1 (fr) * 2008-12-03 2010-06-09 Siemens Aktiengesellschaft Carter de turbine
EP2211023A1 (fr) * 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Distributeur pour turbomachine avec structure support d'aubes directrices segmentée
JP2013256942A (ja) * 2012-06-08 2013-12-26 General Electric Co <Ge> ガスタービンのケーシングシェルのロールインおよび位置合わせのための方法および装置
EP2706200A1 (fr) * 2012-09-10 2014-03-12 Alstom Technology Ltd Procédé pour supprimer un coffrage interne d'une machine
EP2706199A1 (fr) 2012-09-10 2014-03-12 Alstom Technology Ltd Procédé et guide pour supprimer un coffrage interne d'une turbomachine
EP2772617A1 (fr) 2013-02-27 2014-09-03 Alstom Technology Ltd Turbomachine avec moyens de support et procédé de démontage de la machine
JP2014177888A (ja) * 2013-03-14 2014-09-25 Mitsubishi Heavy Ind Ltd 静翼環の取外・取付方法、及びこの方法に用いる静翼セグメントの補助支持装置
EP2851522A1 (fr) * 2013-09-19 2015-03-25 Siemens Aktiengesellschaft Dispositif de rotation pour une turbine à gaz et procédés pour faire tourner un composant
CN104454660A (zh) * 2014-11-07 2015-03-25 中航工业贵州航空动力有限公司 一种航空发动机压气机匣半环装配方法
EP2921657A1 (fr) * 2014-03-20 2015-09-23 Alstom Technology Ltd Outil pour le désassemblage un bôitier interne d'une turbomachine
JP2017053243A (ja) * 2015-09-07 2017-03-16 東芝プラントシステム株式会社 ガスタービン燃焼器分解組立輸送装置
JP2017057721A (ja) * 2015-09-14 2017-03-23 株式会社Ihi 軸流機械の分解方法
WO2017122632A1 (fr) * 2016-01-13 2017-07-20 三菱日立パワーシステムズ株式会社 Procédé et dispositif d'extraction d'aube
EP2690256A3 (fr) * 2012-07-26 2017-08-23 General Electric Company Procédé et système pour l'assemblage et le désassemblage de carters de turbomachines
JP2017207016A (ja) * 2016-05-19 2017-11-24 太平電業株式会社 回転機器用静翼セグメントの取外し方法および装置
US10174618B2 (en) 2013-07-04 2019-01-08 Siemens Aktiengesellschaft Rotor for a turbine
US11746678B1 (en) * 2022-10-31 2023-09-05 General Electric Company Apparatus and method for protecting a replacement part of a turbine assembly

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CN101983280A (zh) * 2008-04-03 2011-03-02 西门子公司 用于水平分开的透平机外壳的装置、导向轮部段和用于水平分开的透平机外壳的导向叶片外圈
JP2011516776A (ja) * 2008-04-03 2011-05-26 シーメンス アクチエンゲゼルシヤフト 水平分割式タービン車室用静翼輪据付装置、水平分割式タービン車室用静翼輪セグメント及び静翼ホルダ
EP2107219A1 (fr) * 2008-04-03 2009-10-07 Siemens Aktiengesellschaft Segment de couronne d'aubes directrices et support de couronne pour un boîtier de turbomachine divisé horizontalement
EP2194236A1 (fr) * 2008-12-03 2010-06-09 Siemens Aktiengesellschaft Carter de turbine
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WO2010084028A1 (fr) * 2009-01-21 2010-07-29 Siemens Aktiengesellschaft Système d'aubes directrices pour une turbomachine comportant un support d'aubes directrices segmenté
US9238976B2 (en) 2009-01-21 2016-01-19 Siemens Aktiengesellschaft Guide vane system for a turbomachine having segmented guide vane carriers
JP2013256942A (ja) * 2012-06-08 2013-12-26 General Electric Co <Ge> ガスタービンのケーシングシェルのロールインおよび位置合わせのための方法および装置
EP2672079A3 (fr) * 2012-06-08 2017-08-23 General Electric Company Procédé et appareil permettant de rouler et d'aligner une coque de boîtier d'une turbine à gaz
EP2690256A3 (fr) * 2012-07-26 2017-08-23 General Electric Company Procédé et système pour l'assemblage et le désassemblage de carters de turbomachines
KR101557274B1 (ko) 2012-09-10 2015-10-05 알스톰 테크놀러지 리미티드 기계로부터 내부 케이싱 제거 방법
EP2706198A1 (fr) * 2012-09-10 2014-03-12 Alstom Technology Ltd Procédé pour supprimer un coffrage interne d'une machine
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KR101562840B1 (ko) 2012-09-10 2015-10-23 알스톰 테크놀러지 리미티드 터보머신으로부터 내부 케이싱을 제거하기 위한 방법 및 가이드
US9162329B2 (en) 2012-09-10 2015-10-20 Alstom Technology Ltd. Method for removing an inner casing from a machine
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JP2014051985A (ja) * 2012-09-10 2014-03-20 Alstom Technology Ltd 機械から内側ケーシングを取り外す方法
US9739177B2 (en) 2013-02-27 2017-08-22 Ansaldo Energia Switzerland AG Rotary flow machine and method for disassembling the same
EP2772617A1 (fr) 2013-02-27 2014-09-03 Alstom Technology Ltd Turbomachine avec moyens de support et procédé de démontage de la machine
US10060449B2 (en) 2013-03-14 2018-08-28 Mitsubishi Hitachi Power Systems, Ltd. Method for attaching/removing vane ring and auxiliary support device for vane segment used in said method
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CN105863749A (zh) * 2013-03-14 2016-08-17 三菱日立电力系统株式会社 静叶扇形体的辅助支撑装置
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KR101834100B1 (ko) 2013-09-19 2018-03-02 지멘스 악티엔게젤샤프트 가스 터빈의 회전 장치 및 구성 부품의 회전 방법
US10711651B2 (en) 2013-09-19 2020-07-14 Siemens Aktiengesellschaft Rotating device for a gas turbine and method for rotating a component
EP2851522A1 (fr) * 2013-09-19 2015-03-25 Siemens Aktiengesellschaft Dispositif de rotation pour une turbine à gaz et procédés pour faire tourner un composant
WO2015039830A1 (fr) 2013-09-19 2015-03-26 Siemens Aktiengesellschaft Dispositif de mise en rotation pour turbine à gaz et procédé permettant de faire tourner un élément structural
AU2014323399B2 (en) * 2013-09-19 2017-01-12 Siemens Aktiengesellschaft Rotating device for a gas turbine and method for rotating a component
CN105793525A (zh) * 2013-09-19 2016-07-20 西门子股份公司 用于燃气涡轮机的转动装置和用于使组成部件转动的方法
EP2921657A1 (fr) * 2014-03-20 2015-09-23 Alstom Technology Ltd Outil pour le désassemblage un bôitier interne d'une turbomachine
CN104454660A (zh) * 2014-11-07 2015-03-25 中航工业贵州航空动力有限公司 一种航空发动机压气机匣半环装配方法
JP2017053243A (ja) * 2015-09-07 2017-03-16 東芝プラントシステム株式会社 ガスタービン燃焼器分解組立輸送装置
JP2017057721A (ja) * 2015-09-14 2017-03-23 株式会社Ihi 軸流機械の分解方法
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JPWO2017122632A1 (ja) * 2016-01-13 2018-07-26 三菱日立パワーシステムズ株式会社 翼引き抜き装置及び方法
CN108474264A (zh) * 2016-01-13 2018-08-31 三菱日立电力系统株式会社 叶片取出装置及方法
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US10954791B2 (en) 2016-01-13 2021-03-23 Mitsubishi Power, Ltd. Blade removal device and method
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