EP2884052B1 - Rotor pour une turbomachine avec bague d'écoulement fermée profilée et son procédé de fabrication - Google Patents

Rotor pour une turbomachine avec bague d'écoulement fermée profilée et son procédé de fabrication Download PDF

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Publication number
EP2884052B1
EP2884052B1 EP13197194.7A EP13197194A EP2884052B1 EP 2884052 B1 EP2884052 B1 EP 2884052B1 EP 13197194 A EP13197194 A EP 13197194A EP 2884052 B1 EP2884052 B1 EP 2884052B1
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EP
European Patent Office
Prior art keywords
rotor
ring
flow contour
blades
contour ring
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
EP13197194.7A
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German (de)
English (en)
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EP2884052A1 (fr
Inventor
Marco Dreymann
Erik Porsch
Dimitri Zelmer
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Siemens AG
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Siemens AG
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Publication date
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Priority to EP13197194.7A priority Critical patent/EP2884052B1/fr
Publication of EP2884052A1 publication Critical patent/EP2884052A1/fr
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Publication of EP2884052B1 publication Critical patent/EP2884052B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates in essence to a turbine machine designed as a turbine or as an axial compressor, along the flow path alternately rows of fixed to a rotatable support vanes and blades attached to a rotor follow one another, wherein at least one of the vane rows comprises free-standing vanes and one of this vane directly adjacent Blade rows includes blades, which are each inserted in at least partially extending in the axial direction retaining grooves. Furthermore, the invention relates to a method for producing a rotor of a compressor from a plurality of rotor base elements.
  • Turbomachines and axial compressors are known in a variety of ways from the extensive state of the art. Basically, they have sequentially rows of blades, which are either made of vanes attached to a non-rotatable support.
  • the carrier may, for example, be designed as a guide blade carrier or as a housing. Both are annular structures in whose interior a rotor is rotatably mounted. Or the rows are formed of blades, which are usually attached to a shaft collar of the rotor.
  • the blades of the blades are disposed in the annular flow path, which typically extends axially between the carrier and the rotor.
  • both Vanes as well as blades can be inserted in their corresponding carrier (the vane support or on the rotor) in circumferential grooves.
  • the circumferential grooves then have a hammer-shaped contour in cross-section, into which the correspondingly executed blade roots of the guide vanes or moving blades are inserted.
  • blades arranged in circumferential grooves all blades of a row sit in one and the same groove. These blades are referred to as blades having a radial foot design.
  • All blades are attached at least the foot side. With reference to annular flow paths, the guide vanes are thus fastened radially on the outside of the flow path boundary, and the rotor blades are radially inward.
  • turbomachines whose housing has a parting line, some combinations of these different constructions are difficult or impossible to implement.
  • Such turbomachines are assembled so that their fitted with blades rotor is first inserted into a lower half of the housing, after which the rotor is then covered by placing the upper half of the housing on the lower.
  • This is also known as a radial design and is in contrast to a Axialbauweise, as found in aircraft engines application.
  • freestanding vanes require a rotor-side mostly rotationally symmetrical wall surface on the rotor, which faces the tips of the free-standing vanes and locally limits the flow path radially inward.
  • This requirement has heretofore made it impossible to use axial foot design blades because their retaining grooves require clearance at the same location to first position the blades at the appropriate radius during assembly and then push them into the respective retaining groove by the axial sliding motion can.
  • an inner ring guide design was mostly used at these axial positions when directly next to it axial blade design blades were used.
  • blades with a radial foot design are more expensive to produce compared to blades with Axialfußdesign.
  • Guide vanes which have an inner ring on the head side, are very complex in manufacture and assembly. In addition, these are susceptible to interference in operation. Furthermore, a seal between the inner ring and the rotor is required, which increases the complexity of the system, if only small leaks are desired.
  • the object of the invention is therefore to provide a rotor for a preferably made in radial construction Turbomachine and a preferably produced in radial flow machine of the type mentioned, in which in particular repeatedly freestanding vanes of a row of vanes can be arranged immediately adjacent to seated in axial holding blades blades.
  • the object underlying the invention is achieved with a rotor for a turbomachine according to the features of claim 1.
  • the object directed to the turbomachine with a turbomachine according to the features of claim 11 is achieved.
  • the features of claim 16 solve the problem of specifying a method for producing a rotor for a turbomachine.
  • the rotor for a turbomachine with an annular cross-sectional flow path thus comprises at least one endless shaft collar, in which at least partially axially extending retaining grooves are provided, each with a seated therein blade to form a blade ring, wherein the rotor comprises at least one Strömungskonturring, which at least one , Which has at most four radially outwardly facing openings as access to a corresponding number of available segment clearances, which segment free space or which segment clearances are open at least on one side, preferably on both sides, and wherein the flow contour ring and / or the remaining rotor means for fixing a closing the access Closing device and wherein said flow contour ring is arranged laterally of the respective shaft collar and whose or their accesses in each case by a respective flow contour ring and / or the rest e rotor attached closure device is closed.
  • the closed flow contour ring is arranged in particular during assembly of the rotor base elements between the two immediately adjacent rotor base elements, in particular with built-rotors.
  • This largely fills the previously free for the assembly of the blades annular space between the adjacent rotor base elements and leaves at least one segment clearance.
  • Each segment free space extends only over a part of the circumference of the flow contour ring and is usually chosen only so large that it is at most slightly larger than the pitch of the adjacent blade ring.
  • one to four segment clearances are now provided instead of the previous Ringfreiraumes.
  • the segment clearances serve in the absence of closure device on the one hand for the disassembly / assembly of the blades and for the placement of a de- or mounting device such as a hydraulic cylinder, by means of which the blades can be pushed out into the holding or out of the holding.
  • a de- or mounting device such as a hydraulic cylinder
  • the flow contour ring forms the hub-side boundary of the flow channel in the axial section of the freestanding guide vanes.
  • a moving blade is to be inserted into each of the retaining grooves provided in the shaft collar. At least one segment free space is not yet closed by the associated closure device, but open.
  • the closed flow contour ring relative to the two rotor base elements is to be rotated in the circumferential direction such that its segment clearance is arranged so that the foot of the relevant blade can be immersed in it from radially outside. Then it can be inserted into the lateral opening of the retaining of said blade root until it is completely absorbed by the retaining groove.
  • the flow contour ring can be rotated in the circumferential direction to the next holding groove according to the pitch of the blade ring, in which then the next blade is mounted in the same manner. These steps are repeated until all the blades of the ring are mounted on the respective shaft collar. Subsequently, the closure device is attached to the closed flow contour ring, whereby the radially outwardly facing opening of the segment space is closed flat and flush.
  • the flow contour ring has only one segment free space with the radially outwardly facing opening.
  • a slightly larger number of segment clearances and thus openings can be provided.
  • Expedient upper limit seems to represent a number of four segment clearances, since otherwise the effort to close the respectively outwardly facing opening is too costly.
  • the closed flow contour ring also comprises an outwardly facing surface, which may be cylindrical, frusto-conical or even a curved truncated cone shape. In principle, it is still rotationally symmetrical, since this opposite to the tips of the vanes in the installed state of the rotor. The rotational symmetry may possibly be excluded if a so-called "stroke-treatment" is arranged opposite the blade tips of the freestanding guide vanes.
  • the closed flow contour ring it is possible to provide a radial flow machine having an annular flow path along which vanes of fixed support and rotor-mounted blades successively follow one another, with at least one of the vanes comprising free-standing vanes and one the blade vane immediately adjacent this vane ring comprises blades which are each inserted in at least partially axially extending retaining grooves of the rotor, wherein the rotor and its associated flow contour ring is configured such that it faces the tips of the free-standing vanes.
  • laterally refers to one or both axially adjacent portions of that shaft collar in which the holding grooves for blades are arranged.
  • the flow contour ring may be made of metal or of glass or carbon fiber reinforced plastic. Since the use in rows of blades is possible, which are exposed to relatively low thermal influences, can be used as a plastic material. The use of plastic is inexpensive and provides a durable and low-weight solution. By contrast, the use of metal is also suitable, especially at higher operating temperatures.
  • a flow contour ring is provided on both sides of the respective shaft collar. This allows in the service case by dismantling each wall element access to mounting space to position on the one hand a tool for pushing out the blade therein, which tool can then push the dismantling blade into the other mounting space available.
  • the radially outwardly facing surface of the flow contour ring and / or the closure element is coated.
  • the layers are to be integrated as abradable layers - possibly called abradables - in a further groove on the outer circumference of the flow contour ring.
  • the access in question, the relevant frontal opening and the segmental clearance in question have a size such that at least one, but no more than two blades of the immediately adjacent ring can be assembled or disassembled at the same time.
  • the size of the closure device, with which the radially outwardly facing opening of the segmental clearance is to close be designed physically small, which reduces their tendency to loss or for release.
  • the flow contour ring and its closure devices are designed such that they block a displacement of the mounted blade along its retaining groove on one side. On this side of the retaining then no further measures are required to prevent the displacement of the blade along the retaining.
  • a comparatively simple, as cost-effective solution is provided as axial securing.
  • this may be integrally formed screwed to the flow contour ring.
  • the closure device is relatively easy to manufacture, wherein it has proved to be advantageous when the screws are in turn secured against loosening.
  • An alternative closure device can be configured in several parts in the manner of a closure piece for circumferential grooves of rotor blade rings. Such closure pieces are known from the extensive prior art.
  • the closure device may comprise a cover member closing the access flush and an intermediate piece, wherein the intermediate piece is seated radially positively in the flow contour ring and screwed to the cover element.
  • This also represents a comparatively inexpensive and easy to install closure device that closes the access permanently and reliably.
  • the flow contour ring freed from at least one shutter is to be rotated about the axis of rotation until the segment clearance is at the appropriate position where the blades are to be installed proved to be useful when the flow contour ring has radially inwardly two to five Gleitcard Suitee to the rest of the rotor. This ensures low adjustment forces. Also, with the help of an additional adjustment in the groove in which the flow contour ring sits, the service friendliness increased and the adjustment force can be further reduced by a leverage.
  • the turbomachine can be designed either as an axial turbine or as an axial compressor.
  • the axial compressor may in particular be that of a stationary gas turbine.
  • Guide plates in which the guide vanes are coupled radially outwards and radially inward via rings, can be dispensed with. These can be replaced by freestanding vanes. This results in savings in manufacturing, storage and production management costs for the components. In addition, despite the use of Axialfußschaufeln a destacking of the rotor in case of service is no longer necessary. At the same time, there are lower leakage flows between the blade tips and the opposite flow contour rings compared to the constructions with inner rings which are to be sealed off from the rotor.
  • the rotor basic elements can not only be comparatively solid rotor elements with a comparatively large axial extension.
  • the rotor basic elements can also be designed in each case as wheel discs, in particular when the rotor is in modular Construction is composed of a plurality of such wheel discs. Such rotor disks can be clamped together either via a central tie rod or via a plurality of decentralized tie rods.
  • the flow contour ring is designed comparatively solid away from its segmental clearance, so that it can be designed as a self-supporting construction.
  • the flow contour ring is also possible for the flow contour ring to be substantially a sheet metal construction comprising some circumferentially distributed and / or extending struts for radial and lateral support.
  • the closed flow contour ring has a width which is detected in the axial direction and which is only slightly larger than the width of the endless shaft collar, likewise detected in the axial direction, in which the rotor blades are inserted.
  • the invention provides a closed flow contour ring for a rotor, a rotor for a turbomachine and a turbomachine, which can be configured in such a way by using the flow contour ring according to the invention in a rotor and by using a rotor in a turbomachine.
  • that, in particular, repeatedly freestanding guide vanes can be arranged directly axially adjacent to rotor blades, which in turn are inserted into at least partially axially extending retaining grooves.
  • a closed flow contour ring is suggested which is mounted on the rotor adjacent a shaft collar having the retaining grooves of axial blade design vanes and which has a laterally and outwardly openable lockable segment clearance for removal of a blade.
  • FIG. 1 shows a section of a longitudinal section through an axial compressor 10 of the prior art, in which 12 guide vanes 14 are arranged in rows on a rotatable carrier.
  • the vanes 14 are hooked with their blade root 16 in the blade carrier 12 in any desired manner.
  • On the blade ends 16 opposite the head ends of the guide vanes 14 so-called inner rings 18 are provided, which couple the blades of the vanes 14 in a row.
  • the inner rings 18 are arranged in a free space 20 which is arranged axially between two shaft collars 23 of adjacent wheel disks 22, in each of which retaining grooves 24 are arranged. In the retaining grooves 24 blades 26 are inserted.
  • the retaining grooves 24 extend substantially in the axial direction, that is, they can also be employed against the axial direction.
  • the side of the shaft collars 23 existing clearances 20 allow for a rotor 19, the subsequent mounting of blades 26.
  • the rotor 19 includes individual wheel discs 22 which are braced by a tie rod 28 together
  • the inner rings 18 formed the hub-side boundary of the flow path 13 in the region of the guide vanes 14, whereas according to FIG. 2 the hub-side boundary of the flow path 13 is formed by the outer peripheral surfaces 40 of the rotor disks 42.
  • FIG. 2 In particular in axial compressors in radial construction instead of guide vanes 14 with inner rings 18 freestanding guide vanes 34 (FIGS. FIG. 2 ), had in the prior art - shown in FIG. 2 -
  • the blades 36 are arranged in circumferential grooves 38 which are provided on the outer peripheral surfaces 40 of the rotor discs 42.
  • the outer peripheral surfaces 40 of the rotor disks 42 also delimit the flow path 13 of the compressor 10 away from the rotor blades 36, which is annular in cross-section and in which the blades of the blades 14, 26, 34, 36 are arranged for compressing the working medium.
  • the wreaths are arranged concentrically to a central axis 15.
  • FIG. 1 illustrated blades 26 with Axialfußdesign immediately adjacent freestanding vanes 34 according to FIG. 2 to be used in turbomachinery in particular with radial design, which is in the FIGS. 3 to 12 shown embodiments of rotors 21 proposed.
  • the rotor 21 comprises at least two immediately adjacent rotor base elements 25, which are designed as wheel discs 22.
  • a shaft collar 23 is provided on the outside, in which the retaining grooves 24, which are usually inclined to the axial direction, are arranged. Between the shaft collars 23 there is a clearance 20 which is required to push the blades 26 into the retaining groove 24.
  • the free spaces 20 may be located in those axial portions of the rotor 21, in which both wheel disks 22 extend axially into it. After assembly of the blades 26 in the retaining grooves 24, the access to the free spaces 20 are flat and continuously cover for the flow.
  • FIG. 3 shows in perspective two directly adjacent wheel discs 22.
  • the wheel discs 22 each have the shaft collar 23, in which along the circumference uniformly distributed retaining grooves 24 are provided for blades 26.
  • the retaining grooves 24 are opposite the rotation axis 15 (FIG. FIGs. 1 and 2 ) slightly inclined. However, they can also be aligned exactly parallel to the axis of rotation 15 of the rotor 21.
  • the outwardly facing surfaces 45 of the shaft collars 23 are hub-side boundary surfaces for the flow path of the turbomachine.
  • a self-contained flow contour ring 46 is arranged between the two shaft collars 23 .
  • a closure device 48 is secured in the flow contour ring 46.
  • the outwardly facing surfaces of the flow contour ring 46 and the closure device 48 are aligned with the outwardly facing surfaces 45 of the shaft collars 23, so that a stepless boundary of the flow path is ensured on the hub side.
  • the closed flow contour ring 46 is in FIG. 4 shown in perspective.
  • the flow contour ring 46 has at least one segment clearance 49 which includes a radially outwardly facing opening 50 for access to the segment clearance 49. Further, the segment clearance 49 is open at both end side surfaces of the flow contour ring 46.
  • FIG. 4 shown in perspective flow contour ring 46 is made comparatively solid and has on its inner side segment-shaped grooves 52, which reduce the weight of the Strömungskonturrings 46.
  • the inner surface of the flow contour ring has inwardly projecting sliding contact surfaces 54 such that at these sliding contact surfaces 54, the flow contour ring 46 may contact the remainder of the rotor.
  • two sliding contact surfaces 54 three or optionally even more sliding contact surfaces can be provided. It is advantageous in any case, if not the entire inwardly facing surface of the flow contour ring 46 is in sliding contact with the rest of the rotor.
  • the flow contour ring 46 has only a comparatively small material thickness in the radial direction, in which holes 56 can be provided according to the exemplary embodiments illustrated here.
  • the opening 50 of the segmental clearance 49 can be closed by means of a closure device 48.
  • a first embodiment of a closure device 48 is shown in FIG FIG. 5 shown in perspective. De facto, the closure device 48 is made in one piece as a cuboid with two holes 51st
  • FIG. 6 shows the longitudinal section through two immediately adjacent rotor disks 22 and arranged between the shaft collars 23 Strömungskonturring 46 and the closure device mounted thereon 48. Due to the employment of the retaining grooves 24 relative to the axial direction is similar to their representation a circumferential groove, which they are not. After complete assembly of all blades 26 of both rings, the closure device 48 is inserted into the segmental clearance 49 of the flow contour ring 46, so that the radially outwardly facing opening 50 is completely closed, except for the openings in the closure device 48 for receiving the screws.
  • the holes 56 provided in the flow contour ring 46 are aligned with the bores 51 of the closure device 48, so that screws can be screwed to the rotor disks 22, after which the closure device 48 is fastened in the flow contour ring 46.
  • the screws need not necessarily be bolted to the rotor disks 22. Instead, it would be conceivable that the holes 56 of the flow contour ring 46 have an internal thread into which the screws are screwed to secure the closure device 48. In this case, the screws should be so long that their headless ends in the installed state can engage positively in the holes of the rotor disk, so as to ensure the fuse described above.
  • a second embodiment of a flow contour ring 46 shows FIG. 7 , where in FIG. 7 the edges of the flow contour ring 46 are shown in phantom and the closure device 48 arranged in its segment clearance 49 is shown as a solid line.
  • the shutter 48 is such as is known from blades for circumferential grooves of blades.
  • the closure device 48 is configured in four parts with a left spacer 48a, a right spacer 48b and a middle spacer 48c, which are listed in the here Sequence in the segment clearance 49 can be used, with the left and right spacers arranged to interlock with undercuts 47 of the flow contour ring 46 can hook.
  • a screw 55 with a trapezoidal beard 53 (FIG. FIG. 8 ) intended.
  • a spring 59 is also provided, which can engage in a corresponding groove which is provided on the shaft collar 23. Also, this present in the circumferential direction positive locking prevents relative movement of the flow contour ring 46 to the remaining rotor during operation of the turbomachine.
  • Projections 57 ( FIG. 7 ) on the left and right spacers 48a, 48c also prevent relative movement of the spacers 48a, 48c with respect to the flow contour ring 46.
  • FIG. 10 A second embodiment of a flow contour ring is shown in FIG FIG. 10 shown in perspective.
  • the Strömungskonturring 46 shown here is designed rather sheet-like with a jacket plate 61, on which an inwardly projecting circumferential web 62 is provided, wherein web 62 and jacket plate 61 are connected to each other stabilizing over distributed along the circumference ribs 63.
  • This flow contour ring 49 may also have sliding contact surfaces 54 distributed in opposite positions or evenly distributed on the inner circumference.
  • the flow contour ring 46 at its twelve o'clock position the segment clearance 49, which is open radially on both sides and the front side.
  • FIG. 11 shows one too FIG. 7 Similar representation of a closure device 48 for the second embodiment of the Strömungskonturrings 46.
  • the closure device 48 according to the second embodiment shown here comprises an intermediate piece 66 and a cover member 68.
  • the intermediate member 66 is via pins 70, which in correspondingly shaped Recesses 72 ( FIG. 10 ) of the Strömungskonturrings 46, whereby it is positively locked in the radial direction with the flow contour ring 46.
  • the cover element 68 is screwed by two screws 74 with the intermediate element 66. Since the cover element 68 bears laterally against the shaft collar 23, the pins 70 can not be released from the recesses 72 when the cover element 68 is mounted, so that the loss of the closure device 48 is reliably avoided.
  • FIGS. 13 to 16 3 sequentially show the different steps of removing the last blade 26 of a blade ring using the flow contour ring 46 of the present invention FIG. 13
  • the circumferential position of the segment clearance 49 for removing the arranged in the right shaft collar 23 blade 26 is unsuitable, since this is to move according to the representation chosen here upwards, which FIG. 14 is shown with the arrow 76.
  • the segment clearance 49 of the flow contour ring 46 is arranged so that the entire blade root of the blade 26 can be pushed into this.
  • the displacement of the blade root of the blade 26 in the segment clearance 49 is in FIG. 15 shown, wherein the movement of the blade 26 is visualized by the arrow 78.
  • the blade 26 can be inserted into the segment clearance 49 so far that the entanglement of the foot of the blade 26 with the retaining groove 24 is released. Subsequently, the blade 26 is the segment space 49 removed, which is in FIG. 16 is shown. The assembly of a blade on a rotor 21 naturally in reverse order.

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Claims (16)

  1. Rotor pour une turbomachine ayant un trajet d'écoulement annulaire en section transversale,
    comprenant au moins un collet (23) d'arbre sans fin, dans lequel sont prévues des rainures (24) de maintien s'étendant, au moins en partie, axialement et ayant chacune une aube (26) mobile, qui y est mise avec formation d'une couronne d'aubes,
    caractérisé en ce que
    le rotor comprend au moins une bague (46) de contour d'écoulement fermée ayant des surfaces latérales du côté frontal et au moins une surface tournée radialement vers l'extérieur, dans laquelle est prévue au moins une ouverture comme accès à des espaces (49) libres de segment présents en nombre correspondant, les espaces (49) libres de segments concernés étant ouverts du côté frontal, au moins d'un côté,
    dans lequel la bague (46) de contour d'écoulement est disposée latéralement au collet (23) d'arbre concerné et son ou ses accès est fermé par un dispositif (48) de fermeture fixé à la bague (46) de contour d'écoulement concerné.
  2. Rotor suivant la revendication 1,
    qui a des moyens de fixation d'un dispositif (48) de fermeture fermant l'accès.
  3. Rotor suivant la revendication 1 ou 2,
    dans lequel la bague (46) de contour d'écoulement est en métal ou en matière plastique renforcée par de la fibre de verre ou par de la fibre de carbone.
  4. Rotor suivant la revendication 1, 2 ou 3,
    dans lequel la surface tournée vers l'extérieur de la bague (46) de contour d'écoulement et/ou celle de l'élément (48) de fermeture est revêtue.
  5. Rotor suivant l'une des revendications précédentes,
    dans lequel l'accès concerné, l'ouverture du côté frontal concernée et l'espace (49) libre de segment concerné ont une dimension telle qu'au moins l'une des aubes (26) mobiles de la couronne immédiatement voisine peut être montée et démontée par ceux-ci.
  6. Rotor suivant l'une des revendications précédentes,
    dans lequel la bague (46) de contour d'écoulement et ses dispositifs (48) de fermeture sont conformés de manière à empêcher, d'un côté, un déplacement des aubes (26) mobiles le long de sa rainure de maintien.
  7. Rotor suivant l'une des revendications précédentes,
    dans lequel le dispositif (48) de fermeture constitué d'une seule pièce est vissé à la bague (46) de contour d'écoulement.
  8. Rotor suivant l'une des revendications 1 à 6,
    dans lequel le dispositif (48) de fermeture est constitué en plusieurs parties à la manière d'une pièce de fermeture pour des rainures périphériques de couronnes d'aubes mobiles.
  9. Rotor suivant l'une des revendications 1 à 6,
    dans lequel le dispositif (48) de fermeture comprend un élément (68) de recouvrement fermant à affleurement l'accès et une pièce (66) intermédiaire, la pièce (66) intermédiaire étant mise à complémentarité de forme radialement dans la bague (46) de contour d'écoulement et vissée à l'élément (68) de recouvrement.
  10. Rotor suivant l'une des revendications précédentes,
    dans lequel la bague (46) de contour d'écoulement a, par rapport au reste du rotor, vers l'intérieur radialement, deux à cinq parties (54) de contact glissant.
  11. Turbomachine ayant un trajet d'écoulement annulaire, comprenant un rotor (21) suivant l'une des revendications 1 à 10, dans laquelle se succèdent, en alternance le long du trajet d'écoulement, des couronnes d'aubes (34) directrices fixées à un support fixe en rotation et des aubes (26) mobiles fixées au rotor,
    dans laquelle au moins l'une des couronnes d'aubes directrices comprenant des aubes (34) directrices dégagées et au moins l'une des deux rangées d'aubes mobiles directement voisines de cette rangée d'aubes directrices comprend des aubes (26) mobiles, qui sont insérées respectivement dans des rainures (24) de maintien, s'étendant axialement au moins en partie, du rotor (21), caractérisée en ce que
    la bague (46) ou les bagues (46) de contour d'écoulement du rotor sont opposées aux pointes des aubes (34) directrices dégagées.
  12. Turbomachine suivant la revendication 11,
    dans laquelle les deux couronnes d'aubes mobiles concernées sont prévues sur deux éléments (25) de base du rotor voisins directement axialement.
  13. Turbomachine suivant la revendication 11 ou 12, constituée sous la forme d'une turbine.
  14. Turbomachine suivant la revendication 11 ou 12, constituée sous la forme d'un compresseur axial.
  15. Turbine à gaz fixe ayant un compresseur axial suivant la revendication 14.
  16. Procédé de fabrication d'un rotor (21) pour une turbomachine suivant l'une des revendications 1 à 10,
    dans lequel le rotor comprend plusieurs éléments (25) rotoriques de base et dans lequel, avant de mettre l'un contre l'autre les éléments (25) rotoriques de base voisins directement, on monte entre eux la bague (46) de contour d'écoulement.
EP13197194.7A 2013-12-13 2013-12-13 Rotor pour une turbomachine avec bague d'écoulement fermée profilée et son procédé de fabrication Not-in-force EP2884052B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13197194.7A EP2884052B1 (fr) 2013-12-13 2013-12-13 Rotor pour une turbomachine avec bague d'écoulement fermée profilée et son procédé de fabrication

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13197194.7A EP2884052B1 (fr) 2013-12-13 2013-12-13 Rotor pour une turbomachine avec bague d'écoulement fermée profilée et son procédé de fabrication

Publications (2)

Publication Number Publication Date
EP2884052A1 EP2884052A1 (fr) 2015-06-17
EP2884052B1 true EP2884052B1 (fr) 2018-02-21

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EP13197194.7A Not-in-force EP2884052B1 (fr) 2013-12-13 2013-12-13 Rotor pour une turbomachine avec bague d'écoulement fermée profilée et son procédé de fabrication

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DE102020200073A1 (de) 2020-01-07 2021-07-08 Siemens Aktiengesellschaft Leitschaufelkranz

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US2683583A (en) * 1948-09-01 1954-07-13 Chrysler Corp Blade attachment
DE1074594B (de) * 1961-02-23 1960-02-04 D Napier &. Son Limited, London Befestigung hohler tragflugelprofilierter Axialturbmen oder Axialverdichter Schaufeln
GB1428365A (en) * 1972-03-15 1976-03-17 Rolls Royce Fluid flow machines
GB2293628B (en) * 1994-09-27 1998-04-01 Europ Gas Turbines Ltd Turbines
FR2973847B1 (fr) * 2011-04-11 2015-10-30 Pellenc Sa Helice de generateur de flux d'air pulse, en particulier pour souffleur portatif.

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