EP2723991B1 - Blade arrangement - Google Patents

Blade arrangement Download PDF

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Publication number
EP2723991B1
EP2723991B1 EP12748427.7A EP12748427A EP2723991B1 EP 2723991 B1 EP2723991 B1 EP 2723991B1 EP 12748427 A EP12748427 A EP 12748427A EP 2723991 B1 EP2723991 B1 EP 2723991B1
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EP
European Patent Office
Prior art keywords
blade
bead
groove
arrangement
blade arrangement
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.)
Active
Application number
EP12748427.7A
Other languages
German (de)
French (fr)
Other versions
EP2723991A1 (en
Inventor
Uwe Sieber
Sascha Dungs
Elliot Griffin
Markus Paus
Stefan Reichling
Hubertus Michael Wigger
Dirk Wistuba
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
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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 EP12748427.7A priority Critical patent/EP2723991B1/en
Publication of EP2723991A1 publication Critical patent/EP2723991A1/en
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Publication of EP2723991B1 publication Critical patent/EP2723991B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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

Definitions

  • the invention relates to a blade arrangement according to the preamble of claim 1.
  • Such blade arrangements are well known from the extensive existing state of the art, see for example the patent application DE 1 085 643 , The known blade arrangements are used both for rows of blades and for blade rows of compressors, wherein in a blade carrier, a circumferential groove for receiving all the blades of the series is provided.
  • the attachment of the blades in the circumferential groove takes place with the aid of a hammer-shaped or dovetail-like positive connection by correspondingly designed blade roots engage behind projections protruding from the side walls of the retaining groove.
  • the object of the invention is therefore to provide a blade assembly in which a durable and reliable and secure fastening of the blades in the circumferential groove is ensured with simple assembly and disassembly.
  • each element is plate-shaped, has at least one bead arranged below the blade in the projection of the blade blade groove for pressing the blade in the groove and in the longitudinal direction of the retaining only partially covered by him pressed blade root.
  • this has a particularly suitable shape, which allows a locally resilient substructure and at another local point a rigid-looking substructure.
  • the element is particularly easy to manufacture and, on the other hand, it is particularly easy to assemble and disassemble. The stiffening effect is generated by a bead or several beads.
  • the inventive solution includes that in the holding between each two blades a one-piece or multi-piece spacer is inserted, which is pressed by the not covered by the blade root part of the element to the projections.
  • a one-piece or multi-piece spacer is inserted, which is pressed by the not covered by the blade root part of the element to the projections.
  • the elements have a longitudinal extent which is equal to the longitudinal extent of blade root and intermediate piece.
  • the assembly of the elements is offset with respect to spacers and blades, so that the element - viewed in the longitudinal direction of the retaining - extends completely under the blade root and each partially extends below the two, the blade root adjacent spacers.
  • each intermediate piece of two elements is pressed against the projections of the retaining groove.
  • the elements are designed such that the respective intermediate pieces are pressed against the projections with less force than the pressed by the respective element to the projections blade root.
  • different stiffnesses of the element can be used particularly advantageously for different requirements.
  • a lower spring force of the element is desirable and not needed, since in operation also do not attack high forces on the intermediate piece.
  • the blades clamped in the blade carrier are exposed to flow forces during operation. This requires a more reliable attachment of the blades to the blade carrier, which requires a larger contact force.
  • the higher contact pressure is achieved by the locally higher rigidity of the element. This will be caused by the bead (s) arranged in the element.
  • the local material plasticization of the bead is provided to compensate for manufacturing tolerances during assembly.
  • a use of the residual elasticity is provided to then absorb the operating forces.
  • a material is advantageously used for the element, which is characterized by a relatively high ratio of the index for maximum tensile strength (Rmax) to the yield strength (RP0.2) (Index Rmax / Rp0.2> 1.5), whereby with material choice the yield strength at the same time still sufficiently large enough for the operating force must be.
  • a third bead geometry as a combination of the first two bead geometries with similar properties leads to a double bead called a double bead, which has a further enlarged elastic range.
  • the beads are located in the element so that they are arranged in the projection of the blade leaf groove bottom direction below the blade.
  • the beads are arranged in principle in the interior of the element or at its edge. This allows easy assembly and disassembly of the elements.
  • the element has at least one opening in its area not covered by the blade root. In this opening can engage a disassembly hook or tool to disassemble it from its operating position.
  • a simple mountability of the element can be achieved if a groove extending along the retaining groove is located as a disassembly groove in the groove bottom of the retaining groove or in the blade root underside.
  • a slide hammer can be comparatively easily attached there and during assembly, the insertion / compression of the element between the blade and the groove is simplified by means of a plunger.
  • the element expediently has an outer contour in the projection of the blade leaf in the direction of the groove bottom (radial viewing axis), which is substantially rectangular. In this projection, the element in question is only half covered by the blade pressed by it.
  • Such contoured elements are particularly inexpensive and easy to produce.
  • At least one longitudinal edge of the element is angled, which bears biased against the correspondingly shaped blade roots. If intermediate pieces are used in the blade arrangement, the angled longitudinal edges can also be prestressed against the correspondingly shaped intermediate pieces.
  • This embodiment makes it possible that the blades are not aligned solely on the basis of the groove geometry and the Schaufelfußgeometrie, but also on the basis of the respective neighboring component - blade or spacer - align. This feature serves to advantageously reduce contact wear.
  • the element on at least one edge at least one further bead for local reinforcement and for guiding the element in a guide groove.
  • This further bead on the edge, preferably the transverse edge can simplify the assembly, because at the local stiffening a plunger for driving / pushing the element between the blade root underside and groove base can be applied without the element during subsequent driving, the element bends locally.
  • the bead is designed as an inner bead, which is located in an at least partially surrounding, outer bead.
  • This embodiment also referred to as a double bead, allows a further enlargement of the elastic region of the element.
  • the use of 3-fold beads or even n-fold beads is conceivable in which a corresponding number of beads from the inside to the outside is virtually stacked or arranged hierarchically.
  • the blade assembly is used in an axially flow-through compressor of a gas turbine, either for a blade ring and / or for a vane ring.
  • a gas turbine either for a blade ring and / or for a vane ring.
  • FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section.
  • the gas turbine 10 has inside a by one Rotation axis 12 rotatably mounted rotor 14, which is also referred to as a turbine runner.
  • rotor 14 Along the rotor 14 follow one another an intake housing 16, an axial turbocharger 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetrically arranged burners 22, a turbine unit 24 and an exhaust housing 26.
  • the Axialturbover Noticer 18 includes a ring-shaped compressor duct with cascading successively compressor stages of blade and Leitschaufelkränzen.
  • the rotor blades 14 arranged on the blades 27 lie with their free-ending blade tips 29 of an outer channel wall 42 of the compressor passage opposite. Also protrude vanes 25 which are secured to the outer duct wall 42 or to a Ver Whyrleitschaufelani.
  • the compressor duct discharges via a compressor outlet diffuser 36 in a plenum 38.
  • the annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas duct 30 of the turbine unit 24. In the turbine unit 24 four successive turbine stages 32 are arranged.
  • a generator or a working machine (each not shown) is coupled.
  • the axial turbocharger 18 draws in ambient air 34 through the intake housing 16 as a medium to be compressed and compresses it.
  • the compressed air is guided through the compressor outlet diffuser 36 into the plenum 38, from where it flows into the burner 22.
  • Fuel also passes into the combustion space 28 via the burners 22.
  • the fuel is burned to a hot gas M with the addition of the compressed air.
  • the hot gas M then flows into the hot gas duct 30, where it relaxes to perform work on the turbine blades of the turbine unit 24.
  • the energy released during this time is absorbed by the rotor 14 and used on the one hand to drive the axial turbocharger 18 and on the other hand to drive a working machine or electric generator.
  • FIG. 2 shows a plan view of a portion of a blade assembly 40, in which only two blades 25, 27 are schematically illustrated with an intermediate piece 44 located therebetween and two elements 46 disposed thereunder.
  • the blades 25, 27 comprise a schematically indicated blade 48 as well as a blade root 50.
  • the plan view takes place in the direction of the radial direction of the gas turbine 10, ie from the blade towards the blade root 50 FIG. 2 not shown is the blade carrier and a holding groove arranged in the carrier.
  • the elements 46 have a rectangular outer contour and are plate-shaped. Colloquially, they are also referred to as sheet-shaped.
  • the blade roots 50 and the blades 25, 27 of the blade assembly with respect to a longitudinal extent of the retaining groove or a circumferential direction U arranged obliquely. This employment is typical for blades.
  • Each element 46 has two beads 52 and two openings 54, respectively.
  • the elements 46 are in the circumferential direction U as long as the blade root 50 and spacer 44 together. However, the elements 46 are arranged centrally below the respective blade 25, 27, so that two adjacent elements 46 each end centrally with their opposite ends below the intermediate pieces 44.
  • FIG. 3 shows the cross section along section line III-III through the blade root 50 of the blade 25, 27 and a blade carrier 56.
  • the blade is in FIG. 3 (and also in the FIGS. 5, 6 . 8, 9 . 11 and 12 ) not shown.
  • a retaining groove 58 extends, in which the blades 25, 27, in detail the blade roots 50 of the blades 25, 27, are inserted in a form-fitting manner.
  • the side walls 60 of the retaining grooves 58 have longitudinally extending projections 62 for forming undercuts 64.
  • hammer-shaped foot regions 66 engage in the undercut 64.
  • the element 46 is braced.
  • a further, along the retaining groove 58 extending disassembly groove 72 is provided in the groove bottom 70.
  • the further groove 72 serves for the access of a disassembly tool, for example a slide hammer.
  • the wall thickness S of the element 46 ( FIG. 14 ) is less than the gap between the blade root bottom 68 and groove bottom 70.
  • the beads 52 produced in the element 46 by deep drawing or by pressing increase the height H of the element 46 beyond the gap, so that the blade root 50 is pressed against the projections 62. This leads to a clearly defined position of the blades 25, 27 in the retaining groove 58.
  • FIG. 4 shows the longitudinal section through the embodiment according to FIG. 2 along the section line IV-IV.
  • the blade assembly 40 is a section of a blade ring of a compressor 12 of the gas turbine 10. Accordingly, the blade carrier 56 is formed by a rotor disk and the blades 25, 27 formed as blades.
  • the elements 46 are substantially planar and thus do not follow the curvature of the retaining groove 58. As a result, the elements 46 press with their central region in which the beads 52 are arranged with greater force blade root lower side 68 and groove bottom 70 apart. The adjacent to the transverse edges 82 portions of the element 46 are due to the planar configuration of the elements 46 and the curved retaining groove 58 then with less force resiliently against the undersides of the intermediate pieces 44. Consequently, the element 46 presses the intermediate pieces 44 and the blades 25, 27 against the projections 62 of the retaining groove 58 due to locally different stiffnesses with forces of different magnitude.
  • FIG. 5 shows essentially the cross section according to FIG. 3 , Here are in FIG. 5 to FIG. 3 identical features provided with the identical reference numerals. To the description of FIG. 5 is largely based on the description of the FIG. 3 directed. According to the second embodiment, however, the longitudinal edges 74 of the element 46 are bent to the groove opening of the retaining groove 58 out. The bent longitudinal edges 74 (see. FIG. 2 ) are preloaded on blade bottom 76 disposed chamfered on. Since the intermediate pieces 44 are formed in a manner analogous to the blade roots 50 of the blades 25, 27, the regions of the longitudinal edges 74 of the element 46 located below the intermediate piece 44 are biased against corresponding chamfers.
  • FIG. 6 A third embodiment of a blade arrangement 40 is shown in FIG FIG. 6 shown schematically. Also FIG. 6 shows largely the same cross-section as FIG. 3 , so in FIG. 6 to FIG. 3 identical features are provided with the same reference numerals.
  • the third embodiment according to FIG. 6 at the blade root lower side 68 a comparatively wide, but provided only with a small depth, in the longitudinal direction of the retaining groove 58 extending groove 78.
  • the groove 78 serves to receive the element 46, so that the groove depth of the groove 78 substantially corresponds to the wall thickness S of the element 46.
  • the longitudinal edges 74 of the element 46 (see. FIG. 2 ) abut against the inclined side walls of the groove 78.
  • a groove 78 arranged on the underside thereof is also provided in the intermediate pieces 44 according to the third embodiment, so that the longitudinal edges 74 of the element 46 also on the side walls of the groove 44 arranged on the intermediate piece 78 are present.
  • FIGS. 8 and 9 show in an analogous manner to the cross section according to FIG. 3 a cross section through a blade assembly 40 according to a fourth embodiment.
  • the cross-sectional contours of the retaining groove 58 and the blade root 50 differ only slightly.
  • Another difference from the previously described embodiments is that no intermediate pieces 44 are provided between adjacent guide vanes 25. Accordingly, the blades 25 lie as shown in the illustration FIG. 7 shown flat and without employment of the blade roots 50 together.
  • the elements 46 are each arranged in half below a pair of adjacent blades 25.
  • stiffening beads 52 are not located in the interior of the element 46, but at two opposite transverse edges 82 of the elements 46.
  • the first variant of the fourth embodiment according to FIG. 8 constructed in an analogous manner as the second embodiment according to FIG. 5 with the angled longitudinal edges 74 of the element 46.
  • a second variant of the fourth embodiment, shown in FIG. 9 structurally corresponds essentially to the third embodiment FIG. 6 in which the element 46 is largely sunk in a groove 78 disposed on the blade root lower side 68.
  • a fifth embodiment of the blade assembly 40 is in a plan view according to FIG. 10 shown, to the two variants, a first in cross section in FIG. 11 and a second in the Cross section in FIG. 12 are shown.
  • the fifth embodiment shown is essentially based on the FIG. 2 illustrated first embodiment.
  • further beads 86 are provided at the transverse edges 82 - in a manner analogous to that in FIGS FIG. 7 shown fourth embodiment - provided.
  • the further beads 86 either engage in the dismantling groove 72 (FIG. FIG. 11 ) or in a blade bottom side groove 78 ( FIG. 12 ) for aligning or guiding the elements 46.
  • FIGS. 14 and 15 each show an embodiment of the element 46 in cross section according to the section line III-III FIG. 2 , Unlike the in FIG. 2 shown element 46 are in the FIGS. 14, 15 only one bead 52 and not two beads 52 shown.
  • Each bead 52 includes two convexly bent portions X and a concave portion V interposed therebetween.
  • the convex portions X each have a radius R2 and the concave portions V have a radius R1.
  • the concave portion V also has a chord length a, wherein the bead 52 includes a bead width b.
  • the first embodiment is achieved when R1> 1.5 * S, 3 * R2>R1> 0.7 * R2 and 10 * b to 1.7 * b> a.
  • portion V represents the area of plastic deformation with the higher loading force and higher spring rate and the portions X the areas for the elastic deformation with low spring rate, which also FIG. 13 represents.
  • the invention relates to a blade assembly 40 having a blade carrier 56 and a retaining groove 58 disposed therein, which has on its side walls 60 longitudinally extending projections 62 for forming undercuts 64, and in which a number of blades 25, 27 for forming a blade ring one Turbomachine used is, wherein each blade 25, 27 next to a blade 48 for fastening a hammer-shaped, engaging in the undercuts 64 blade root 50 and is pressed by between a blade root bottom 68 and a groove bottom 70 of the retaining groove 58 disposed element 46 to the projections 62.
  • each element 46 is plate-shaped, in the projection of the airfoil 48 towards the groove bottom 70 at least one below the airfoil 48 arranged bead 52 has for pressing and in the longitudinal direction of the retaining groove 58 is only partially covered by the pressed him blade root 50.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft eine Schaufelanordnung gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a blade arrangement according to the preamble of claim 1.

Derartige Schaufelanordnungen sind aus dem umfangreich vorhandenen Stand der Technik bestens bekannt, siehe zum Beispiel die Auslegeschrift DE 1 085 643 . Die bekannten Schaufelanordnungen werden sowohl für Leitschaufelreihen als auch für Laufschaufelreihen von Verdichtern eingesetzt, wobei in einem Schaufelträger eine Umfangsnut zur Aufnahme aller Schaufeln der Reihe vorgesehen ist. Die Befestigung der Schaufeln in der Umfangsnut erfolgt mit Hilfe eines hammerförmigen oder schwalbenschwanzähnlichen Formschlusses, indem entsprechend ausgebildete Schaufelfüße von den Seitenwänden der Haltenut hervorstehende Vorsprünge hintergreifen. Um eine spielfreie, verschleißarme und zuverlässige Verspannung der Schaufeln in der Haltenut herbeizuführen ist es bekannt, zwischen Schaufelfußunterseite und Nutgrund Unterbauungen in Gestalt von Passfedern, Federelementen in Form einer Spiral-feder oder einer längs wie quer geschlitzten Spannhülse einzusetzen. Damit lassen sich in radialer Richtung vorhandene Montage- und Fertigungsspiele zwischen Schaufel und Nut kompensieren, was eine einfache Herstellung und Montage ermöglicht. Problematisch ist, dass die Spiele in radialer Richtung zu Schwierigkeiten bei der Gewährleistung der Toleranzen in Nutumfangsrichtung führen können. Daher ist es bekannt, dass zur Einstellung der Radialspalte zwischen Schaufelblattspitze und einer dieser unmittelbar gegenüberliegenden Kanalbegrenzung die Profilenden überschliffen oder durch Drehen auf Maß gebracht werden, wobei währenddessen die in der Nut montierten Schaufeln nach außen gedrückt sind. Abgesehen davon besteht häufig das Problem, eine einfache Montierbarkeit und Demontierbarkeit von Schaufeln und den Unterbauungen bei geringen Herstellungskosten zu erreichen.Such blade arrangements are well known from the extensive existing state of the art, see for example the patent application DE 1 085 643 , The known blade arrangements are used both for rows of blades and for blade rows of compressors, wherein in a blade carrier, a circumferential groove for receiving all the blades of the series is provided. The attachment of the blades in the circumferential groove takes place with the aid of a hammer-shaped or dovetail-like positive connection by correspondingly designed blade roots engage behind projections protruding from the side walls of the retaining groove. In order to bring about a backlash-free, low-wear and reliable clamping of the blades in the retaining groove, it is known to use subfloors in the form of feather keys, spring elements in the form of a spiral spring or a longitudinally and transversely slotted clamping sleeve between the underside of the blade root and groove base. This can be in the radial direction existing assembly and manufacturing games compensate between the blade and groove, which allows easy production and assembly. The problem is that the games in the radial direction can lead to difficulties in ensuring the tolerances in Nutumfangsrichtung. Therefore, it is known that for adjustment of the radial gap between the blade tip and one of these immediately opposite channel boundary, the profile ends are ground or made by turning to measure, during which the blades mounted in the groove are pressed outwards. Apart from that, there is often the problem to achieve a simple assembly and disassembly of blades and the substructures with low production costs.

Aufgabe der Erfindung ist daher die Bereitstellung einer Schaufelanordnung, bei der eine langlebige und zugleich zuverlässige sowie sichere Befestigung der Schaufeln in der Umfangsnut bei einfacher Montage und Demontage gewährleistet ist.The object of the invention is therefore to provide a blade assembly in which a durable and reliable and secure fastening of the blades in the circumferential groove is ensured with simple assembly and disassembly.

Die Aufgabe wird mit einer Schaufelanordnung gemäß den Merkmalen des Anspruchs 1 gelöst. Vorteilhafte Ausgestaltungen der Erfindung sind in den Unteransprüchen angegeben, die in beliebiger Weise miteinander kombiniert werden können.The object is achieved with a blade arrangement according to the features of claim 1. Advantageous embodiments of the invention are specified in the subclaims, which can be combined with one another in any desired manner.

Erfindungsgemäß ist vorgesehen, dass jedes Element plattenförmig ausgebildet ist, in der Projektion von Schaufelblatt Richtung Nutgrund zumindest eine unterhalb des Schaufelblatts angeordnete Sicke zum Anpressen der Schaufel in der Nut aufweist und in Längsrichtung der Haltenut lediglich teilweise des vom ihm angepressten Schaufelfußes überdeckt ist. Mit Hilfe des erfindungsgemäßen Elements ist es möglich, das dieses eine besonders geeignete Form aufweist, die eine lokal federnde Unterbauung und an einer anderen lokalen Stelle eine steif wirkende Unterbauung ermöglicht. Das Element lässt sich zudem einerseits besonders einfach herstellen und andererseits zugleich besonders einfach montieren und demontieren. Die versteifende Wirkung wird durch eine Sicke oder mehrere Sicken erzeugt. Die einfache Montierbarkeit und Demontierbarkeit wird dadurch erreicht, dass in Längsrichtung der Haltenut das betreffende Element lediglich teilweise durch den von ihm angepressten Schaufelfuß überdeckt ist. Somit steht stets ein Abschnitt des Elements hervor, welches für ein Demontagewerkzeug besonders einfach erreichbar ist. Des Weiteren ermöglicht die plattenförmige Geometrie des Elements eine platzsparende Konstruktion und Schaufelanordnung.According to the invention, it is provided that each element is plate-shaped, has at least one bead arranged below the blade in the projection of the blade blade groove for pressing the blade in the groove and in the longitudinal direction of the retaining only partially covered by him pressed blade root. With the aid of the element according to the invention, it is possible that this has a particularly suitable shape, which allows a locally resilient substructure and at another local point a rigid-looking substructure. On the one hand, the element is particularly easy to manufacture and, on the other hand, it is particularly easy to assemble and disassemble. The stiffening effect is generated by a bead or several beads. The ease of assembly and disassembly is achieved in that in the longitudinal direction of the retaining the element in question is only partially covered by the pressed by him blade root. Thus, always a section of the element stands out, which is particularly easy to reach for a disassembly tool. Furthermore, the plate-shaped geometry of the element allows a space-saving design and blade arrangement.

Weiterhin beinhaltet die erfindungsgemässe Lösung, dass in der Haltenut zwischen je zwei Schaufeln ein einteiliges oder mehrteiliges Zwischenstück eingesetzt ist, das von dem durch den Schaufelfuß nicht überdeckten Teil des Elements an die Vorsprünge angepresst ist. In diesem Fall existieren in identischer Anzahl Schaufeln, Zwischenstücke und Elemente, wobei die Elemente eine Längserstreckung aufweisen, die gleich der Längserstreckung von Schaufelfuß und Zwischenstück ist. Die Montage der Elemente erfolgt in Bezug auf Zwischenstücke und Schaufeln versetzt, so dass das Element - in Längsrichtung der Haltenut gesehen - sich vollständig unter dem Schaufelfuß hindurch und jeweils teilweise sich bis unter die beiden, den Schaufelfuß benachbarten Zwischenstücken erstreckt. Damit wird jedes Zwischenstück von zwei Elementen an die Vorsprünge der Haltenut gepresst.Furthermore, the inventive solution includes that in the holding between each two blades a one-piece or multi-piece spacer is inserted, which is pressed by the not covered by the blade root part of the element to the projections. In this case exist in identical Number of blades, intermediate pieces and elements, wherein the elements have a longitudinal extent which is equal to the longitudinal extent of blade root and intermediate piece. The assembly of the elements is offset with respect to spacers and blades, so that the element - viewed in the longitudinal direction of the retaining - extends completely under the blade root and each partially extends below the two, the blade root adjacent spacers. Thus, each intermediate piece of two elements is pressed against the projections of the retaining groove.

Vorzugsweise sind die Elemente derartig ausgebildet, dass die betreffenden Zwischenstücke mit geringerer Kraft an die Vorsprünge angepresst werden als der von dem betreffenden Element an die Vorsprünge angepresste Schaufelfuß. Insbesondere damit lassen sich verschiedene Steifigkeiten des Elements für verschiedene Anforderungen besonders vorteilhaft nutzen. Für die Montage der Zwischenstücke ist nämlich eine niedrigere Federkraft des Elements wünschenswert und auch nicht benötigt, da im Betrieb auch keine hohen Kräfte an dem Zwischenstück angreifen. Dahingegen sind die im Schaufelträger festgeklemmten Schaufeln im Betrieb Strömungskräften ausgesetzt. Dies erfordert eine zuverlässigere Befestigung der Schaufeln am Schaufelträger, was eine größere Anpresskraft erforderlich macht. Die höhere Anpresskraft wird durch die lokal höhere Steifigkeit des Elements erreicht. Diese wird durch die im Element angeordnete(n) Sicke(n) hervorrufen.Preferably, the elements are designed such that the respective intermediate pieces are pressed against the projections with less force than the pressed by the respective element to the projections blade root. In particular, different stiffnesses of the element can be used particularly advantageously for different requirements. For the assembly of the intermediate pieces namely a lower spring force of the element is desirable and not needed, since in operation also do not attack high forces on the intermediate piece. In contrast, the blades clamped in the blade carrier are exposed to flow forces during operation. This requires a more reliable attachment of the blades to the blade carrier, which requires a larger contact force. The higher contact pressure is achieved by the locally higher rigidity of the element. This will be caused by the bead (s) arranged in the element.

Bei einer steiferen Unterbauung der Schaufel können vorteilhaft unterschiedlich wirkende Funktionsprinzipien für Montage und den anschließenden Betrieb verwendet werden. Zum einen ist die lokale Material-Plastifizierung der Sicke zum Ausgleich von Fertigungstoleranzen bei der Montage vorgesehen. Zum anderen ist eine Nutzung der Rest-Elastizität vorgesehen, um dann die Betriebskräfte aufzunehmen. Hierzu wird vorteilhaft ein Material für das Element benutzt, welches sich durch eine relativ hohe Verhältniszahl der Kennziffer für maximale Zugfestigkeit (Rmax) zur Streckgrenze (RP0.2) auszeichnet (Kennziffer Rmax/Rp0.2 > 1,5), wobei bei Materialwahl die Streckgrenze gleichzeitig noch ausreichend groß genug für die Betriebskraft sein muss.In the case of a stiffer substructure of the blade, it is advantageously possible to use differently acting functional principles for assembly and subsequent operation. On the one hand, the local material plasticization of the bead is provided to compensate for manufacturing tolerances during assembly. On the other hand, a use of the residual elasticity is provided to then absorb the operating forces. For this purpose, a material is advantageously used for the element, which is characterized by a relatively high ratio of the index for maximum tensile strength (Rmax) to the yield strength (RP0.2) (Index Rmax / Rp0.2> 1.5), whereby with material choice the yield strength at the same time still sufficiently large enough for the operating force must be.

Der lokal steifere Bereich des Elements wird vorzugsweise als Sicke ausgeführt. Besonders vorteilhaft ist die Gestaltung der Sicke in einer Weise, bei der sich eine geknickte Kennlinie im Kraft-Weg-Zusammenhang ergibt. Dadurch wird über einen weiten Bereich eine Rest-Elastizität zur Aufnahme der Betriebskräfte sichergestellt. Dies kann mit einer ersten Sickengeometrie erreicht werden, bei der das Element eine Wandstärke S und die Sicke im Querschnitt eine Sickenbreite b sowie zwei konvexe Abschnitte mit einem Radius R2 und einen dazwischen angeordneten konkaven Abschnitt mit einem Radius R1 mit einer Sehnenlänge A aufweist, für die gilt:

  • R1 > 1,5S,
  • 3*R2 > R1 < 0,7R2 und
  • 10b bis 1,7b > a.
The locally more rigid region of the element is preferably designed as a bead. Particularly advantageous is the design of the bead in a manner that results in a kinked curve in the force-displacement relationship. As a result, over a wide range, a residual elasticity to accommodate the operating forces is ensured. This can be achieved with a first bead geometry, in which the element has a wall thickness S and the bead has in cross section a bead width b and two convex sections with a radius R2 and a concave section with a radius R1 with a chord length A arranged therebetween applies:
  • R1> 1.5S,
  • 3 * R2> R1 <0.7R2 and
  • 10b to 1.7b> a.

Eine zweite Sickengeometrie mit ähnlichen Eigenschaften wird erreicht, wenn R1 > 5S ist, 3*R2 > R1 und a' < 0,9b.A second bead geometry with similar properties is achieved when R1> 5S, 3 * R2> R1 and a '<0.9b.

Eine dritte Sickengeometrie als Kombination der ersten beiden Sickengeometrien mit ähnlichen Eigenschaften führt zu einer als Doppelsicke bezeichneten 2-fach Sicke, welche einen weiter vergrößerten elastischen Bereich aufweist.A third bead geometry as a combination of the first two bead geometries with similar properties leads to a double bead called a double bead, which has a further enlarged elastic range.

Vorzugsweise sind die Sicken im Element derart angesiedelt, dass sie in der Projektion von Schaufelblatt Richtung Nutgrund unterhalb des Schaufelblatts angeordnet sind. Mit anderen Worten: da die Elemente entlang der Umfangsnut stets zu den Schaufeln versetzt angesiedelt sind, sind die Sicken prinzipiell im Innenbereich des Elements oder an dessen Rand angeordnet. Dies erlaubt eine einfache Montage und Demontage der Elemente.Preferably, the beads are located in the element so that they are arranged in the projection of the blade leaf groove bottom direction below the blade. In other words, since the elements are always offset along the circumferential groove to the blades, the beads are arranged in principle in the interior of the element or at its edge. This allows easy assembly and disassembly of the elements.

Weiter bevorzugt weist das Element in seinem nicht vom Schaufelfuß überdeckten Bereich zumindest eine Öffnung auf. In diese Öffnung kann ein Demontagehaken oder Werkzeug eingreifen, um es aus seiner Betriebsposition zu demontieren.More preferably, the element has at least one opening in its area not covered by the blade root. In this opening can engage a disassembly hook or tool to disassemble it from its operating position.

Eine einfache Montierbarkeit des Elements lässt sich erreichen, wenn im Nutgrund der Haltenut oder in der Schaufelfußunterseite eine sich längs der Haltenut erstreckende Nut als Demontagenut angesiedelt ist. Bei der Demontage kann dort vergleichsweise einfach ein Gleithammer angesetzt werden und bei der Montage ist das Hereinschlagen/-drücken des Elements zwischen Schaufel und Nut mittels eines Stößels vereinfacht.A simple mountability of the element can be achieved if a groove extending along the retaining groove is located as a disassembly groove in the groove bottom of the retaining groove or in the blade root underside. During disassembly, a slide hammer can be comparatively easily attached there and during assembly, the insertion / compression of the element between the blade and the groove is simplified by means of a plunger.

Zweckmäßigerweise weist das Element in der Projektion von Schaufelblatt Richtung Nutgrund (radiale Sichtachse) eine äußere Kontur auf, die im Wesentlichen rechteckig ist. In dieser Projektion ist das betreffende Element nur halb durch die von ihm angepresste Schaufel überdeckt. Derartig konturierte Elemente sind besonders kostengünstig und einfach herstellbar.The element expediently has an outer contour in the projection of the blade leaf in the direction of the groove bottom (radial viewing axis), which is substantially rectangular. In this projection, the element in question is only half covered by the blade pressed by it. Such contoured elements are particularly inexpensive and easy to produce.

Besonders vorteilhaft ist die Ausgestaltung, bei der zumindest eine Längskante des Elements abgewinkelt ist, die an den dazu korrespondierend ausgeformten Schaufelfüßen vorgespannt anliegt. Sofern Zwischenstücke in der Schaufelanordnung verwendet werden, können die abgewinkelten Längskanten auch an den dazu korrespondierend ausgeformten Zwischenstücken vorgespannt anliegen. Diese Ausgestaltung ermöglicht, dass die Schaufeln nicht allein aufgrund der Nutgeometrie und der Schaufelfußgeometrie ausgerichtet werden, sondern sich auch anhand des jeweiligen Nachbarbauteils - Schaufel oder Zwischenstück - ausrichten. Dieses Merkmal dient der vorteilhaften Verringerung von Kontaktverschleiß.Particularly advantageous is the embodiment in which at least one longitudinal edge of the element is angled, which bears biased against the correspondingly shaped blade roots. If intermediate pieces are used in the blade arrangement, the angled longitudinal edges can also be prestressed against the correspondingly shaped intermediate pieces. This embodiment makes it possible that the blades are not aligned solely on the basis of the groove geometry and the Schaufelfußgeometrie, but also on the basis of the respective neighboring component - blade or spacer - align. This feature serves to advantageously reduce contact wear.

Weiter vorteilhaft weist das Element an mindestens einem Rand zumindest eine weitere Sicke zur lokalen Versteifung und zur Führung des Elements in einer Führungsnut auf. Diese weitere Sicke am Rand, vorzugsweise der Querkante, kann die Montage vereinfachen, da an der lokalen Versteifung ein Stößel zum Einschlagen/Einstoßen des Elements zwischen Schaufelfußunterseite und Nutgrund angesetzt werden kann, ohne dass beim anschließenden Eintreiben sich das Element örtlich verbiegt.Further advantageously, the element on at least one edge at least one further bead for local reinforcement and for guiding the element in a guide groove. This further bead on the edge, preferably the transverse edge, can simplify the assembly, because at the local stiffening a plunger for driving / pushing the element between the blade root underside and groove base can be applied without the element during subsequent driving, the element bends locally.

Besonders bevorzugt ist die Ausführungsform, bei der die Sicke als innere Sicke ausgestaltet ist, die in einer diese zumindest teilweise umgebenden, äußeren Sicke angesiedelt ist. Diese auch als Doppelsicke bezeichnete Ausführungsform ermöglicht eine weitere Vergrößerung des elastischen Bereichs des Elements. Ebenso ist die Verwendung von 3-fach-Sicken oder gar n-fach Sicken denkbar, bei denen eine entsprechende Anzahl an Sicken von innen nach außen quasi gestapelt bzw. hierarchisch angeordnet ist.Particularly preferred is the embodiment in which the bead is designed as an inner bead, which is located in an at least partially surrounding, outer bead. This embodiment, also referred to as a double bead, allows a further enlargement of the elastic region of the element. Likewise, the use of 3-fold beads or even n-fold beads is conceivable in which a corresponding number of beads from the inside to the outside is virtually stacked or arranged hierarchically.

Besonders bevorzugt ist die Ausgestaltung, bei der die Schaufelanordnung in einem axial durchströmbaren Verdichter einer Gasturbine verwendet wird, entweder für einen Laufschaufelkranz und/oder für einen Leitschaufelkranz. Dies gewährleistet einen zuverlässigen, sicheren und besonders effizienten Betrieb der Gasturbine, da mit dieser Ausgestaltung die Radialspalte zwischen den Schaufelblattspitzen und der gegenüberliegenden Kanalwand des Strömungskanals des Verdichters besonders klein ausgebildet werden können.Particularly preferred is the embodiment in which the blade assembly is used in an axially flow-through compressor of a gas turbine, either for a blade ring and / or for a vane ring. This ensures a reliable, safe and particularly efficient operation of the gas turbine, since with this embodiment, the radial gaps between the blade tips and the opposite channel wall of the flow channel of the compressor can be made particularly small.

Die Erfindung wird anhand mehrerer Ausführungsbeispiele, welche die Erfindung nicht einschränken, in der nachfolgenden Figurenbeschreibung näher erläutert. Dabei werden weitere Merkmale und weitere Vorteile angegeben. Es zeigen:

FIG 1
einen Längsteilschnitt durch eine Gasturbine,
FIG 2
die Draufsicht auf einen Ausschnitt einer Schaufelanordnung gemäß einer ersten Ausgestaltung,
FIG 3
einen Querschnitt durch die Schaufelanordnung gemäß FIG 2 gemäß Schnittlinie III-III,
FIG 4
den Längsschnitt durch den Ausschnitt der Schaufelanordnung gemäß FIG 2 gemäß Schnittlinie IV-IV,
FIG 5, FIG 6
die Querschnitte durch eine Schaufelanordnung analog zur Schnittlinie IV-IV für eine zweite und dritte Ausgestaltung,
FIG 7
eine Draufsicht auf einen Abschnitt einer Schaufelanordnung gemäß einer vierten Ausgestaltung (ohne Zwischenstücke),
FIG 8, FIG 9
zwei Varianten der vierten Ausgestaltung gemäß FIG 7 im Querschnitt gemäß Schnittlinie III-III,
FIG 10
eine Draufsicht auf einen Abschnitt einer Schaufelanordnung gemäß einer fünften Ausgestaltung (ohne Zwischenstücke),
FIG 11, FIG 12
zwei Varianten der fünften Ausgestaltung gemäß FIG 7 im Querschnitt gemäß Schnittlinie III-III,
FIG 13
ein Kraft-Elastizitäts-Diagramm,
FIG 14, FIG
15 den Querschnitt durch ein Element mit unterschiedlichen Geometrien von Sicken und
FIG 16
den Querschnitt durch eine Sickengeometrie in Form einer Doppelsicke.
The invention will be explained in more detail in the following description of the figures with reference to several embodiments, which do not limit the invention. In this case, further features and other advantages are given. Show it:
FIG. 1
a partial longitudinal section through a gas turbine,
FIG. 2
the top view of a section of a blade assembly according to a first embodiment,
FIG. 3
a cross section through the blade assembly according to FIG. 2 according to section line III-III,
FIG. 4
the longitudinal section through the cutout of the blade assembly according to FIG. 2 according to section line IV-IV,
FIG. 5, FIG. 6
the cross sections through a blade arrangement analogous to the section line IV-IV for a second and third embodiment,
FIG. 7
a plan view of a portion of a blade assembly according to a fourth embodiment (without spacers),
8, FIG. 9
two variants of the fourth embodiment according to FIG. 7 in cross-section according to section line III-III,
FIG. 10
a plan view of a portion of a blade assembly according to a fifth embodiment (without spacers),
FIG. 11, FIG. 12
two variants of the fifth embodiment according to FIG. 7 in cross-section according to section line III-III,
FIG. 13
a force-elasticity diagram,
FIG. 14, FIG
15 shows the cross section through an element with different geometries of beads and
FIG. 16
the cross section through a bead geometry in the form of a double bead.

In den Figuren sind identische Merkmale mit den gleichen Bezugszeichen versehen.In the figures, identical features are provided with the same reference numerals.

Figur 1 zeigt eine stationäre Gasturbine 10 in einem Längsteilschnitt. Die Gasturbine 10 weist im Innern einen um eine Rotationsachse 12 drehgelagerten Rotor 14 auf, der auch als Turbinenläufer bezeichnet wird. Entlang des Rotors 14 folgen aufeinander ein Ansauggehäuse 16, ein Axialturboverdichter 18, eine torusartige Ringbrennkammer 20 mit mehreren rotationssymmetrisch zueinander angeordneten Brennern 22, eine Turbineneinheit 24 und ein Abgasgehäuse 26. FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section. The gas turbine 10 has inside a by one Rotation axis 12 rotatably mounted rotor 14, which is also referred to as a turbine runner. Along the rotor 14 follow one another an intake housing 16, an axial turbocharger 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetrically arranged burners 22, a turbine unit 24 and an exhaust housing 26.

Der Axialturboverdichter 18 umfasst einen ringförmig ausgebildeten Verdichterkanal mit darin kaskadisch aufeinanderfolgenden Verdichterstufen aus Laufschaufel- und Leitschaufelkränzen. Die am Rotor 14 angeordneten Laufschaufeln 27 liegen mit ihren frei endenden Schaufelblattspitzen 29 einer äußeren Kanalwand 42 des Verdichterkanals gegenüber. Darein ragen ebenso Leitschaufeln 25, die an der äußeren Kanalwand 42 oder an einem Verdichterleitschaufelträger gefestigt sind. Der Verdichterkanal mündet über einen Verdichterausgangsdiffusor 36 in einem Plenum 38. Darin ist die Ringbrennkammer 20 mit ihrem Verbrennungsraum 28 vorgesehen, der mit einem ringförmigen Heißgaskanal 30 der Turbineneinheit 24 kommuniziert. In der Turbineneinheit 24 sind vier hintereinander geschaltete Turbinenstufen 32 angeordnet. Am Rotor 14 ist ein Generator oder eine Arbeitsmaschine (jeweils nicht dargestellt) angekoppelt.The Axialturboverdichter 18 includes a ring-shaped compressor duct with cascading successively compressor stages of blade and Leitschaufelkränzen. The rotor blades 14 arranged on the blades 27 lie with their free-ending blade tips 29 of an outer channel wall 42 of the compressor passage opposite. Also protrude vanes 25 which are secured to the outer duct wall 42 or to a Verdichterleitschaufelträger. The compressor duct discharges via a compressor outlet diffuser 36 in a plenum 38. The annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas duct 30 of the turbine unit 24. In the turbine unit 24 four successive turbine stages 32 are arranged. On the rotor 14, a generator or a working machine (each not shown) is coupled.

Im Betrieb der Gasturbine 10 saugt der Axialturboverdichter 18 durch das Ansauggehäuse 16 als zu verdichtendes Medium Umgebungsluft 34 an und verdichtet diese. Die verdichtete Luft wird durch den Verdichterausgangsdiffusor 36 in das Plenum 38 geführt, von wo aus es in die Brenner 22 einströmt. Über die Brenner 22 gelangt auch Brennstoff in den Verbrennungsraum 28. Dort wird der Brennstoff unter Zugabe der verdichteten Luft zu einem Heißgas M verbrannt. Das Heißgas M strömt anschließend in den Heißgaskanal 30, wo es sich arbeitsleistend an den Turbinenschaufeln der Turbineneinheit 24 entspannt. Die währenddessen freigesetzte Energie wird vom Rotor 14 aufgenommen und einerseits zum Antrieb des Axialturboverdichters 18 und andererseits zum Antrieb einer Arbeitsmaschine oder elektrischen Generators genutzt.During operation of the gas turbine 10, the axial turbocharger 18 draws in ambient air 34 through the intake housing 16 as a medium to be compressed and compresses it. The compressed air is guided through the compressor outlet diffuser 36 into the plenum 38, from where it flows into the burner 22. Fuel also passes into the combustion space 28 via the burners 22. There, the fuel is burned to a hot gas M with the addition of the compressed air. The hot gas M then flows into the hot gas duct 30, where it relaxes to perform work on the turbine blades of the turbine unit 24. The energy released during this time is absorbed by the rotor 14 and used on the one hand to drive the axial turbocharger 18 and on the other hand to drive a working machine or electric generator.

Die FIG 2 zeigt eine Draufsicht auf einen Ausschnitt einer Schaufelanordnung 40, bei der lediglich zwei Schaufeln 25, 27 mit einem dazwischen angesiedelten Zwischenstück 44 und zwei darunter angeordneten Elementen 46 schematisch dargstellt sind. Die Schaufeln 25, 27 umfassen ein schematisch angedeutetes Schaufelblatt 48 sowie einen Schaufelfuß 50. Die Draufsicht erfolgt in Richtung der Radialrichtung der Gasturbine 10, d. h. vom Schaufelblatt in Richtung Schäufelfuß 50. In FIG 2 nicht dargestellt ist der Schaufelträger sowie eine im Träger angeordnete Haltenut. Die Elemente 46 weisen eine rechteckige äußere Kontur auf und sind plattenförmig ausgebildet. Umgangssprachlich werden sie auch als blechförmig bezeichnet. Im ersten Ausführungsbeispiel (FIG 2) sind die Schaufelfüße 50 und die Schaufeln 25, 27 der Schaufelanordnung gegenüber einer Längserstreckung der Haltenut bzw. einer Umfangsrichtung U schräg angeordnet. Diese Anstellung ist für Laufschaufeln typisch.The FIG. 2 shows a plan view of a portion of a blade assembly 40, in which only two blades 25, 27 are schematically illustrated with an intermediate piece 44 located therebetween and two elements 46 disposed thereunder. The blades 25, 27 comprise a schematically indicated blade 48 as well as a blade root 50. The plan view takes place in the direction of the radial direction of the gas turbine 10, ie from the blade towards the blade root 50 FIG. 2 not shown is the blade carrier and a holding groove arranged in the carrier. The elements 46 have a rectangular outer contour and are plate-shaped. Colloquially, they are also referred to as sheet-shaped. In the first embodiment ( FIG. 2 ) are the blade roots 50 and the blades 25, 27 of the blade assembly with respect to a longitudinal extent of the retaining groove or a circumferential direction U arranged obliquely. This employment is typical for blades.

Jedes Element 46 weist zwei Sicken 52 und jeweils zwei Öffnungen 54 auf. Die Elemente 46 sind in Umfangsrichtung U ebenso lang wie Schaufelfuß 50 und Zwischenstück 44 zusammen. Jedoch sind die Elemente 46 mittig unterhalb der betreffenden Schaufel 25, 27 angeordnet, so dass zwei benachbarte Elemente 46 jeweils mit ihren gegenüberliegenden Enden unterhalb der Zwischenstücke 44 mittig enden.Each element 46 has two beads 52 and two openings 54, respectively. The elements 46 are in the circumferential direction U as long as the blade root 50 and spacer 44 together. However, the elements 46 are arranged centrally below the respective blade 25, 27, so that two adjacent elements 46 each end centrally with their opposite ends below the intermediate pieces 44.

FIG 3 zeigt den Querschnitt gemäß Schnittlinie III-III durch den Schaufelfuß 50 der Schaufel 25, 27 und einem Schaufelträger 56. Das Schaufelblatt ist in FIG 3 (und auch in den Figuren 5, 6, 8, 9, 11 und 12) nicht dargestellt. Im Schaufelträger 56 erstreckt sich eine Haltenut 58, in denen die Schaufeln 25, 27, im Detail die Schaufelfüße 50 der Schaufeln 25, 27, formschlüssig eingesetzt sind. Zur Bildung der Formschlüsse weisen die Seitenwände 60 der Haltenuten 58 sich längs erstreckende Vorsprünge 62 zur Bildung von Hinterschneidungen 64 auf. In die Hinterschneidung 64 greifen korrespondierend ausgeführte, hammerförmige Fußbereiche 66 ein. FIG. 3 shows the cross section along section line III-III through the blade root 50 of the blade 25, 27 and a blade carrier 56. The blade is in FIG. 3 (and also in the FIGS. 5, 6 . 8, 9 . 11 and 12 ) not shown. In the blade carrier 56, a retaining groove 58 extends, in which the blades 25, 27, in detail the blade roots 50 of the blades 25, 27, are inserted in a form-fitting manner. To form the form-fit, the side walls 60 of the retaining grooves 58 have longitudinally extending projections 62 for forming undercuts 64. Correspondingly executed, hammer-shaped foot regions 66 engage in the undercut 64.

Zwischen einer Schaufelfußunterseite 68 und einem Nutgrund 70 der Haltenut 58 ist das Element 46 verspannt. Zudem ist im Nutgrund 70 eine weitere, sich längs der Haltenut 58 erstreckende Demontagenut 72 vorgesehen. Die weitere Nut 72 dient für den Zugang eines Demontagewerkzeugs, beispielsweise eines Gleithammers.Between a blade root bottom 68 and a groove bottom 70 of the retaining groove 58, the element 46 is braced. In addition, a further, along the retaining groove 58 extending disassembly groove 72 is provided in the groove bottom 70. The further groove 72 serves for the access of a disassembly tool, for example a slide hammer.

Die Wandstärke S des Elements 46 (FIG 14) ist geringer als das Spaltmaß zwischen Schaufelfußunterseite 68 und Nutgrund 70. Die im Element 46 durch Tiefziehen oder durch Einpressen hergestellten Sicken 52 vergrößern die Höhe H des Elements 46 über das Spaltmaß hinaus, so dass der Schaufelfuß 50 an die Vorsprünge 62 angepresst wird. Dies führt zu einer eindeutigen definierten Lage der Schaufeln 25, 27 in der Haltenut 58.The wall thickness S of the element 46 ( FIG. 14 ) is less than the gap between the blade root bottom 68 and groove bottom 70. The beads 52 produced in the element 46 by deep drawing or by pressing increase the height H of the element 46 beyond the gap, so that the blade root 50 is pressed against the projections 62. This leads to a clearly defined position of the blades 25, 27 in the retaining groove 58.

FIG 4 zeigt den Längsschnitt durch die Ausgestaltung gemäß FIG 2 entlang der Schnittlinie IV-IV. Bei der in den Figuren 2, 3 und 4 dargestellten Ausführungsform der Schaufelanordnung 40 handelt es sich um einen Ausschnitt eines Laufschaufelkranzes eines Verdichters 12 der Gasturbine 10. Demnach ist der Schaufelträger 56 von einer Rotorscheibe gebildet und die Schaufeln 25, 27 als Laufschaufeln ausgebildet. FIG. 4 shows the longitudinal section through the embodiment according to FIG. 2 along the section line IV-IV. In the in the FIGS. 2, 3 and 4 illustrated embodiment of the blade assembly 40 is a section of a blade ring of a compressor 12 of the gas turbine 10. Accordingly, the blade carrier 56 is formed by a rotor disk and the blades 25, 27 formed as blades.

Die Elemente 46 sind im Wesentlichen eben und folgen somit nicht der Krümmung der Haltenut 58. Dadurch ergibt sich, dass die Elemente 46 mit ihren mittleren Bereich, in dem die Sicken 52 angeordnet sind, mit größerer Kraft Schaufelfußunterseite 68 und Nutgrund 70 auseinander pressen. Die an die Querkanten 82 angrenzenden Abschnitte des Elements 46 liegen aufgrund der ebenen Ausgestaltung der Elemente 46 und der gekrümmten Haltenut 58 dann mit geringerer Kraft federnd an den Unterseiten der Zwischenstücke 44 an. Folglich presst das Element 46 die Zwischenstücke 44 und die Schaufeln 25, 27 aufgrund lokal unterschiedlicher Steifigkeiten mit unterschiedlich großen Kräften an die Vorsprünge 62 der Haltenut 58 an.The elements 46 are substantially planar and thus do not follow the curvature of the retaining groove 58. As a result, the elements 46 press with their central region in which the beads 52 are arranged with greater force blade root lower side 68 and groove bottom 70 apart. The adjacent to the transverse edges 82 portions of the element 46 are due to the planar configuration of the elements 46 and the curved retaining groove 58 then with less force resiliently against the undersides of the intermediate pieces 44. Consequently, the element 46 presses the intermediate pieces 44 and the blades 25, 27 against the projections 62 of the retaining groove 58 due to locally different stiffnesses with forces of different magnitude.

Eine zweite Ausgestaltung einer Schaufelanordnung 40 ist in FIG 5 dargestellt. FIG 5 zeigt im Wesentlichen den Querschnitt gemäß FIG 3. Dabei sind in FIG 5 zu FIG 3 identische Merkmale mit den identischen Bezugszeichen versehen. Zur Beschreibung der FIG 5 wird weitestgehend auf die Beschreibung der FIG 3 verwiesen. Gemäß der zweiten Ausgestaltung sind jedoch die Längskanten 74 des Elements 46 zur Nutöffnung der Haltenut 58 hin umgebogen. Die umgebogenen Längskanten 74 (vgl. FIG 2) liegen an schaufelfußunterseitig angeordneten Fasen 76 vorgespannt an. Da die Zwischenstücke 44 in analoger Weise zu den Schaufelfüßen 50 der Schaufeln 25, 27 ausgebildet sind, liegen auch die unterhalb des Zwischenstücks 44 angesiedelte Bereiche der Längskanten 74 des Elements 46 vorgespannt an korrespondierenden Fasen an. Durch die umgebogenen Längskanten 74 des Elements 46 sowie der vorgespannten Anlage der Elemente 46 an den Schaufelfüßen 50 bzw. Zwischenstücken 44 wird eine kraftschlüssige Kopplung der benachbarten Bauteile - Schaufelfuß 50 und Zwischenstück 44 - hervorgerufen, die deren Ausrichtung verbessert und Kontaktverschleiß zwischen den Bauteilen verringert.A second embodiment of a blade arrangement 40 is shown in FIG FIG. 5 shown. FIG. 5 shows essentially the cross section according to FIG. 3 , Here are in FIG. 5 to FIG. 3 identical features provided with the identical reference numerals. To the description of FIG. 5 is largely based on the description of the FIG. 3 directed. According to the second embodiment, however, the longitudinal edges 74 of the element 46 are bent to the groove opening of the retaining groove 58 out. The bent longitudinal edges 74 (see. FIG. 2 ) are preloaded on blade bottom 76 disposed chamfered on. Since the intermediate pieces 44 are formed in a manner analogous to the blade roots 50 of the blades 25, 27, the regions of the longitudinal edges 74 of the element 46 located below the intermediate piece 44 are biased against corresponding chamfers. The bent longitudinal edges 74 of the element 46 and the biased contact of the elements 46 on the blade roots 50 and spacers 44, a frictional coupling of the adjacent components - blade root 50 and spacer 44 - caused, which improves their alignment and reduces contact wear between the components.

Eine dritte Ausgestaltung einer Schaufelanordnung 40 ist in FIG 6 schematisch dargestellt. Auch FIG 6 zeigt weitestgehend den gleichen Querschnitt wie FIG 3, so dass in FIG 6 zu FIG 3 identische Merkmale mit den gleichen Bezugszeichen versehen sind. Im Unterschied zu der Ausgestaltung gemäß FIG 3 weist die dritte Ausgestaltung gemäß FIG 6 an der Schaufelfußunterseite 68 eine vergleichsweise breite, jedoch nur mit einer geringen Tiefe versehene, sich in Längsrichtung der Haltenut 58 erstreckende Nut 78 auf. Die Nut 78 dient zur Aufnahme des Elements 46, so dass die Nuttiefe der Nut 78 im Wesentlichen der Wandstärke S des Elements 46 entspricht. Die Längskanten 74 des Elements 46 (vgl. FIG 2) liegen an den geneigten Seitenwänden der Nut 78 an. Im gleichen Maße wie beim Schaufelfuß 50 ist auch bei den Zwischenstücken 44 gemäß der dritten Ausgestaltung eine an deren Unterseite angeordnete Nut 78 vorgesehen, so dass die Längskanten 74 des Elements 46 auch an den Seitenwänden der am Zwischenstück 44 angeordneten Nut 78 anliegen. Durch die gleichzeitige Anlage der Elemente 46 an Schaufel 25, 27 und Zwischenstück 44 wird eine Kopplung der benachbarten Schaufelkranzbauteile herbeigeführt, was Verschleiß, insbesondere Kontaktverschleiß, reduziert. Sowohl bei der zweiten Ausgestaltung gemäß FIG 5 und der dritten Ausgestaltung gemäß FIG 6 der erfindungsgemäßen Schaufelanordnung 40 sind die Schaufeln als Laufschaufeln 27 ausgebildet.A third embodiment of a blade arrangement 40 is shown in FIG FIG. 6 shown schematically. Also FIG. 6 shows largely the same cross-section as FIG. 3 , so in FIG. 6 to FIG. 3 identical features are provided with the same reference numerals. In contrast to the embodiment according to FIG. 3 has the third embodiment according to FIG. 6 at the blade root lower side 68 a comparatively wide, but provided only with a small depth, in the longitudinal direction of the retaining groove 58 extending groove 78. The groove 78 serves to receive the element 46, so that the groove depth of the groove 78 substantially corresponds to the wall thickness S of the element 46. The longitudinal edges 74 of the element 46 (see. FIG. 2 ) abut against the inclined side walls of the groove 78. In the same extent as the blade root 50, a groove 78 arranged on the underside thereof is also provided in the intermediate pieces 44 according to the third embodiment, so that the longitudinal edges 74 of the element 46 also on the side walls of the groove 44 arranged on the intermediate piece 78 are present. By the simultaneous contact of the elements 46 on blade 25, 27 and intermediate piece 44, a coupling of the adjacent blade ring components is brought about, which reduces wear, in particular contact wear. Both in the second embodiment according to FIG. 5 and the third embodiment according to FIG. 6 In the case of the blade arrangement 40 according to the invention, the blades are designed as moving blades 27.

Die Figuren 8 und 9 zeigen in analoger Weise zum Querschnitt gemäß FIG 3 einen Querschnitt durch eine Schaufelanordnung 40 gemäß einer vierten Ausgestaltung. Im Gegensatz zu den vorgenannten Ausgestaltungen sind die in FIG 7, 8 und FIG 9 gezeigten Anordnungen als Leitschaufelkränze ausgestaltet und nicht als Laufschaufelkränze. Dadurch unterscheiden sich die Querschnittskonturen der Haltenut 58 sowie des Schaufelfußes 50 lediglich geringfügig. Ein weiterer Unterschied zu den bisher beschriebenen Ausgestaltungen liegt darin, dass zwischen benachbarten Leitschaufeln 25 keine Zwischenstücke 44 vorgesehen sind. Demnach liegen die Schaufeln 25, wie in der Darstellung nach FIG 7 gezeigt, flächig und ohne Anstellung der Schaufelfüße 50 aneinander. In diesem Fall sind die Elemente 46 jeweils hälftig unter einem Paar benachbarter Schaufeln 25 angeordnet. Daraus ergibt sich, dass die versteifenden Sicken 52 auch nicht in Innenbereich im Element 46 angesiedelt sind, sondern an zwei gegenüberliegenden Querkanten 82 der Elemente 46. Ansonsten ist die erste Variante der vierten Ausgestaltung gemäß FIG 8 in analoger Weise konstruiert wie die zweite Ausgestaltung gemäß FIG 5 mit den abgewinkelten Längskanten 74 des Elements 46. Eine zweite Variante der vierten Ausgestaltung, gezeigt in FIG 9, entspricht strukturell im Wesentlichen der dritten Ausgestaltung nach FIG 6, bei der das Element 46 in eine an der Schaufelfußunterseite 68 angeordnete Nut 78 größtenteils versenkt ist.The FIGS. 8 and 9 show in an analogous manner to the cross section according to FIG. 3 a cross section through a blade assembly 40 according to a fourth embodiment. In contrast to the aforementioned embodiments, the in FIGS. 7, 8 and 9 arrangements shown designed as vane rings and not as blade rings. As a result, the cross-sectional contours of the retaining groove 58 and the blade root 50 differ only slightly. Another difference from the previously described embodiments is that no intermediate pieces 44 are provided between adjacent guide vanes 25. Accordingly, the blades 25 lie as shown in the illustration FIG. 7 shown flat and without employment of the blade roots 50 together. In this case, the elements 46 are each arranged in half below a pair of adjacent blades 25. It follows that the stiffening beads 52 are not located in the interior of the element 46, but at two opposite transverse edges 82 of the elements 46. Otherwise, the first variant of the fourth embodiment according to FIG. 8 constructed in an analogous manner as the second embodiment according to FIG. 5 with the angled longitudinal edges 74 of the element 46. A second variant of the fourth embodiment, shown in FIG FIG. 9 , structurally corresponds essentially to the third embodiment FIG. 6 in which the element 46 is largely sunk in a groove 78 disposed on the blade root lower side 68.

Eine fünfte Ausgestaltung der Schaufelanordnung 40 ist in einer Draufsicht gemäß FIG 10 dargestellt, zu der zwei Varianten, eine erste im Querschnitt in FIG 11 und eine zweite im Querschnitt in FIG 12, gezeigt sind. Die in FIG 5 dargestellte fünfte Ausgestaltung basiert im Wesentlichen auf der in FIG 2 dargestellten ersten Ausgestaltung. Jedoch sind zusätzlich zu den im Innenbereich des Elements 46 angeordneten Sicken 52 an den Querkanten 82 weitere Sicken 86 - in analoger Weise zu der in FIG 7 gezeigten vierten Ausgestaltung - vorgesehen. Durch die Verwendung der weiteren Sicken 86 am Rand lässt sich beim Eintreiben des Elements 46 zwischen Schaufelfußunterseite 68 und Nutgrund 70 ein Verbiegen oder Ausknicken des Elements 46 sicher vermeiden. Zugleich greifen die weiteren Sicken 86 entweder in die Demontagenut 72 (FIG 11) oder in eine schaufelfußunterseitig angeordnete Nut 78 (FIG 12) zum Ausrichten oder Führen der Elemente 46 ein.A fifth embodiment of the blade assembly 40 is in a plan view according to FIG. 10 shown, to the two variants, a first in cross section in FIG. 11 and a second in the Cross section in FIG. 12 are shown. In the FIG. 5 The fifth embodiment shown is essentially based on the FIG. 2 illustrated first embodiment. However, in addition to the beads 52 arranged in the inner region of the element 46, further beads 86 are provided at the transverse edges 82 - in a manner analogous to that in FIGS FIG. 7 shown fourth embodiment - provided. By using the further beads 86 on the edge, bending or buckling of the element 46 can be reliably avoided when the element 46 is driven in between the blade footer bottom 68 and groove base 70. At the same time, the further beads 86 either engage in the dismantling groove 72 (FIG. FIG. 11 ) or in a blade bottom side groove 78 ( FIG. 12 ) for aligning or guiding the elements 46.

Die Figuren 14 und 15 zeigen jeweils eine Ausgestaltung des Elements 46 im Querschnitt gemäß der Schnittlinie III-III aus FIG 2. Im Gegensatz zu dem in FIG 2 dargestellten Element 46 sind in den Figuren 14, 15 lediglich eine Sicke 52 und nicht zwei Sicken 52 dargestellt. Jede Sicke 52 umfasst zwei konvex gebogene Abschnitte X und einen dazwischen angeordneten konkaven Abschnitt V. Die konvexen Abschnitte X weisen jeweils einen Radius R2 und die konkaven Abschnitte V einen Radius R1 auf. Der konkave Abschnitt V weist zudem eine Sehnenlänge a auf, wobei die Sicke 52 eine Sickenbreite b umfasst. Um die Sicke 52 selber mit einem Bereich einer plastischen Deformation für höhere Belastungskraft und höhere Federrate sowie für einen Bereich mit elastischer Deformation mit niedriger Federrate zu erhalten, werden zwei Ausführungsformen des Elements vorgeschlagen. Die erste Ausführungsform wird erreicht, wenn
R1 > 1,5*S, 3*R2 > R1 > 0,7*R2 und 10*b bis 1,7*b > a ist. Beispielhaft können die Parameter folgende Maße aufweisen: R1 = 2 mm; R2 = 2 mm; S = 1 mm; a = 3,5 mm und b = 10 mm.The FIGS. 14 and 15 each show an embodiment of the element 46 in cross section according to the section line III-III FIG. 2 , Unlike the in FIG. 2 shown element 46 are in the FIGS. 14, 15 only one bead 52 and not two beads 52 shown. Each bead 52 includes two convexly bent portions X and a concave portion V interposed therebetween. The convex portions X each have a radius R2 and the concave portions V have a radius R1. The concave portion V also has a chord length a, wherein the bead 52 includes a bead width b. In order to obtain the bead 52 itself with a range of plastic deformation for higher loading force and higher spring rate as well as for a range with elastic deformation with low spring rate, two embodiments of the element are proposed. The first embodiment is achieved when
R1> 1.5 * S, 3 * R2>R1> 0.7 * R2 and 10 * b to 1.7 * b> a. By way of example, the parameters may have the following dimensions: R1 = 2 mm; R2 = 2 mm; S = 1 mm; a = 3.5 mm and b = 10 mm.

Die zweite Ausgestaltung eines Elements 46 sieht vor, dass

  • R1 > 5*S,
  • 3*R2 < R1 und
  • a < 0,9*b ist.
The second embodiment of an element 46 provides that
  • R1> 5 * S,
  • 3 * R2 <R1 and
  • a <0.9 * b.

Beispielhaft können die Parameter folgende Maße aufweisen:

  • R1 = 20 mm; R2 = 2 mm; S = 1 mm; a = 6 mm und b = 10 mm.
By way of example, the parameters may have the following dimensions:
  • R1 = 20 mm; R2 = 2 mm; S = 1 mm; a = 6 mm and b = 10 mm.

Mit Hilfe der gezeigten Ausgestaltung ist es möglich, dass der Abschnitt V der Bereich der plastischen Deformation mit der höheren Belastungskraft und höheren Federrate darstellt und die Abschnitte X die Bereiche für die elastische Deformation mit niedriger Federrate, was auch FIG 13 darstellt.With the aid of the illustrated embodiment, it is possible for the portion V to represent the area of plastic deformation with the higher loading force and higher spring rate and the portions X the areas for the elastic deformation with low spring rate, which also FIG. 13 represents.

FIG 16 zeigt den Querschnitt durch eine spezielle Sickengeometrie. Bei der speziellen Sickengeometrie handelt es sich um eine Mehrfach-Sicke 55, bei der eine innere Sicke 55i von einer oder mehreren Sicken 55a umgeben sind. Die Sicken 55i, 55a der Mehrfachsicke 55 sind quasi gestapelt bzw. hierarchisch mit einer gemeinsamen Mitte M angeordnet. Bei der in FIG 16 gezeigten Mehrfachsicke 55 handelt es sich um eine 2-fach Sicke, auch Doppelsicke genannt. Doppelsicke bedeutet dabei, dass in einem prinzipiell konkaven Abschnitt Va einer ersten (dann äußeren) Sicke 55a eine zweite (dann innere) Sicke 55i angesiedelt ist. Diese Sickenkombination weist gegenüber den vorgenannten Geometrien, die als i-fach-Sicken bezeichnet werden können, eine weiter gesteigerte Elastizität auf, wodurch größere Fertigungstoleranzen für die Schaufelfüße 50, ggf. Zwischenstücke 44 und Haltenut 58 zugelassen werden können. Maße für die Sickengeometrie nach FIG 16 sind dann beispielsweise:

  • R20 = 20 mm; R1.2 = 2 mm; R2 = 2 mm; ba = 11 mm, aa = bi = 7,4 mm, R3 = 2 mm und ai = 3,2 mm.
FIG. 16 shows the cross section through a special bead geometry. The special bead geometry is a multiple bead 55 in which an inner bead 55i is surrounded by one or more beads 55a. The beads 55i, 55a of the multiple bead 55 are arranged in a quasi-stacked or hierarchical manner with a common center M. At the in FIG. 16 shown Mehrfachsicke 55 is a 2-fold bead, also called double bead. Double bead means that a second (then inner) bead 55i is located in a principally concave section Va of a first (then outer) bead 55a. This bead combination has over the aforementioned geometries, which can be referred to as i-fold beads, a further increased elasticity, whereby larger manufacturing tolerances for the blade roots 50, possibly intermediate pieces 44 and retaining groove 58 can be allowed. Dimensions for the bead geometry after FIG. 16 are then, for example:
  • R20 = 20 mm; R1.2 = 2 mm; R2 = 2 mm; ba = 11 mm, aa = bi = 7.4 mm, R3 = 2 mm and ai = 3.2 mm.

Insgesamt betrifft die Erfindung eine Schaufelanordnung 40 mit einem Schaufelträger 56 und einer darin angeordneten Haltenut 58, welche an ihren Seitenwänden 60 sich längs erstreckende Vorsprünge 62 zur Bildung von Hinterschneidungen 64 aufweist, und in der eine Anzahl von Schaufeln 25, 27 zur Bildung eines Schaufelkranzes einer Turbomaschine eingesetzt ist, wobei jede Schaufel 25, 27 neben einem Schaufelblatt 48 zur Befestigung einen hammerförmigen, in die Hinterschneidungen 64 eingreifenden Schaufelfuß 50 aufweist und durch zwischen einer Schaufelfußunterseite 68 und einem Nutgrund 70 der Haltenut 58 angeordnetes Element 46 an die Vorsprünge 62 gepresst ist. Um eine besonders sichere, zuverlässige, langlebige und verschleißarme Befestigung anzugeben, die eine besonders einfache Montage und Demontage ermöglicht ist vorgesehen, dass jedes Element 46 plattenförmig ausgebildet ist, in der Projektion von Schaufelblatt 48 in Richtung Nutgrund 70 zumindest eine unterhalb des Schaufelblatts 48 angeordnete Sicke 52 zum Anpressen aufweist und in Längsrichtung der Haltenut 58 lediglich teilweise des von ihm angepressten Schaufelfußes 50 überdeckt ist.Overall, the invention relates to a blade assembly 40 having a blade carrier 56 and a retaining groove 58 disposed therein, which has on its side walls 60 longitudinally extending projections 62 for forming undercuts 64, and in which a number of blades 25, 27 for forming a blade ring one Turbomachine used is, wherein each blade 25, 27 next to a blade 48 for fastening a hammer-shaped, engaging in the undercuts 64 blade root 50 and is pressed by between a blade root bottom 68 and a groove bottom 70 of the retaining groove 58 disposed element 46 to the projections 62. In order to provide a particularly safe, reliable, durable and low-wear attachment, which allows a particularly simple assembly and disassembly is provided that each element 46 is plate-shaped, in the projection of the airfoil 48 towards the groove bottom 70 at least one below the airfoil 48 arranged bead 52 has for pressing and in the longitudinal direction of the retaining groove 58 is only partially covered by the pressed him blade root 50.

Claims (13)

  1. Blade arrangement (40), with a number of blades (25, 27), a number of plate-shaped elements (46), a number of intermediate pieces (44), a blade carrier (56) and with a holding groove (58) which is arranged therein and which has on its side walls (60) longitudinally extending projections (62) for the formation of undercuts (64), and in which the number of blades (25, 27) for forming a blade ring of a turbomachine are inserted, each blade (25, 27) having in addition to an airfoil (48), for fastening, a blade root (50) engaging into the undercuts (64) and being pressed against the projections (62) by in each case a plate-shaped element (46) arranged between a blade root underside (68) and a groove bottom (70) of the holding groove (58) and having at least one bead (52, 55), characterized in that each element (46) is covered in the longitudinal direction of the holding groove (58) only partially by the blade root (50) pressed down by said element and in that an intermediate piece (44) is inserted in the holding groove (58) between two blades (25, 27) and is pressed against the projections (62) by that part of the element (46) which is not covered by the blade root (50).
  2. Blade arrangement (40) according to Claim 1, in which the element (46) presses the respective intermediate piece (44) against the projections (62) with lower force than it presses the respective blade root (50).
  3. Blade arrangement (40) according to Claim 2, in which that region of the element (46) which is covered by the blade root (50) is designed to be partially more rigid than the remaining part of the respective element (46).
  4. Blade arrangement (40) according to one of the preceding claims, in which the element (46) has, in its region not covered by the respective blade root (50), at least one orifice for demounting.
  5. Blade arrangement (40) according to one of the preceding claims, in which a longitudinally extending groove (72, 78) is arranged in the groove bottom (70) of the holding groove (58) or in the blade root underside (68).
  6. Blade arrangement (40) according to one of the preceding claims, in which the element (46) has, in a projection, an outer contour which is essentially rectangular.
  7. Blade arrangement (40) according to Claim 6, in which at least one longitudinal edge (74) of the element (46) is angled and bears, prestressed, against the blade roots (50) shaped correspondingly to it.
  8. Blade arrangement (40) according to Claim 7, in which at least one longitudinal edge (74) of the element (46) is angled and bears, prestressed, against the blade root (50) shaped correspondingly to it and against the intermediate piece (44) shaped correspondingly to it.
  9. Blade arrangement (40) according to Claim 6 or 7, in which at least one further bead (86) is provided at at least one margin of the element (46).
  10. Blade arrangement (40) according to one of the preceding claims, in which the element (46) has a wall thickness (s) and the bead (52, 55, 86) has in cross section a bead width (b) and also two convex portions (X) with a radius (R2) and a concave portion (V), arranged between them, with a radius (R1), with a chord length (a), to which the following applies:
    R1 > 1.5*s,
    3*R2 > R1 < 0.7*R2 and
    10*b to 1.7*b > a
    or
    R1 > 5*s,
    3*R2 < R1 and
    a < 0.9*b.
  11. Blade arrangement (40) according to one of Claims 1 to 10, in which the bead is configured as a multiple bead.
  12. Blade arrangement (40) according to Claim 11, in which the multiple bead (55) comprises an inner bead (55i) which is established in at least one outer bead (55a) at least partially surrounding the latter.
  13. Axial compressor for a gas turbine (10), with a moving blade ring and/or a guide blade ring designed as a blade arrangement (40) according to one of the preceding claims.
EP12748427.7A 2011-08-24 2012-08-14 Blade arrangement Active EP2723991B1 (en)

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EP11178635A EP2562356A1 (en) 2011-08-24 2011-08-24 Blade assembly
PCT/EP2012/065840 WO2013026735A1 (en) 2011-08-24 2012-08-14 Blade arrangement
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EP1803900A1 (en) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Closure unit for the remaining space between the first and the last blades of a bladed ring inserted in a circumferencial slot of a turbomachine, and corresponding turbomachine
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EP2090750A1 (en) 2008-02-14 2009-08-19 Siemens Aktiengesellschaft Turbomachine rotor, rotor blade for such a turbomachine rotor, supporting strip for such a rotor blade in the turbomachine rotor and corresponding assembling method

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BR112014003884A2 (en) 2017-03-14
WO2013026735A1 (en) 2013-02-28
CA2846053C (en) 2019-11-26
KR101939866B1 (en) 2019-01-17
BR112014003884B1 (en) 2021-11-03
CN104053858A (en) 2014-09-17
TW201326537A (en) 2013-07-01
JP2014527594A (en) 2014-10-16
MX2014002130A (en) 2014-03-27
BR112014003884B8 (en) 2023-04-25
JP5922237B2 (en) 2016-05-24
RU2014111052A (en) 2015-09-27
TWI606175B (en) 2017-11-21
RU2603696C2 (en) 2016-11-27
US9708919B2 (en) 2017-07-18
KR20140068077A (en) 2014-06-05
EP2723991A1 (en) 2014-04-30
ES2558014T3 (en) 2016-02-01
MX340744B (en) 2016-07-05
CA2846053A1 (en) 2013-02-28
US20140234111A1 (en) 2014-08-21
EP2562356A1 (en) 2013-02-27
CN104053858B (en) 2016-02-17

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