EP1653049B1 - Vane ring assembly for gas turbines and method to modify the same - Google Patents

Vane ring assembly for gas turbines and method to modify the same Download PDF

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Publication number
EP1653049B1
EP1653049B1 EP05109944A EP05109944A EP1653049B1 EP 1653049 B1 EP1653049 B1 EP 1653049B1 EP 05109944 A EP05109944 A EP 05109944A EP 05109944 A EP05109944 A EP 05109944A EP 1653049 B1 EP1653049 B1 EP 1653049B1
Authority
EP
European Patent Office
Prior art keywords
vane
radially
blade
carrier
flange
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
EP05109944A
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German (de)
French (fr)
Other versions
EP1653049A1 (en
Inventor
Bruno Benedetti
Andreas Boegli
Christopher Hulme
James Ritchie
Patrick Wolfgang Schnedler
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General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Publication date
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Publication of EP1653049A1 publication Critical patent/EP1653049A1/en
Application granted granted Critical
Publication of EP1653049B1 publication Critical patent/EP1653049B1/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the present invention relates to a guide vane ring of a turbomachine, in particular an axially flow turbine or a compressor, in particular a gas turbine, having the features of the preamble of claim 1.
  • the invention also relates to a method for modifying such a vane ring, with the features of the preamble of the claim 7th
  • a vane ring usually consists of several blades. which are arranged side by side in the circumferential direction and are thereby fastened individually or in groups of a plurality of blades to an annular blade carrier.
  • This blade carrier which usually consists of two semi-annular or semi-circular parts, in turn, is attached to a housing of the turbomachine.
  • the vane carrier for the vane ring has an upstream inlet groove and a downstream outlet groove. These grooves extend in the circumferential direction.
  • the blades or the blade groups each have a blade root, which has an inlet-side inlet flange and a downstream outlet flange.
  • the flanges also extend in the circumferential direction and stand axially from the respective blade root. When assembled, the inlet flanges engage the inlet groove and the outlet flanges engage the outlet groove.
  • upstream and downstream refer to those in operation the flow machine prevailing flow direction in the region of the guide vane ring.
  • the flanges In the case of large blades and in particular in the case of large blade groups, it is customary for the flanges to be supported on the blade carrier both radially inward and radially outwardly in the region of the respective groove. In this way, a particularly intensive attachment of the blades on the blade carrier can be achieved, which is also required to support the large flow forces or pressure differences that may occur during operation of the turbomachine. Especially with large blades and the blade carrier are very large components that are exposed during operation of the turbomachine different thermal loads. On the one hand, during operation of the turbomachine, in particular in the case of a turbine, there are large temperature differences between a cooling gas and a hot gas.
  • the thermal loads vary during transient operating conditions, that is, for example, during startup and when switching off the turbomachine. Varying thermal loads on the blade carrier can deform it. It is regularly observed a kind of ovalization, in which the two blade carrier halves, which abut one another at their peripheral ends in a parting plane, expand along the parting plane, so that the radii of the blade carrier parts increase at abutting peripheral ends or contract in the region of the parting plane, thereby reduce the radii of the blade carrier parts at abutting circumferential ends. At the same time this can lead to a twist within the blade carrier.
  • the blade carrier part regularly to larger deformations than the upper blade carrier part, which is usually much better integrated into the housing of the turbomachine.
  • the mentioned Deformations of the blade carrier are transmitted via the grooves on the flanges and thus via the blade roots in the blades or in the blade groups, whereby these high voltages are exposed.
  • the blades can be supported radially inwardly over shrouds in the circumferential direction to each other, which generates additional stresses in these, when the blades change their position by deformation of the blade carrier.
  • a stator blade for a turbomachine which can be fixed in a turbomachine to an annular blade carrier.
  • the blade carrier has an inlet-side inlet groove and an outlet-side outlet groove.
  • the grooves extend in the circumferential direction.
  • the blade has a blade root having an upstream inlet flange and a downstream outlet flange.
  • the flanges extend in the circumferential direction and are axially spaced from the respective blade root. When assembled, the inlet flange engages the inlet groove while the outlet flange engages the outlet groove. Both flanges are spaced between their end portions both radially inwardly and radially outwardly of the blade carrier.
  • both flanges have both at their front end portion in the circumferential direction and at its rear end portion in the circumferential direction in each case a claw-like projection on each of which radially inwardly and radially outwardly a respective contact zone in the form of a mating surface is formed, which rests in the mounted state on the blade carrier ,
  • the invention aims to remedy this situation.
  • the invention as characterized in the claims, deals with the problem for a guide vane ring of the type mentioned to show a way that reduces the risk of cracking on the blades.
  • the invention is based on the general idea, the attachment of the blades or the blade groups on the blade carrier in such a way that they can accommodate a change in shape of the blade carrier, without that it comes to particularly high stresses in the blade. This is achieved by the fact that within the connection between the blade root and blade carrier degrees of freedom are provided which allow deformations of the blade carrier, which typically occur during thermal loading of the blade carrier, so that such deformation of the blade carrier to no or only to a reduced strain in the Shovel foot and thus in the respective blade or blade group leads.
  • the invention proposes for this purpose, in which a flange, for example at the inlet flange, both at a front end portion in the circumferential direction and at a rear end portion in the circumferential direction both radially inside and radially outside each provide a contact zone which bears against the blade carrier.
  • a flange for example at the inlet flange, both at a front end portion in the circumferential direction and at a rear end portion in the circumferential direction both radially inside and radially outside each provide a contact zone which bears against the blade carrier.
  • the one end portion for example at the front end portion, provided radially inward a contact zone which bears against the blade carrier, while this end portion is spaced radially outward from the blade carrier.
  • a contact zone is again provided radially on the outside, which contacts the blade carrier, while this end section is then spaced radially inward from the blade carrier.
  • the contact zones are arranged diametrically opposite one another with respect to the end sections, or the end sections are positioned diametrically opposite to the blade carrier. This results in each end portion of the blade root a degree of freedom that allows a change in radius of the blade carrier and a distortion of the blade carrier.
  • the flanges are spaced between their end portions both radially inwardly and radially outwardly from the blade carrier.
  • the contact zones the front end portion as large a distance from the contact zones of the rear end portion, whereby a particularly large elasticity is provided in the blade root.
  • the blade root in the region of its flanges can absorb relatively large changes in shape of the blade carrier elastically, so that critical loads and stresses of the blade root and thus the blades or blade groups can be avoided or reduced.
  • the diametrically arranged with respect to the end portions spacings between the flange and the blade carrier can be dimensioned so that in a normal operation of the turbomachine prevailing between inflow and outflow pressure difference by elastic bending deformation of the blade or the blade group and / or the blade carrier reduces the spacing and brings the corresponding end portion to the blade carrier for conditioning.
  • the respective blade root is supported on both end portions and on both flanges both radially inwardly and radially outwardly on the blade carrier, resulting in a particularly intensive fixation of the blade or the blade group on the blade carrier.
  • the desired spacings between the blade root and blade carrier can then form diametrically with respect to the one flange relative to the end sections. Accordingly, the blade root can then better follow the changing geometry of the blade carrier, which reduces the load on the blades.
  • FIG. 1 has a guide ring 1 of a turbomachine, not shown otherwise, preferably a turbine or a compressor, preferably a gas turbine, a plurality of vanes or short blades 2, which are arranged adjacent to each other in the circumferential direction 3.
  • the blades 2 are attached to a blade carrier 4, which in turn is attached to a housing 5 of the turbomachine.
  • the blades 2 may be fastened individually to the blade carrier 4 or combined into blade groups 6, which are formed from two or more blades 2 and are fastened together on the blade carrier 4.
  • the blade carrier 4 is designed annular and expediently in the region of a dividing plane 7, in which preferably also a rotation axis 8 or longitudinal central axis 8 of the turbomachine is divided, so that accordingly Fig. 1 an upper blade carrier part 4a and a lower blade carrier part 4b are provided. It is clear that such a blade carrier 4 can in principle also serve for fastening the blades 2 of a plurality of guide blade rings 1 adjacent one another in the axial direction.
  • Fig. 5 shows a longitudinal section through a blade carrier 4, in which the blades 2 of a plurality of stator blade rings 1, that is, a plurality of turbine stages or compressor stages can be attached.
  • the vane carrier 4 has an inflow-side inflow groove 9 and an outflow-side outflow groove 10
  • Fig. 5 the grooves 9 and 10 different vane rings 1 in the reference numerals by single quotation marks.
  • the two grooves 9, 10 - each vane ring 1 - extend in each case in the circumferential direction 3 and thereby run closed in a closed ring.
  • a blade group 6 comprises three blades 2, which have a common blade root 11, which at the same time is the blade root 11 of the blade group 6.
  • the following explanations for the blade root 11 of the blade group 6 also apply correspondingly to a blade root 11 of a single blade 2.
  • an inflow-side inlet flange 12 is formed, which extends in the circumferential direction 3 and thereby projects axially from the blade root 11.
  • the blade root 11 also has a downstream outlet flange 13, which likewise extends in the circumferential direction 3 and projects axially from the blade root 11.
  • the flanges 12 and 13 are in opposite directions from the blade root 11 each axially outward.
  • the inlet flange 12 engages in the inlet groove 9, while the outlet flange 13 engages in the outlet groove 10.
  • the engagement takes place in each case axially, which forms a positive connection between the blade root 11 and the blade carrier 4 in the radial direction.
  • the blade root 11 and thus also its flanges 12 and 13 have a front end portion 14 in the circumferential direction 3 and spaced therefrom a rear end portion 15 in the circumferential direction 3. Between the end portions 14 and 15, a central portion 16 is formed, which is preferably approximately the same in the circumferential direction 3 Length, as the two end portions 14 and 15 together. Likewise, the central portion 16 may be longer in the circumferential direction 3 than the two end portions 14, 15 together.
  • deformations of the blade carrier 4 may occur due to thermal loads, in particular in transient operating states. It is in the Fig. 3a and 3b reproduced the original circular shape of the blade carrier 4 with a broken line, while the respective deformation form is shown by a solid line.
  • the two blade carrier parts 4a and 4b abut each other in the circumferential direction at circumferential ends 14 and 15. Due to the thermal load of the blade carrier 4, it comes to an ovalization, in the Fig. 3a and 3b is strongly indicated.
  • an ovalization according to Fig. 3a form a kind of constriction in the region of the parting line 7, which arises because the abutting circumferential ends 14 and 15 to move along the parting line 7, which is accompanied by a reduction of the bending radius of the blade carrier parts 4a and 4b.
  • the ovalization according to Fig. 3b also lead to the abutting circumferential ends 14 and 15 along the parting plane 7 from each other.
  • Fig. 4a to 4c show enlarged sectional views through one of the grooves 9 or 10, in which one of the flanges 12 or 13 engages.
  • the simultaneous contacting is represented here for better illustration by a game 21, which is radially equal to the outside and radially in the ideal case ideally.
  • Fig. 3b arises in the region of the groove 9, 10 a deformation accordingly Fig. 4b which causes the respective flange 12, 13 to be subjected to an extremely high degree of pressure radially inward in the region of its end sections 14, 15 and radially outwardly in the region of its middle section 16, which is indicated by corresponding arrows 17.
  • the aforementioned game 21 disappears in these areas.
  • Fig. 5 is the blade carrier 4 once shown by a solid line in a deformed state usually resulting in operation and with a broken line in an undeformed initial state, which occurs in cold turbomachine.
  • Fig. 6 shows an axial section through the foot 11 of a blade 2 and a blade group 6, wherein also here two different operating states are shown. Hatched is the cut in the normal operating state, ie with a hot turbomachine. In contrast, an undeformed initial state, which occurs in cold turbomachine, unhatched reproduced. It can be seen that the inlet-side inlet flange 12 can tilt by an angle ⁇ , while the downstream-side outlet flange 13 can tilt by an angle ⁇ . To make matters worse, that the two angles ⁇ and ⁇ can vary in size. In Fig. 6 the deformations are exaggerated again clearly and in particular are not to scale.
  • Fig. 7 now shows an inflow-side axial view of the blade root 11 of the blade group 6.
  • the viewer facing inlet flange 12 is further down, so radially further inside, arranged as the viewer facing away from and concealed outlet flange 13, the further up, ie radially on outside, is arranged. From the arrangement of the flanges 12, 13 it follows that this must be a blade group 6 of a turbine.
  • the flanges 12 and 13 are machined on their radial sides so that they contact the blade carrier 4 in the associated grooves 9, 10 in selected contact zones, which will be explained in more detail below.
  • the contact zones are in the Fig. 7 to 9 With greater line width indicated and designated 18.
  • arrows 19 indicate where in the installed state a force transmission between blade root 11 and blade carrier 4 takes place.
  • the contact zones 18 are distributed as follows:
  • One of the flanges 12, 13, in this case the outflow-side outlet flange 13, is provided both at its front end section 14 and at its rear end section 15, both radially inward and radially outwardly, with such a contact zone 18 which in the installed state on the blade carrier 4, So lie radially within the Auslenfinnut 10.
  • the outlet flange 13 thus results in a kind of 4-point storage.
  • the inlet flange 12 is provided only at one end portion, here at the front end portion 14, radially outwardly with such a contact zone 18 which rests in the installed state on the blade carrier 4, while radially inwardly formed so that the end portion 14 in Installation state is spaced from the blade carrier 4.
  • the inlet flange 12 is provided at its other end portion, so here at the rear end portion 15 radially inwardly with such a contact zone 18 which rests in the installed state on the blade carrier 4, while radially outwardly shaped so that the rear end portion 15 in the installed state of Blade carrier 4 is spaced.
  • results for the inlet flange 12 is a kind of 2-point storage.
  • the two contact zones 18 and accordingly the two unspecified distance zones with respect to the end sections 14 and 15 are arranged diametrically opposite one another on the inlet flange 12.
  • connection of the blade root 11 to the blade carrier 4 is given defined degrees of freedom which, in the case of the typical deformations of the blade carrier 4, which it thermally effects in transient operating conditions, results in a reduction of the blade carrier Force transmission between blade carrier 4 and blade root 11 effect.
  • the blade roots 11 and thus the blades 2 or the blade groups 6 are less heavily loaded by the deformations of the blade carrier 4.
  • the central portion 16 in the circumferential direction 3 is dimensioned comparatively large, in particular equal to or greater than the two end portions 14, 15 together.
  • the contact zones 18 can also be made specifically so that there is a linear contact or contact on the blade carrier 4, which may be oriented, for example, radially or in the circumferential direction. Likewise, the contact zones 18 can also be designed so that point-like contacts with the blade carrier 4 result.
  • the distances between the inlet flange 12 in the region of the end sections 14 and 15 relative to the blade carrier 4 can be dimensioned so that a pressure difference between inflow side and downstream side of the respective guide vane ring 1, which occurs during normal operation of the turbomachine, an elastic bending deformation of the blades 2 and of the blade group 6 and / or the blade carrier 4, which reduces said distances, and preferably so far that the corresponding end portions 14 and 15 then also come to rest on the blade carrier 4. In the load state then the said additional degrees of freedom are canceled. In transient conditions, said pressure difference decreases, whereby the end portions 14 and 15 lift off the blade carrier 4 again to restore the degrees of freedom, which reduce the stresses in the blade root 11 in the deformations of the blade carrier 4.
  • the inlet flange 12 is provided with two contact zones 18 and the outlet flange 13 is provided with four contact zones 18, the distribution of the contact zones 18 may also be reversed. Likewise, the distribution of the contact zones 18 in the case of the flange 12 equipped with only two contact zones 18 at the two end sections 14, 15 can be reversed with respect to the arrangement inside and outside.
  • the blades 2 may be connected radially inwardly via shrouds 20 and be supported in the circumferential direction in the mounted state.
  • the blades 2 or the blade groups 6 are removed from the blade carrier 4.
  • the dismantled blade groups 6 can in the region of the blade root 11, for example, as in Fig. 8 be designed. This means that both the inlet flange 12 and the outlet flange 13 both at the front end portion 14 and at the rear end portion 15 both radially inwardly and radially outwardly each with a contact zone 18 and 18 'is equipped.
  • a developed blade 2 can, for example, in the region of its blade root 11 as in Fig. 9 be configured and accordingly have a particular distribution of contact zones 18 and 18 '.
  • the flanges 12 and 13 of the blade roots 11 are now processed in the removed blades 2 or in the removed blade groups 6.
  • the two radially outer sides of the flanges 12 and 13 are each formed as a continuous contact zones 18 '.
  • the outlet flange 13 has radially inside only a single contact zone 18 ', which is also arranged in the central portion 16.
  • the machining of this blade root 11 takes place in such a way that at the outlet flange 13 on the radially outer side of the central portion 16 is removed so far that only one of the desired contact zones 18 remains only in the end portions 14 and 15.
  • the contact zone 18 'in the middle section 16 is removed by appropriate material removal.
  • a suitable material application for. B. by welding or soldering, respectively, the desired inner contact zone 18th created in order to obtain an appropriate shape here, as in Fig. 7 is reproduced.
  • the inlet flange 12 is here processed so that the provided in the front end portion 14, radially inward contact zone 18 'is completely removed. Furthermore, the radially outer, continuous contact zone 18 'is removed radially outward in the region of the middle section 16 and in the region of the rear end section 15 until the in Fig. 7 reproduced shape results. Thus, even with the in Fig. 9 reproduced blade foot type in Fig. 7 reproduced inventive contour can be produced.
  • the method shown here is particularly suitable for retrofitting a conventional vane ring in the guide vane ring 1 according to the invention, the blades 2 can absorb the deformations of the blade carrier 4 better.

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

Abstract

Flanges (12,13) are formed to the foot (11) of a vane group (6). Radially spaced contact zones (18) are formed individually to the front and rear sections (14,15) of the flanges and rest against the vane supporting regions of the guide vane ring. An independent claim is also included for modification method of a guide vane ring.

Description

Technisches GebietTechnical area

Die vorliegende Erfindung betrifft einen Leitschaufelring einer Strömungsmaschine, insbesondere einer axial durchströmten Turbine oder eines Verdichters, insbesondere einer Gasturbine, mit den Merkmalen des Oberbegriffs des Anspruchs 1. Die Erfindung betrifft außerdem ein Verfahren zum Modifizieren eines derartigen Leitschaufelrings, mit den Merkmalen des Oberbegriffs des Anspruchs 7.The present invention relates to a guide vane ring of a turbomachine, in particular an axially flow turbine or a compressor, in particular a gas turbine, having the features of the preamble of claim 1. The invention also relates to a method for modifying such a vane ring, with the features of the preamble of the claim 7th

Stand der TechnikState of the art

Ein Leitschaufelring besteht üblicherweise aus mehreren Schaufeln. die in Umfangsrichtung nebeneinander angeordnet sind und dabei einzeln oder in Gruppen aus mehreren Schaufeln an einem ringförmigen Schaufelträger befestigt sind. Dieser Schaufelträger. der üblicherweise aus zwei halbringförmigen oder halbkreisförmigen Teilen besteht, ist seinerseits an einem Gehäuse der Strömungsmaschine befestigt. Üblicherweise besjtzt der Schaufelträger für den Leitschaufelring eine anströmseitige Einlassnut sowie eine abströmseitige Auslassnut. Diese Nuten erstrecken sich dabei in Umfangsrichtung. Die Schaufeln bzw. die Schaufelgruppen weisen jeweils einen Schaufelfuß auf, der einen anströmseitigen Einlassflansch sowie einen abströmseitigen Auslassflansch aufweist. Auch die Flansche erstrecken sich in Umfangsrichtung und stehen dabei axial vom jeweiligen Schaufelfuß ab. Im montierten Zustand greifen die Einlassflansche in die Einlassnut und die Auslassflansche in die Auslassnut ein. Die Begriffe "anströmseitig" und "abströmseitig" beziehen sich auf die im Betrieb der Strömungsmaschine herrschende Strömungsrichtung im Bereich des Leitschaufelrings.A vane ring usually consists of several blades. which are arranged side by side in the circumferential direction and are thereby fastened individually or in groups of a plurality of blades to an annular blade carrier. This blade carrier. which usually consists of two semi-annular or semi-circular parts, in turn, is attached to a housing of the turbomachine. Usually, the vane carrier for the vane ring has an upstream inlet groove and a downstream outlet groove. These grooves extend in the circumferential direction. The blades or the blade groups each have a blade root, which has an inlet-side inlet flange and a downstream outlet flange. The flanges also extend in the circumferential direction and stand axially from the respective blade root. When assembled, the inlet flanges engage the inlet groove and the outlet flanges engage the outlet groove. The terms "upstream" and "downstream" refer to those in operation the flow machine prevailing flow direction in the region of the guide vane ring.

Bei großen Schaufeln und insbesondere bei großen Schaufelgruppen ist es üblich, dass sich die Flansche sowohl radial innen als auch radial außen im Bereich der jeweiligen Nut am Schaufelträger abstützen. Hierdurch kann eine besonders intensive Befestigung der Schaufeln am Schaufelträger erzielt werden, was auch zur Abstützung der großen Strömungskräfte bzw. Druckdifferenzen, die im Betrieb der Strömungsmaschine auftreten können, erforderlich ist. Gerade bei großen Schaufeln sind auch die Schaufelträger sehr große Bauteile, die im Betrieb der Strömungsmaschine unterschiedlichen thermischen Belastungen ausgesetzt sind. Zum einen bestehen im Betrieb der Strömungsmaschine, insbesondere bei einer Turbine, große Temperaturunterschiede zwischen einem Kühlgas und einem Heißgas. Zum anderen kommt es auch im Heißgas zu großen Temperaturunterschieden, wenn dieses sich beim Durchgang durch die jeweilige Turbinenstufe entspannt. Die thermischen Belastungen variieren während transienter Betriebszustände, also beispielsweise beim Hochfahren und beim Abschalten der Strömungsmaschine. Variierende thermische Belastungen des Schaufelträgers können diesen verformen. Dabei ist regelmäßig eine Art Ovalisierung zu beobachten, bei der die beiden Schaufelträgerhälften, die an ihren Umfangsenden in einer Trennebene aneinanderstoßen, sich entlang der Trennebene aufweiten, so dass sich die Radien der Schaufelträgerteile bei aneinander anliegenden Umfangsenden vergrößern oder im Bereich der Trennebene zusammenziehen, wodurch sich die Radien der Schaufelträgerteile bei aneinander anliegenden Umfangsenden verkleinern. Gleichzeitig kann es dadurch zu einer Verwindung innerhalb des Schaufelträgers kommen.In the case of large blades and in particular in the case of large blade groups, it is customary for the flanges to be supported on the blade carrier both radially inward and radially outwardly in the region of the respective groove. In this way, a particularly intensive attachment of the blades on the blade carrier can be achieved, which is also required to support the large flow forces or pressure differences that may occur during operation of the turbomachine. Especially with large blades and the blade carrier are very large components that are exposed during operation of the turbomachine different thermal loads. On the one hand, during operation of the turbomachine, in particular in the case of a turbine, there are large temperature differences between a cooling gas and a hot gas. On the other hand, it also comes in the hot gas to large temperature differences, if this relaxes when passing through the respective turbine stage. The thermal loads vary during transient operating conditions, that is, for example, during startup and when switching off the turbomachine. Varying thermal loads on the blade carrier can deform it. It is regularly observed a kind of ovalization, in which the two blade carrier halves, which abut one another at their peripheral ends in a parting plane, expand along the parting plane, so that the radii of the blade carrier parts increase at abutting peripheral ends or contract in the region of the parting plane, thereby reduce the radii of the blade carrier parts at abutting circumferential ends. At the same time this can lead to a twist within the blade carrier.

Außerdem kommt es beim unteren Schaufelträgerteil regelmäßig zu größeren Deformationen als beim oberen Schaufelträgerteil, das üblicherweise erheblich besser in das Gehäuse der Strömungsmaschine eingebunden ist. Die genannten Verformungen des Schaufelträgers werden über die Nuten auf die Flansche und somit über die Schaufelfüße in die Schaufeln bzw. in die Schaufelgruppen übertragen, wodurch auch diese hohen Spannungen ausgesetzt sind. Darüber hinaus können die Schaufeln radial innen über Deckbänder in Umfangsrichtung aneinander abgestützt sein, was in diesen zusätzliche Spannungen erzeugt, wenn die Schaufeln durch Deformation des Schaufelträgers ihre Position verändern.In addition, it comes at the lower blade carrier part regularly to larger deformations than the upper blade carrier part, which is usually much better integrated into the housing of the turbomachine. The mentioned Deformations of the blade carrier are transmitted via the grooves on the flanges and thus via the blade roots in the blades or in the blade groups, whereby these high voltages are exposed. In addition, the blades can be supported radially inwardly over shrouds in the circumferential direction to each other, which generates additional stresses in these, when the blades change their position by deformation of the blade carrier.

Die genannten Verspannungen können Risse verursachen und die Lebenszeit der Schaufeln reduzieren. Im schlimmsten Fall kann es zu einem Ausfall der Strömungsmaschine kommen.The stresses mentioned can cause cracks and reduce the life of the blades. In the worst case, there may be a failure of the turbomachine.

Aus der DE 14 76 928 A ist eine Leitschaufel für eine Strömungsmaschine bekannt, die in einer Strömungsmaschine an einem ringförmigen Schaufelträger befestigt werden kann. Der Schaufelträger weist eine anströmseitige Einlassnut und eine abströmseitige Auslassnut auf. Die Nuten erstrecken sich in Umfangsrichtung. Die Schaufel weist einen Schaufelfuß auf, der einen anströmseitigen Einlassflansch und eine abströmseitigen Auslassflansch aufweist. Die Flansche erstrecken sich in Umfangsrichtung und stehen vom jeweiligen Schaufelfuß axial ab. Im montierten Zustand greift der Einlassflansch in die Einlassnut ein, während der Auslassflansch in die Auslassnut eingreift. Beide Flansche sind zwischen ihren Endabschnitten sowohl radial innen als auch radial außen vom Schaufelträger beabstandet. Ferner weisen beide Flansche sowohl an ihrem in Umfangsrichtung vorderen Endabschnitt als auch an ihrem in Umfangsrichtung hinteren Endabschnitt jeweils einen pratzenartigen Vorsprung auf, an denen jeweils radial innen und radial außen jeweils eine Kontaktzone in Form einer Passfläche ausgebildet ist, die im montierten Zustand am Schaufelträger anliegt.From the DE 14 76 928 A a stator blade for a turbomachine is known, which can be fixed in a turbomachine to an annular blade carrier. The blade carrier has an inlet-side inlet groove and an outlet-side outlet groove. The grooves extend in the circumferential direction. The blade has a blade root having an upstream inlet flange and a downstream outlet flange. The flanges extend in the circumferential direction and are axially spaced from the respective blade root. When assembled, the inlet flange engages the inlet groove while the outlet flange engages the outlet groove. Both flanges are spaced between their end portions both radially inwardly and radially outwardly of the blade carrier. Furthermore, both flanges have both at their front end portion in the circumferential direction and at its rear end portion in the circumferential direction in each case a claw-like projection on each of which radially inwardly and radially outwardly a respective contact zone in the form of a mating surface is formed, which rests in the mounted state on the blade carrier ,

Aus der EP 1 039 096 A2 sind Leitschaufeln bekannt, die einerseits über einen Flansch, der in eine Flanschaufnahme eines Schaufelträgers hineinragt, und andererseits über einen Radialsteg, der mit dem Schaufelträger verschraubt ist, am Schaufelträger befestigt sind. Ferner sind die Leitschaufeln im montierten Zustand radial innen über Deckbänder miteinander verbunden.From the EP 1 039 096 A2 Guide vanes are known, on the one hand via a flange which projects into a Flanschaufnahme a blade carrier, and on the other hand via a radial web, which is bolted to the blade carrier, attached to the blade carrier. Furthermore, the guide vanes are connected to each other in the assembled state radially inside over shrouds.

Darstellung der ErfindungPresentation of the invention

Hier will die Erfindung Abhilfe schaffen. Die Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, beschäftigt sich mit Problem, für einen Leitschaufelring der eingangs genannten Art eine Möglichkeit aufzuzeigen, welche die Gefahr einer Rissbildung an den Schaufeln reduziert.The invention aims to remedy this situation. The invention, as characterized in the claims, deals with the problem for a guide vane ring of the type mentioned to show a way that reduces the risk of cracking on the blades.

Erfindungsgemäß wird dieses Problem durch die Gegenstände der unabhängigen Ansprüche gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der abhängigen Ansprüche.According to the invention, this problem is solved by the subject matters of the independent claims. Advantageous embodiments are the subject of the dependent claims.

Die Erfindung beruht auf dem allgemeinen Gedanken, die Befestigung der Schaufeln bzw. der Schaufelgruppen am Schaufelträger so auszugestalten, dass diese eine Formänderung des Schaufelträgers aufnehmen können, ohne dass es dabei zu besonders großen Spannungen in der Schaufel kommt. Erreicht wird dies dadurch, dass innerhalb der Anbindung zwischen Schaufelfuß und Schaufelträger gezielt Freiheitsgrade vorgesehen werden, welche Verformungen des Schaufelträgers, die typischerweise bei thermischen Belastungen des Schaufelträgers auftreten, zulassen, so dass eine solche Verformung des Schaufelträgers zu keiner oder nur zu einer reduzierten Verspannung im Schaufelfuß und somit in der jeweiligen Schaufel bzw. Schaufelgruppe führt.The invention is based on the general idea, the attachment of the blades or the blade groups on the blade carrier in such a way that they can accommodate a change in shape of the blade carrier, without that it comes to particularly high stresses in the blade. This is achieved by the fact that within the connection between the blade root and blade carrier degrees of freedom are provided which allow deformations of the blade carrier, which typically occur during thermal loading of the blade carrier, so that such deformation of the blade carrier to no or only to a reduced strain in the Shovel foot and thus in the respective blade or blade group leads.

Die Erfindung schlägt hierzu vor, bei dem einen Flansch, z.B. beim Einlassflansch, sowohl an einem in Umfangsrichtung vorderen Endabschnitt als auch an einem in Umfangsrichtung hinteren Endabschnitt sowohl radial innen als auch radial außen jeweils eine Kontaktzone vorzusehen, die am Schaufelträger anliegt. Im Unterschied dazu wird am anderen Flansch, also beispielsweise am Auslassflansch, an dem einen Endabschnitt, z.B. am vorderen Endabschnitt, radial innen eine Kontaktzone vorgesehen, die am Schaufelträger anliegt, während dieser Endabschnitt radial außen vom Schaufelträger beabstandet ist. Am jeweils anderen Endabschnitt, also beispielsweise am hinteren Endabschnitt, ist dann radial außen wieder eine Kontaktzone vorgesehen, die am Schaufelträger anliegt, während dieser Endabschnitt dann radial innen vom Schaufelträger beabstandet ist. Auf diese Weise sind bei einem der Flansche, also hier exemplarisch am abströmseitigen Auslassflansch, die Kontaktzonen bezüglich der Endabschnitte diametral gegenüberliegenden angeordnet bzw. sind die Endabschnitte diametral gegenüberliegend beabstandet zum Schaufelträger positioniert. Hierdurch ergibt sich in jedem Endabschnitt des Schaufelfußes ein Freiheitsgrad, der eine Radiusänderung des Schaufelträgers sowie eine Verwindung des Schaufelträgers zulässt. Gleichzeitig wird vorgeschlagen, dass die Flansche zwischen ihren Endabschnitten sowohl radial innen als auch radial außen vom Schaufelträger beabstandet sind. Auf diese Weise besitzen die Kontaktzonen des vorderen Endabschnitts einen möglichst großen Abstand von den Kontaktzonen des hinteren Endabschnitts, wodurch im Schaufelfuß eine besonders große Elastizität bereitgestellt wird. Dementsprechend kann der Schaufelfuß im Bereich seiner Flansche auch relativ große Formänderungen des Schaufelträgers elastisch aufnehmen, so dass kritische Belastungen und Verspannungen des Schaufelfußes und somit der Schaufeln bzw. Schaufelgruppen vermieden bzw. reduziert werden können.The invention proposes for this purpose, in which a flange, for example at the inlet flange, both at a front end portion in the circumferential direction and at a rear end portion in the circumferential direction both radially inside and radially outside each provide a contact zone which bears against the blade carrier. In contrast, at the other flange, so for example at the outlet, at the one end portion, for example at the front end portion, provided radially inward a contact zone which bears against the blade carrier, while this end portion is spaced radially outward from the blade carrier. At the respective other end section, that is to say for example at the rear end section, a contact zone is again provided radially on the outside, which contacts the blade carrier, while this end section is then spaced radially inward from the blade carrier. In this way, in one of the flanges, that is to say here exemplarily on the outflow-side outlet flange, the contact zones are arranged diametrically opposite one another with respect to the end sections, or the end sections are positioned diametrically opposite to the blade carrier. This results in each end portion of the blade root a degree of freedom that allows a change in radius of the blade carrier and a distortion of the blade carrier. At the same time it is proposed that the flanges are spaced between their end portions both radially inwardly and radially outwardly from the blade carrier. In this way, have the contact zones the front end portion as large a distance from the contact zones of the rear end portion, whereby a particularly large elasticity is provided in the blade root. Accordingly, the blade root in the region of its flanges can absorb relatively large changes in shape of the blade carrier elastically, so that critical loads and stresses of the blade root and thus the blades or blade groups can be avoided or reduced.

Gemäß einer besonders vorteilhaften Ausführungsform können die bezüglich der Endabschnitte diametral angeordneten Beabstandungen zwischen dem Flansch und dem Schaufelträger so dimensioniert sein, dass in einem Normalbetrieb der Strömungsmaschine eine zwischen Anströmseite und Abströmseite herrschende Druckdifferenz durch elastische Biegeverformung der Schaufel bzw. der Schaufelgruppe und/oder des Schaufelträgers die Beabstandung reduziert und den entsprechenden Endabschnitt an den Schaufelträger zur Anlage bringt. Mit anderen Worten, im Normalbetrieb ist der jeweilige Schaufelfuß an beiden Endabschnitten und an beiden Flanschen sowohl radial innen als auch radial außen am Schaufelträger abgestützt, wodurch sich eine besonders intensive Fixierung der Schaufel bzw. der Schaufelgruppe am Schaufelträger ergibt. Bei transienten Betriebszuständen, bei denen also reduzierte Druckdifferenzen zwischen Anströmseite und Abströmseite herrschen und bei denen die Deformationen des Schaufelträgers hauptsächlich stattfinden, können sich dann die gewünschten Beabstandungen zwischen Schaufelfuß und Schaufelträger an dem einen Flansch bezüglich der Endabschnitte diametral ausbilden. Dementsprechend kann der Schaufelfuß dann der sich ändernden Geometrie des Schaufelträgers besser folgen, was die Belastung der Schaufeln reduziert.According to a particularly advantageous embodiment, the diametrically arranged with respect to the end portions spacings between the flange and the blade carrier can be dimensioned so that in a normal operation of the turbomachine prevailing between inflow and outflow pressure difference by elastic bending deformation of the blade or the blade group and / or the blade carrier reduces the spacing and brings the corresponding end portion to the blade carrier for conditioning. In other words, in normal operation, the respective blade root is supported on both end portions and on both flanges both radially inwardly and radially outwardly on the blade carrier, resulting in a particularly intensive fixation of the blade or the blade group on the blade carrier. In transient operating conditions, in which there are thus reduced pressure differences between inflow side and outflow side and in which the deformations of the blade carrier mainly take place, the desired spacings between the blade root and blade carrier can then form diametrically with respect to the one flange relative to the end sections. Accordingly, the blade root can then better follow the changing geometry of the blade carrier, which reduces the load on the blades.

Weitere wichtige Merkmale und Vorteile der vorliegenden Erfindung ergeben sich aus den Unteransprüchen, aus den Zeichnungen und aus der zugehörigen Figurenbeschreibung anhand der Zeichnungen.Other important features and advantages of the present invention will become apparent from the dependent claims, from the drawings and from the associated figure description with reference to the drawings.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Bevorzugte Ausführungsbeispiele der Erfindung sind in den Zeichnungen dargestellt und werden in der nachfolgenden Beschreibung näher erläutert, wobei sich gleiche Bezugszeichen auf gleiche oder ähnliche oder funktionalgleiche Komponenten beziehen. Es zeigen, jeweils schematisch,

Fig. 1
einen stark vereinfachten Querschnitt durch eine Strömungsmaschine im Bereich eines Leitschaufelrings,
Fig. 2
eine perspektivische Ansicht auf eine Schaufelgruppe,
Fig. 3a und 3b
vereinfachte Darstellungen wie in Fig. 1, jedoch bei unterschiedlichen Verformungszuständen,
Fig. 4a - 4c
vergrößerte Schnittdarstellungen im Bereich einer Nut eines Schaufelträgers mit darin eingreifendem Flansch eines Schaufelfußes bei unterschiedlichen Verformungszuständen des Schaufelträgers,
Fig. 5
einen Axialschnitt durch einen Schaufelträger bei unterschiedlichen Verformungszuständen,
Fig. 6
einen Axialschnitt durch einen Schaufelfuß bei unterschiedlichen Verformungszuständen,
Fig. 7
eine vereinfachte axiale Ansicht auf einen Schaufelfuß nach der Erfindung,
Fig. 8
eine Ansicht wie in Fig. 7, jedoch bei einem Schaufelfuß eines Leitschaufelrings vor dessen Modifikation,
Fig. 9
einen Ansicht wie in Fig. 8, jedoch bei einer anderen Ausführungsform des Schaufelfußes.
Preferred embodiments of the invention are illustrated in the drawings and will be explained in more detail in the following description, wherein like reference numerals refer to the same or similar or functionally identical components. Show, in each case schematically,
Fig. 1
a greatly simplified cross-section through a turbomachine in the region of a guide vane ring,
Fig. 2
a perspective view of a blade group,
Fig. 3a and 3b
simplified representations as in Fig. 1 but at different states of deformation,
Fig. 4a - 4c
enlarged sectional views in the region of a groove of a blade carrier with a flange of a blade root engaging therein in the case of different deformation states of the blade carrier,
Fig. 5
an axial section through a blade carrier at different deformation states,
Fig. 6
an axial section through a blade root at different deformation states,
Fig. 7
a simplified axial view of a blade root according to the invention,
Fig. 8
a view like in Fig. 7 but with a blade root of a vane ring prior to its modification,
Fig. 9
a view like in Fig. 8 but in another embodiment of the blade root.

Wege zur Ausführung der ErfindungWays to carry out the invention

Entsprechend Fig. 1 besitzt ein Leitschaufelring 1 einer im übrigen nicht dargestellten Strömungsmaschine, vorzugsweise einer Turbine oder eines Verdichters, vorzugsweise einer Gasturbine, mehrere Leitschaufeln oder kurz Schaufeln 2, die in Umfangsrichtung 3 zueinander benachbart angeordnet sind. Die Schaufeln 2 sind an einem Schaufelträger 4 befestigt, der seinerseits an einem Gehäuse 5 der Strömungsmaschine befestigt ist.Corresponding Fig. 1 has a guide ring 1 of a turbomachine, not shown otherwise, preferably a turbine or a compressor, preferably a gas turbine, a plurality of vanes or short blades 2, which are arranged adjacent to each other in the circumferential direction 3. The blades 2 are attached to a blade carrier 4, which in turn is attached to a housing 5 of the turbomachine.

Dabei können die Schaufeln 2 einzeln am Schaufelträger 4 befestigt sein oder zu Schaufelgruppen 6 zusammengefasst sein, die aus zwei oder mehr Schaufeln 2 gebildet sind und gemeinsam am Schaufelträger 4 befestigt sind. Der Schaufelträger 4 ist dabei ringförmig ausgestaltet und zweckmäßig im Bereich einer Teilungsebene 7, in welcher vorzugsweise auch eine Rotationsachse 8 bzw. Längsmittelachse 8 der Strömungsmaschine liegt, geteilt, so dass entsprechend Fig. 1 ein oberer Schaufelträgerteil 4a sowie ein unterer Schaufelträgerteil 4b vorhanden sind. Es ist klar, dass ein derartiger Schaufelträger 4 grundsätzlich auch zur Befestigung der Schaufeln 2 von mehreren, in axialer Richtung benachbarter Leitschaufelringe 1 dienen kann.In this case, the blades 2 may be fastened individually to the blade carrier 4 or combined into blade groups 6, which are formed from two or more blades 2 and are fastened together on the blade carrier 4. The blade carrier 4 is designed annular and expediently in the region of a dividing plane 7, in which preferably also a rotation axis 8 or longitudinal central axis 8 of the turbomachine is divided, so that accordingly Fig. 1 an upper blade carrier part 4a and a lower blade carrier part 4b are provided. It is clear that such a blade carrier 4 can in principle also serve for fastening the blades 2 of a plurality of guide blade rings 1 adjacent one another in the axial direction.

Beispielsweise zeigt Fig. 5 einen Längsschnitt durch einen Schaufelträger 4, bei dem die Schaufeln 2 mehrerer Leitschaufelringe 1, also mehrerer Turbinenstufen bzw. Verdichterstufen befestigt werden können. Für jeden Leitschaufelring 1 besitzt der Schaufelträger 4 eine anströmseitige Einlassnut 9 sowie eine abströmseitige Auslassnut 10. Dabei sind in Fig. 5 die Nuten 9 und 10 unterschiedlicher Leitschaufelringe 1 in den Bezugszeichen durch Hochkommata gekennzeichnet. Die beiden Nuten 9, 10 - je Leitschaufelring 1 - erstrecken sich dabei jeweils in Umfangsrichtung 3 und laufen dabei ringförmig geschlossen um.For example, shows Fig. 5 a longitudinal section through a blade carrier 4, in which the blades 2 of a plurality of stator blade rings 1, that is, a plurality of turbine stages or compressor stages can be attached. For each vane ring 1, the vane carrier 4 has an inflow-side inflow groove 9 and an outflow-side outflow groove 10 Fig. 5 the grooves 9 and 10 different vane rings 1 in the reference numerals by single quotation marks. The two grooves 9, 10 - each vane ring 1 - extend in each case in the circumferential direction 3 and thereby run closed in a closed ring.

Bezugnehmen auf Fig. 2 umfasst eine Schaufelgruppe 6 beispielsweise drei Schaufeln 2, die einen gemeinsamen Schaufelfuß 11 aufweisen, der gleichzeitig der Schaufelfuß 11 der Schaufelgruppe 6 ist. Die nachfolgenden Erläuterungen für den Schaufelfuß 11 der Schaufelgruppe 6 gelten in entsprechender Weise auch für einen Schaufelfuß 11 einer einzelnen Schaufel 2.Referring to Fig. 2 For example, a blade group 6 comprises three blades 2, which have a common blade root 11, which at the same time is the blade root 11 of the blade group 6. The following explanations for the blade root 11 of the blade group 6 also apply correspondingly to a blade root 11 of a single blade 2.

Am Schaufelfuß 11 ist ein anströmseitiger Einlassflansch 12 ausgebildet, der sich in Umfangsrichtung 3 erstreckt und dabei axial vom Schaufelfuß 11 absteht. In entsprechender Weise besitzt der Schaufelfuß 11 auch einen abströmseitigen Auslassflansch 13, der sich ebenfalls in Umfangsrichtung 3 erstreckt und dabei axial vom Schaufelfuß 11 absteht. Dabei stehen die Flansche 12 und 13 in entgegengesetzten Richtungen vom Schaufelfuß 11 jeweils axial nach außen ab.At the blade root 11 an inflow-side inlet flange 12 is formed, which extends in the circumferential direction 3 and thereby projects axially from the blade root 11. Correspondingly, the blade root 11 also has a downstream outlet flange 13, which likewise extends in the circumferential direction 3 and projects axially from the blade root 11. In this case, the flanges 12 and 13 are in opposite directions from the blade root 11 each axially outward.

Im montierten Zustand greift der Einlassflansch 12 in die Einlassnut 9 ein, während der Auslassflansch 13 in die Auslassnut 10 eingreift. Der Eingriff erfolgt dabei jeweils axial, wodurch sich in radialer Richtung ein Formschluss zwischen Schaufelfuß 11 und Schaufelträger 4 ausbildet.In the assembled state, the inlet flange 12 engages in the inlet groove 9, while the outlet flange 13 engages in the outlet groove 10. The engagement takes place in each case axially, which forms a positive connection between the blade root 11 and the blade carrier 4 in the radial direction.

Der Schaufelfuß 11 und somit auch seine Flansche 12 und 13 besitzen einen in Umfangsrichtung 3 vorderen Endabschnitt 14 sowie beabstandet dazu einen in Umfangsrichtung 3 hinteren Endabschnitt 15. Zwischen den Endabschnitten 14 und 15 ist ein Mittelabschnitt 16 ausgebildet, der vorzugsweise in der Umfangsrichtung 3 etwa dieselbe Länge aufweist, wie die beiden Endabschnitte 14 und 15 zusammen. Ebenso kann der Mittelabschnitt 16 in Umfangsrichtung 3 länger sein als die beiden Endabschnitte 14, 15 zusammen.The blade root 11 and thus also its flanges 12 and 13 have a front end portion 14 in the circumferential direction 3 and spaced therefrom a rear end portion 15 in the circumferential direction 3. Between the end portions 14 and 15, a central portion 16 is formed, which is preferably approximately the same in the circumferential direction 3 Length, as the two end portions 14 and 15 together. Likewise, the central portion 16 may be longer in the circumferential direction 3 than the two end portions 14, 15 together.

Gemäß den Fig. 3a und 3b kann es im Betrieb der Strömungsmaschine aufgrund thermischer Belastungen, insbesondere bei transienten Betriebszuständen zu Verformungen des Schaufelträgers 4 kommen. Dabei ist in den Fig. 3a und 3b die ursprüngliche Kreisform des Schaufelträgers 4 mit unterbrochener Linie wiedergegeben, während die jeweilige Deformationsform mit durchgezogener Linie wiedergegeben ist.According to the Fig. 3a and 3b In the operation of the turbomachine, deformations of the blade carrier 4 may occur due to thermal loads, in particular in transient operating states. It is in the Fig. 3a and 3b reproduced the original circular shape of the blade carrier 4 with a broken line, while the respective deformation form is shown by a solid line.

Die beiden Schaufelträgerteile 4a und 4b stoßen in Umfangsrichtung an Umfangsenden 14 und 15 aneinander. Durch die thermische Belastung des Schaufelträgers 4 kommt es zu einer Ovalisierung, die in den Fig. 3a und 3b übertrieben stark angedeutet ist. Zum einen kann sich bei einer derartigen Ovalisierung gemäß Fig. 3a im Bereich der Trennebene 7 eine Art Einschnürung ausbilden, die dadurch entsteht, dass sich die aneinander anliegenden Umfangsenden 14 und 15 entlang der Trennebene 7 aufeinander zu bewegen, was mit einer Verkleinerung des Biegeradius der Schaufelträgerteile 4a und 4b einhergeht. Zum anderen kann die Ovalisierung gemäß Fig. 3b auch dazu führen, dass sich die aneinander anstoßenden Umfangsenden 14 und 15 entlang der Trennebene 7 voneinander entfernen. Dies ist gleichbedeutend damit, dass sich der Biegeradius der Schaufelträgerteile 4a, 4b vergrößert. Diese Ovalisierung führt gleichzeitig zu einer Verwindung des Schaufelträgers 4. Des Weiteren fällt in der Regel die Deformierung des unteren Schaufelträgerteils 4b deutlich größer aus als die Deformierung des oberen Schaufelträgerteils 4a, da das obere Schaufelträgerteil 4a regelmäßig stärker mit dem Gehäuse 5 verbunden ist, was zu einer Aussteifung des oberen Schaufelträgerteils 4a führt.The two blade carrier parts 4a and 4b abut each other in the circumferential direction at circumferential ends 14 and 15. Due to the thermal load of the blade carrier 4, it comes to an ovalization, in the Fig. 3a and 3b is strongly indicated. On the one hand, in such an ovalization according to Fig. 3a form a kind of constriction in the region of the parting line 7, which arises because the abutting circumferential ends 14 and 15 to move along the parting line 7, which is accompanied by a reduction of the bending radius of the blade carrier parts 4a and 4b. On the other hand, the ovalization according to Fig. 3b also lead to the abutting circumferential ends 14 and 15 along the parting plane 7 from each other. This is equivalent to the fact that the bending radius of the blade carrier parts 4a, 4b increases. This ovalization leads at the same time to a distortion of the blade carrier 4. Furthermore, as a rule, the deformation of the lower blade carrier part 4b is significantly greater than that Deformation of the upper blade carrier part 4a, since the upper blade carrier part 4a is regularly more strongly connected to the housing 5, which leads to a stiffening of the upper blade carrier part 4a.

Die Fig. 4a bis 4c zeigen vergrößerte Schnittansichten durch eine der Nuten 9 oder 10, in welche einer der Flansche 12 oder 13 eingreift. Dabei ist die Krümmung, die sich in Umfangsrichtung 3 ergibt, stark übertrieben dargestellt. Erkennbar ist, dass in einer unverformten Ausgangsstellung gemäß Fig. 4a die Nut 9, 10 dieselbe Krümmung besitzt wie der Flansch 12, 13, so dass entlang des Flansches 12, 13 eine gleichmäßige Kontaktierung mit dem Schaufelträger 4 stattfindet. Die gleichzeitige Kontaktierung ist hier zur besseren Veranschaulichung durch ein Spiel 21 repräsentiert, das radial außen und radial innen im Idealfall gleich groß ist.The Fig. 4a to 4c show enlarged sectional views through one of the grooves 9 or 10, in which one of the flanges 12 or 13 engages. The curvature that results in the circumferential direction 3, greatly exaggerated. It can be seen that in an undeformed starting position according to Fig. 4a the groove 9, 10 has the same curvature as the flange 12, 13, so that along the flange 12, 13 takes place a uniform contact with the blade carrier 4. The simultaneous contacting is represented here for better illustration by a game 21, which is radially equal to the outside and radially in the ideal case ideally.

Bei einer Ovalisierung entsprechend Fig. 3b entsteht im Bereich der Nut 9, 10 eine Deformierung entsprechend Fig. 4b, die dazu führt, dass der jeweilige Flansch 12, 13 radial innen im Bereich seiner Endabschnitte 14, 15 sowie radial außen im Bereich seines Mittelabschnitts 16 extrem stark auf Druck belastet wird, was durch entsprechende Pfeile 17 angedeutet ist. Das zuvor genannte Spiel 21 verschwindet in diesen Bereichen.In an ovalization accordingly Fig. 3b arises in the region of the groove 9, 10 a deformation accordingly Fig. 4b which causes the respective flange 12, 13 to be subjected to an extremely high degree of pressure radially inward in the region of its end sections 14, 15 and radially outwardly in the region of its middle section 16, which is indicated by corresponding arrows 17. The aforementioned game 21 disappears in these areas.

Bei einer Ovalisierung entsprechend Fig. 3a kommt es zu dem in Fig. 4c wiedergegebenen Verformungszustand, bei dem der jeweilige Flansch 12, 13 radial innen im Bereich seines Mittelabschnitts 16 und radial außen im Bereich seiner Endabschnitte 14, 15 extremen Druckbelastungen ausgesetzt ist, die wieder durch Pfeile 17 angedeutet sind. Auch in diesem Fall verschwindet das oben genannte Spiel 21. Dabei ist klar, dass ein derartiges Spiel 21 im tatsächlichen Einbauzustand nicht vorhanden sein muss, Es dient hier lediglich zur Erläuterung der sich einstellenden Verformungen und Belastungen.In an ovalization accordingly Fig. 3a it comes to that in Fig. 4c reproduced deformation state in which the respective flange 12, 13 radially inward in the region of its central portion 16 and radially outside in the region of its end portions 14, 15 exposed to extreme pressure loads, which are again indicated by arrows 17. In this case, the above-mentioned game 21 disappears. It is clear that such a game 21 does not have to be present in the actual installed state, it serves only to explain the self-adjusting deformations and loads.

In Fig. 5 ist der Schaufelträger 4 einmal mit durchgezogener Linie in einem üblicherweise im Betrieb entstehenden verformten Zustand und mit unterbrochener Linie in einem unverformten Ausgangszustand wiedergegeben, der sich bei kalter Strömungsmaschine einstellt.In Fig. 5 is the blade carrier 4 once shown by a solid line in a deformed state usually resulting in operation and with a broken line in an undeformed initial state, which occurs in cold turbomachine.

Fig. 6 zeigt einen Axialschnitt durch den Fuß 11 einer Schaufel 2 bzw. einer Schaufelgruppe 6, wobei auch hier zwei unterschiedliche Betriebszustände wiedergegeben sind. Schraffiert ist der Schnitt im normalen Betriebszustand, also bei heißer Strömungsmaschine. Im Unterschied dazu ist ein unverformter Ausgangszustand, der sich bei kalter Strömungsmaschine einstellt, unschraffiert wiedergegeben. Erkennbar ist, dass sich der anströmseitige Einlassflansch 12 um einen Winkel α verkippen kann, während sich der abströmseitige Auslassflansch 13 um einen Winkel β verkippen kann. Erschwerend kommt hinzu, dass die beiden Winkel α und β unterschiedlich groß ausfallen können. In Fig. 6 sind die Deformationen wieder übertrieben deutlich wiedergegeben und sind insbesondere nicht maßstäblich zu nehmen. Fig. 6 shows an axial section through the foot 11 of a blade 2 and a blade group 6, wherein also here two different operating states are shown. Hatched is the cut in the normal operating state, ie with a hot turbomachine. In contrast, an undeformed initial state, which occurs in cold turbomachine, unhatched reproduced. It can be seen that the inlet-side inlet flange 12 can tilt by an angle α, while the downstream-side outlet flange 13 can tilt by an angle β. To make matters worse, that the two angles α and β can vary in size. In Fig. 6 the deformations are exaggerated again clearly and in particular are not to scale.

Fig. 7 zeigt nun eine anströmseitige Axialansicht auf den Schaufelfuß 11 der Schaufelgruppe 6. Der dem Betrachter zugewandte Einlassflansch 12 ist dabei weiter unten, also radial weiter innen, angeordnet, als der vom Betrachter abgewandte und an sich verdeckte Auslassflansch 13, der weiter oben, also radial weiter außen, angeordnet ist. Aus der Anordnung der Flansche 12, 13 ergibt sich, dass es sich hierbei um eine Schaufelgruppe 6 einer Turbine handeln muss. Fig. 7 now shows an inflow-side axial view of the blade root 11 of the blade group 6. The viewer facing inlet flange 12 is further down, so radially further inside, arranged as the viewer facing away from and concealed outlet flange 13, the further up, ie radially on outside, is arranged. From the arrangement of the flanges 12, 13 it follows that this must be a blade group 6 of a turbine.

Erfindungswesentlich ist nun, dass die Flansche 12 und 13 an ihren radialen Seiten so bearbeitet sind, dass sie in den zugehörigen Nuten 9, 10 den Schaufelträger 4 in ausgewählten Kontaktzonen, die im folgenden noch näher erläutert werden, kontaktieren. Die Kontaktzonen sind in den Fig. 7 bis 9 mit größerer Strichstärke angedeutet und mit 18 bezeichnet. Des Weiteren deuten Pfeile 19 an, wo im Einbauzustand eine Kraftübertragung zwischen Schaufelfuß 11 und Schaufelträger 4 stattfindet.It is now essential to the invention that the flanges 12 and 13 are machined on their radial sides so that they contact the blade carrier 4 in the associated grooves 9, 10 in selected contact zones, which will be explained in more detail below. The contact zones are in the Fig. 7 to 9 With greater line width indicated and designated 18. Furthermore, arrows 19 indicate where in the installed state a force transmission between blade root 11 and blade carrier 4 takes place.

Erfindungsgemäß sind die Kontaktzonen 18 wie folgt verteilt:According to the invention, the contact zones 18 are distributed as follows:

Einer der Flansche 12, 13, hier der abströmseitige Auslassflansch 13, ist sowohl an seinem vorderen Endabschnitt 14 als auch an seinem hinteren Endabschnitt 15, sowohl radial innen als auch radial außen jeweils mit einer derartigen Kontaktzone 18 ausgestattet, die im Einbauzustand am Schaufelträger 4, also innerhalb der Auslassnut 10 radial anliegen. Für den Auslassflansch 13 ergibt sich somit eine Art 4-Punkt-Lagerung. Im Unterschied dazu ist hier der Einlassflansch 12 nur an dem einen Endabschnitt, hier am vorderen Endabschnitt 14, radial außen mit einer solchen Kontaktzone 18 versehen, die im Einbauzustand am Schaufelträger 4 anliegt, während er radial innen so geformt ist, dass der Endabschnitt 14 im Einbauzustand vom Schaufelträger 4 beabstandet ist. Des Weiteren ist der Einlassflansch 12 an seinem anderen Endabschnitt, also hier am hinteren Endabschnitt 15 radial innen mit einer derartigen Kontaktzone 18 ausgestattet, die im Einbauzustand am Schaufelträger 4 anliegt, während er radial außen so geformt ist, dass der hintere Endabschnitt 15 im Einbauzustand vom Schaufelträger 4 beabstandet ist. Insoweit ergibt sich für den Einlassflansch 12 eine Art 2-Punkt-Lagerung. Dabei sind die beiden Kontaktzonen 18 und dementsprechend die beiden nicht näher bezeichneten Abstandszonen bezüglich der Endabschnitte 14 und 15 einander diametral gegenüberliegend am Einlassflansch 12 angeordnet.One of the flanges 12, 13, in this case the outflow-side outlet flange 13, is provided both at its front end section 14 and at its rear end section 15, both radially inward and radially outwardly, with such a contact zone 18 which in the installed state on the blade carrier 4, So lie radially within the Auslaßnut 10. For the outlet flange 13 thus results in a kind of 4-point storage. In contrast, here the inlet flange 12 is provided only at one end portion, here at the front end portion 14, radially outwardly with such a contact zone 18 which rests in the installed state on the blade carrier 4, while radially inwardly formed so that the end portion 14 in Installation state is spaced from the blade carrier 4. Furthermore, the inlet flange 12 is provided at its other end portion, so here at the rear end portion 15 radially inwardly with such a contact zone 18 which rests in the installed state on the blade carrier 4, while radially outwardly shaped so that the rear end portion 15 in the installed state of Blade carrier 4 is spaced. In that regard, results for the inlet flange 12 is a kind of 2-point storage. In this case, the two contact zones 18 and accordingly the two unspecified distance zones with respect to the end sections 14 and 15 are arranged diametrically opposite one another on the inlet flange 12.

Durch diese erfindungsgemäß vorgeschlagene Bauweise erhält die Anbindung des Schaufelfußes 11 an den Schaufelträger 4 definierte Freiheitsgrade, die bei den typischen Verformungen des Schaufelträgers 4, die dieser bei transienten Betriebzuständen thermisch bedingt durchführt, eine Reduzierung der Kraftübertragung zwischen Schaufelträger 4 und Schaufelfuß 11 bewirken. Auf diese Weise werden die Schaufelfüße 11 und somit die Schaufeln 2 bzw. die Schaufelgruppen 6 weniger stark durch die Verformungen des Schaufelträgers 4 belastet.As a result of this design proposed according to the invention, the connection of the blade root 11 to the blade carrier 4 is given defined degrees of freedom which, in the case of the typical deformations of the blade carrier 4, which it thermally effects in transient operating conditions, results in a reduction of the blade carrier Force transmission between blade carrier 4 and blade root 11 effect. In this way, the blade roots 11 and thus the blades 2 or the blade groups 6 are less heavily loaded by the deformations of the blade carrier 4.

Wie bereits weiter oben erläutert, ist es dabei von Vorteil, wenn die Endabschnitte 14, 15 und somit die daran ausgebildeten Kontaktzonen 18 in Umfangsrichtung 3 relativ weit voneinander beabstandet sind. Dementsprechend ist der Mittelabschnitt 16 in Umfangsrichtung 3 vergleichsweise groß dimensioniert, insbesondere gleich groß wie oder größer als die beiden Endabschnitte 14, 15 zusammen.As already explained above, it is advantageous if the end portions 14, 15 and thus the contact zones formed thereon 18 in the circumferential direction 3 are relatively far apart. Accordingly, the central portion 16 in the circumferential direction 3 is dimensioned comparatively large, in particular equal to or greater than the two end portions 14, 15 together.

Die Kontaktzonen 18 können außerdem gezielt so gefertigt sein, dass sich eine linienförmige Anlage oder Kontaktierung am Schaufelträger 4 ergibt, die beispielsweise radial oder in Umfangsrichtung orientiert sein kann. Ebenso können die Kontaktzonen 18 auch so ausgestaltet sein, dass sich punktförmige Kontaktierungen mit dem Schaufelträger 4 ergeben.The contact zones 18 can also be made specifically so that there is a linear contact or contact on the blade carrier 4, which may be oriented, for example, radially or in the circumferential direction. Likewise, the contact zones 18 can also be designed so that point-like contacts with the blade carrier 4 result.

Besonders vorteilhaft ist eine Ausgestaltung, die für die Anbindung der Schaufelfüße 11 am Schaufelträger 4 die gewünschten Freiheitsgrade im wesentlichen nur dann bereitstellt, wenn sich der Schaufelträger 4, beispielsweise aufgrund transienter Betriebszustände der Strömungsmaschine, verformt, während die genannten zusätzlichen Freiheitsgrade zu Gunsten einer erhöhten Abstützung entfallen können, wenn sich die Strömungsmaschine in einem Nenn- oder Normalbetrieb befindet. Zweckmäßig können daher die Abstände beim Einlassflansch 12 im Bereich der Endabschnitte 14 und 15 gegenüber dem Schaufelträger 4 so dimensioniert sein, dass eine Druckdifferenz zwischen Anströmseite und Abströmseite des jeweiligen Leitschaufelrings 1, die sich im Normalbetrieb der Strömungsmaschine einstellt, eine elastische Biegeverformung der Schaufeln 2 bzw. der Schaufelgruppe 6 und/oder des Schaufelträgers 4 erzwingt, welche die genannten Abstände reduziert, und zwar vorzugsweise so weit, dass die entsprechenden Endabschnitte 14 und 15 dann ebenfalls am Schaufelträger 4 zur Anlage kommen. Im Belastungszustand sind dann die genannten zusätzlichen Freiheitsgrade aufgehoben. Bei transienten Zuständen sinkt die genannte Druckdifferenz, wodurch die Endabschnitte 14 und 15 wieder vom Schaufelträger 4 abheben, um die Freiheitsgrade wieder herzustellen, welche die Spannungen im Schaufelfuß 11 bei den Verformungen des Schaufelträgers 4 reduzieren.Particularly advantageous is an embodiment that provides the desired degrees of freedom substantially only for the connection of the blade roots 11 on the blade carrier 4, when the blade carrier 4, for example due to transient operating conditions of the turbomachine, deformed, while said additional degrees of freedom in favor of increased support can be omitted if the turbomachine is in a nominal or normal operation. Appropriately, therefore, the distances between the inlet flange 12 in the region of the end sections 14 and 15 relative to the blade carrier 4 can be dimensioned so that a pressure difference between inflow side and downstream side of the respective guide vane ring 1, which occurs during normal operation of the turbomachine, an elastic bending deformation of the blades 2 and of the blade group 6 and / or the blade carrier 4, which reduces said distances, and preferably so far that the corresponding end portions 14 and 15 then also come to rest on the blade carrier 4. In the load state then the said additional degrees of freedom are canceled. In transient conditions, said pressure difference decreases, whereby the end portions 14 and 15 lift off the blade carrier 4 again to restore the degrees of freedom, which reduce the stresses in the blade root 11 in the deformations of the blade carrier 4.

Obwohl im vorliegenden Beispiel der Einlassflansch 12 mit zwei Kontaktzonen 18 und der Auslassflansch 13 mit vier Kontaktzonen 18 ausgestattet sind, kann die Verteilung der Kontaktzonen 18 auch umgekehrt sein. Ebenso kann die Verteilung der Kontaktzonen 18 bei dem mit nur zwei Kontaktzonen 18 ausgestatteten Flansch 12 an den beiden Endabschnitten 14, 15 bezüglich der Anordnung innen und außen umgekehrt sein.Although in the present example the inlet flange 12 is provided with two contact zones 18 and the outlet flange 13 is provided with four contact zones 18, the distribution of the contact zones 18 may also be reversed. Likewise, the distribution of the contact zones 18 in the case of the flange 12 equipped with only two contact zones 18 at the two end sections 14, 15 can be reversed with respect to the arrangement inside and outside.

Entsprechend Fig. 2 können die Schaufeln 2 radial innen über Deckbänder 20 miteinander verbunden sein und im montierten Zustand in Umfangsrichtung aneinander abgestützt sein.Corresponding Fig. 2 For example, the blades 2 may be connected radially inwardly via shrouds 20 and be supported in the circumferential direction in the mounted state.

Im folgenden wird ein erfindungsgemäßes Verfahren zum Modifizieren eines herkömmlichen Laufschaufelrings näher erläutert:In the following, a method according to the invention for modifying a conventional blade ring is explained in more detail:

Zunächst werden die Schaufeln 2 bzw. die Schaufelgruppen 6 aus dem Schaufelträger 4 ausgebaut. Die ausgebauten Schaufelgruppen 6 können im Bereich des Schaufelfußes 11 beispielsweise wie in Fig. 8 ausgestaltet sein. Das bedeutet, dass sowohl der Einlassflansch 12 als auch der Auslassflansch 13 sowohl am vorderen Endabschnitt 14 als auch am hinteren Endabschnitt 15 sowohl radial innen als auch radial außen jeweils mit einer Kontaktzone 18 bzw. 18' ausgestattet ist. Eine ausgebaute Schaufel 2 kann beispielsweise im Bereich ihres Schaufelfußes 11 wie in Fig. 9 ausgestaltet sein und dementsprechend eine besondere Verteilung von Kontaktzonen 18 bzw. 18' aufweisen.First, the blades 2 or the blade groups 6 are removed from the blade carrier 4. The dismantled blade groups 6 can in the region of the blade root 11, for example, as in Fig. 8 be designed. This means that both the inlet flange 12 and the outlet flange 13 both at the front end portion 14 and at the rear end portion 15 both radially inwardly and radially outwardly each with a contact zone 18 and 18 'is equipped. A developed blade 2 can, for example, in the region of its blade root 11 as in Fig. 9 be configured and accordingly have a particular distribution of contact zones 18 and 18 '.

In einem weiteren Verfahrensschritt werden nun bei den ausgebauten Schaufeln 2 bzw. bei den ausgebauten Schaufelgruppen 6 die Flansche 12 und 13 der Schaufelfüße 11 bearbeitet.In a further method step, the flanges 12 and 13 of the blade roots 11 are now processed in the removed blades 2 or in the removed blade groups 6.

Bei einer Schaufelgruppe 6 gemäß Fig. 8 wird beispielsweise mittels eines Fräsers oder dgl. am Einlassflansch 12 an dessen vorderen Endabschnitt 14 die radial innere Kontaktzone 18' entfernt. Ebenso wird beim Einlassflansch 12 an dessen hinteren Endabschnitt 15 die radial äußere Kontaktzone 18' entfernt. In der Folge besitzt dann der bearbeitete Schaufelfuß 11 im Bereich seiner Flansche 12, 13 die gleiche Gestalt wie der erfindungsgemäß ausgebildete Schaufelfuß 11 gemäß Fig. 7.For a blade group 6 according to Fig. 8 For example, by means of a milling cutter or the like. At the inlet flange 12 at the front end portion 14, the radially inner contact zone 18 'is removed. Likewise, at the inlet flange 12 at its rear end portion 15, the radially outer contact zone 18 'is removed. As a result, the machined blade root 11 in the region of its flanges 12, 13 then has the same shape as the blade root 11 designed according to the invention Fig. 7 ,

Beim Schaufelfuß 11 gemäß Fig. 9 sind die beiden radial außen liegenden Seiten der Flansche 12 und 13 jeweils als durchgehende Kontaktzonen 18' ausgebildet. Des Weiteren besitzt der Auslassflansch 13 radial innen nur eine einzige Kontaktzone 18', die außerdem im Mittelabschnitt 16 angeordnet ist. Die Bearbeitung dieses Schaufelfußes 11 erfolgt dabei so, dass beim Auslassflansch 13 an der radial außen liegenden Seite der Mittelabschnitt 16 so weit abgetragen wird, dass nur noch in den Endabschnitten 14 und 15 jeweils eine der gewünschten Kontaktzonen 18 übrig bleibt. Des Weiteren wird an der radial innen liegenden Seite die Kontaktzone 18' im Mittelabschnitt 16 durch entsprechenden Materialabtrag entfernt. Außerdem wird radial innen an den Endabschnitten 14 und 15 durch einen geeigneten Materialauftrag, z. B. durch Schweißen oder Löten, jeweils die gewünschte innen liegende Kontaktzone 18 geschaffen, um auch hier eine entsprechende Formgebung zu erhalten, wie sie in Fig. 7 wiedergegeben ist.At the blade root 11 according to Fig. 9 the two radially outer sides of the flanges 12 and 13 are each formed as a continuous contact zones 18 '. Furthermore, the outlet flange 13 has radially inside only a single contact zone 18 ', which is also arranged in the central portion 16. The machining of this blade root 11 takes place in such a way that at the outlet flange 13 on the radially outer side of the central portion 16 is removed so far that only one of the desired contact zones 18 remains only in the end portions 14 and 15. Furthermore, on the radially inner side, the contact zone 18 'in the middle section 16 is removed by appropriate material removal. In addition, radially inward at the end portions 14 and 15 by a suitable material application, for. B. by welding or soldering, respectively, the desired inner contact zone 18th created in order to obtain an appropriate shape here, as in Fig. 7 is reproduced.

Der Einlassflansch 12 wird hier so bearbeitet, dass die im vorderen Endabschnitt 14 vorgesehene, radial innen liegende Kontaktzone 18' vollständig entfernt wird. Des Weiteren wird die radial außen vorhandene, durchgehende Kontaktzone 18' radial außen im Bereich des Mittelabschnitts 16 sowie im Bereich des hinteren Endabschnitts 15 so weit abgetragen, bis sich die in Fig. 7 wiedergegebene Gestalt ergibt. Somit kann auch bei dem in Fig. 9 wiedergegebenen Schaufelfußtyp die in Fig. 7 wiedergegebene erfindungsgemäße Kontur hergestellt werden.The inlet flange 12 is here processed so that the provided in the front end portion 14, radially inward contact zone 18 'is completely removed. Furthermore, the radially outer, continuous contact zone 18 'is removed radially outward in the region of the middle section 16 and in the region of the rear end section 15 until the in Fig. 7 reproduced shape results. Thus, even with the in Fig. 9 reproduced blade foot type in Fig. 7 reproduced inventive contour can be produced.

Insgesamt eignet sich somit das hier gezeigte Verfahren in besonderer Weise zur Umrüstung eines herkömmlichen Leitschaufelrings in den erfindungsgemäßen Leitschaufelring 1, dessen Schaufeln 2 die Verformungen des Schaufelträgers 4 besser aufnehmen können.Overall, therefore, the method shown here is particularly suitable for retrofitting a conventional vane ring in the guide vane ring 1 according to the invention, the blades 2 can absorb the deformations of the blade carrier 4 better.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Leitschaufelringvane ring
22
Schaufelshovel
33
Umfangsrichtungcircumferentially
44
Schaufelträgerblade carrier
4a4a
oberer Schaufelträgerteilupper blade carrier part
4b4b
unterer Schaufelträgerteillower blade carrier part
55
Gehäusecasing
66
Schaufelgruppescoop group
77
Trennebeneparting plane
88th
Längsmittelachse/RotationsachseLongitudinal center axis / axis of rotation
99
Einlassnutinlet groove
1010
Auslassnutexhaust groove
1111
Schaufelfußblade
1212
Einlassflanschinlet flange
1313
Auslassflanschoutlet flange
1414
vorderer Endabschnittfront end section
1515
hinterer Endabschnittrear end section
1616
Mittelabschnittmidsection
1717
Druckbelastungpressure load
1818
Kontaktzonecontact zone
1919
Druckbelastungpressure load
2020
Deckbandshroud
2121
Spielgame

Claims (7)

  1. Guide vane ring of a turbomachine, comprising
    - a number of vanes (2) which can be fastened individually or in groups (6) comprising a plurality of vanes (2) on an annular vane carrier (4) which can itself be fastened to a casing (5) of the turbomachine,
    - the vane carrier (4) having an inflow-side inlet groove (9) and an outflow-side outlet groove (10),
    - the grooves (9, 10) extending in the circumferential direction (3),
    - the vane (2) or the vane group (6) having in each case a vane root (11) which has an inflow-side inlet flange (12) and an outflow-side outlet flange (13),
    - the flanges (12, 13) extending in the circumferential direction (3) and projecting axially from the respective vane root (11),
    - in the mounted state, in the case of the vane root (11), the inlet flange (12) engaging into the inlet groove (9) and the outlet flange (13) into the outlet groove (10),
    - the flanges (12, 13), between their end portions (14, 15), being spaced apart in its mounted state from the vane carrier (4) both radially on the inside and radially on the outside,
    - the outside-flow flange (13) having both on a front end portion (14) in the circumferential direction (3) and in a rear end portion (15) in the circumferential direction (3), both radially on the inside and radially on the outside, in each case a contact zone (18) which in its mounted state bears against the vane carrier (4),
    characterized in that
    - the inflow-side flange (12) having on one end portion (15), radially on the inside, a contact zone (18) which in its mounted state bears against the vane carrier (4) and which is spaced apart from the vane carrier (4) radially on the outside, and having on the other end portion (14), radially on the outside, a contact zone (18) which in its mounted state bears against the vane carrier (4) and which is spaced apart from the vane carrier (4) radially on the inside.
  2. Guide vane ring according to Claim 1, characterized in that the two end portions (14, 15) of the respective flange (12, 13) are in the circumferential direction (3) approximately the same size as or smaller than a middle portion (16) arranged between the end portions (14, 15).
  3. Guide vane ring according to Claim 1 or 2, characterized in that, in the mounted state, the vanes (2) are connected to one another and/or supported against one another radially on the inside via shrouds (20).
  4. Guide vane ring according to one of Claims 1 to 3, characterized in that the contact zones (18) are configured such that linear or punctiform bearing contact against the vane carrier (4) is formed.
  5. Guide vane ring according to Claim 1, characterized in that the turbomachine is an axial-throughflow turbine or a compressor.
  6. Guide vane ring according to Claim 5, characterized in that the turbomachine is a gas turbine.
  7. Method for the modification of a guide vane ring (1) of a turbomachine, in particular of an axial-throughflow turbine or a compressor, in particular of a gas turbine,
    - in which vanes (2) and/or vane groups (6) comprising a plurality of vanes (2) are demounted from an annular vane carrier (4),
    - in which flanges (12, 13) of vane roots (11) of the demounted vanes (2) and/or of the demounted vane groups (6) are machined,
    - in which the machined vanes (2) and/or vane groups (6) are installed in the vane carrier (4) again,
    characterized in that
    the machining of the demounted vanes (2) and/or vane groups (6) takes place in such a way that, after the installation of the vanes (2) and/or vane groups (6), there is a guide vane ring (1) according to one of Claims 1 to 6.
EP05109944A 2004-10-26 2005-10-25 Vane ring assembly for gas turbines and method to modify the same Not-in-force EP1653049B1 (en)

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US7798775B2 (en) * 2006-12-21 2010-09-21 General Electric Company Cantilevered nozzle with crowned flange to improve outer band low cycle fatigue
US8096755B2 (en) * 2006-12-21 2012-01-17 General Electric Company Crowned rails for supporting arcuate components
US20100068050A1 (en) * 2008-09-12 2010-03-18 General Electric Company Gas turbine vane attachment
EP2236761A1 (en) * 2009-04-02 2010-10-06 Siemens Aktiengesellschaft Stator blade carrier
US8328511B2 (en) * 2009-06-17 2012-12-11 General Electric Company Prechorded turbine nozzle
ES2431290T3 (en) * 2010-02-03 2013-11-25 Alstom Technology Ltd Turbine guide blade
EP3147457B1 (en) * 2015-09-22 2019-01-30 Ansaldo Energia Switzerland AG Gas turbine comprising a guide vane and a guide vane carrier
CN106799569B (en) * 2017-01-19 2019-08-23 中国航发沈阳发动机研究所 A kind of combinational processing method of the stator blade on band sector installation side
EP3438416B1 (en) * 2017-08-04 2021-03-17 MTU Aero Engines GmbH Stator blade segment for a turbo engine

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DE1476928A1 (en) 1965-05-29 1969-07-31 Bergmann Borsig Veb Guide vane root for turbines with high inlet temperature
US5641267A (en) * 1995-06-06 1997-06-24 General Electric Company Controlled leakage shroud panel
US6183192B1 (en) 1999-03-22 2001-02-06 General Electric Company Durable turbine nozzle
DE10210866C5 (en) 2002-03-12 2008-04-10 Mtu Aero Engines Gmbh Guide vane mounting in a flow channel of an aircraft gas turbine

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DE502005009179D1 (en) 2010-04-22
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US20060251519A1 (en) 2006-11-09
EP1653049A1 (en) 2006-05-03

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