EP1653049B1 - Couronne d'aubes directrices pour turbines à gaz et procédé pour sa modification - Google Patents

Couronne d'aubes directrices pour turbines à gaz et procédé pour sa modification 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
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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)
English (en)
Other versions
EP1653049A1 (fr
Inventor
Bruno Benedetti
Andreas Boegli
Christopher Hulme
James Ritchie
Patrick Wolfgang Schnedler
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General Electric Technology GmbH
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Alstom Technology AG
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Filing date
Publication date
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Publication of EP1653049A1 publication Critical patent/EP1653049A1/fr
Application granted granted Critical
Publication of EP1653049B1 publication Critical patent/EP1653049B1/fr
Not-in-force legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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.

Claims (7)

  1. Couronne d'aubes directrices de turbomachine, comprenant :
    - une pluralité d'aubes (2) qui peuvent être fixées individuellement ou en groupes (6) constitués de plusieurs aubes (2) sur un support d'aubes de forme annulaire (4) qui pour sa part peut être fixé sur un boîtier (5) de la turbomachine,
    - le support d'aubes (4) présentant une rainure d'entrée (9) du côté de l'afflux et une rainure de sortie (10) du côté de l'échappement,
    - les rainures (9, 10) s'étendant dans la direction périphérique (3),
    - l'aube (2) ou le groupe d'aubes (6) présentant à chaque fois une base d'aube (11), qui présente une bride d'entrée (12) du côté de l'afflux et une bride de sortie (13) du côté de l'échappement,
    - les brides (12, 13) s'étendant dans la direction périphérique (3) et dépassant axialement de chaque base d'aube (11),
    - la bride d'entrée (12), dans l'état monté au niveau de la base d'aube (11) venant en prise dans la rainure d'entrée (9) et la bride de sortie (13) venant en prise dans la rainure d'échappement (10),
    - les brides (12, 13) étant espacées, dans l'état monté, entre leurs portions d'extrémité (14, 15) à la fois radialement à l'intérieur et radialement à l'extérieur du support d'aubes (4),
    - la bride (13) du côté de l'échappement présentant à la fois sur une portion d'extrémité avant (14), dans le sens périphérique (3), ainsi que dans une portion d'extrémité arrière (15), dans le sens périphérique (3), à la fois radialement à l'intérieur et radialement à l'extérieur à chaque fois une zone de contact (18) qui s'applique, dans l'état monté, contre le support d'aubes (4),
    caractérisée en ce que
    la bride (12) présente, sur l'une des portions d'extrémité (15), radialement à l'intérieur, une zone de contact (18) du côté de l'afflux, qui s'applique dans l'état monté contre le support d'aubes (4), et qui est espacée radialement à l'extérieur du support d'aubes (4), et présente sur l'autre portion d'extrémité (14), radialement à l'extérieur, une zone de contact (18) qui s'applique dans l'état monté contre le support d'aubes (4), et qui est espacée radialement à l'intérieur du support d'aubes (4).
  2. Couronne d'aubes directrices selon la revendication 1,
    caractérisée en ce que
    les deux portions d'extrémité (14, 15) de la bride respective (12, 13), dans la direction périphérique (3), sont approximativement égales ou inférieures à une portion centrale (16) disposée entre les portions d'extrémité (14, 15).
  3. Couronne d'aubes directrices selon la revendication 1 ou 2,
    caractérisée en ce que
    les aubes (2), dans l'état monté, sont connectées l'une à l'autre et/ou sont supportées l'une contre l'autre radialement à l'intérieur par le biais de bandes de recouvrement (20).
  4. Couronne d'aubes directrices selon l'une quelconque des revendications 1 à 3,
    caractérisée en ce que
    les zones de contact (18) sont configurées de telle sorte qu'un appui de forme linéaire ou ponctuel soit créé sur le support d'aubes (4).
  5. Couronne d'aubes directrices selon la revendication 1,
    caractérisée en ce que
    la turbomachine est une turbine à écoulement axial ou un compresseur.
  6. Couronne d'aubes directrices selon la revendication 5,
    caractérisée en ce que
    la turbomachine est une turbine à gaz.
  7. Procédé pour modifier une rangée d'aubes directrices (1) d'une turbomachine, notamment d'une turbine à écoulement axial ou d'un compresseur, notamment d'une turbine à gaz,
    - dans lequel des aubes (2) et/ou des groupes d'aubes (6) constitués de plusieurs aubes (2) sont démontés d'un support d'aubes de forme annulaire (4),
    - dans lequel des brides (12, 13) de bases d'aubes (11) des aubes démontées (2) et/ou des groupes d'aubes démontés (6) sont traitées,
    - dans lequel les aubes traitées (2) et/ou les groupes d'aubes traités (6) sont à nouveau montés dans le support d'aubes (4),
    caractérisé en ce que
    le traitement des aubes démontées (2) et/ou des groupes d'aubes démontés (6) s'effectue de telle sorte qu'après le montage des aubes (2) et/ou des groupes d'aubes (6), une couronne d'aubes directrices (1) selon l'une quelconque des revendications 1 à 6 soit produite.
EP05109944A 2004-10-26 2005-10-25 Couronne d'aubes directrices pour turbines à gaz et procédé pour sa modification Not-in-force EP1653049B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH17692004 2004-10-26

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EP1653049A1 EP1653049A1 (fr) 2006-05-03
EP1653049B1 true EP1653049B1 (fr) 2010-03-10

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US (1) US7458772B2 (fr)
EP (1) EP1653049B1 (fr)
AT (1) ATE460564T1 (fr)
DE (1) DE502005009179D1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8096755B2 (en) * 2006-12-21 2012-01-17 General Electric Company Crowned rails for supporting arcuate components
US7798775B2 (en) * 2006-12-21 2010-09-21 General Electric Company Cantilevered nozzle with crowned flange to improve outer band low cycle fatigue
US20100068050A1 (en) * 2008-09-12 2010-03-18 General Electric Company Gas turbine vane attachment
EP2236761A1 (fr) * 2009-04-02 2010-10-06 Siemens Aktiengesellschaft Support d'aube directrice
US8328511B2 (en) * 2009-06-17 2012-12-11 General Electric Company Prechorded turbine nozzle
ES2431290T3 (es) * 2010-02-03 2013-11-25 Alstom Technology Ltd Álabe de guía de turbina
EP3147457B1 (fr) 2015-09-22 2019-01-30 Ansaldo Energia Switzerland AG Turbine à gaz avec aube directrice et support d'aubes directrices
CN106799569B (zh) * 2017-01-19 2019-08-23 中国航发沈阳发动机研究所 一种带扇形安装边的静子叶片的组合加工方法
ES2865387T3 (es) * 2017-08-04 2021-10-15 MTU Aero Engines AG Segmento de paletas guía para una turbina

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1476928A1 (de) 1965-05-29 1969-07-31 Bergmann Borsig Veb Leitschaufelfuss fuer Turbinen mit hoher Eintrittstemperatur
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 (de) 2002-03-12 2008-04-10 Mtu Aero Engines Gmbh Leitschaufelbefestigung in einem Strömungskanal einer Fluggasturbine

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US20060251519A1 (en) 2006-11-09
ATE460564T1 (de) 2010-03-15
US7458772B2 (en) 2008-12-02
DE502005009179D1 (de) 2010-04-22
EP1653049A1 (fr) 2006-05-03

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