EP1697618B1 - Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator - Google Patents

Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator Download PDF

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Publication number
EP1697618B1
EP1697618B1 EP04797660A EP04797660A EP1697618B1 EP 1697618 B1 EP1697618 B1 EP 1697618B1 EP 04797660 A EP04797660 A EP 04797660A EP 04797660 A EP04797660 A EP 04797660A EP 1697618 B1 EP1697618 B1 EP 1697618B1
Authority
EP
European Patent Office
Prior art keywords
stator blade
stator
press
carrier
segment
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
EP04797660A
Other languages
German (de)
English (en)
Other versions
EP1697618A1 (fr
Inventor
Wilhelm Schulten
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP04797660A priority Critical patent/EP1697618B1/fr
Publication of EP1697618A1 publication Critical patent/EP1697618A1/fr
Application granted granted Critical
Publication of EP1697618B1 publication Critical patent/EP1697618B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the invention relates to an annular guide vane carrier with a plurality of guide vanes for a turbomachine for fastening the guide vanes according to
  • Gas turbines coupled to generators are used to convert fossil energy into electrical energy.
  • a gas turbine has along its rotor shaft in the flow direction of the gases to a compressor, a combustion chamber and a turbine unit.
  • the compressor draws in ambient air and compresses it.
  • the compressor air is mixed with a fuel and fed to the combustion chamber.
  • the mixture burns to a hot gaseous working medium and flows into the vaned turbine unit.
  • the vanes mounted on the housing of the turbine unit direct the working fluid onto the blades attached to the rotor so as to cause the rotor to rotate.
  • the thus recorded rotational energy of the rotor is converted by the generator coupled to the rotor into electrical energy. Furthermore, it is used to drive the compressor.
  • a compressor having a vane carrier as a housing for holding freestanding vanes.
  • a circumferential groove is provided with undercuts.
  • the housing is divided into two halves, so that when the housing is open, the guide vanes can be used for mounting in the divided circumferential groove and moved along it. Furthermore, it is described that intermediate pieces provided between the guide vanes are fixed by inserted documents.
  • the circumferential groove and the complementary Leitschaufelfborne the vanes are used with radial play in the circumferential groove.
  • the object of the invention is to provide a guide vane carrier with a plurality of guide vanes with reduced flow losses. Furthermore, it is the object of the invention to provide a method for mounting guide vanes on an annular guide vane carrier of a turbomachine thereto.
  • turbomachine task provides that aligned for each vane of the contact area and the support area in the radial direction of the rotor.
  • each vane or each Leitschaufelfuß is assigned at least one press segment.
  • a groove-shaped recess is provided in the groove bottom of the circumferential groove.
  • the pressing segments create a bias that presses the vane root against the undercuts of the circumferential groove so that the vane has a tight and secure fit with no play.
  • each press segment is supported in a support region in the recess and presses the guide blade foot unsprung against the undercut via a radially aligned contact region.
  • a resilient mounting of the guide vanes as for example from the aforementioned US 998,820 is known, is specifically avoided here.
  • all the press segments arranged in a recess adjoin one another in the circumferential direction to form a press segment ring, then all the press segments can be of identical construction and can be pushed one after the other one after the other for mounting. This reduces the manufacturing and assembly costs.
  • each pressing segment in the circumferential direction comprises at least two sections, wherein one of the sections in the radial direction has an excess to form the bias voltage.
  • the recess has an inner support region as an abutment on which the press segment is supported.
  • the oversize is slightly larger than the distance from the vane root to the inner support area.
  • Displacement in the circumferential direction of the assembled vanes is prevented when at least one securing element in the vane ring secures a vane against displacement in the circumferential direction.
  • platform elements are provided between two adjacent guide vanes of a guide vane ring.
  • the vane root can be made more compact and narrow, so that manufacturing processes such as forging or milling with little material use per blank are possible.
  • the platform element may additionally consist of a cheaper material, such as e.g. ST37, as the vane are made.
  • the turbomachine is a compressor.
  • the Fig. 5 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotational axis 2 rotor 3, which is also referred to as a turbine rotor or rotor shaft. Along the rotor 3 successively follow an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing. 9
  • annular compressor passage 10 is provided which extends in the direction of the annular combustion chamber 6 in cross section rejuvenated.
  • a diffuser 11 is arranged, which communicates with the annular combustion chamber 6 in flow communication.
  • the annular combustion chamber 6 forms a combustion chamber 12 for a mixture of a fuel and compressed air.
  • a hot gas duct 13 arranged in the turbine 8 is in flow communication with the combustion chamber 12, the exhaust gas casing 9 being arranged downstream of the hot gas duct 13.
  • blade rings are alternately arranged.
  • a stator blade ring 15 formed from guide vanes 14
  • a rotor blade ring 17 formed from rotor blades 16.
  • the stationary stator blades 14 are connected to a guide blade carrier 18, whereas the rotor blades 16 are connected to the rotor 3 by means of a disk 19.
  • the Fig. 1 shows a section through a vane support 18 and a freestanding vane 14.
  • the annular vane support 18 has on its the compressor passage 10 facing wall on an inner circumferential groove 21.
  • On the side walls 22 each formed by a projection 23 undercuts 24 are provided.
  • groove base 25 also two groove-shaped recesses 26 are arranged, the may also be formed as further circumferential grooves. The recesses 26 protrude into the guide blade carrier 18 with a radial depth which is greater than the width B of their opening in the groove base 25.
  • the vane 14 extends with its Leitschaufelfuß 27 in the circumferential groove 21 into it.
  • the guide blade root 27 is complementary to the undercuts 24 of the circumferential groove 21, ie T-shaped, formed so that the guide vane 14 is held in the circumferential groove 21.
  • a compressor channel 10 radially outwardly delimiting platform 29 is provided from which extends the freestanding airfoil profile 28 in the compressor passage 10 inside.
  • each press segments 30 are arranged, which presses the Leitschaufelfuß 27 with a bias to the projections 23 of the circumferential groove 21.
  • Fig. 2 shows the vane support 18 and the vane 14 according to section II-II of Fig. 1 , Between two adjacent vanes 14 of a vane ring 15, a platform member 32 is provided which limits the compressor duct 10 radially outward. In this case, the platform element 32 is hooked analogously to a guide blade foot 27 in the circumferential groove 21.
  • the pressing segment 30 abuts against the supporting wall 40 with a supporting region 31. Radially further inside, the pressing segment 30 points into a first section 34 (FIG. Figure 4 ) on its side facing the guide blade root 27, a contact region 33 which bears against the guide blade root 27 and presses against the projections 23; Supporting region 31 and contact region 33 lie on a radius for each guide blade (14, 16) and are aligned.
  • a second section 35 (FIG. Fig. 4 ) is a surface 36 which springs back relative to the contact region 33, the Platform element 32 facing. In the operating position, the surface 36 of the rear side of a side facing the guide blade 14 of the platform member 32 is contactless or with only comparatively low bias against.
  • Fig. 3 shows a cut through Fig. 1 according to the section plane III-III. Between two guide vanes 14, the platform element 32 is arranged.
  • the circumferential groove 21 extends in the circumferential direction U, wherein on the side walls 22, the undercuts 24 are shown.
  • groove base 25 are two recesses 26 with Abstütz alloyn 40.
  • left recess 26 is a press segment 30 is arranged, the surface 36 is shown.
  • the platform element 32 has, on an end face facing the guide blade 14, a recess 37 into which a tool with a lever can be inserted in order to push the guide blade 14 away from the contact region 33 in the direction of the surface 36 for disassembly.
  • every third platform element 32 can be fixed by a securing element 38, which is introduced into a further recess 39 of the downstream side of the guide vane 14.
  • the pressing segments 30 and securing elements 38 are located between the guide blade carrier 18 and the guide vanes 14 or the platform elements 32, so that they can not get into the compressor channel 10.
  • Fig. 4 shows the pressing segment 30 with the first portion 34 and the second portion 35.
  • the contact portion 33 is spaced from the opposite support portion 31 at a distance B 1 .
  • the surface 36 to the opposite rear side in another Distance B 2 spaced.
  • the distance B 1 is greater than the distance B 2 .
  • the curvature of the pressing segment 30 in the circumferential direction is not darg Nurse here.
  • the distance B 1 corresponds to a distance S ( Fig.1 ) measured between the support portion 31 and the vane root plus an oversize of about 0.3 mm.
  • the section 35 without oversize has a distance B 2 which can correspond approximately to the distance S.
  • a press segment 30 is first introduced into each groove-shaped recess 26. Either then the vane 14 can be introduced by radially in-moving into the circumferential groove 21 with subsequent rotation, so that the provided on the guide blade root 27 T-shaped projections engage behind the undercut 24. Or they are inserted into the circumferential groove 21, if this has a suitable opening, such as the parting line of the housing. Subsequently, the guide blade 14 is displaced in the direction of the free pressing segments 30 until the guide blade root 27 covers the surface 36 of the pressing segments 30 and abuts against the protruding contact region 33.
  • the guide blade 14 With a tool and with increased force, the guide blade 14 can now be pushed over the contact area 33 until the Leitschaufelfuß 27 completely covers the contact area 33. In this case, a part of the excess of the Leitschaufelfuß 27 is abraded. The prevailing in the press segment 30 bias then presses the Leitschaufelfuß 27 from the outside against the undercut 24 of the circumferential groove 21. Thus, a secure and predetermined position of the guide vane 14 is given.
  • a construction without platform elements 32 is also conceivable if the platforms 29 of the guide vanes 14 in the circumferential direction U are configured so wide that they fill the space bridged by the platform elements 32.
  • the pressing segments 30 remain unchanged.

Landscapes

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

Claims (11)

  1. Support ( 18 ) annulaire d'aube directrice pour la fixation d'aubes ( 14, 16 ) directrices d'une turbomachine, ayant plusieurs aubes ( 14, 16 ) directrices s'étendant radialement à une même distance angulaire rapportée à un rotor ( 3 ) et ayant des emplantures ( 27 ) d'aubes directrices qui se trouvent vers l'extérieur, qui forment des aubes ( 14, 16 ) directrices d'un anneau ( 15 ) d'aubes directrices,
    sur lequel les emplantures ( 27 ) d'aubes directrices sont maintenues dans une rainure ( 21 ) périphérique intérieure ayant des contre dépouilles ( 24 ) qui peuvent être accrochées par les emplantures ( 27 ) d'aubes directrices, ainsi que
    ayant au moins un évidement ( 26 ) en forme de rainure dans le fond ( 25 ) de la rainure ( 21 ) périphérique, s'étendant le long de son pourtour et ayant au moins un segment ( 30 ) annulaire de pression, qui y est disposé et qui appuie sous précontrainte ( 23 ) sur les emplantures ( 27 ) d'aubes directrices
    le segment de pression s'appuyant radialement, considéré de l'extérieur, dans l'évidement ( 26 ) en forme de rainure, dans une zone ( 31 ) d'appui et s'appliquant à l'emplanture ( 17 ) d'aubes directrices, considérée radialement, vers l'intérieur, avec formation d'une zone de contact,
    caractérisé
    en ce que le segment ( 30 ) de pression sert d'appui, sans suspension, aux aubes ( 14, 15 ) directrices et
    en ce que pour chaque aube ( 14, 16 ) directrice, la zone de contact et la zone ( 31 ) d'appui sont alignées considérées dans la direction radiale du rotor ( 3 ).
  2. Support ( 18 ) d'aubes directrices suivant la revendication 1,
    caractérisé
    en ce qu'il est prévu dans le fond ( 25 ) de la rainure, deux évidements ( 26 ) en forme de rainure, dans lesquelles se trouvent respectivement des segments ( 30 ) de pression.
  3. Support ( 18 ) d'aubes directrices suivant la revendication 1,
    caractérisé
    en ce que les segments de pression d'un évidement ( 26 ), l'un à côté de l'autre dans la direction ( U ) périphérique, forment un anneau de segment de pression.
  4. Support ( 18 ) d'aubes directrices suivant l'une des revendications précédentes,
    caractérisé
    en ce que chaque segment ( 30 ) de pression comprend, dans la direction ( U ) périphérique au moins deux parties, au moins l'une des parties ayant dans la direction radiale, un surdimensionnement pour la formation de la précontrainte ( 23 ).
  5. Support ( 18 ) d'aubes directrices suivant la revendication 4,
    caractérisé
    en ce que la partie pourvue d'un surdimensionnement a une largeur ( B1 ), qui est plus grande que la distance de l'emplanture ( 27 ) de l'aube directrice à la zone ( 31 ) intérieure d'appui.
  6. Support ( 18 ) d'aubes directrices suivant l'une des revendications précédentes,
    caractérisé
    en ce que l'anneau ( 15 ) d'aubes directrices est empêché de se déplacer dans la direction ( U ) périphérique par au moins un élément ( 38 ) de blocage.
  7. Support ( 18 ) d'aubes directrices suivant l'une des revendications précédentes,
    caractérisé
    en ce que des éléments ( 32 ) de plateforme sont prévus respectivement entre deux aubes ( 14, 16 ) directrices voisines d'un anneau ( 15 ) d'aubes directrices.
  8. Support ( 18 ) d'aubes directrices suivant l'une des revendications précédentes,
    caractérisé
    en ce que les emplantures ( 27 ) d'aubes directrices et/ou les éléments ( 32 ) de plateforme ont un évidement ( 37, 38 ) pour le retrait.
  9. Turbomachine
    caractérisée en ce qu'elle est équipée d'un support ( 18 ) annulaire d'aubes directrices suivant l'une des revendications 1 à 8.
  10. Turbomachine suivant la revendication 9,
    caractérisée
    en ce qu'elle est constituée en compresseur ( 5 ).
  11. Procédé de montage d'aubes ( 14, 16 ) directrices dans un dispositif suivant l'une ou plusieurs des revendications 1 à 9, caractérisé
    en ce que pour monter chaque aube ( 14, 16 ) directrice sur le support ( 18 ) d'aubes directrices, on effectue les stades opératoires suivants :
    a) on introduit un segment ( 30 ) de pression dans un évidement ( 26 ), de manière à ce que sa partie pourvue d'un surdimensionnement soit tournée vers une aube ( 14, 16 ) directrice déjà montée,
    b) on déplace ensuite le segment de pression vers l'aube ( 14, 16 ) directrice montée, jusqu'à ce qu'il s'applique au segment de pression de l'aube ( 14, 16 ) directrice voisine,
    c) on introduit ensuite une aube ( 14, 16 ) directrice dans la rainure ( 21 ) périphérique et on la déplace en direction du segment ( 30 ) de pression, jusqu'à ce que son emplanture ( 27 ) de l'aube directrice s'applique à la partie pourvue d'un surdimensionnement,
    d) sous l'action d'une force, on déplace l'emplanture ( 27 ) de l'aube directrice au-dessus de la partie munie du surdimensionnement, jusqu'à ce que l'emplanture ( 27 ) de l'aube directrice s'applique à l'aube ( 14, 16 ) directrice déjà montée, de manière à ce qu'elle soit poussée sans suspension sur la contre dépouille ( 24 ) sous une précontrainte ( 23 ) produite par le segment ( 30 ) de pression.
EP04797660A 2003-12-23 2004-11-05 Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator Not-in-force EP1697618B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04797660A EP1697618B1 (fr) 2003-12-23 2004-11-05 Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03029771A EP1548232A1 (fr) 2003-12-23 2003-12-23 Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator
PCT/EP2004/012553 WO2005066463A1 (fr) 2003-12-23 2004-11-05 Turbomachine comportant un support a aubes directrices et procede de montage d'aubes directrices sur un support a aubes directrices
EP04797660A EP1697618B1 (fr) 2003-12-23 2004-11-05 Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator

Publications (2)

Publication Number Publication Date
EP1697618A1 EP1697618A1 (fr) 2006-09-06
EP1697618B1 true EP1697618B1 (fr) 2012-12-26

Family

ID=34530723

Family Applications (2)

Application Number Title Priority Date Filing Date
EP03029771A Withdrawn EP1548232A1 (fr) 2003-12-23 2003-12-23 Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator
EP04797660A Not-in-force EP1697618B1 (fr) 2003-12-23 2004-11-05 Stator et une pluralite d'aubes statoriques et procede de fixation d'aubes statoriques dans le stator

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP03029771A Withdrawn EP1548232A1 (fr) 2003-12-23 2003-12-23 Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator

Country Status (2)

Country Link
EP (2) EP1548232A1 (fr)
WO (1) WO2005066463A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7806655B2 (en) * 2007-02-27 2010-10-05 General Electric Company Method and apparatus for assembling blade shims
US8047778B2 (en) * 2009-01-06 2011-11-01 General Electric Company Method and apparatus for insuring proper installation of stators in a compressor case
US8133019B2 (en) * 2009-01-21 2012-03-13 General Electric Company Discrete load fins for individual stator vanes
CH703997A1 (de) * 2010-10-27 2012-04-30 Alstom Technology Ltd Schaufelanordnung, insbesondere Leitschaufelanordnung.
EP2679776A1 (fr) * 2012-06-28 2014-01-01 Alstom Technology Ltd Système de refroidissement et procédé pour turbine à flux axial
EP2851515A1 (fr) * 2013-09-24 2015-03-25 Siemens Aktiengesellschaft Agencement de fixation d'aubes de turbine
US9388704B2 (en) 2013-11-13 2016-07-12 Siemens Energy, Inc. Vane array with one or more non-integral platforms
EP2995775A1 (fr) * 2014-09-15 2016-03-16 Siemens Aktiengesellschaft Dispositif destiné à enfoncer une aube directrice dans une rainure d'aube
FR3048719B1 (fr) * 2016-03-14 2018-03-02 Safran Aircraft Engines Redresseur de flux pour turbomachine avec plateformes integrees et rapportees
US11125092B2 (en) 2018-08-14 2021-09-21 Raytheon Technologies Corporation Gas turbine engine having cantilevered stators

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US998820A (en) * 1908-05-13 1911-07-25 George Westinghouse Turbine-blading.
GB216737A (en) * 1923-08-02 1924-06-05 Karl Baumann Improvements relating to elastic fluid turbines
DE518106C (de) * 1924-02-18 1931-02-24 Jan Kieswetter Einrichtung zum Ausgleich verschiedener Waermeausdehnungen zwischen einer aeusseren Gehaeusewand und einer Zwischenwand des gleichen Gehaeuses, insbesondere bei Dampf- oder Gasturbinen
CH482915A (de) * 1967-11-03 1969-12-15 Sulzer Ag Leitvorrichtung für Axialturbine
IT1062412B (it) * 1976-06-15 1984-10-10 Nuovo Pignone Spa Sistema perfezionato di bloccaggio in posizione delle pale sulla casca statorica di un compressore assiale operante in ambiente pulverulento
US5205708A (en) * 1992-02-07 1993-04-27 General Electric Company High pressure turbine component interference fit up
DE4436731A1 (de) * 1994-10-14 1996-04-18 Abb Management Ag Verdichter

Also Published As

Publication number Publication date
WO2005066463A1 (fr) 2005-07-21
EP1697618A1 (fr) 2006-09-06
EP1548232A1 (fr) 2005-06-29

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