EP1306525B1 - Antirotation support system for the nozzle sector of a turbomachine - Google Patents

Antirotation support system for the nozzle sector of a turbomachine Download PDF

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Publication number
EP1306525B1
EP1306525B1 EP02292633A EP02292633A EP1306525B1 EP 1306525 B1 EP1306525 B1 EP 1306525B1 EP 02292633 A EP02292633 A EP 02292633A EP 02292633 A EP02292633 A EP 02292633A EP 1306525 B1 EP1306525 B1 EP 1306525B1
Authority
EP
European Patent Office
Prior art keywords
pin
holes
sector
inlet nozzle
guide vane
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.)
Expired - Lifetime
Application number
EP02292633A
Other languages
German (de)
French (fr)
Other versions
EP1306525A1 (en
Inventor
Serge Bongrand
Fabrice Marois
Alain Henri Daniel Bouron
Jacky Naudet
Sébastien Georges Roger Goux
Gabriel Radeljak
Dominique Raulin
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1306525A1 publication Critical patent/EP1306525A1/en
Application granted granted Critical
Publication of EP1306525B1 publication Critical patent/EP1306525B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • 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
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts

Definitions

  • the subject of this invention is a device for stopping in rotation a sector bearing vanes fixed in a shell forming part of a casing of a turbomachine.
  • the ferrules of the turbomachines are generally composed of two complementary sectors each extending over a half-turn and which are provided with a continuous circular rabbet for receiving stator sectors carrying fixed vanes and which extend over portions of circumference smaller.
  • This device as such leaves the sectors free to slide in the ferrule sliding together in the rabbet, which produces wear and noise during operation.
  • it is planned to add a rotation stop system for these sectors, which has already taken various forms in the known devices. It is first possible to place bars crossing the rabbets between the ferrule sectors, so as to stop the movement of the rectifier sectors.
  • This system is simple but has the disadvantage that it can not install more than two stop means in rotation: it therefore only partially remedies the anarchic movement of the blade sectors.
  • the invention relates to a rotation stop system of a very simple nature and which can equip at a lower cost an already existing machine that has the desire to improve.
  • This system applies individually to the rectifier sectors and thus ensures total immobility of the sectors if it is provided on each of them, without requiring excessive costs.
  • Another advantage of the invention is that the seal between the rectifier sectors is not compromised.
  • the rotational stop device comprises a pair of bores operated in extension in a rectifier sector and the shell respectively, as well as a pin engaged in the bores and means for holding the pin in the bores. holes.
  • the holes may in particular be operated through a rim of the rectifier sector and through a rabbet of the ferrule in which the rim is depressed.
  • the holding means then advantageously comprise a rod engaged under the rim in the rabbet and occupying a recess intersecting the pin; they may also include a tongue protruding from the pawn and abutting against the rectifier sector on one side, the ferrule on the other side.
  • the pin has a non-circular section and is fitted into a bore having a corresponding non-circular section.
  • FIG. 1 shows a portion of a ferrule 15 and a rectifier sector 16; the latter comprises an edge 17 directed in an axial direction engaged in a rebate 18 formed between a hook portion 19, bent in the other axial direction, and a cylindrical main portion 20 of the shell 15.
  • the shell 15 comprises a bore 21 passing through the hook portion 19, and the sector member 16 also includes a bore 22 intersecting the flange 17 and extending the bore 21; Figure 4 helps to better grasp the layout.
  • a pin 23 also seen in Figure 2 is engaged in the holes 21 and 22 and thus ensures the rotation stop sector 16 relative to the shell 15. It is retained in the holes 21 and 22 by a fastening ring 24 engaged at the bottom of the rabbet 18, under the rim 17, from a not shown orifice operated in the hook portion 19, and which passes through a recess 25 of the pin 23.
  • the accidental extraction of the pin 23 can still be prevented by a tongue 26 protruding from the pin 23 and abutting on one side against the ferrule and on the other side against a rectifier sector 16. This can be accomplished by joining the rectifier sector 16 to the ferrule after having put the pin 23 in place in the holes 21 and 22.
  • the ferrule 15 is joined to another ferrule 27 which is radially internal to it, the bore 21 opens on the lower side on the other ferrule 27, and the tongue 26 abuts against the Another ferrule 27, which does not change anything, however.
  • the ring 24 is then slid to the bottom of the rabbet 18; it can extend in front of a series of rectifier sectors 16 and retain as many counters 23.
  • FIG. 3 Another embodiment, whose implantation is also shown in Figure 4, appears in Figure 3 and comprises a pin 30 comprising a pair of side projections 31.
  • the pin 30 is, like the previous one, engaged in a hole 32 operated in a rim 33 of a rectifier sector 34, as well as in a bore 35 extending the former and operated here through the other ferrule 27.
  • the counter 30 When the other ferrule 27 and the rectifier sector 34 are assembled, the counter 30 having previously been engaged in the holes 32 and 35, they include a cavity 36 occupied by the projections 31 by preventing the pin 30 is extracted. This is the same mounting mode for the pins 23 and 30.
  • the pins 23 and 30 have non-circular portions such as plane facets 37 and 38, engaged in one of the holes 21, 22, 32 and 35 to prevent accidental rotation of the pin 23 or 30 which would interfere with the assembly. ; the holes in which these non-circular portions are engaged obviously have a section of complementary shape.
  • the ends of the pins can be tapered to facilitate their insertions in the holes; one of them bears the reference 39 for the pawn 30; it is shaped like a pyramid.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Component Parts Of Construction Machinery (AREA)

Description

Le sujet de cette invention est un dispositif d'arrêt en rotation d'un secteur porteur d'aubes fixes dans une virole faisant partie d'un carter d'une turbomachine.The subject of this invention is a device for stopping in rotation a sector bearing vanes fixed in a shell forming part of a casing of a turbomachine.

Les viroles des turbomachines sont généralement composées de deux secteurs complémentaires s'étendant chacun sur un demi-tour et qui sont munis d'une feuillure circulaire continue pour recevoir des secteurs de redresseur porteurs d'aubes fixes et qui s'étendent sur des portions de circonférence plus petites. Ce dispositif tel quel laisse les secteurs libres de coulisser dans la virole en glissant ensemble dans la feuillure, ce qui produit de l'usure et du bruit pendant le fonctionnement. C'est pourquoi on prévoit d'ajouter un système d'arrêt en rotation de ces secteurs, qui a déjà pris diverses formes dans les dispositifs connus. Il est d'abord possible de placer des barrettes croisant les feuillures entre les secteurs de virole, de façon à arrêter le mouvement des secteurs de redresseur. Ce système est simple mais présente l'inconvénient qu'on ne peut pas installer plus de deux moyens d'arrêt en rotation : il ne remédie donc que partiellement au mouvement anarchique des secteurs d'aubes.The ferrules of the turbomachines are generally composed of two complementary sectors each extending over a half-turn and which are provided with a continuous circular rabbet for receiving stator sectors carrying fixed vanes and which extend over portions of circumference smaller. This device as such leaves the sectors free to slide in the ferrule sliding together in the rabbet, which produces wear and noise during operation. This is why it is planned to add a rotation stop system for these sectors, which has already taken various forms in the known devices. It is first possible to place bars crossing the rabbets between the ferrule sectors, so as to stop the movement of the rectifier sectors. This system is simple but has the disadvantage that it can not install more than two stop means in rotation: it therefore only partially remedies the anarchic movement of the blade sectors.

On a encore prévu de lier individuellement les secteurs d'aubes à un carter extérieur par des tiges d'extension radiale, mais il est évident qu'une telle construction complique beaucoup la machine.It has also been planned to bind the blade sectors individually to an outer casing with rods of radial extension, but it is obvious that such a construction greatly complicates the machine.

Il est encore connu, comme indiqué dans le document US 2,955,800, de lier les secteurs d'aubes à un carter extérieur par des clés de verrouillage.It is still known, as indicated in US Pat. No. 2,955,800, to link the blade sectors to an outer casing by locking keys.

L'invention a pour objet un système d'arrêt en rotation de nature très simple et qui puisse équiper à moindre coût une machine déjà existante qu'on a le désir de perfectionner. Ce système s'applique individuellement aux secteurs de redresseur et assure donc une immobilité totale des secteurs s'il est prévu sur chacun d'eux, sans nécessiter de frais excessifs. Un autre avantage de l'invention est que l'étanchéité entre les secteurs de redresseur n'est pas compromise.The invention relates to a rotation stop system of a very simple nature and which can equip at a lower cost an already existing machine that has the desire to improve. This system applies individually to the rectifier sectors and thus ensures total immobility of the sectors if it is provided on each of them, without requiring excessive costs. Another advantage of the invention is that the seal between the rectifier sectors is not compromised.

Sous sa forme la plus générale, le dispositif d'arrêt en rotation comprend une paire de perçages opérés en prolongement dans un secteur de redresseur et la virole respectivement, ainsi qu'un pion engagé dans les perçages et des moyens de maintien du pion dans les perçages.In its most general form, the rotational stop device comprises a pair of bores operated in extension in a rectifier sector and the shell respectively, as well as a pin engaged in the bores and means for holding the pin in the bores. holes.

Les perçages peuvent notamment être opérés à travers un rebord du secteur de redresseur et à travers une feuillure de la virole dans laquelle le rebord est enfoncé.The holes may in particular be operated through a rim of the rectifier sector and through a rabbet of the ferrule in which the rim is depressed.

Les moyens de maintien comprennent alors avantageusement un jonc engagé sous le rebord dans la feuillure et occupant un évidement coupant le pion ; ils peuvent aussi comprendre une languette saillant du pion et venant buter contre le secteur de redresseur d'un côté, la virole de l'autre côté.The holding means then advantageously comprise a rod engaged under the rim in the rabbet and occupying a recess intersecting the pin; they may also include a tongue protruding from the pawn and abutting against the rectifier sector on one side, the ferrule on the other side.

Il est avantageux que le pion ait une section non circulaire et soit ajusté dans un perçage ayant une section non circulaire correspondante.It is advantageous that the pin has a non-circular section and is fitted into a bore having a corresponding non-circular section.

L'invention sera maintenant décrite en référence aux figures dont :

  • la figure 1 est une vue d'une réalisation particulière de l'invention,
  • la figure 2 représente le pion isolément,
  • la figure 3 est une vue d'une deuxième réalisation de l'invention, et
  • la figure 4 illustre la disposition de l'invention dans la machine.
The invention will now be described with reference to the figures of which:
  • FIG. 1 is a view of a particular embodiment of the invention,
  • FIG. 2 represents the pion in isolation,
  • FIG. 3 is a view of a second embodiment of the invention, and
  • Figure 4 illustrates the arrangement of the invention in the machine.

On a représenté à la figure 1 une portion d'une virole 15 et d'un secteur de redresseur 16 ; ce dernier comprend un rebord 17 dirigé dans un sens axial engagé dans une feuillure 18 réalisée entre une portion en crochet 19, courbée dans l'autre sens axial, et une portion principale 20 cylindrique de la virole 15. La virole 15 comprend un perçage 21 traversant la portion de crochet 19, et l'élément de secteur 16 comprend aussi un perçage 22 coupant le rebord 17 et prolongeant le perçage 21 ; la figure 4 aide à mieux saisir la disposition.FIG. 1 shows a portion of a ferrule 15 and a rectifier sector 16; the latter comprises an edge 17 directed in an axial direction engaged in a rebate 18 formed between a hook portion 19, bent in the other axial direction, and a cylindrical main portion 20 of the shell 15. The shell 15 comprises a bore 21 passing through the hook portion 19, and the sector member 16 also includes a bore 22 intersecting the flange 17 and extending the bore 21; Figure 4 helps to better grasp the layout.

Un pion 23 vu aussi à la figure 2 est engagé dans les perçages 21 et 22 et assure donc l'arrêt en rotation du secteur 16 par rapport à la virole 15. Il est retenu dans les perçages 21 et 22 par un jonc de fixation 24 engagé au fond de la feuillure 18, sous le rebord 17, à partir d'un orifice non représenté opéré dans la partie en crochet 19, et qui traverse un évidement 25 du pion 23. L'extraction accidentelle du pion 23 peut encore être empêchée par une languette 26 saillant du pion 23 et butant d'un côté contre la virole et de l'autre côté contre un secteur de redresseur 16. Cela peut être accompli en joignant le secteur de redresseur 16 à la virole après avoir mis le pion 23 en place dans les perçages 21 et 22. La virole 15 est jointe à une autre virole 27 qui lui est radialement interne, le perçage 21 s'ouvre du côté inférieur sur l'autre virole 27, et la languette 26 bute contre l'autre virole 27, ce qui ne change cependant rien.A pin 23 also seen in Figure 2 is engaged in the holes 21 and 22 and thus ensures the rotation stop sector 16 relative to the shell 15. It is retained in the holes 21 and 22 by a fastening ring 24 engaged at the bottom of the rabbet 18, under the rim 17, from a not shown orifice operated in the hook portion 19, and which passes through a recess 25 of the pin 23. The accidental extraction of the pin 23 can still be prevented by a tongue 26 protruding from the pin 23 and abutting on one side against the ferrule and on the other side against a rectifier sector 16. This can be accomplished by joining the rectifier sector 16 to the ferrule after having put the pin 23 in place in the holes 21 and 22. The ferrule 15 is joined to another ferrule 27 which is radially internal to it, the bore 21 opens on the lower side on the other ferrule 27, and the tongue 26 abuts against the Another ferrule 27, which does not change anything, however.

Le jonc 24 est ensuite glissé au fond de la feuillure 18 ; il peut s'étendre devant une série de secteurs de redresseur 16 et retenir autant de pions 23.The ring 24 is then slid to the bottom of the rabbet 18; it can extend in front of a series of rectifier sectors 16 and retain as many counters 23.

Un autre mode de réalisation, dont l'implantation est aussi représentée à la figure 4, apparaît à la figure 3 et comprend un pion 30 comprenant une paire de saillies latérales 31. Le pion 30 est, comme le précédent, engagé dans un perçage 32 opéré dans un rebord 33 d'un secteur de redresseur 34, ainsi que dans un perçage 35 prolongeant le précédent et opéré ici à travers l'autre virole 27. Quand l'autre virole 27 et le secteur de redresseur 34 sont assemblés, le pion 30 ayant été auparavant engagé dans les perçages 32 et 35, ils englobent une cavité 36 qu'occupent les saillies 31 en empêchant que le pion 30 ne soit extrait. On procède donc au même mode de montage pour les pions 23 et 30.Another embodiment, whose implantation is also shown in Figure 4, appears in Figure 3 and comprises a pin 30 comprising a pair of side projections 31. The pin 30 is, like the previous one, engaged in a hole 32 operated in a rim 33 of a rectifier sector 34, as well as in a bore 35 extending the former and operated here through the other ferrule 27. When the other ferrule 27 and the rectifier sector 34 are assembled, the counter 30 having previously been engaged in the holes 32 and 35, they include a cavity 36 occupied by the projections 31 by preventing the pin 30 is extracted. This is the same mounting mode for the pins 23 and 30.

Les pions 23 et 30 présentent des portions non circulaires telles que des facettes planes 37 et 38, engagées dans l'un des perçages 21, 22, 32 et 35 afin d'interdire une rotation accidentelle du pion 23 ou 30 qui gênerait l'assemblage ; les perçages dans lesquels ces portions non circulaires sont engagées ont évidemment une section de forme complémentaire. Les extrémités des pions peuvent être effilées pour faciliter leurs insertions dans les perçages ; l'une d'elles porte la référence 39 pour le pion 30 ; elle est en forme de pyramide .The pins 23 and 30 have non-circular portions such as plane facets 37 and 38, engaged in one of the holes 21, 22, 32 and 35 to prevent accidental rotation of the pin 23 or 30 which would interfere with the assembly. ; the holes in which these non-circular portions are engaged obviously have a section of complementary shape. The ends of the pins can be tapered to facilitate their insertions in the holes; one of them bears the reference 39 for the pawn 30; it is shaped like a pyramid.

Il est clair que d'autres modes de réalisation sont possibles, ne fût-ce qu'en combinant certains des éléments décrits sur les deux modes de réalisation complètement décrits ici.It is clear that other embodiments are possible, if only by combining some of the elements described in the two embodiments fully described here.

Claims (3)

  1. Turbomachine guide vane sector/inlet nozzle assembly comprising a guide vane sector (16, 34), an inlet nozzle (15, 27) and an anti-rotation device for stopping the guide vane sector (16, 34) rotating in the inlet nozzle (15, 27), the anti-rotation device comprising a pair of holes (21, 22, 32, 35), made in an extension piece in the sector and the inlet nozzle respectively, a pin (23, 30) engaged in the holes, and retention means (24, 26, 31) for keeping the pin in the holes,
    characterized in that the retention means comprise a tab (26, 31) projecting from the pin and butting against the guide vane sector on one side, and against the inlet nozzle on the other.
  2. Assembly according to Claim 1, characterized in that the holes are made through a rim (17) of the guide vane sector (16) and through a rebate (18) of the inlet nozzle (15), into which rebate the rim is fitted, and in that the retention means comprise a rod (24) engaged under the rim in the rebate and occupying a recess intersecting the pin.
  3. Assembly according to Claim 1, characterized in that the pin has a non-circular cross section (37, 38) which is fitted into one of the holes, which has a corresponding non-circular cross section.
EP02292633A 2001-10-25 2002-10-24 Antirotation support system for the nozzle sector of a turbomachine Expired - Lifetime EP1306525B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0113780A FR2831600B1 (en) 2001-10-25 2001-10-25 DEVICE FOR ROTATING A SECTOR HOLDING BLADES OF FIXED BLADES IN A RUBBER OF A TURBOMACHINE
FR0113780 2001-10-25

Publications (2)

Publication Number Publication Date
EP1306525A1 EP1306525A1 (en) 2003-05-02
EP1306525B1 true EP1306525B1 (en) 2006-12-20

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP02292633A Expired - Lifetime EP1306525B1 (en) 2001-10-25 2002-10-24 Antirotation support system for the nozzle sector of a turbomachine

Country Status (10)

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US (1) US7018173B2 (en)
EP (1) EP1306525B1 (en)
JP (1) JP4256778B2 (en)
CA (1) CA2464126C (en)
DE (1) DE60216874T2 (en)
ES (1) ES2273983T3 (en)
FR (1) FR2831600B1 (en)
RU (1) RU2297539C2 (en)
UA (1) UA79757C2 (en)
WO (1) WO2003036050A1 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7094025B2 (en) * 2003-11-20 2006-08-22 General Electric Company Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction
FR2871845B1 (en) * 2004-06-17 2009-06-26 Snecma Moteurs Sa GAS TURBINE COMBUSTION CHAMBER ASSEMBLY WITH INTEGRATED HIGH PRESSURE TURBINE DISPENSER
EP1939459B1 (en) * 2006-12-27 2018-04-25 Safran Aero Boosters SA System with jaws for connecting two flanges, in particular for a compressor shroud
RU2509898C2 (en) * 2009-09-02 2014-03-20 Сименс Акциенгезелльшафт Adjustment device
JP2011169246A (en) * 2010-02-19 2011-09-01 Mitsubishi Heavy Ind Ltd Gas turbine casing structure
FR2972124B1 (en) * 2011-03-01 2014-05-16 Snecma METHOD FOR PRODUCING A METAL PIECE SUCH AS A TURBOMACHINE BLADE REINFORCEMENT
JP6141871B2 (en) * 2011-12-29 2017-06-07 エリオット・カンパニー High temperature gas expansion device inlet casing assembly and method
ITCO20120014A1 (en) * 2012-04-06 2013-10-07 Nuovo Pignone Srl DIAPHRAGM RING OF STATHY STAKE, STEAM TURBINE AND METHOD
FR2989725B1 (en) * 2012-04-23 2014-04-11 Snecma TURBINE FLOOR
WO2014062220A1 (en) 2012-10-17 2014-04-24 United Technologies Corporation Structural guide vane circumferential load bearing shear pin
CN104047541B (en) * 2014-06-19 2015-12-09 西南石油大学 A kind of new type auto blowout prevention turbodrill stator
US10502059B2 (en) 2015-02-02 2019-12-10 United Technologies Corporation Alignment tie rod device and method of utilization
ES2904551T3 (en) * 2016-02-16 2022-04-05 MTU Aero Engines AG Connection arrangement for the casing element of an intermediate casing of a turbine
GB2588929B (en) * 2019-11-14 2023-09-27 Cummins Ltd Pin member for turbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955800A (en) * 1957-05-28 1960-10-11 Gen Motors Corp Turbomachine stator assembly
GB1387866A (en) * 1972-06-21 1975-03-19 Rolls Royce Aerofoil members for gas turbine engines
US4868963A (en) * 1988-01-11 1989-09-26 General Electric Company Stator vane mounting method and assembly
US5211536A (en) * 1991-05-13 1993-05-18 General Electric Company Boltless turbine nozzle/stationary seal mounting
FR2780443B1 (en) * 1998-06-25 2000-08-04 Snecma HIGH PRESSURE TURBINE STATOR RING OF A TURBOMACHINE
US6095750A (en) * 1998-12-21 2000-08-01 General Electric Company Turbine nozzle assembly

Also Published As

Publication number Publication date
US20040240992A1 (en) 2004-12-02
JP4256778B2 (en) 2009-04-22
RU2004115731A (en) 2005-05-20
UA79757C2 (en) 2007-07-25
ES2273983T3 (en) 2007-05-16
WO2003036050A1 (en) 2003-05-01
JP2005506485A (en) 2005-03-03
DE60216874T2 (en) 2007-08-02
DE60216874D1 (en) 2007-02-01
US7018173B2 (en) 2006-03-28
FR2831600B1 (en) 2004-01-02
EP1306525A1 (en) 2003-05-02
CA2464126C (en) 2011-05-31
CA2464126A1 (en) 2003-05-01
RU2297539C2 (en) 2007-04-20
FR2831600A1 (en) 2003-05-02

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