EP1335113A1 - Fastening device for gas turbine distributor sectors - Google Patents
Fastening device for gas turbine distributor sectors Download PDFInfo
- Publication number
- EP1335113A1 EP1335113A1 EP03290288A EP03290288A EP1335113A1 EP 1335113 A1 EP1335113 A1 EP 1335113A1 EP 03290288 A EP03290288 A EP 03290288A EP 03290288 A EP03290288 A EP 03290288A EP 1335113 A1 EP1335113 A1 EP 1335113A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sectors
- sealing
- distributor
- casing
- axial
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 claims abstract description 29
- 238000011144 upstream manufacturing Methods 0.000 claims description 10
- 238000011084 recovery Methods 0.000 claims description 7
- 239000005557 antagonist Substances 0.000 claims 1
- 125000006850 spacer group Chemical group 0.000 description 2
- 230000003042 antagnostic effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 210000003027 ear inner Anatomy 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Images
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
- F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
-
- 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
- This invention relates to an arrangement for hanging sectors in an arc distributor.
- the distributors considered here are meet in turbomachinery and carry blades attached to the stator responsible for straightening the flow of gas. Distributor areas are mounted at the inside of the stator housing by overlaps of hooks by making them rest on bearing faces some of which must take back the efforts exerted on the distributor vanes.
- the outer ring 3 of distributor sectors 1 includes an upstream leg 4 and a downstream leg 5 all two in the form of a hook, and the casing 2 comprises upstream legs 6 and downstream legs 7 still in the form of hook, and associated in pairs with a distributor given.
- leg 4 of sector 1 is engaged around leg 6 of housing 2, but downstream it is the tab 7 of the casing 2 which is engaged around the leg 5 of sector 1. This is justified if we consider that the forces F exerted on the distributor are essentially directed downstream, and transmitted to casing 2 partially as a moment comprising a centripetal radial force R1 at the front and an R2 centrifuge downstream. Legs 4 and 5 of sectors 1 therefore rest on legs 6 and 7 of the casing 2 to the contact faces 8 and 9 which are faces recovery of efforts.
- the axial component of the efforts F is also transmitted to the casing 2 by an axial force X which is exerted downstream of leg 5, at one end curved hook 10 of tab 7; the face of contact between tab 5 and end 10 is therefore a axial resumption of force 11.
- sectors 1 and 16 of distributor and sealing which alternate axially in the machine are assembled together since the outer ring 3 of distributor sectors 1 includes upstream a tab 20 which engages in the downstream end of the neighboring sealing sectors 16, and that the sealing sectors 16 likewise have a upstream tab 21 which engages under tab 5 downstream of the neighboring crown 3 of the distributor 1.
- the legs 20 and 21 maintain sectors 1 in position and 16.
- the invention relates to a distributor sector attachment arrangement of a different kind, the essential purpose of which is not use hook-shaped legs belonging to the casing, in order to simplify it and to make the mounting of the dispenser more convenient.
- the basic idea behind the invention is that the force recovery faces in the directions directed axially and radially outwards will now be located on the sealing areas, the casing essentially providing only unsolicited or poorly stressed bearing faces, if although the efforts it must withstand will be considerably reduced.
- a notable form of the invention is characterized in that the distributor sectors and sealing include tabs at two ends opposite axial, the legs of the sectors of dispenser are clamped between the legs of the sealing sectors and the housing, and the sectors are fixed to the housing by a portion median.
- the overall shape of the distributor sectors, to which the reference 25 is now associated, is not substantially modified, and they also include an outer ring 26 provided with a tab 27 upstream and a tab 28 at the downstream.
- the legs 27 and 28 are supported by their outer faces on radial faces 29 and 30 directed towards the inside of the housing, which now bears the reference 31.
- Sealing sectors, now 32, are still arranged alternately with the sectors 25 of dispenser and they comprise, in addition to an abradable crown 33, an outer crown 34 whose downstream 35 and upstream ends 36 serve to enclose the tabs 27 and 28 between them and between the bearing faces 29 and 30 respectively of the casing 31.
- the downstream end 35 carries a radial support face directed towards the outside 37 on which the centripetal radial force R 1 weighs
- the upstream end 36 carries a radial support face directed towards the outside 38 and an axial bearing face 39 for resuming the axial force X.
- the outer rings 34 are joined to the casing 31 with a middle portion provided with a rib 40 (or a boss) penetrating into a groove 41 (or a creu x) of complementary shape of the casing 31 to precisely adjust the position of the sealing sectors 32. Screws 42 are engaged through the boss 40 and the casing 31 to fix the sealing sectors 32 to the latter. These screws (42) are secured to the housing by the nut 46.
- Another fixing means such as a pin engaged by force, would fulfill the same function.
- the complicated and fragile forms of hooks really disappear from the housing 31 like sealing sectors 32.
- the bearing faces 29 and 30 of the casing 31 are established on massive parts and therefore resistant.
- the radial and axial R2 and X forces exerted by the leg downstream 28 are on different pieces, which relieves them both.
- the forces R 1 and X exert antagonistic moments R 1 xL and Xxl on the outer ring 34 around the point of attachment of the screw 42 to the casing 31, and it is possible to adjust the lever arms L and 1 of the forces R and X respectively by a judicious choice of the position of the screw 42 so that their moments have comparable values and that the bending produced on the screw 42 is therefore greatly reduced.
- the distributor sectors 25 can be mounted by purely axial movements, the sealing sectors 32 then being mounted behind them, which is more convenient and gives more freedom to arrange the machine. Corner pieces 43, fixed to the casing 31 by pins 44, can be added to provide an axial abutment face 45 to the distributor sectors 25.
- this typical axial assembly allows decrease the axial clearances between the stator vanes (inner ring 12 of sectors 1 in Figure 1) and the rotor blades (inner ring 13 of the blades rotor 15 in Figure 1); as a result, this reduces the leakage sections (47) between rotor and stator and ensures better efficiency of the whole planed.
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)
- Surgical Instruments (AREA)
- Coating Apparatus (AREA)
Abstract
Description
Cette invention concerne un agencement d'accrochage de secteurs en arc de cercle de distributeur.This invention relates to an arrangement for hanging sectors in an arc distributor.
Les distributeurs considérés ici se
rencontrent dans les turbomachines et portent les aubes
fixées au stator chargées de redresser l'écoulement des
gaz. Les secteurs du distributeur sont montés à
l'intérieur du carter de stator par des imbrications de
crochets en les faisant reposer sur des faces d'appui
dont certaines doivent reprendre les efforts exercés
sur les aubes du distributeur. Dans la réalisation
connue de la figure 1, où les secteurs portent la
référence 1 et le carter de stator la référence 2, la
couronne extérieure 3 des secteurs 1 de distributeur
comprend une patte amont 4 et une patte aval 5 toutes
deux en forme de crochet, et le carter 2 comprend des
pattes amont 6 et des pattes aval 7 encore en forme de
crochet, et associées par paires à un distributeur
donné. A l'amont, la patte 4 du secteur 1 est engagée
autour de la patte 6 du carter 2, mais à l'aval c'est
la patte 7 du carter 2 qui est engagée autour de la
patte 5 du secteur 1. Ceci est justifié si on considère
que les efforts F exercés sur le distributeur sont
essentiellement dirigés vers l'aval, et transmis au
carter 2 partiellement sous forme d'un moment
comprenant une force radiale centripète R1 à l'avant et
une centrifuge R2 à l'aval. Les pattes 4 et 5 des
secteurs 1 s'appuient donc sur les pattes 6 et 7 du
carter 2 aux faces de contact 8 et 9 qui sont des faces
de reprise d'efforts. La composante axiale des efforts
F est aussi transmise au carter 2 par une force axiale
X qui s'exerce à l'aval de la patte 5, à une extrémité
courbée en crochet 10 de la patte 7 ; la face de
contact entre la patte 5 et l'extrémité 10 est donc une
face axiale de reprise d'effort 11.The distributors considered here are
meet in turbomachinery and carry blades
attached to the stator responsible for straightening the flow of
gas. Distributor areas are mounted at
the inside of the stator housing by overlaps of
hooks by making them rest on bearing faces
some of which must take back the efforts exerted
on the distributor vanes. In the realization
known from FIG. 1, where the sectors bear the
reference 1 and the
Un inconvénient de cette conception est que
les pattes 6 et 7 du carter 2 sont fortement chargées,
ce qui est d'autant plus préoccupant que leur forme en
crochet les rend fragiles et qu'elles sont soumises à
des échauffements en service d'autant plus importants
qu'elles sont fortement saillantes vers l'intérieur de
la veine des gaz, et que la résistance intrinsèque de
la matière qui les constitue peut être affaiblie. Le
carter se trouve alourdi par les pattes qu'il faut
rendre massives, sa fabrication est plus difficile en
raison de la complication de sa forme et il doit en
pratique être construit en un matériau assez noble qui
n'est en rien justifié par les efforts qu'il doit subir
hors des pattes.One drawback of this design is that
the
Un autre inconvénient de cette conception
apparaít au montage : comme il est nécessaire que la
patte aval 5 des secteurs 1 passe par-dessous
l'extrémité courbée en crochet 10, les secteurs 1
doivent être présentés obliquement, avant d'être
tournés quand ils ont été engagés derrière l'extrémité
courbée en crochet 10, pour établir le contact à la
face de reprise d'efforts 9 en aval. Les flèches Z1 et
Z2 illustrent ce mouvement d'inclinaison puis de
redressement des secteurs 1 au montage. On s'aperçoit
qu'il faut prévoir un jeu suffisant entre une couronne
intérieure 12 des secteurs 1 et une couronne intérieure
13 des étages d'aubes 14 du rotor 15, ce qui oblige à
compromettre l'étanchéité à cet endroit.Another disadvantage of this design
appears during assembly: as it is necessary that the
Quand les secteurs de distributeurs ont été
mis en place, il est possible d'installer des secteurs
d'étanchéité 16 situés en aval, qui comprennent une
couronne de matière dite abradable 17 coopérant avec
des léchettes 18 des aubes mobiles 14 pour former des
joints à labyrinthes, et qui comprennent encore une
couronne de support 19 dont les extrémités sont
configurées pour s'adapter sur les pattes 6 et 7 du
carter 2. Le système d'accrochage est d'ailleurs
similaire à celui des secteurs 1 de distributeur,
puisque la couronne 19 repose à l'amont sur une face
radialement extérieure d'une des pattes (7) du carter
2, et à l'aval sur une face radialement intérieure de
l'autre des pattes (6). Enfin, les secteurs 1 et 16 de
distributeur et d'étanchéité qui alternent axialement
dans la machine sont assemblés entre eux puisque la
couronne extérieure 3 des secteurs 1 de distributeur
comprend à l'amont une patte 20 qui s'engage dans
l'extrémité aval des secteurs d'étanchéité 16 voisins,
et que les secteurs d'étanchéité 16 ont de même une
patte amont 21 qui s'engage sous la patte 5 en aval de
la couronne voisine 3 du distributeur 1. Les pattes 20
et 21 assurent le maintien en position des secteurs 1
et 16. When the distributor sectors were
set up, it is possible to install sectors
sealing 16 located downstream, which include a
crown of so-called
Le document US - 4 529 355 - A décrit un agencement où le carter porte les secteurs d'étanchéité et de distributeurs par des entretoises qui lui sont vissées. Il est donc lisse, mais les crochets sont sur les entretoises qui sont par ailleurs lourdes et encombrantes. Cette conception antérieure semble donc encore moins bonne.Document US-4,529,355-A describes a arrangement where the housing carries the sealing sectors and distributors by spacers which are screwed. So it's smooth, but the hooks are on the spacers which are otherwise heavy and cumbersome. This earlier conception therefore seems even worse.
Maintenant, l'invention est relative à un agencement d'accrochage de secteurs de distributeur d'un genre différent, dont le but essentiel est de ne pas recourir à des pattes en forme de crochet appartenant au carter, afin de simplifier celui-ci et de rendre le montage du distributeur plus commode. L'idée fondamentale à la source de l'invention est que les faces de reprise d'efforts dans les directions dirigées axialement et radialement vers l'extérieur seront désormais situées sur les secteurs d'étanchéité, le carter ne fournissant plus essentiellement que des faces d'appui non sollicitées ou peu sollicitées, si bien que les efforts auquel il doit résister seront considérablement réduits.Now, the invention relates to a distributor sector attachment arrangement of a different kind, the essential purpose of which is not use hook-shaped legs belonging to the casing, in order to simplify it and to make the mounting of the dispenser more convenient. The basic idea behind the invention is that the force recovery faces in the directions directed axially and radially outwards will now be located on the sealing areas, the casing essentially providing only unsolicited or poorly stressed bearing faces, if although the efforts it must withstand will be considerably reduced.
Une forme notable de l'invention est caractérisée en ce que les secteurs de distributeurs et d'étanchéité comprennent des pattes à deux extrémités axiales opposées, les pattes des secteurs de distributeur sont enserrées entre les pattes des secteurs d'étanchéité et le carter, et les secteurs d'étanchéité sont fixés au carter par une portion médiane.A notable form of the invention is characterized in that the distributor sectors and sealing include tabs at two ends opposite axial, the legs of the sectors of dispenser are clamped between the legs of the sealing sectors and the housing, and the sectors are fixed to the housing by a portion median.
Dans des formes particulières de réalisation, on s'efforce de réduire les efforts transmis au carter par les secteurs d'étanchéité, et notamment le moment résultant des efforts produits sur les différences faces d'appui.In particular forms of we strive to reduce efforts transmitted to the casing by the sealing sectors, and in particular the moment resulting from the efforts produced on the differences between the bearing faces.
Tous les aspects de l'invention seront maintenant découverts au moyen de la comparaison des figures suivantes :
- la figure 1 déjà décrite illustre un agencement d'accrochage de secteur de distributeur d'un genre connu ;
- et la figure 2 illustre l'agencement conforme à l'invention dans une réalisation favorite.
- Figure 1 already described illustrates a dispenser sector attachment arrangement of a known type;
- and Figure 2 illustrates the arrangement according to the invention in a preferred embodiment.
La forme d'ensemble des secteurs de
distributeurs, auxquels est maintenant associée la
référence 25, n'est pas sensiblement modifiée, et ils
comprennent encore une couronne extérieure 26 munie
d'une patte 27 à l'amont et une patte 28 à l'aval. Les
pattes 27 et 28 s'appuient par leurs faces extérieures
sur des faces 29 et 30 radiales dirigées vers
l'intérieur du carter, qui porte désormais la référence
31. Des secteurs d'étanchéité, désormais 32, sont
encore disposés alternativement avec les secteurs 25 de
distributeur et ils comprennent, en plus d'une couronne
abradable 33, une couronne extérieure 34 dont les
extrémités aval 35 et amont 36 servent à enserrer les
pattes 27 et 28 entre elles et entre les faces d'appui
29 et 30 respectivement du carter 31. Plus précisément,
l'extrémité aval 35 porte une face d'appui radiale
dirigée vers l'extérieur 37 sur laquelle pèse l'effort
radial centripète R1, et l'extrémité amont 36 porte une
face d'appui radiale dirigée vers l'extérieur 38 et une
face axiale d'appui 39 de reprise de l'effort axial X.
Les couronnes extérieures 34 sont unies au carter 31 à
une portion médiane munie d'une nervure 40 (ou d'un
bossage) pénétrant dans un sillon 41 (ou un creux) de
forme complémentaire du carter 31 pour ajuster avec
précision la position des secteurs d'étanchéité 32. Des
vis 42 sont engagées à travers le bossage 40 et le
carter 31 pour fixer les secteurs d'étanchéité 32 à
celui-ci. Ces vis (42) sont solidarisées avec le carter
par l'écrou 46. Un autre moyen de fixation, tel qu'un
pion engagé à force, remplirait la même fonction.The overall shape of the distributor sectors, to which the
La plus grande partie des efforts
s'exerçant sur les secteurs 25 de distribution est
reprise ici par les secteurs d'étanchéité 32. Ceux-ci
doivent donc être dimensionnés en conséquence, mais ils
sont cependant plutôt moins chargés que les pattes en
forme de crochet du carter 2 de la réalisation connue.Most of the effort
practicing on the
Les formes compliquées et fragiles des
crochets disparaissent en vérité du carter 31 comme des
secteurs d'étanchéité 32. Les faces d'appui 29 et 30 du
carter 31 sont établies sur des parties massivese et
donc résistantes. Les forces R2 et X radiale et axiale
exercées par la patte à l'aval 28 le sont sur des
pièces différentes, ce qui les soulage toutes deux.The complicated and fragile forms of
hooks really disappear from the
En outre, les forces R1 et X exercent des
moments R1xL et Xxl antagonistes sur la couronne
extérieure 34 autour du point d'attache de la vis 42 au
carter 31, et il est possible d'ajuster les bras de
levier L et 1 des forces R et X respectivement par un
choix judicieux de la position de la vis 42 pour que
leurs moments aient des valeurs comparables et que la
flexion produite sur la vis 42 soit donc très diminuée.
Par ailleurs, on observe que les secteurs 25 de
distributeur peuvent être montés par des mouvements
purement axiaux, les secteurs d'étanchéité 32 étant
ensuite montés derrière eux, ce qui est plus commode et
donne plus de liberté pour agencer la machine. Des
pièces 43 en cornière, fixées au carter 31 par des
pions 44, peuvent être ajoutées pour offrir une face de
butée axiale 45 aux secteurs 25 de distributeur.In addition, the forces R 1 and X exert antagonistic moments R 1 xL and Xxl on the
En plus, ce montage typique axial permet de
diminuer les jeux axiaux entre les aubes du stator
(couronne intérieure 12 des secteurs 1 de la figure 1)
et les aubes du rotor (couronne intérieure 13 des aubes
du rotor 15 sur la figure 1) ; en conséquence, ceci
permet de diminuer les sections de fuite (47) entre
rotor et stator et assure un meilleur rendement de
l'ensemble aubagé.In addition, this typical axial assembly allows
decrease the axial clearances between the stator vanes
(
Quoique la vue de la figure 2 soit moins
complète que ceslle de la figure 1, il doit être
compris que l'invention s'étend sur un groupe d'étages
de secteurs de distributeur 25 et d'étanchéité 32, et
notamment qu'un étage de secteurs de distributeurs 25
s'appuie par ses deux extrémités sur deux étages de
secteurs d'étanchéité 32 successifs de la manière
décrite. On s'est efforcé surtout de représenter les
secteurs d'étanchéité 32 puisque les secteurs de
distributeur 25 sont essentiellement identiques à ceux
de la figure 1.Although the view in Figure 2 is less
complete as shown in Figure 1, it must be
understood that the invention extends over a group of
Claims (5)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0201460A FR2835563B1 (en) | 2002-02-07 | 2002-02-07 | ARRANGEMENT FOR HANGING SECTORS IN A CIRCLE OF A CIRCLE OF A BLADE-BEARING DISTRIBUTOR |
| FR0201460 | 2002-02-07 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1335113A1 true EP1335113A1 (en) | 2003-08-13 |
| EP1335113B1 EP1335113B1 (en) | 2005-11-02 |
Family
ID=27589603
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP03290288A Expired - Lifetime EP1335113B1 (en) | 2002-02-07 | 2003-02-05 | Fastening device for gas turbine distributor sectors |
Country Status (11)
| Country | Link |
|---|---|
| US (2) | US20030146578A1 (en) |
| EP (1) | EP1335113B1 (en) |
| JP (1) | JP4087720B2 (en) |
| CN (1) | CN100357569C (en) |
| CA (1) | CA2418357C (en) |
| DE (1) | DE60302077T2 (en) |
| ES (1) | ES2250844T3 (en) |
| FR (1) | FR2835563B1 (en) |
| MA (1) | MA25948A1 (en) |
| RU (1) | RU2311539C2 (en) |
| UA (1) | UA76424C2 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1840339A1 (en) * | 2006-03-30 | 2007-10-03 | Snecma | Device for attaching ring sectors around a turbine wheel of a turbomachine |
| FR2928963A1 (en) * | 2008-03-19 | 2009-09-25 | Snecma Sa | TURBINE DISPENSER FOR A TURBOMACHINE. |
| FR2944554A1 (en) * | 2009-04-16 | 2010-10-22 | Snecma | High pressure turbine for turbo machine of aircraft, has downstream radial wall carrying axial support unit supported on upstream radial wall for axially retaining external structure of distributor with respect to case |
| FR2981602A1 (en) * | 2011-10-25 | 2013-04-26 | Snecma Propulsion Solide | PROCESS FOR MANUFACTURING TURBINE DISPENSER SECTOR OR COMPRESSOR RECTIFIER OF COMPOSITE MATERIAL FOR TURBOMACHINE AND TURBINE OR COMPRESSOR INCORPORATING A DISPENSER OR RECTIFIER FORMED OF SUCH SECTORS |
| EP2896796A1 (en) * | 2014-01-20 | 2015-07-22 | Techspace Aero S.A. | Stator of an axial turbomachine and corresponding turbomachine |
| FR3083564A1 (en) * | 2018-07-05 | 2020-01-10 | Safran Aircraft Engines | TURBINE COMPRISING AN ABRADABLE ELEMENT WITH AN ADJUSTABLE RADIAL POSITION |
Families Citing this family (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2829525B1 (en) * | 2001-09-13 | 2004-03-12 | Snecma Moteurs | ASSEMBLY OF SECTORS OF A TURBINE DISTRIBUTOR TO A CRANKCASE |
| DE102004016222A1 (en) * | 2004-03-26 | 2005-10-06 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement for automatic running gap adjustment in a two-stage or multi-stage turbine |
| FR2875535B1 (en) * | 2004-09-21 | 2009-10-30 | Snecma Moteurs Sa | TURBINE MODULE FOR GAS TURBINE ENGINE |
| US7523616B2 (en) * | 2005-11-30 | 2009-04-28 | General Electric Company | Methods and apparatuses for assembling a gas turbine engine |
| US7637110B2 (en) * | 2005-11-30 | 2009-12-29 | General Electric Company | Methods and apparatuses for assembling a gas turbine engine |
| US7493771B2 (en) * | 2005-11-30 | 2009-02-24 | General Electric Company | Methods and apparatuses for assembling a gas turbine engine |
| US7771160B2 (en) * | 2006-08-10 | 2010-08-10 | United Technologies Corporation | Ceramic shroud assembly |
| US7665960B2 (en) | 2006-08-10 | 2010-02-23 | United Technologies Corporation | Turbine shroud thermal distortion control |
| FR2923525B1 (en) * | 2007-11-13 | 2009-12-18 | Snecma | SEALING A ROTOR RING IN A TURBINE FLOOR |
| FR2928961B1 (en) * | 2008-03-19 | 2015-11-13 | Snecma | SECTORIZED DISPENSER FOR A TURBOMACHINE. |
| FR2930592B1 (en) * | 2008-04-24 | 2010-04-30 | Snecma | TURBINE DISPENSER FOR A TURBOMACHINE |
| FR2939836B1 (en) * | 2008-12-12 | 2015-05-15 | Snecma | SEAL FOR PLATFORM SEAL IN A TURBOMACHINE ROTOR |
| US8167546B2 (en) * | 2009-09-01 | 2012-05-01 | United Technologies Corporation | Ceramic turbine shroud support |
| US8608424B2 (en) * | 2009-10-09 | 2013-12-17 | General Electric Company | Contoured honeycomb seal for a turbomachine |
| US8647055B2 (en) * | 2011-04-18 | 2014-02-11 | General Electric Company | Ceramic matrix composite shroud attachment system |
| FR2974841B1 (en) * | 2011-05-04 | 2013-06-07 | Snecma | SEALING DEVICE FOR TURBINE MACHINE TURBINE DISPENSER |
| US9291061B2 (en) * | 2012-04-13 | 2016-03-22 | General Electric Company | Turbomachine blade tip shroud with parallel casing configuration |
| WO2014163673A2 (en) | 2013-03-11 | 2014-10-09 | Bronwyn Power | Gas turbine engine flow path geometry |
| FR3057015B1 (en) * | 2016-09-30 | 2018-12-07 | Safran Aircraft Engines | ROTOR DISK HAVING VARIABLE THICKNESS CANVAS |
| RU190280U1 (en) * | 2019-01-09 | 2019-06-25 | Публичное Акционерное Общество "Одк-Сатурн" | DEVICE FOR FIXING SEGMENT OF SEGPLATES IN THE FORCE CASE OF A TURBINE STATOR |
| BE1027280B1 (en) * | 2019-05-16 | 2020-12-15 | Safran Aero Boosters Sa | TURBOMACHINE COMPRESSOR HOUSING |
| FR3100838B1 (en) * | 2019-09-13 | 2021-10-01 | Safran Aircraft Engines | TURBOMACHINE SEALING RING |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2858104A (en) * | 1954-02-04 | 1958-10-28 | A V Roe Canada Ltd | Adjustable gas turbine shroud ring segments |
| US2942844A (en) * | 1952-12-22 | 1960-06-28 | Gen Motors Corp | Turbine nozzle |
| GB856599A (en) * | 1958-06-16 | 1960-12-21 | Gen Motors Corp | Improvements relating to axial-flow compressors |
| US4529355A (en) * | 1982-04-01 | 1985-07-16 | Rolls-Royce Limited | Compressor shrouds and shroud assemblies |
| US5288206A (en) * | 1991-11-20 | 1994-02-22 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Turbo aero engine equipped with means facilitating adjustment of plays of the stator and between the stator and rotor |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2623728A (en) * | 1945-01-16 | 1952-12-30 | Power Jets Res & Dev Ltd | Mounting of blades in compressors, turbines, and the like |
| US2693904A (en) * | 1950-11-14 | 1954-11-09 | A V Roe Canada Ltd | Air bleed for compressors |
| US2834537A (en) * | 1954-01-18 | 1958-05-13 | Ryan Aeronautical Co | Compressor stator structure |
| GB2078309B (en) * | 1980-05-31 | 1983-05-25 | Rolls Royce | Mounting nozzle guide vane assemblies |
| SU1663202A1 (en) * | 1988-05-12 | 1991-07-15 | Государственный научно-исследовательский институт гражданской авиации | Stator of turbo-driven set |
| US4902198A (en) * | 1988-08-31 | 1990-02-20 | Westinghouse Electric Corp. | Apparatus for film cooling of turbine van shrouds |
| JPH03213602A (en) * | 1990-01-08 | 1991-09-19 | General Electric Co <Ge> | Self cooling type joint connecting structure to connect contact segment of gas turbine engine |
| FR2685936A1 (en) * | 1992-01-08 | 1993-07-09 | Snecma | DEVICE FOR CONTROLLING THE GAMES OF A TURBOMACHINE COMPRESSOR HOUSING. |
| US5299910A (en) * | 1992-01-23 | 1994-04-05 | General Electric Company | Full-round compressor casing assembly in a gas turbine engine |
| US5288208A (en) * | 1993-06-01 | 1994-02-22 | Cummins Richard L | Marine propeller block apparatus |
| US5462403A (en) * | 1994-03-21 | 1995-10-31 | United Technologies Corporation | Compressor stator vane assembly |
| US5531457A (en) * | 1994-12-07 | 1996-07-02 | Pratt & Whitney Canada, Inc. | Gas turbine engine feather seal arrangement |
| US6341938B1 (en) * | 2000-03-10 | 2002-01-29 | General Electric Company | Methods and apparatus for minimizing thermal gradients within turbine shrouds |
-
2002
- 2002-02-07 FR FR0201460A patent/FR2835563B1/en not_active Expired - Fee Related
-
2003
- 2003-01-31 JP JP2003024269A patent/JP4087720B2/en not_active Expired - Lifetime
- 2003-02-04 CA CA2418357A patent/CA2418357C/en not_active Expired - Lifetime
- 2003-02-04 MA MA27026A patent/MA25948A1/en unknown
- 2003-02-05 EP EP03290288A patent/EP1335113B1/en not_active Expired - Lifetime
- 2003-02-05 ES ES03290288T patent/ES2250844T3/en not_active Expired - Lifetime
- 2003-02-05 DE DE60302077T patent/DE60302077T2/en not_active Expired - Lifetime
- 2003-02-06 US US10/359,222 patent/US20030146578A1/en not_active Abandoned
- 2003-02-06 UA UA2003021092A patent/UA76424C2/en unknown
- 2003-02-06 RU RU2003103610/06A patent/RU2311539C2/en active
- 2003-02-07 CN CNB031217737A patent/CN100357569C/en not_active Expired - Lifetime
-
2004
- 2004-10-05 US US10/957,690 patent/US7290982B2/en not_active Expired - Lifetime
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2942844A (en) * | 1952-12-22 | 1960-06-28 | Gen Motors Corp | Turbine nozzle |
| US2858104A (en) * | 1954-02-04 | 1958-10-28 | A V Roe Canada Ltd | Adjustable gas turbine shroud ring segments |
| GB856599A (en) * | 1958-06-16 | 1960-12-21 | Gen Motors Corp | Improvements relating to axial-flow compressors |
| US4529355A (en) * | 1982-04-01 | 1985-07-16 | Rolls-Royce Limited | Compressor shrouds and shroud assemblies |
| US5288206A (en) * | 1991-11-20 | 1994-02-22 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Turbo aero engine equipped with means facilitating adjustment of plays of the stator and between the stator and rotor |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7789619B2 (en) | 2006-03-30 | 2010-09-07 | Snecma | Device for attaching ring sectors around a turbine rotor of a turbomachine |
| FR2899274A1 (en) * | 2006-03-30 | 2007-10-05 | Snecma Sa | DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE |
| RU2403405C2 (en) * | 2006-03-30 | 2010-11-10 | Снекма | Device for fixing ring sectors around turbine shaft of turbine machine, turbine machine, ring sector and turbine of turbine machine |
| EP1840339A1 (en) * | 2006-03-30 | 2007-10-03 | Snecma | Device for attaching ring sectors around a turbine wheel of a turbomachine |
| WO2009118490A3 (en) * | 2008-03-19 | 2009-11-26 | Snecma | Turbine distributor for turbine engine |
| FR2928963A1 (en) * | 2008-03-19 | 2009-09-25 | Snecma Sa | TURBINE DISPENSER FOR A TURBOMACHINE. |
| US8662835B2 (en) | 2008-03-19 | 2014-03-04 | Snecma | Nozzle for a turbomachine turbine |
| FR2944554A1 (en) * | 2009-04-16 | 2010-10-22 | Snecma | High pressure turbine for turbo machine of aircraft, has downstream radial wall carrying axial support unit supported on upstream radial wall for axially retaining external structure of distributor with respect to case |
| FR2981602A1 (en) * | 2011-10-25 | 2013-04-26 | Snecma Propulsion Solide | PROCESS FOR MANUFACTURING TURBINE DISPENSER SECTOR OR COMPRESSOR RECTIFIER OF COMPOSITE MATERIAL FOR TURBOMACHINE AND TURBINE OR COMPRESSOR INCORPORATING A DISPENSER OR RECTIFIER FORMED OF SUCH SECTORS |
| WO2013060977A3 (en) * | 2011-10-25 | 2013-08-08 | Herakles | Method for manufacturing a turbine nozzle guide vanes sector or a compressor guide vanes sector from composite material for a turbomachine |
| US9784113B2 (en) | 2011-10-25 | 2017-10-10 | Herakles | Method of fabricating a turbine or compressor guide vane sector made of composite material for a turbine engine, and a turbine or a compressor incorporating such guide vane sectors |
| EP2896796A1 (en) * | 2014-01-20 | 2015-07-22 | Techspace Aero S.A. | Stator of an axial turbomachine and corresponding turbomachine |
| FR3083564A1 (en) * | 2018-07-05 | 2020-01-10 | Safran Aircraft Engines | TURBINE COMPRISING AN ABRADABLE ELEMENT WITH AN ADJUSTABLE RADIAL POSITION |
Also Published As
| Publication number | Publication date |
|---|---|
| DE60302077T2 (en) | 2006-07-20 |
| FR2835563B1 (en) | 2004-04-02 |
| US20030146578A1 (en) | 2003-08-07 |
| JP4087720B2 (en) | 2008-05-21 |
| ES2250844T3 (en) | 2006-04-16 |
| FR2835563A1 (en) | 2003-08-08 |
| EP1335113B1 (en) | 2005-11-02 |
| CN100357569C (en) | 2007-12-26 |
| UA76424C2 (en) | 2006-08-15 |
| CA2418357C (en) | 2010-10-26 |
| CN1443927A (en) | 2003-09-24 |
| MA25948A1 (en) | 2003-12-31 |
| CA2418357A1 (en) | 2003-08-07 |
| US20050042081A1 (en) | 2005-02-24 |
| US7290982B2 (en) | 2007-11-06 |
| RU2311539C2 (en) | 2007-11-27 |
| DE60302077D1 (en) | 2005-12-08 |
| JP2003269111A (en) | 2003-09-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1335113B1 (en) | Fastening device for gas turbine distributor sectors | |
| EP0463955B1 (en) | Fixing a crown to a turbine wheel | |
| EP0356305B1 (en) | Turbine stator ring held by a turbine casing | |
| EP1288444B1 (en) | Fixing stator elements in a turbomachine casing | |
| EP2060750B1 (en) | Stage of a turbine or compressor, in particular of a turbomachine | |
| FR2641031A1 (en) | ||
| CA2398319C (en) | Bladed rotor disc side-plate and corresponding arrangement | |
| CA2956882C (en) | Turbomachine module | |
| EP0214876B1 (en) | Multifunctional support disc for a labyrinth seal of a turbo machine rotor | |
| CA2537435C (en) | Device for adjusting the centring of a synchronization ring for the control of turning vanes in a turbine engine | |
| FR2466610A1 (en) | ROTOR ASSEMBLY | |
| FR2928963A1 (en) | TURBINE DISPENSER FOR A TURBOMACHINE. | |
| EP1199444A1 (en) | Linkage arrangement of a stator ring to a support strut | |
| EP3591178A1 (en) | Aircraft turbine engine sealing module | |
| CA2641017A1 (en) | Improved turbojet stator blade spacing system control ring | |
| EP1635039A1 (en) | Coupling device with key elements for mounting a seal ring to the stator blades of a gas turbine | |
| WO2022096822A1 (en) | Assembly for a turbomachine | |
| FR2963806A1 (en) | DEVICE FOR LOCKING A FOOT OF A ROTOR BLADE | |
| WO2003036050A1 (en) | Device for stopping in rotation a fixed blade bearing sector in a gas turbine casing | |
| FR3010154A1 (en) | INTERMEDIATE CASTER SEAL PANEL FOR A DOUBLE FLOW AIRCRAFT TURBOMACHINE | |
| FR2889863A1 (en) | COMPRESSOR COMPRISING A PLURALITY OF HOUSINGS RECONSTITUTING AN ANNULAR VOLUME OF FLOW SEPARATION IN A TURBOMACHINE. | |
| FR2824593A1 (en) | Stator blades pivot support installation comprises bringing together two rings comprising half of internal pivot bores and sliding snap ring into groove in junction between rings | |
| FR2927685A1 (en) | SEAL RING ASSEMBLY AND TURBINE ENGINE COMPRISING SUCH AN ASSEMBLY | |
| EP3880940B1 (en) | Device for centring and guiding in rotation a rotating part with interlaced arms | |
| WO2003023193A1 (en) | Assembly of sectors of a dispensing unit in a gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
| AK | Designated contracting states |
Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT SE SI SK TR |
|
| AX | Request for extension of the european patent |
Extension state: AL LT LV MK RO |
|
| 17P | Request for examination filed |
Effective date: 20040115 |
|
| AKX | Designation fees paid |
Designated state(s): DE ES FR GB IT SE |
|
| GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
| GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
| GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
| RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SNECMA |
|
| AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE ES FR GB IT SE |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
| REF | Corresponds to: |
Ref document number: 60302077 Country of ref document: DE Date of ref document: 20051208 Kind code of ref document: P |
|
| REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
| GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20060130 |
|
| REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2250844 Country of ref document: ES Kind code of ref document: T3 |
|
| PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
| 26N | No opposition filed |
Effective date: 20060803 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20130207 Year of fee payment: 11 |
|
| REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20150731 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140206 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 14 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 15 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 16 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Owner name: SAFRAN AIRCRAFT ENGINES Effective date: 20170719 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20220124 Year of fee payment: 20 Ref country code: DE Payment date: 20220119 Year of fee payment: 20 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20220120 Year of fee payment: 20 Ref country code: IT Payment date: 20220119 Year of fee payment: 20 Ref country code: FR Payment date: 20220119 Year of fee payment: 20 |
|
| REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 60302077 Country of ref document: DE |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 Expiry date: 20230204 |
|
| REG | Reference to a national code |
Ref country code: SE Ref legal event code: EUG |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20230204 |