FR2895021A1 - Turbomachine e.g. low pressure turbine, for aircraft`s jet engine, has rotor composed of disks that are reunited by annular connecting part, and sealing unit arranged between blades of each disks and crown of diffuser blade - Google Patents
Turbomachine e.g. low pressure turbine, for aircraft`s jet engine, has rotor composed of disks that are reunited by annular connecting part, and sealing unit arranged between blades of each disks and crown of diffuser blade Download PDFInfo
- Publication number
- FR2895021A1 FR2895021A1 FR0512791A FR0512791A FR2895021A1 FR 2895021 A1 FR2895021 A1 FR 2895021A1 FR 0512791 A FR0512791 A FR 0512791A FR 0512791 A FR0512791 A FR 0512791A FR 2895021 A1 FR2895021 A1 FR 2895021A1
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- Prior art keywords
- disks
- blades
- annular
- turbomachine
- turbomachine according
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Links
- 238000007789 sealing Methods 0.000 title claims abstract description 13
- 238000012550 audit Methods 0.000 claims 1
- 239000000463 material Substances 0.000 description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 208000018747 cerebellar ataxia with neuropathy and bilateral vestibular areflexia syndrome Diseases 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 210000003462 vein Anatomy 0.000 description 2
- 240000000731 Fagus sylvatica Species 0.000 description 1
- 235000010099 Fagus sylvatica Nutrition 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Classifications
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
L'invention se rapporte a une turbomachine du type comportant un rotorThe invention relates to a turbomachine of the type comprising a rotor
compose de plusieurs disques aubages assembles les uns aux autres selon un axe commun et un stator comportant des couronnes d'aubes de redresseur intercalees axialement entre ces disques. Elie concerne plus particulierement un nouvel agencement visant a la fois a simplifier ('assemblage des disques entre eux et a ameliorer I'etancheite inter-etages. L'invention s'applique notamment a une turbine et plus particulierement a la turbine basse pression d'un turboreacteur d'avion. Dans une turbine basse pression, par exemple, I'etancheite entre etages est assuree par des moyens d'etancheite rotatifs constitues, classiquement, d'une garniture en materiau abradable, a structure en nid d'abeille, et d'une ou plusieurs Iechettes. L'ensemble est connu sous le nom de joint a labyrinthe. La garniture est generalement solidaire d'une couronne d'aubes de redresseur intercalee axialement entre deux disques aubages adjacents du rotor. Ces disques comportent Iateralement des parois annulaires appelees toiles, qui sont boulonnees entre elles. Les Iechettes sont generalement intercalees entre des brides d'assemblage desdites toiles. Le socle annulaire de ladite couronne d'aubes de redresseur comporte des bequets qui s'etendent jusqu'au voisinage des plate-formes des aubes mobiles rattachees aux deux disques voisins, amont et aval, du rotor. L'ensemble definit ainsi une cavite annulaire a I'interieur de laquelle se situe ledit joint a labyrinthe. La veine d'air chaud qui circule dans la turbine se trouve radialement a I'exterieur de cette cavite. De ('air relativement plus froid, sous pression, circule dans la cavite en passant par les alveoles des disques de rotor qui retiennent les pieds d'aubes. Cet air froid en surpression protege lesdites toiles. De plus, en limitant les fuites d'air chaud de la veine, on augmente le rendement de la turbine. L'invention vise notamment a simplifier et a alleger la structure decrite ci-dessus, notamment en supprimant I'assemblage des disques par boulons. On a propose de solidariser entre eux les disques par une piece soudee (remplacant les toiles) et dans laquelle on usine les Iechettes. Cette solution est couteuse car I'usinage des Iechettes est difficile a realiser. De plus, un traitement in situ des Iechettes, notamment un revetement d'alumine est parfois necessaire. II doit etre effectue a I'aide d'une torche a plasma. Ce traitement est difficile a mettre en oeuvre car les lechettes sont peu accessibles. L'invention permet de surmonter tous ces inconvenients. Plus precisement, ('invention concerne une turbomachine comportant un rotor compose de plusieurs disques aubages assembles les uns aux autres selon un axe commun et un stator comportant au moins une couronne d'aubes de redresseur intercalee axialement entre deux tels disques, chaque disque de rotor comportant des alveoles dans lesquelles sont montees des aubes mobiles, caracterisee en ce que, au moins deux disques consecutifs etant reunis par une partie de liaison annulaire coaxiale, rattachee aux disques radialement interieurement par rapport auxdites alveoles, des moyens d'etancheite sont agences entre ('ensemble des aubes de chacun de ces deux disques et la couronne d'aubes de redresseur, intercalee entre eux. consists of several bladed disks assembled to each other along a common axis and a stator comprising stator vanes crowns interposed axially between these disks. Elie more particularly relates to a new arrangement aimed both at simplifying the assembly of the discs with one another and improving the interstage tightness.The invention applies in particular to a turbine and more particularly to the low pressure turbine. In a low-pressure turbine, for example, the sealing between stages is provided by rotary sealing means conventionally constituted by a packing made of abradable material, having a honeycomb structure, and The set is generally known as a labyrinth seal The lining is generally integral with a ring of stator vanes interposed axially between two adjacent blades of the rotor rotor. annular called the canvases, which are bolted together.The scraps are generally interposed between assembly flanges of said canvases.The annular base of said crown of straightening blades ur comprises beeches which extend up to the vicinity of the platforms of the moving blades connected to the two neighboring disks, upstream and downstream, of the rotor. The assembly thus defines an annular cavity within which said labyrinth seal is located. The hot air stream circulating in the turbine is located radially outside this cavity. Relatively cold air, under pressure, circulates in the cavite through the alveoli of the rotor disks which hold the blade roots, This cold air under pressure protects these webs and by limiting leaks The invention aims, in particular, at simplifying and relieving the structure described above, in particular by eliminating the assembly of the disks by bolts. discs by a welded piece (replacing the cloths) and in which the wastes are machined.This solution is expensive because the machining of the scraps is difficult to achieve.In addition, an in situ treatment of the scrap, including a coating of alumina is sometimes necessary, it must be carried out with the aid of a plasma torch.This treatment is difficult to implement because the licks are not very accessible.The invention makes it possible to overcome all these drawbacks. n relates to a turbomachine comprising a rotor composed of several blade disks assembled to each other along a common axis and a stator comprising at least one ring of stator vanes interposed axially between two such disks, each rotor disk comprising alveoli in which are mounted mobile blades, characterized in that, at least two consecutive discs being reunis by a coaxial annular connecting portion, attached to the discs radially internally relative to said alveoli, sealing means are arranged between ('set of blades of each of these two disks and the crown of straightener vanes, interposed between them.
Selon un mode de realisation possible, ladite partie de liaison est une piece annulaire soudee aux deux disques. Selon une autre possibilite, ladite partie de liaison et les deux disques peuvent etre realises d'un seul tenant. L'invention est particulierement applicable sur les deux derniers etages d'une turbine basse pression ou turbomachine analogue. Selon un mode de realisation avantageux, les moyens d'etancheite comportent une garniture abradable annulaire installee a la partie radialement la plus interne de ladite couronne d'aubes de redresseur situee entre les deux disques et deux supports annulaires rattaches respectivement audites aubes mobiles des deux disques et portant des lechettes cooperant avec ladite garniture abradable. La structure inverse est possible, a savoir que des lechettes peuvent etre solidaires de la couronne d'aubes de redresseur tandis que des garnitures de materiau abradable sont portees par des supports annulaires prolongeant les plate-formes. Ainsi, on reconstitue une cavite annulaire dans laquelle on fait circuler de I'air relativement froid, sous pression, introduit par les alveoles des pieds d'aubes. De plus, avec les alliages utilises pour realiser les aubages du rotor, c'est-e-dire les plate-formes dont lesdits supports constituent des prolongements, it n'est plus necessaire de proceder a un revetement par mise en oeuvre d'une torche a plasma. Chaque support annulaire peut etre constitue par des segments s'etendant Cate a cote avec recouvrement circonferentiel, chaque segment etant dans le prolongement de la plate-forme d'une aube. L'invention sera mieux comprise et d'autres avantages de celleci apparaltront plus clairement a la lumiere de la description qui va suivre de plusieurs modes de realisation conformes a son principe, donnee uniquement a titre d'exemple et faite en reference aux dessins annexes dans lesquels : - la figure 1 est une demi coupe partielle d'une turbine basse pression comportant le perfectionnement de I'invention ; - la figure 2 est une vue de detail illustrant une variante ; - La figure 2A represente une modification de la variante de la figure 2 - Ia figure 3 est une autre vue de detail montrant une modification d'un support annulaire dans le mode de realisation de la figure 1 - la figure 4 est une section IV-IV de la figure 1. En se reportant plus particulierement a la figure 1, on a represente partiellement les deux derniers stages de la turbine basse pression 11 d'un turboreacteur. On distingue notamment deux disques aubages 13, 15 faisant partie du rotor 17 et rune des couronnes d'aubes de redresseur 19 faisant partie du stator. Les deux disques portent chacun une serie d'aubes 21, 23 mobiles en rotation. L'axe de rotation des disques aubages est indique X'X. La couronne d'aubes de redresseur 19 est intercalee, axialement, entre les deux disques aubages. Classiquement, chaque aube mobile comporte une pale 21a, 23a s'stendant radialement a I'exterieur d'une plate-forme 21b, 23b. De I'autre cote de ladite plate-forme, un pied d'aube 21c, 23c, solidaire de celle-ci est engage dans une alveole correspondante 27, 29 definie a la peripherie exterieure du disque 13, 15 de I'etage considers. Des butses 30 maintiennent axialement les pieds d'aubes dans leurs alveoles, sans empecher pour autant une circulation d'air relativement frais, d'amont en aval, dans lesdites alveoles. Par ailleurs, la couronne d'aubes de redresseur 19 comporte aussi une pluralite d'aubes fixes 31, ici encastrees dans la structure du carter 32. Ces cubes fixes sont montees cote a cote, circonferentiellement. According to one possible embodiment, said connecting portion is an annular piece welded to both disks. According to another possibility, said connecting portion and the two discs can be made in one piece. The invention is particularly applicable to the last two stages of a low pressure turbine or similar turbine engine. According to an advantageous embodiment, the sealing means comprise an annular abradable gasket installed at the radially innermost portion of said rectifier blade ring situated between the two disks and two annular supports pieced respectively to said blades of the two disks. and carrying licks cooperating with said abradable liner. The reverse structure is possible, namely that licks may be integral with the crown of straightener vanes while abradable material fittings are carried by annular supports extending the platforms. Thus, it reconstructs an annular cavity in which is circulated relatively cold air, under pressure, introduced by the alveoli of the blade roots. In addition, with the alloys used to realize the rotor blades, that is to say the platforms of which said supports are extensions, it is no longer necessary to proceed to a coating by implementation of a plasma torch. Each annular support may be constituted by segments extending Cate adjacent with circumferential overlap, each segment being in the extension of the platform of a blade. The invention will be better understood and other advantages thereof will appear more clearly in the light of the following description of several embodiments in accordance with its principle, given solely by way of example and with reference to the accompanying drawings in which: - Figure 1 is a partial half section of a low pressure turbine comprising the refinement of 1'invention; - Figure 2 is a detail view illustrating a variant; FIG. 2A shows a modification of the variant of FIG. 2; FIG. 3 is another detail view showing a modification of an annular support in the embodiment of FIG. 1; FIG. 4 is a section IV. IV of FIG. 1. Referring more particularly to FIG. 1, the last two stages of the low-pressure turbine 11 of a turbojet were partially represented. In particular, there are two blade disks 13, 15 forming part of the rotor 17 and rune of the stator vane rings 19 forming part of the stator. Both discs each carry a series of vanes 21, 23 movable in rotation. The axis of rotation of the bladed discs is X'X. The ring of stator vanes 19 is interposed, axially, between the two blade disks. Conventionally, each blade has a blade 21a, 23a extending radially outside a platform 21b, 23b. On the other side of said platform, a blade root 21c, 23c, secured thereto is engaged in a corresponding alveole 27, 29 defined at the outer periphery of the disk 13, 15 of 1'etage dos. Targets 30 axially maintain the blade roots in their alveoli, without preventing a relatively fresh air flow, upstream to downstream, in said alveoli. Furthermore, the ring of stator vanes 19 also comprises a plurality of vanes 31 fixed here in the structure of the casing 32. These fixed cubes are mounted side by side, circumferentially.
Les aubes fixes comportent aussi, a leurs extremites internes, des embases 33. L'ensemble des embases forme un socle annulaire de la couronne d'aubes de redresseur. Les plate-formes 21a, 23a des aubes mobiles et les embases 33 des aubes fixes delimitent la paroi interieure de la veine. Les disques sont par exemple en titane tandis que les aubes (et leurs plate-formes) sont en alliage a base de nickel. L'agencement decrit jusqu'a present est classique. Selon une caracteristique remarquable de ('invention, au moins deux disques consecutifs 13, 15 sont reunis par une partie de liaison annulaire 37 coaxiale, rattachee aux disques radialement interieurement par rapport audites alveoles 27, 29 tandis que des moyens d'etancheite 39 sont agences entre ('ensemble des aubes 21, 23 de chacun de ces deux disques et la couronne d'aubes de redresseur 19, intercalee entre eux. II est a noter que la partie de liaison annulaire 37 qui s'etend entre les deux disques est de forme simple et constituee d'une seule piece. Cette partie de liaison remplace les tones utilisees anterieurement et souvent boulonnees entre elles. Dans I'exemple ladite partie de liaison 37 est une piece annulaire soudee aux deux disques 13, 15 en sorte que la jonction entre ceux-ci est considerablement simplifiee. On pourrait aussi envisager que ladite partie de liaison et les deux disques soient d'un seul tenant. Dans I'exemple de la figure 1, lesdits moyens d'etancheite 39 comportent une garniture en materiau abradable 41, annulaire, installee a Ia partie radialement la plus interne de ladite couronne d'aubes de redresseur 19 qui se trouve situee entre les deux disques et deux supports annulaires 43, 45 rattaches respectivement audites aubes mobiles des deux disques, portant des lechettes 47 qui cooperent avec ladite garniture en materiau abradable. La garniture abradable 41 peut titre une garniture connue, du type a nid d'abeille. Les supports annulaires 43, 45 peuvent titre formes par des prolongements des plate-formes.des aubes mobiles, reconstituant des parois annulaires qui portent les lechettes. S'agissant de pieces en alliage a base de nickel, les lechettes 47 ne necessitent generalement pas de traitement a I'aide d'une torche plasma. Lesdits supports annulaires 43, 45 sont constitues par des segments 51 associes respectivement aux plate-formes d'aubes. Ces segments sont courbes, et s'etendent cote a cote avec recouvrement a dans le sens circonferentiel, comme visible sur la section de la figure 4. Ainsi, une cavite annulaire 55 se trouve definie entre les deux disques, ladite partie de liaison et les moyens d'etancheite tels que decrits ci-dessus. En fonctionnement, I'air frais sous pression qui circule au centre du rotor, passe par les alveoles 27 et traverse la cavite annulaire, en la maintenant sous une certaine pression qui s'oppose aux fuites de gaz chaud provenant de la veine. The fixed vanes also have, at their internal ends, bases 33. The set of bases forms an annular base of the crown of stator vanes. The platforms 21a, 23a of the blades and the bases 33 of the blades define the inner wall of the vein. The discs are for example titanium while the blades (and their platforms) are nickel-based alloy. The arrangement described so far is conventional. According to a remarkable feature of the invention, at least two consecutive disks 13, 15 are joined by a coaxial annular connecting portion 37, attached to the disks radially internally with respect to the alveoli 27, 29 while the sealing means 39 are between the set of vanes 21, 23 of each of these two disks and the ring of stator vanes 19 interposed between them, it should be noted that the annular connecting portion 37 which extends between the two disks is simple form and formed of a single piece.This connecting part replaces the tones previously used and often bolted together.In the example said connecting portion 37 is an annular piece welded to the two discs 13, 15 so that the junction The connection portion and the two disks can be considered as being in one piece, in the example of FIG. comprise an annular abradable material lining 41, installed at the radially innermost part of said stator vane crown 19 which is situated between the two disks and two annular supports 43, 45 attached respectively to said blades of the two disks; carrying licks 47 which cooperate with said lining of abradable material. The abradable liner 41 may be a known liner of the honeycomb type. The annular supports 43, 45 may be formed by extensions of the mobile blade platforms, restoring annular walls which carry the licks. In the case of nickel alloy parts, the licks 47 generally do not require treatment with a plasma torch. Said annular supports 43, 45 are constituted by segments 51 associated respectively with the blade platforms. These segments are curved, and extend side by side with overlap a in the circumferential direction, as visible in the section of FIG. 4. Thus, an annular cavity 55 is defined between the two disks, the said connecting portion and the sealing means as described above. In operation, the fresh air under pressure which circulates in the center of the rotor, passes through the alveoli 27 and passes through the annular cavity, maintaining it under a certain pressure which opposes the leakage of hot gas from the vein.
Dans le mode de realisation de la figure 2, on adopte un agencement inverse. En effet, Ies moyens d'etancheits 39a comportent deux supports annulaires 43a, 45a rattaches respectivement aux cubes mobiles des deux disques et portant des garnitures abradables annulaires 59. Des Iechettes 61 solidaires de ladite couronne d'aubes de redresseur 19 cooperent avec ces garnitures abradables. Bien entendu, chaque support annulaire est segments comme represents sur la figure 4, c'est-a-dire avec recouvrement dans le sens circonferentiel. Dans le mode de realisation de la figure 2A, chaque support annulaire segments 43a, 45a porte deux garnitures annulaires 59, 60 en materiau abradable, situees de part et d'autre de celui-ci. La couronne d'aubes de redresseur porte, pour chaque disque, deux series de Iechettes 61, 63 (soit 4 au total) cooper-ant avec ces garnitures. Enfin, selon le mode de realisation de la figure 3, chaque segment du support annulaire 43b comporte un prolongement radial interne 67 s'etendant en regard d'une alveole 27 correspondante. On peut ainsi reguler dans une certaine mesure le debit d'air frais qui est introduit dans la chambre annulaire 55 et donc controler a la fois le refroidissement et la pression qui y regne. L'invention peut aussi s'appliquer a un compresseur. Elie vise aussi tout turboreacteur equips dune turbine et/ou d'un compresseur equipes du perfectionnement decrit ci-dessus. In the embodiment of FIG. 2, a reverse arrangement is adopted. Indeed, the sealing means 39a comprise two annular supports 43a, 45a attached respectively to the movable cubes of the two disks and bearing annular abradable fittings 59. Desechettes 61 integral with said ring of stator vanes 19 cooperate with these abradable gaskets . Of course, each annular support is segments as shown in Fig. 4, i.e. with circumferential overlap. In the embodiment of FIG. 2A, each segmental annular support 43a, 45a carries two annular fittings 59, 60 made of abradable material, situated on either side of it. The crown of straightener vanes carries, for each disk, two series of Iechettes 61, 63 (ie 4 in total) cooper-ant with these pads. Finally, according to the embodiment of FIG. 3, each segment of the annular support 43b has an internal radial extension 67 extending opposite a corresponding alveole 27. It is thus possible to regulate to a certain extent the flow of fresh air which is introduced into the annular chamber 55 and thus to control both the cooling and the pressure therein. The invention can also be applied to a compressor. Elie also targets any turbojet equipped with a turbine and / or a compressor equipped with the improvement described above.
Claims (12)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0512791A FR2895021B1 (en) | 2005-12-16 | 2005-12-16 | INTER-STAGE SEALING SYSTEM IN A TURBOMACHINE |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0512791A FR2895021B1 (en) | 2005-12-16 | 2005-12-16 | INTER-STAGE SEALING SYSTEM IN A TURBOMACHINE |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| FR2895021A1 true FR2895021A1 (en) | 2007-06-22 |
| FR2895021B1 FR2895021B1 (en) | 2010-09-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR0512791A Active FR2895021B1 (en) | 2005-12-16 | 2005-12-16 | INTER-STAGE SEALING SYSTEM IN A TURBOMACHINE |
Country Status (1)
| Country | Link |
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| FR (1) | FR2895021B1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1780380A2 (en) * | 2005-10-27 | 2007-05-02 | United Technologies Corporation | Gas turbine blade to vane interface seal |
| WO2013118701A1 (en) * | 2012-02-06 | 2013-08-15 | 三菱重工業株式会社 | Sealing structure and rotating machine equipped with same |
| EP2987953A3 (en) * | 2014-08-20 | 2016-05-25 | United Technologies Corporation | Gas turbine rotors |
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|---|---|---|---|---|
| US3761200A (en) * | 1970-12-05 | 1973-09-25 | Secr Defence | Bladed rotors |
| GB1524108A (en) * | 1975-12-12 | 1978-09-06 | Mtu Muenchen Gmbh | Rotor for fluid flow machine |
| US5156525A (en) * | 1991-02-26 | 1992-10-20 | General Electric Company | Turbine assembly |
| US20030133803A1 (en) * | 2002-01-17 | 2003-07-17 | Snecma Moteurs | Turbomachine rotor arrangement |
| US20040012151A1 (en) * | 2000-09-25 | 2004-01-22 | Alexander Beeck | Sealing arrangement |
| US20050175446A1 (en) * | 2004-02-09 | 2005-08-11 | Siemens Westinghouse Power Corporation | Compressor system with movable seal lands |
-
2005
- 2005-12-16 FR FR0512791A patent/FR2895021B1/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3761200A (en) * | 1970-12-05 | 1973-09-25 | Secr Defence | Bladed rotors |
| GB1524108A (en) * | 1975-12-12 | 1978-09-06 | Mtu Muenchen Gmbh | Rotor for fluid flow machine |
| US5156525A (en) * | 1991-02-26 | 1992-10-20 | General Electric Company | Turbine assembly |
| US20040012151A1 (en) * | 2000-09-25 | 2004-01-22 | Alexander Beeck | Sealing arrangement |
| US20030133803A1 (en) * | 2002-01-17 | 2003-07-17 | Snecma Moteurs | Turbomachine rotor arrangement |
| US20050175446A1 (en) * | 2004-02-09 | 2005-08-11 | Siemens Westinghouse Power Corporation | Compressor system with movable seal lands |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1780380A2 (en) * | 2005-10-27 | 2007-05-02 | United Technologies Corporation | Gas turbine blade to vane interface seal |
| EP1780380A3 (en) * | 2005-10-27 | 2011-07-20 | United Technologies Corporation | Gas turbine blade to vane interface seal |
| WO2013118701A1 (en) * | 2012-02-06 | 2013-08-15 | 三菱重工業株式会社 | Sealing structure and rotating machine equipped with same |
| JP2013160313A (en) * | 2012-02-06 | 2013-08-19 | Mitsubishi Heavy Ind Ltd | Seal structure and rotary machine including the same |
| CN103958949A (en) * | 2012-02-06 | 2014-07-30 | 三菱日立电力系统株式会社 | Sealing structure and rotating machine equipped with same |
| CN103958949B (en) * | 2012-02-06 | 2016-03-16 | 三菱日立电力系统株式会社 | Sealing configuration and possess the rotating machinery of sealing structure |
| EP2987953A3 (en) * | 2014-08-20 | 2016-05-25 | United Technologies Corporation | Gas turbine rotors |
| US10006364B2 (en) | 2014-08-20 | 2018-06-26 | United Technologies Corporation | Gas turbine rotors |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2895021B1 (en) | 2010-09-03 |
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