EP2369136A1 - Weight-reduced single-piece multi-stage drum of an axial flow compressor - Google Patents
Weight-reduced single-piece multi-stage drum of an axial flow compressor Download PDFInfo
- Publication number
- EP2369136A1 EP2369136A1 EP10156427A EP10156427A EP2369136A1 EP 2369136 A1 EP2369136 A1 EP 2369136A1 EP 10156427 A EP10156427 A EP 10156427A EP 10156427 A EP10156427 A EP 10156427A EP 2369136 A1 EP2369136 A1 EP 2369136A1
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- EP
- European Patent Office
- Prior art keywords
- central portion
- rotation
- axis
- rotor stage
- annular zone
- 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.)
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- 239000012530 fluid Substances 0.000 claims abstract description 19
- 239000003351 stiffener Substances 0.000 claims abstract description 7
- 238000011144 upstream manufacturing Methods 0.000 claims description 35
- 210000003462 vein Anatomy 0.000 claims description 4
- 238000010276 construction Methods 0.000 description 25
- 239000000463 material Substances 0.000 description 10
- 230000008901 benefit Effects 0.000 description 7
- 230000002787 reinforcement Effects 0.000 description 6
- 240000006108 Allium ampeloprasum Species 0.000 description 3
- 235000005254 Allium ampeloprasum Nutrition 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000004513 sizing Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
Images
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
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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
- 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
- F01D5/063—Welded rotors
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
- F04D29/329—Details of the hub
Definitions
- the invention consists of an axial turbomachine compressor drum rotor stage, said compressor being intended to be traversed by a fluid stream in a direction generally oriented along the axis of rotation, the rotor stage comprising a generally symmetrical wall in revolution.
- the junction of the upstream and / or downstream stiffening part with the central part of the support zone is set back from the upstream and / or downstream edge, respectively, of said central part, so as to that the upstream and / or downstream edge of said central portion is projecting.
- the fact that the connecting portions are slightly recessed from the respective edges of the central portion allows to limit certain concentrations of stresses in the dawn.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
L'invention a trait à un tambour de compresseur de turbomachine axiale, plus particulièrement à un étage rotorique d'un tel compresseur, sachant que le tambour peut être constitué d'un assemblage de plusieurs parties correspondant à différents étages rotoriques.The invention relates to an axial turbomachine compressor drum, more particularly to a rotor stage of such a compressor, knowing that the drum may consist of an assembly of several parts corresponding to different rotor stages.
Plus particulièrement encore, l'invention a trait à des mesures de construction d'un tambour de compresseur de turbomachine axiale, ces mesures étant destinées notamment à alléger le tambour.More particularly still, the invention relates to measurements of construction of an axial turbomachine compressor drum, these measures being intended in particular to lighten the drum.
D'une manière générale, un tambour de compresseur est un corps creux généralement symétrique en révolution par rapport à son axe de rotation qui correspond à l'axe de la turbomachine. Le corps creux a une forme générale d'ovale ou d'ogive selon la forme de l'écoulement. Plusieurs rangées d'aubes sont fixées au tambour de manière à former différents étage rotoriques, sachant que chaque étage rotorique coopère avec un étage statorique constitué d'une rangée d'aubes statoriques, chaque paire d'étages rotorique et statorique formant ainsi un étage de compression du compresseur.In general, a compressor drum is a hollow body generally symmetrical in revolution with respect to its axis of rotation which corresponds to the axis of the turbomachine. The hollow body has a general shape of oval or ogive according to the shape of the flow. Several rows of blades are fixed to the drum so as to form different rotor stages, knowing that each rotor stage cooperates with a stator stage consisting of a row of stator vanes, each pair of rotor and stator stages thus forming a stage of compressing the compressor.
Les efforts centrifuges exercés par les aubes rotoriques sur le tambour sont très élevés, en particulier lorsque le tambour est de grand diamètre et/ou à grande vitesse de rotation. Il est un souci constant pour les designers de compresseurs d'assurer une tenue mécanique satisfaisante du tambour et des aubes tout en veillant à alléger le tambour au maximum.The centrifugal forces exerted by the rotor blades on the drum are very high, in particular when the drum is of large diameter and / or at a high speed of rotation. It is a constant concern for the compressor designers to ensure a satisfactory mechanical strength of the drum and the blades while ensuring to lighten the drum to the maximum.
Un design classique est notamment divulgué au document de brevet
Le document de brevet
Une demande de brevet européen n°
L'invention a pour objectif de proposer un étage rotorique de tambour ou un tambour palliant au moins un des inconvénients sus mentionnés, plus particulièrement l'invention a pour objectif de proposer un tambour allégé.The object of the invention is to propose a drum rotor stage or a drum which overcomes at least one of the disadvantages mentioned above, more particularly the object of the invention is to propose a lightened drum.
L'invention consiste en un étage rotorique de tambour de compresseur de turbomachine axiale, ledit compresseur étant destiné à être traversé par une veine fluide dans une direction orientée généralement selon l'axe de rotation, l'étage rotorique comprenant une paroi généralement symétrique en révolution par rapport à l'axe de rotation et formant un corps creux, ladite paroi comprenant un voile et une zone annulaire destinée à supporter une rangée d'aubes et intégralement formée avec le voile; chacune desdites aubes ayant un bord d'attaque et un bord de fuite; remarquable en ce que ladite zone annulaire comprend une partie centrale surélevée par rapport audit voile, dont la surface extérieure délimite la veine fluide entre les aubes et est d'un seul tenant et formée intégralement sur le pourtour de ladite zone annulaire depuis un bord amont de ladite partie centrale jusqu'au bord d'attaque de la rangée d'aubes et/ou depuis un bord aval de ladite partie centrale jusqu'au bord de fuite de la rangée d'aubes.The invention consists of an axial turbomachine compressor drum rotor stage, said compressor being intended to be traversed by a fluid stream in a direction generally oriented along the axis of rotation, the rotor stage comprising a generally symmetrical wall in revolution. relative to the axis of rotation and forming a hollow body, said wall comprising a web and an annular zone for supporting a row of blades and integrally formed with the web; each of said blades having a leading edge and a trailing edge; characterized in that said annular zone comprises a raised central portion with respect to said web, the outer surface of which delimits the fluid vein between the vanes and is in one piece and integrally formed around the periphery of said annular zone from an upstream edge of said central portion to the leading edge of the row of blades and / or from a downstream edge of said central portion to the trailing edge of the row of blades.
Cette construction permet d'obtenir un tambour rigidifié et allégé. En effet, le fait de surélever la zone de support des aubes crée un bossage ou demi-caisson au niveau de la paroi sous la rangée d'aube, c'est-à-dire exactement là où les efforts sont les plus grands. De plus, le fait de prévoir une surface continue au niveau de la partie centrale délimitant la veine fluide évite de déforcer le bossage ainsi créé. En comparaison avec l'état de la technique, cette construction remplace les attaches classiques comme les brochages et alvéoles, ainsi que les « poireaux » massifs par une forme particulière de la paroi au niveau de la zone destinée à supporter les aubes. La surface intérieure du bossage ou demi-caisson est préférentiellement libre de nervure, par exemple du type « poireau » servant uniquement de renfort et ajoutant de la massivité. Les aubes peuvent être formées intégralement avec le rotor ou encore être soudée sur la surface en question. Alternativement, une partie inférieure des aubes peut être formée intégralement avec le rotor, la partie restante des aubes étant ensuite soudée à cette partie.This construction makes it possible to obtain a stiffened and lightened drum. Indeed, raising the support area of the blades creates a boss or half-box at the wall under the blade row, that is to say exactly where the efforts are greatest. In addition, the fact of providing a continuous surface at the central portion defining the fluid stream avoids deforcing the boss thus created. In comparison with the state of the technique, this construction replaces conventional fasteners such as pin-holes and alveoli, as well as massive "leeks" by a particular shape of the wall at the level of the zone intended to support the blades. The inner surface of the boss or half-box is preferably free of rib, for example of the type "leek" serving only reinforcement and adding massiveness. The vanes can be integrally formed with the rotor or welded to the surface in question. Alternatively, a lower part of the blades may be formed integrally with the rotor, the remaining portion of the blades being then welded to this part.
Les caractéristiques selon lesquelles la partie centrale est d'un seul tenant et formée intégralement sur le pourtour de ladite zone annulaire depuis un bord amont de ladite partie centrale jusqu'au bord d'attaque de la rangée d'aubes et/ou depuis un bord aval de ladite partie centrale jusqu'au bord de fuite de la rangée d'aubes sont certes intéressantes mais non essentielles. Elles permettent cependant de distinguer l'invention de l'enseignement de la demande de brevet européen non encore publiée qui sera potentiellement interférente.The features according to which the central portion is integral and integrally formed around the periphery of said annular zone from an upstream edge of said central portion to the leading edge of the blade row and / or from an edge downstream of said central portion to the trailing edge of the row of blades are certainly interesting but not essential. However, they make it possible to distinguish the invention from the teaching of the unpublished European patent application which will be potentially interfering.
Selon un mode avantageux de l'invention, la surface extérieure de la partie centrale de la zone annulaire est généralement lisse, préférentiellement généralement cylindrique, conique ou de forme bombée sur de la longueur de ladite surface selon l'axe de rotation.According to an advantageous embodiment of the invention, the outer surface of the central portion of the annular zone is generally smooth, preferably generally cylindrical, conical or curved over the length of said surface along the axis of rotation.
Une pareille construction de la surface extérieure de la partie centrale présente l'avantage de garantir une bonne aérodynamique.Such a construction of the outer surface of the central portion has the advantage of ensuring good aerodynamics.
Selon un autre mode avantageux de l'invention, au moins une partie, préférentiellement la totalité, de chaque aube est intégralement formée avec la zone annulaire. Alternativement les aubes peuvent être soudées à leur base à la zone annulaire. Différentes configurations de liaison par soudure sont possibles, avec ou sans plate-forme intégralement formée avec l'aube.According to another advantageous embodiment of the invention, at least a portion, preferably all, of each blade is integrally formed with the annular zone. Alternatively the vanes can be welded at their base to the annular zone. Different weld connection configurations are possible, with or without platform integrally formed with the blade.
Selon un encore autre mode avantageux de l'invention, la zone annulaire comprend au moins une partie raidisseur généralement perpendiculaire à l'axe de rotation ou inclinée, préférentiellement selon un angle moyen de plus de 40° avec l'axe de rotation, reliant la partie centrale au voile. Ce raidisseur peut être une simple nervure émanant du voile et rejoignant la zone support. En fonction de divers paramètres de dimensionnement, il est possible de ne prévoir qu'une seule partie raidisseur centrale pour une rangée d'aubes, assurant la liaison entre le voile et la zone annulaire. Dans ce cas, la partie raidisseur pourrait avoir une forme de nervure généralement perpendiculaire à l'axe de rotation et la zone annulaire aurait une forme de bandage. Le voile serait libre de raidisseur sur sa face interne au droit du raidisseur.According to another advantageous embodiment of the invention, the annular zone comprises at least one stiffening part generally perpendicular to the axis of rotation or inclined, preferably at an average angle of more than 40 ° with the axis of rotation, connecting the central part to the veil. This stiffener may be a simple rib emanating from the veil and joining the support zone. Depending on various sizing parameters, it is possible to provide only one central stiffening portion for a row of blades, providing the connection between the web and the annular zone. In this case, the stiffening portion could have a rib shape generally perpendicular to the axis of rotation and the annular zone would have a bandage shape. The veil would be free of stiffener on its internal face to the right of the stiffener.
Selon un encore autre mode avantageux de l'invention, la zone annulaire comprend une partie raidisseur amont reliant la partie centrale au voile en amont et une partie raidisseur aval reliant la partie centrale au voile en aval. La présence de deux raidisseurs assurant la liaison de la partie centrale au voile assure une stabilité optimale de la zone annulaire support des aubes.According to another advantageous embodiment of the invention, the annular zone comprises an upstream stiffening part connecting the central part to the veil upstream and a downstream stiffening part connecting the central part to the veil downstream. The presence of two stiffeners ensuring the connection of the central part to the veil ensures optimum stability of the annular support area of the blades.
Selon un encore autre mode avantageux de l'invention, la ou au moins une des parties raidisseur est généralement perpendiculaire à l'axe de rotation ou inclinée selon un angle moyen de plus de 40° avec l'axe de rotation, préférentiellement selon un angle moyen de plus de 50°. L'inclinaison d'une ou des deux parties raidisseur permet de modifier la raideur longitudinale du tambour et, partant, la dynamique longitudinale du tambour. Cette mesure peut ainsi permettre de bien contrôler les modes vibratoires en relation avec les jeux fonctionnels entre les éléments rotoriques et statoriques.According to another advantageous embodiment of the invention, the or at least one of the stiffening parts is generally perpendicular to the axis of rotation or inclined at an average angle of more than 40 ° with the axis of rotation, preferably at an angle average of more than 50 °. The inclination of one or both stiffener parts makes it possible to modify the longitudinal stiffness of the drum and hence the longitudinal dynamics of the drum. This measurement can thus be used to control vibratory modes in relation to the functional clearances between the rotor and stator elements.
Selon un encore autre mode avantageux de l'invention, la surface intérieure de la partie centrale et des parties amont et aval de la zone annulaire forme une cavité annulaire ouverte vers l'intérieur du corps creux de l'étage rotorique. Cette mesure définit une forme optimale de bossage assurant un renforcement tout en minimisant l'apport de matière.According to yet another advantageous embodiment of the invention, the inner surface of the central part and the upstream and downstream parts of the annular zone form an annular cavity open towards the inside of the hollow body of the rotor stage. This measure defines an optimal shape of boss providing reinforcement while minimizing the supply of material.
Selon un encore autre mode avantageux de l'invention, la section de la zone annulaire dans un plan passant par l'axe de rotation présente un profil en forme générale de U dont l'ouverture est dirigée vers l'axe de rotation.According to yet another advantageous embodiment of the invention, the section of the annular zone in a plane passing through the axis of rotation has a generally U-shaped profile whose opening is directed towards the axis of rotation.
Selon un encore autre mode avantageux de l'invention, la ou au moins une des parties raidisseurs est en saillie du voile vers l'intérieur du corps creux. Ces parties en saillie augmentent de manière intéressante la raideur des parties raidisseurs.According to yet another advantageous embodiment of the invention, the or at least one of the stiffening parts is projecting from the web towards the interior of the hollow body. These projecting parts advantageously increase the stiffness of the stiffening parts.
Selon un encore autre mode avantageux de l'invention, la jonction de la partie raidisseur amont avec la partie centrale de la zone annulaire est approximativement à l'aplomb, selon une direction perpendiculaire à l'axe de rotation, de l'intersection du bord d'attaque de la rangée d'aubes avec ladite partie centrale et/ou la jonction de la partie raidisseur aval avec la partie centrale de ladite zone annulaire est approximativement à l'aplomb, selon une direction perpendiculaire à l'axe de rotation, de l'intersection du bord de fuite de la rangée d'aubes avec ladite partie centrale. Cet agencement permet d'optimiser la reprise des contraintes exercées par les aubes en rotation.According to another advantageous embodiment of the invention, the junction of the upstream stiffening portion with the central portion of the annular zone is approximately perpendicular, in a direction perpendicular to the axis of rotation, of the intersection of the edge. driving the vane row with said central portion and / or the junction of the downstream stiffening portion with the central portion of said annular zone is approximately plumb, in a direction perpendicular to the axis of rotation, of the intersection of the trailing edge of the row of vanes with said central portion. This arrangement makes it possible to optimize the recovery of the stresses exerted by the rotating blades.
Selon un encore autre mode avantageux de l'invention, la jonction de la partie raidisseur amont et/ou aval avec la partie centrale de la zone support est en retrait du bord amont et/ou aval, respectivement, de ladite partie centrale, de manière ce que le bord amont et/ou aval de ladite partie centrale soit en saillie. Le fait que les parties de liaison soient légèrement en retrait des bords respectifs de la partie centrale permet de limiter certaines concentrations de contraintes dans l'aube.According to yet another advantageous embodiment of the invention, the junction of the upstream and / or downstream stiffening part with the central part of the support zone is set back from the upstream and / or downstream edge, respectively, of said central part, so as to that the upstream and / or downstream edge of said central portion is projecting. The fact that the connecting portions are slightly recessed from the respective edges of the central portion allows to limit certain concentrations of stresses in the dawn.
Selon un encore autre mode avantageux de l'invention, la jonction de la partie raidisseur amont avec la partie centrale de la zone annulaire est en retrait en aval de l'intersection du bord d'attaque de la rangée d'aubes avec ladite partie centrale et/ou la jonction de la partie raidisseur aval avec la partie centrale de ladite zone est en retrait en amont de l'intersection du bord de fuite de la rangée d'aubes avec ladite partie centrale.According to another advantageous embodiment of the invention, the junction of the upstream stiffening part with the central part of the annular zone is set back downstream of the intersection of the leading edge of the row of vanes with said central portion. and / or the junction of the downstream stiffening portion with the central portion of said zone is recessed upstream of the intersection of the trailing edge of the row of vanes with said central portion.
Selon un encore autre mode avantageux de l'invention, la partie centrale s'étend selon l'axe de rotation depuis le bord d'attaque jusqu'au bord de fuite de la rangée d'aube.According to another advantageous embodiment of the invention, the central portion extends along the axis of rotation from the leading edge to the trailing edge of the blade row.
Selon un encore autre mode avantageux de l'invention, la partie centrale s'étend selon l'axe de rotation, préférentiellement exclusivement, depuis un congé de raccordement du bord d'attaque jusqu'à un congé de raccordement du bord de fuite de la rangée d'aube.According to another advantageous embodiment of the invention, the central portion extends along the axis of rotation, preferably exclusively, since a connection fillet from the leading edge to a connection fillet of the trailing edge of the blade row.
L'invention consiste également en un tambour de compresseur de turbomachine axiale comprenant au moins un étage, préférentiellement plusieurs étages, tels que définis ci-avant.The invention also consists of an axial turbomachine compressor drum comprising at least one stage, preferably several stages, as defined above.
D'autres caractéristiques et avantages de la présente invention seront mieux compris à l'aide de la description et des dessins.Other features and advantages of the present invention will be better understood from the description and drawings.
La
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Un compresseur comprenant un tambour ou rotor selon l'invention est illustré à la
Comme on peut le voir à la
Le rotor ou tambour représenté à la
Le rotor comprend ainsi trois de ces zones construites de manière similaire. La zone support de la première rangées d'aubes rotoriques va ainsi être décrite plus en détails, sachant que cette description s'applique également aux autres étages du rotor.The rotor thus comprises three of these zones constructed in a similar manner. The support zone of the first rows of rotor blades will thus be described in more detail, knowing that this description also applies to the other stages of the rotor.
La zone support de la paroi 4 est de forme annulaire et constituée essentiellement de deux parties 20 et 22 de paroi sous forme de nervures généralement perpendiculaires à l'axe de rotation et d'une partie centrale 21 supportant la rangée d'aubes. La partie centrale 21 est ainsi surélevée par rapport à la paroi avoisinante formant le voile. Cette surélévation dans une direction généralement perpendiculaire à l'axe de rotation et orientée vers l'extérieur du corps creux permet à la surface extérieure de la partie centrale 21 d'être au niveau des surfaces des viroles intérieures avoisinantes 18 délimitant la veine fluide. Ces surfaces des viroles intérieures sont en effet à distance du voile en raison de la hauteur des léchettes et de l'épaisseur nécessaire de la virole. Les surfaces des viroles intérieures et des parties centrales 21 des zones annulaires, qui délimitent la veine fluide sont ainsi généralement compensées et alignées de manière à assurer un écoulement le moins perturbé possible.The support zone of the
La partie centrale 21 de la zone support annulaire est généralement de section généralement droite ou légèrement courbée de manière à correspondre à la forme générale de la veine fluide du rotor. Cette partie centrale présente une forme généralement annulaire avec les pieds d'aubes intégralement formés avec elle. Elle présente une longueur, selon une direction longitudinale, qui correspond essentiellement à la largeur dans cette direction des pieds d'aube avec leurs congés de raccordement. La partie centrale 21 constitue ainsi une plateforme généralement annulaire pour la rangée d'aube. Les parties latérales amont 20 et aval 22 sous forme de nervures relient cette plateforme au reste du voile. La zone annulaire support des aubes forme ainsi une cavité annulaire à l'intérieur du corps creux et ouverte vers ce dernier, en direction de l'axe de rotation. La section de la zone annulaire dans un plan passant par l'axe de rotation présente un profil généralement en « U » dont l'ouverture est dirigée vers l'axe de rotation.The
Les jonctions des parties latérales amont 20 et aval 22 avec la partie centrale sont telles qu'elles sont à distance des extrémités respectives de la plateforme formée par la partie centrale. La jonction de la partie amont 20 avec la partie centrale 21 est approximativement à l'aplomb (selon une perpendiculaire à l'axe de rotation) du bord d'attaque de l'aube, plus précisément à l'aplomb de l'intersection de la prolongation du bord d'attaque de l'aube avec la plateforme. Il en va de même pour la partie de paroi aval avec le bord de fuite de l'aube. La plateforme formée par la partie centrale présente ainsi un bord en saillie côté amont et pareillement un bord en saillie côté aval. Cette construction permet d'optimiser la reprise des efforts centrifuges exercés par les aubes. En effet, la massivité des aubes est présente sur toute leur largeur, si bien que le fait de prévoir la retenue de la plateforme à distance de ses bords amont et aval permet d'éviter une concentration de contraintes défavorable au niveau du congé de raccordement. De plus, ces mesures de constructions ménagent une certaine place entre le bord amont et le voile, et pareillement entre le bord aval et le voile, cette place permettant de rapprocher les rangées d'aubes rotoriques et statoriques, respectivement, ce qui allège considérable le poids total du compresseur.The junctions of the upstream and downstream
Les parties de paroi amont 20 et aval 22 de la zone annulaire sont en saillie du voile vers l'intérieur du corps creux, formant ainsi des nervures 24 et 26 internes au corps creux. Elles contribuent au renforcement du rotor et présentent l'avantage que leur massivité est quelque peu en retrait du voile et donc plus proche de l'axe de rotation.The upstream and
Il est à noter que les pieds d'aubes ne doivent pas nécessairement être intégralement formés avec le rotor. En effet, il est tout-à-fait envisageable de prévoir la zone support lisse, éventuellement pourvue d'un orifice destiné à assurer ou renforcer la fixation des aubes par la suite. Les aubes peuvent en effet être simplement soudées à leurs pieds à la zone support, à fleur de la surface extérieure de la partie centrale 21. Les aubes peuvent également présenter à leurs pieds une surface assimilable à une plateforme de fixation destinée à être insérée dans un orifice correspondant de la zone annulaire pour y être ensuite soudée. Dans ce cas, cette plateforme serait idéalement de taille réduite, à savoir essentiellement centrée sur l'aube et à distance des bords d'attaque et de fuite.It should be noted that the blade roots do not have to be integrally formed with the rotor. Indeed, it is quite possible to provide the smooth support zone, possibly provided with an orifice intended to ensure or reinforce the attachment of the blades thereafter. The blades can indeed be simply welded at their feet to the support zone, flush with the outer surface of the
Il est également à noter que la paroi du rotor ne doit pas nécessairement être construite en une seule pièce. En effet, il peut même être souhaitable de prévoir plusieurs tronçons destinés à être assemblés. Une telle construction permet de faire un gain substantiel de matière à usiner car elle permet une première mise à forme par forgeage qui sera sensiblement plus proche de la forme définitive. Il en résulte une diminution de perte de matière enlevée par usinage ainsi qu'une diminution du temps d'usinage.It should also be noted that the rotor wall does not have to be built in one piece. Indeed, it may even be desirable to provide several sections to be assembled. Such a construction makes it possible to make a substantial gain in the material to be machined because it enables a first shaping by forging which will be substantially closer to the final shape. This results in a reduction in loss of material removed by machining and a reduction in machining time.
La
La
La
La
La
Il est important de noter que les différentes constructions alternatives des zones support d'aubes du rotor sont purement exemplatives et non limitatives. Il existe donc d'autres constructions similaires conformes à l'invention.It is important to note that the different alternative constructions of the rotor blade support zones are purely illustrative and not limiting. There are therefore other similar constructions in accordance with the invention.
De plus, il est à noter que chaque étage rotorique pourra avoir une construction de la zone annulaire support des aubes qui lui sera spécifique en fonction de divers paramètres de dimensionnement.In addition, it should be noted that each rotor stage may have a construction of the annular support area of the blades which will be specific to it according to various sizing parameters.
Dans la description de l'invention qui a été fait ci-avant, la paroi constituant le voile et la zone annulaire support d'un étage rotorique est prévue d'un seul tenant. Bien que ce mode de réalisation semble être le plus pratique à ce jour, il est à noter que l'invention pourrait prévoir que la paroi de l'étage rotorique soit composée de plusieurs tronçons de paroi assemblés par exemple par soudage.In the description of the invention which has been made above, the wall constituting the web and the annular support area of a rotor stage is provided in one piece. Although this embodiment seems to be the most practical to date, it should be noted that the invention could provide that the wall of the rotor stage is composed of several wall sections assembled for example by welding.
Claims (15)
caractérisé en ce que
ladite zone annulaire comprend une partie centrale (21) surélevée par rapport audit voile, dont la surface extérieure délimite la veine fluide entre les aubes (14) et est d'un seul tenant sur le pourtour de ladite zone annulaire depuis un bord amont (30) de ladite partie centrale (21) jusqu'au bord d'attaque (26) de la rangée d'aubes (14) et/ou depuis un bord aval (32) de ladite partie centrale (21) jusqu'au bord de fuite (28) de la rangée d'aubes.Axial turbomachine compressor drum rotor stage, said compressor being intended to be traversed by a fluid stream in a direction oriented generally along the axis of rotation, the rotor stage comprising a wall (4) generally symmetrical in revolution with respect to the axis of rotation and forming a hollow body, said wall comprising a web and an annular area (20, 21, 22) for supporting a row of vanes (14) and integrally formed with the web; each of said blades having a leading edge (26) and a trailing edge (28);
characterized in that
said annular zone comprises a central portion (21) raised with respect to said web, whose outer surface delimits the fluid vein between the vanes (14) and is in one piece on the periphery of said annular zone from an upstream edge (30). ) from said central portion (21) to the leading edge (26) of the row of vanes (14) and / or from a downstream edge (32) of said central portion (21) to the trailing edge (28) of the row of blades.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10156427A EP2369136B1 (en) | 2010-03-12 | 2010-03-12 | Weight-reduced single-piece multi-stage drum of an axial flow compressor |
CA2733435A CA2733435C (en) | 2010-03-12 | 2011-03-08 | Reduced monobloc multistage drum of axial compressor |
RU2011108828/06A RU2556945C2 (en) | 2010-03-12 | 2011-03-10 | Stage of axial compressor of turbine machine with drum rotor |
US13/045,115 US8932012B2 (en) | 2010-03-12 | 2011-03-10 | Reduced monobloc multistage drum of axial compressor |
CN201110059219.5A CN102192186B (en) | 2010-03-12 | 2011-03-11 | Reduced monoblock multistage drum of axial compressor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10156427A EP2369136B1 (en) | 2010-03-12 | 2010-03-12 | Weight-reduced single-piece multi-stage drum of an axial flow compressor |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2369136A1 true EP2369136A1 (en) | 2011-09-28 |
EP2369136B1 EP2369136B1 (en) | 2012-12-19 |
Family
ID=42244385
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10156427A Active EP2369136B1 (en) | 2010-03-12 | 2010-03-12 | Weight-reduced single-piece multi-stage drum of an axial flow compressor |
Country Status (5)
Country | Link |
---|---|
US (1) | US8932012B2 (en) |
EP (1) | EP2369136B1 (en) |
CN (1) | CN102192186B (en) |
CA (1) | CA2733435C (en) |
RU (1) | RU2556945C2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2818635A1 (en) * | 2013-06-25 | 2014-12-31 | Techspace Aero S.A. | Drum of axial turbomachine compressor with mixed fixation of blades |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
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US9234435B2 (en) | 2013-03-11 | 2016-01-12 | Pratt & Whitney Canada Corp. | Tip-controlled integrally bladed rotor for gas turbine |
EP2801702B1 (en) * | 2013-05-10 | 2020-05-06 | Safran Aero Boosters SA | Inner shroud of turbomachine with abradable seal |
EP2843196B1 (en) * | 2013-09-03 | 2020-04-15 | Safran Aero Boosters SA | Turbomachine compressor and corresponding turbomachine |
EP2930308B1 (en) * | 2014-04-11 | 2021-07-28 | Safran Aero Boosters SA | Faceted axial turbomachine housing |
US20150354361A1 (en) * | 2014-06-09 | 2015-12-10 | General Electric Company | Rotor assembly and method of manufacturing thereof |
US9333603B1 (en) | 2015-01-28 | 2016-05-10 | United Technologies Corporation | Method of assembling gas turbine engine section |
CN105673559B (en) * | 2016-04-13 | 2018-04-06 | 上海理工大学 | Efficient meridionally-accelerated axial flow fan with casing |
BE1025092B1 (en) * | 2017-03-31 | 2018-10-29 | Safran Aero Boosters S.A. | BRUSH SEAL FOR TURBOMACHINE ROTOR |
CN113503264A (en) * | 2021-07-22 | 2021-10-15 | 浙江华擎航空发动机科技有限公司 | Multistage compressor adopting combined shafting structure |
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GB2059819A (en) | 1979-10-12 | 1981-04-29 | Gen Motors Corp | Manufacture of axial compressor rotor |
US4784572A (en) | 1987-10-14 | 1988-11-15 | United Technologies Corporation | Circumferentially bonded rotor |
EP1319842A1 (en) * | 2001-12-17 | 2003-06-18 | Techspace Aero S.A. | Rotor or rotating element for turbocompressor |
US20030223873A1 (en) * | 2002-05-30 | 2003-12-04 | Carrier Charles William | Inertia welding of blades to rotors |
WO2006110125A2 (en) * | 2004-12-01 | 2006-10-19 | United Technologies Corporation | Stacked annular components for turbine engines |
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US2944326A (en) * | 1955-06-02 | 1960-07-12 | Gen Electric | Method of staking blades |
US4201513A (en) * | 1976-12-07 | 1980-05-06 | Rolls-Royce (1971) Limited | Gas turbine engines |
FR2637321B1 (en) * | 1988-10-05 | 1990-11-30 | Snecma | TURBOMACHINE ROTOR PROVIDED WITH A BLADE FIXING DEVICE |
GB9325135D0 (en) * | 1993-12-08 | 1994-02-09 | Rolls Royce Plc | Manufacture of wear resistant components |
US6077002A (en) * | 1998-10-05 | 2000-06-20 | General Electric Company | Step milling process |
US6969239B2 (en) * | 2002-09-30 | 2005-11-29 | General Electric Company | Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine |
RU2264561C1 (en) * | 2004-06-08 | 2005-11-20 | Аверичкин Павел Алексеевич | Axial-flow compressor stage of gas-turbine engine |
US7329092B2 (en) * | 2006-01-27 | 2008-02-12 | General Electric Company | Stator blade airfoil profile for a compressor |
US8087884B2 (en) * | 2006-11-30 | 2012-01-03 | General Electric Company | Advanced booster stator vane |
ATE548540T1 (en) * | 2008-12-24 | 2012-03-15 | Techspace Aero Sa | ROTOR STAGE OF A ONE-PIECE BLADED COMPRESSOR DRUM OF AN AXIAL FLOW MACHINE AND CORRESPONDING PRODUCTION METHOD. |
-
2010
- 2010-03-12 EP EP10156427A patent/EP2369136B1/en active Active
-
2011
- 2011-03-08 CA CA2733435A patent/CA2733435C/en active Active
- 2011-03-10 RU RU2011108828/06A patent/RU2556945C2/en not_active IP Right Cessation
- 2011-03-10 US US13/045,115 patent/US8932012B2/en active Active
- 2011-03-11 CN CN201110059219.5A patent/CN102192186B/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
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GB2059819A (en) | 1979-10-12 | 1981-04-29 | Gen Motors Corp | Manufacture of axial compressor rotor |
US4784572A (en) | 1987-10-14 | 1988-11-15 | United Technologies Corporation | Circumferentially bonded rotor |
EP1319842A1 (en) * | 2001-12-17 | 2003-06-18 | Techspace Aero S.A. | Rotor or rotating element for turbocompressor |
US20030223873A1 (en) * | 2002-05-30 | 2003-12-04 | Carrier Charles William | Inertia welding of blades to rotors |
WO2006110125A2 (en) * | 2004-12-01 | 2006-10-19 | United Technologies Corporation | Stacked annular components for turbine engines |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2818635A1 (en) * | 2013-06-25 | 2014-12-31 | Techspace Aero S.A. | Drum of axial turbomachine compressor with mixed fixation of blades |
Also Published As
Publication number | Publication date |
---|---|
CA2733435C (en) | 2017-01-17 |
CN102192186A (en) | 2011-09-21 |
US20110223013A1 (en) | 2011-09-15 |
RU2556945C2 (en) | 2015-07-20 |
US8932012B2 (en) | 2015-01-13 |
CN102192186B (en) | 2015-03-25 |
EP2369136B1 (en) | 2012-12-19 |
RU2011108828A (en) | 2012-09-20 |
CA2733435A1 (en) | 2011-09-12 |
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