EP1503040B1 - Lightweight inter-blade platform for a blade support disk of a turbo engine - Google Patents

Lightweight inter-blade platform for a blade support disk of a turbo engine Download PDF

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Publication number
EP1503040B1
EP1503040B1 EP04291888A EP04291888A EP1503040B1 EP 1503040 B1 EP1503040 B1 EP 1503040B1 EP 04291888 A EP04291888 A EP 04291888A EP 04291888 A EP04291888 A EP 04291888A EP 1503040 B1 EP1503040 B1 EP 1503040B1
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EP
European Patent Office
Prior art keywords
securing
blade
orifices
support disk
platform
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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EP04291888A
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German (de)
French (fr)
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EP1503040A1 (en
Inventor
Michèle Jacqueline Queriault
Claude Robert Louis Lejars
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Safran Aircraft Engines SAS
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SNECMA SAS
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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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to the field of turbojets, and more particularly that of the inter-blade platforms for the blade support disks of turbojet blowers.
  • Blowers (or "fan") of turbojet whose blades have a curvilinear foot, generally comprise blade support discs equipped with inter-blade platforms reported to optimize the flow of air between the blades , and more precisely to reconstruct the aerodynamic profile of the internal "vein" at the blades.
  • the first mode is to arrange the three brackets in the form of flanges provided with an orifice for the passage of a fixing pin.
  • the second mode is to arrange two of the three brackets in the form of flanges provided with an orifice for the passage of a fixing pin, and to provide the third fastening lug of a bayonet type fixing device.
  • the document US 5, 277, 548 discloses a platform which comprises a deflecting part whose lower face comprises two fixing lugs which are each pierced with an orifice for the passage of a fixing pin.
  • the reported platforms being generally metallic or composite, their three fastening tabs are formed by machining a solid block.
  • accessibility to the central fastening tab is difficult, which makes its machining particularly difficult.
  • the weight of the platforms is relatively important, which contributes to weigh down the turbojets they equip.
  • the blade when an incident occurs on a blade, for example due to the ingestion of a foreign body by the turbojet, the blade can move (or flex) and interfere with the side edge of one of the neighboring platforms.
  • said platforms deform while remaining substantially in place, which can cause significant damage to the level of the dawn, or even in the engine part of the turbojet engine located downstream of the blades, and / or induce a loss of efficiency of the turbojet, or even its disablement.
  • the invention therefore aims to improve the situation.
  • an inter-blade platform for a blade support disc of a turbojet fan, comprising a deflecting part comprising a lower face provided with a first fixing lug provided with a first orifice. for the passage of a first fixing pin, and a second fixing lug provided with second and third holes for the passage of second and third fixing pins, these fixing pins being intended to secure the two fastening lugs ( or flanges) to the support disk between two adjacent blades.
  • first and second orifices may be placed in the first and second fixing lugs, substantially facing each other, so that the first and second fixing pins are substantially aligned according to the same axis.
  • the platform in case of rupture of the third fixing pin, under the impact of a blade (or any other constraint, in particular centrifugal), the platform can be rotated about the axis defined by the two other fixing pins. This frees up space for the constrained dawn and prevents the platform from being subjected to a deforming deformation both to neighboring blades and performance.
  • the third fixing pin may have a lower resistance to stress than that of the first and second fixing pins.
  • the sections of the first and second fixing pins may be greater than that of the third fixing pin and / or their materials may be different.
  • Such a platform can be made of a metallic or composite material.
  • the invention also relates to a blade support disk comprising a multiplicity of inter-blade platforms of the type shown above and respectively interposed between pairs of adjacent blades.
  • the invention relates to an inter-blade platform for equipping a blade support disc for a blower (or “fan”) of a turbojet engine equipped with curvilinear foot blades (also called “wide rope” blades).
  • a blade support disk 1 is an element of a fan (not shown), mounted on a rotor shaft and on which are fixed a plurality of blades 2, on foot curvilinear, and a multiplicity of inter-blade platforms 3 reported, preferably metal (for example aluminum). More specifically, each reported platform 3 is installed on the support disc 1, between two adjacent blades 2 so as to reconstitute the aerodynamic profile of the internal "vein" at the blades.
  • each platform 3 comprises a deflecting part 4 comprising a lower face 5 provided with a first fixing lug (or flange) 6 provided with a first port 7 for the passage of a first securing pin 8, and a second bracket (or flange) 9 provided with second 10 and third 11 orifices for the passage of second 12 and third 13 fixing pins.
  • the second 10 and third 11 orifices are placed next to each other, substantially in the same level, so that the third pin 13 undergoes the least possible constraints. But, they could also be superimposed or shifted laterally and vertically.
  • the fixing pins 8, 12 and 13 are preferably of the shouldered and threaded type. They each comprise a rod whose one end is provided with a shouldered head and the other end of a thread cooperating with a nut 14, 15 or 16, so as to immobilize the corresponding fastening lug 6 or 9 on one end. fastening lugs 17 or 18 of an element 19 of the support disk 1.
  • the first fixing pin 8 is intended to immobilize the first fastening lug 6 on the fastening lug 17 of the element 19
  • the second 12 and third 13 fixing pins are intended to immobilize the second fixing lug 9 on the bracket 18 of said element 19.
  • the first orifice 7 and the second orifice 10 are placed in the first 6 and second 9 fastening lugs, substantially facing one another, so that the first 8 and second 12 fixing pins are substantially aligned along the same axis X.
  • the platform 3 when the third attachment pin 13 breaks, for example due to a centrifugal stress or under the impact of a blade 2 subjected to a constraint, the platform 3 can pivot around the X axis defined by the alignment of the two fixing pins 8 and 12. The platform 3 released can then follow the movements of the blades constrained (or afflicted) by the events, so that the whole finds a new position equilibrium, the platform 3 can indeed rely on a blade side 2 to a certain extent (beyond a certain displacement there is indeed rupture of the platform and pions).
  • the platform 3 is little or not deformed, which guarantees a streamline aerodynamic little modified, but above all it remains fully in place, which prevents it is ingested by the turbojet engine.
  • the third broken attachment pin 13 remains trapped in the "box" delimited by the platform 3, so that it does not risk damaging elements located at the rear of the fan.
  • this rotation of the platform 3 frees room for the blade 2 which has moved under the effect of the constraint, which prevents it from being badly damaged.
  • the latter may have dimensions that are identical to those of the first 8 and second 12 fixing pins, but have a resistance to stresses lower than their transverse section smaller than that of the first 8 and second 12 fixing pins. This last solution is illustrated in FIG.
  • first 7 and second 10 orifices have substantially identical dimensions but greater than those of the third orifice 11 in order to receive first 8 and second 12 fixing pins, the transverse section of which is greater than that of the third fixing pin 13.
  • the first 8 and second 12 securing pins thus support the centrifugal forces, while said third pin attachment 13 serves in normal operation to ensure the isostatism of the plate -form 3 and abnormal operation to trigger, in case of rupture, the pivoting of said platform 3.

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

Description

L'invention concerne le domaine des turboréacteurs, et plus particulièrement celui des plate-formes inter-aubes pour les disques de support d'aubes des soufflantes de turboréacteur.The invention relates to the field of turbojets, and more particularly that of the inter-blade platforms for the blade support disks of turbojet blowers.

Les soufflantes (ou "fan") de turboréacteur, dont les aubes présentent un pied curviligne, comprennent généralement des disques de support d'aubes équipés de plate-formes inter-aubes rapportées destinées à optimiser l'écoulement de l'air entre les aubes, et plus précisément à reconstituer le profil aérodynamique de la "veine" interne au niveau des aubes.Blowers (or "fan") of turbojet, whose blades have a curvilinear foot, generally comprise blade support discs equipped with inter-blade platforms reported to optimize the flow of air between the blades , and more precisely to reconstruct the aerodynamic profile of the internal "vein" at the blades.

Ces plate-formes rapportées comprennent une partie déflectrice dont la face inférieure comporte fréquemment trois pattes de fixation (une amont, une centrale et une aval) destinées à permettre leur solidarisation, de façon isostatique, à un disque de support. Deux modes de réalisation sont couramment rencontrés. Le premier mode consiste à agencer les trois pattes de fixation sous la forme de brides pourvues d'un orifice pour le passage d'un pion de fixation. Le second mode consiste à agencer deux des trois pattes de fixation sous la forme de brides pourvues d'un orifice pour le passage d'un pion de fixation, et à pourvoir la troisième patte de fixation d'un dispositif de fixation de type baïonnette.These reported platforms comprise a deflecting part whose underside frequently comprises three fastening tabs (an upstream, a central and a downstream) intended to enable their isostatically secured to a support disc. Two embodiments are commonly encountered. The first mode is to arrange the three brackets in the form of flanges provided with an orifice for the passage of a fixing pin. The second mode is to arrange two of the three brackets in the form of flanges provided with an orifice for the passage of a fixing pin, and to provide the third fastening lug of a bayonet type fixing device.

Le document US 5, 277, 548 décrit une plate-forme qui comporte une partie déflectrice dont la face inférieure comporte deux pattes de fixation qui sont chacune percées d'un orifice pour le passage d'un pion de fixation.The document US 5, 277, 548 discloses a platform which comprises a deflecting part whose lower face comprises two fixing lugs which are each pierced with an orifice for the passage of a fixing pin.

Les plate-formes rapportées étant généralement métalliques ou composites, leurs trois pattes de fixation sont formées par usinage d'un bloc massif. Or, du fait de la présence des pattes de fixation amont et aval, l'accessibilité à la patte de fixation centrale est difficile, ce qui rend son usinage particulièrement délicat. En outre, en raison de la présence de trois pattes de fixation le poids des plate-formes est relativement important, ce qui contribue à alourdir les turboréacteurs qu'elles équipent.The reported platforms being generally metallic or composite, their three fastening tabs are formed by machining a solid block. However, because of the presence of the upstream and downstream fastening tabs, accessibility to the central fastening tab is difficult, which makes its machining particularly difficult. In addition, because of the presence of three fastening lugs the weight of the platforms is relatively important, which contributes to weigh down the turbojets they equip.

De plus, lorsqu'un incident survient sur une aube, par exemple en raison de l'ingestion d'un corps étranger par le turboréacteur, l'aube peut se déplacer (ou fléchir) et interférer avec le bord latéral de l'une des plate-formes voisines. Or, du fait du mode de solidarisation des plate-formes, lors d'une telle interférence lesdites plate-formes se déforment tout en demeurant sensiblement en place, ce qui peut provoquer des dégâts importants au niveau de l'aube, voire même dans la partie moteur du turboréacteur située en aval des aubes, et/ou induire une perte d'efficacité du turboréacteur, voire sa mise hors service.In addition, when an incident occurs on a blade, for example due to the ingestion of a foreign body by the turbojet, the blade can move (or flex) and interfere with the side edge of one of the neighboring platforms. However, because of the mode of attachment of the platforms, during such interference said platforms deform while remaining substantially in place, which can cause significant damage to the level of the dawn, or even in the engine part of the turbojet engine located downstream of the blades, and / or induce a loss of efficiency of the turbojet, or even its disablement.

L'invention a donc pour but d'améliorer la situation.The invention therefore aims to improve the situation.

Elle propose à cet effet une plate-forme inter-aubes, pour un disque de support d'aubes d'une soufflante de turboréacteur, comprenant une partie déflectrice comportant une face inférieure munie d'une première patte de fixation pourvue d'un premier orifice pour le passage d'un premier pion de fixation, et d'une seconde patte de fixation pourvue de deuxième et troisième orifices pour le passage de deuxième et troisième pions de fixation, ces pions de fixation étant destinés à solidariser les deux pattes de fixation (ou brides) au disque de support entre deux aubes adjacentes.It proposes for this purpose an inter-blade platform, for a blade support disc of a turbojet fan, comprising a deflecting part comprising a lower face provided with a first fixing lug provided with a first orifice. for the passage of a first fixing pin, and a second fixing lug provided with second and third holes for the passage of second and third fixing pins, these fixing pins being intended to secure the two fastening lugs ( or flanges) to the support disk between two adjacent blades.

Ainsi, en n'utilisant plus que deux pattes de fixation, d'une part, on facilite notablement les opérations d'usinage, et d'autre part, on réduit sensiblement le poids des plate-formes. L'isostatisme est néanmoins conservé du fait de la solidarisation de la plate-forme par l'intermédiaire de trois pions de fixation.Thus, by using only two brackets, on the one hand, it significantly facilitates machining operations, and on the other hand, significantly reduces the weight of the platforms. Isostasis is nevertheless preserved because of the fastening of the platform by means of three fixing pins.

Dans un mode de réalisation particulièrement avantageux, les premier et second orifices peuvent être placés dans les première et seconde pattes de fixation, sensiblement en regard l'un de l'autre, de sorte que les premier et deuxième pions de fixation soient sensiblement alignés suivant un même axe.In a particularly advantageous embodiment, the first and second orifices may be placed in the first and second fixing lugs, substantially facing each other, so that the first and second fixing pins are substantially aligned according to the same axis.

De la sorte, en cas de rupture du troisième pion de fixation, sous l'impact d'une aube (ou de toute autre contrainte, notamment centrifuge), la plate-forme peut être entraînée en rotation autour de l'axe défini par les deux autres pions de fixation. Cela permet de libérer de la place pour l'aube contrainte et d'éviter que la plate-forme ne fasse l'objet d'une déformation nuisible tant aux aubes voisines qu'aux performances.In this way, in case of rupture of the third fixing pin, under the impact of a blade (or any other constraint, in particular centrifugal), the platform can be rotated about the axis defined by the two other fixing pins. This frees up space for the constrained dawn and prevents the platform from being subjected to a deforming deformation both to neighboring blades and performance.

Par ailleurs, afin de favoriser la rupture du troisième pion de fixation en cas d'incident, le troisième pion de fixation peut présenter une résistance aux contraintes inférieure à celle des premier et second pions de fixation. Pour ce faire, les sections des premier et deuxième pions de fixation peuvent être supérieures à celle du troisième pion de fixation et/ou leurs matériaux peuvent être différents.Furthermore, in order to promote breaking of the third fixing pin in the event of an incident, the third fixing pin may have a lower resistance to stress than that of the first and second fixing pins. To do this, the sections of the first and second fixing pins may be greater than that of the third fixing pin and / or their materials may be different.

Une telle plate-forme peut être réalisée dans un matériau métallique ou composite.Such a platform can be made of a metallic or composite material.

L'invention concerne également un disque de support d'aubes comportant une multiplicité de plate-formes inter-aubes du type de celle présentée ci-avant et respectivement intercalées entre des paires d'aubes adjacentes.The invention also relates to a blade support disk comprising a multiplicity of inter-blade platforms of the type shown above and respectively interposed between pairs of adjacent blades.

D'autres caractéristiques et avantages de l'invention apparaîtront à l'examen de la description détaillée ci-après, et des dessins annexés, sur lesquels :

  • la figure 1 illustre de façon schématique une partie d'un disque de support d'aubes dans une vue de face,
  • la figure 2 illustre de façon schématique, dans une vue en coupe transversale décalée, un mode de réalisation d'une plate-forme inter-aubes selon l'invention, et
  • la figure 3 est une vue en coupe selon l'axe III-III de la figure 2, d'une plate-forme inter-aubes selon l'invention illustrant un exemple de réalisation d'une patte de fixation à deux orifices.
Other features and advantages of the invention will appear on examining the detailed description below, and the attached drawings, in which:
  • FIG. 1 schematically illustrates a portion of a blade support disc in a front view,
  • FIG. 2 schematically illustrates, in an offset cross-sectional view, an embodiment of an inter-blade platform according to the invention, and
  • Figure 3 is a sectional view along the axis III-III of Figure 2, an inter-blade platform according to the invention illustrating an embodiment of a fastening lug with two orifices.

Les dessins annexés pourront non seulement servir à compléter l'invention, mais aussi contribuer à sa définition, le cas échéant.The attached drawings may not only serve to complete the invention, but also contribute to its definition, if any.

L'invention porte sur une plate-forme inter-aubes destinée à équiper un disque de support d'aubes pour une soufflante (ou "fan") de turboréacteur équipée d'aubes à pied curviligne (également appelées aubes "large corde").The invention relates to an inter-blade platform for equipping a blade support disc for a blower (or "fan") of a turbojet engine equipped with curvilinear foot blades (also called "wide rope" blades).

Comme cela est partiellement illustré sur la figure 1, un disque de support d'aubes 1 est un élément d'une soufflante (non représentée), monté sur un arbre de rotor et sur lequel sont fixés une multiplicité d'aubes 2, à pied curviligne, et une multiplicité de plate-formes inter-aubes 3 rapportées, de préférence métalliques (par exemple en aluminium). Plus précisément, chaque plate-forme rapportée 3 est installée sur le disque de support 1, entre deux aubes 2 adjacentes de manière à reconstituer le profil aérodynamique de la "veine" interne au niveau des aubes.As is partially illustrated in FIG. 1, a blade support disk 1 is an element of a fan (not shown), mounted on a rotor shaft and on which are fixed a plurality of blades 2, on foot curvilinear, and a multiplicity of inter-blade platforms 3 reported, preferably metal (for example aluminum). More specifically, each reported platform 3 is installed on the support disc 1, between two adjacent blades 2 so as to reconstitute the aerodynamic profile of the internal "vein" at the blades.

Comme cela est illustré sur les figures 2 et 3, chaque plate-forme 3, selon l'invention, comprend une partie déflectrice 4 comportant une face inférieure 5 munie d'une première patte de fixation (ou bride) 6 pourvue d'un premier orifice 7 pour le passage d'un premier pion de fixation 8, et d'une seconde patte de fixation (ou bride) 9 pourvue de deuxième 10 et troisième 11 orifices pour le passage de second 12 et troisième 13 pions de fixation.As illustrated in FIGS. 2 and 3, each platform 3, according to the invention, comprises a deflecting part 4 comprising a lower face 5 provided with a first fixing lug (or flange) 6 provided with a first port 7 for the passage of a first securing pin 8, and a second bracket (or flange) 9 provided with second 10 and third 11 orifices for the passage of second 12 and third 13 fixing pins.

Préférentiellement, et comme illustré, les deuxième 10 et troisième 11 orifices sont placés l'un à côté de l'autre, sensiblement en un même niveau, afin que le troisième pion 13 subisse le moins de contraintes possible. Mais, ils pourraient également être superposés ou décalés latéralement et en hauteur.Preferably, and as illustrated, the second 10 and third 11 orifices are placed next to each other, substantially in the same level, so that the third pin 13 undergoes the least possible constraints. But, they could also be superimposed or shifted laterally and vertically.

Les pions de fixation 8, 12 et 13 sont préférentiellement de type épaulé et fileté. Ils comprennent chacun une tige dont une extrémité est munie d'une tête épaulée et l'autre extrémité d'un filetage coopérant avec un écrou 14, 15 ou 16, de manière à immobiliser la patte de fixation correspondante 6 ou 9 sur l'une des pattes de fixation 17 ou 18 d'un élément 19 du disque de support 1. En d'autres termes, le premier pion de fixation 8 est destiné à immobiliser la première patte de fixation 6 sur la patte de fixation 17 de l'élément 19, et les deuxième 12 et troisième 13 pions de fixation sont destinés à immobiliser la seconde patte de fixation 9 sur la patte de fixation 18 dudit élément 19.The fixing pins 8, 12 and 13 are preferably of the shouldered and threaded type. They each comprise a rod whose one end is provided with a shouldered head and the other end of a thread cooperating with a nut 14, 15 or 16, so as to immobilize the corresponding fastening lug 6 or 9 on one end. fastening lugs 17 or 18 of an element 19 of the support disk 1. In other words, the first fixing pin 8 is intended to immobilize the first fastening lug 6 on the fastening lug 17 of the element 19, and the second 12 and third 13 fixing pins are intended to immobilize the second fixing lug 9 on the bracket 18 of said element 19.

Ainsi, en utilisant deux pattes de fixation 6 et 9 et trois pions de fixation 8, 12 et 13 l'isostatisme est respecté.Thus, by using two fixing lugs 6 and 9 and three fixing pins 8, 12 and 13, the isostatism is respected.

Dans un mode de réalisation particulièrement avantageux, illustré sur la figure 2, le premier orifice 7 et le second orifice 10 sont placés dans les première 6 et seconde 9 pattes de fixation, sensiblement en regard l'un de l'autre, de sorte que les premier 8 et deuxième 12 pions de fixation soient sensiblement alignés suivant un même axe X.In a particularly advantageous embodiment, illustrated in FIG. 2, the first orifice 7 and the second orifice 10 are placed in the first 6 and second 9 fastening lugs, substantially facing one another, so that the first 8 and second 12 fixing pins are substantially aligned along the same axis X.

Grâce à cet agencement particulier, lorsque le troisième pion de fixation 13 se rompt, par exemple du fait d'une contrainte centrifuge ou sous l'impact d'une aube 2 objet d'une contrainte, la plate-forme 3 peut pivoter autour de l'axe X défini par l'alignement des deux pions de fixation 8 et 12. La plate-forme 3 libérée peut ensuite suivre les mouvements des aubes contraintes (ou affligées) par les événements, si bien que l'ensemble retrouve une nouvelle position d'équilibre, la plate-forme 3 pouvant en effet s'appuyer sur un flanc d'aube 2 jusqu'à un certain point (au-delà d'un certain déplacement il y a en effet rupture de la plate-forme et des pions).Thanks to this particular arrangement, when the third attachment pin 13 breaks, for example due to a centrifugal stress or under the impact of a blade 2 subjected to a constraint, the platform 3 can pivot around the X axis defined by the alignment of the two fixing pins 8 and 12. The platform 3 released can then follow the movements of the blades constrained (or afflicted) by the events, so that the whole finds a new position equilibrium, the platform 3 can indeed rely on a blade side 2 to a certain extent (beyond a certain displacement there is indeed rupture of the platform and pions).

Ainsi, la plate-forme 3 est peu ou pas déformée, ce qui garantit un flux aérodynamique peu modifié, mais surtout elle demeure intégralement en place, ce qui évite qu'elle soit ingérée par le moteur du turboréacteur. En outre, le troisième pion de fixation 13 rompu reste prisonnier du "caisson" que délimite la plate-forme 3, si bien qu'il ne risque pas d'endommager des éléments situés à l'arrière de la soufflante. De plus, cette rotation de la plate-forme 3 libère de la place pour l'aube 2 qui s'est déplacée sous l'effet de la contrainte, ce qui permet d'éviter qu'elle ne soit gravement endommagée.Thus, the platform 3 is little or not deformed, which guarantees a streamline aerodynamic little modified, but above all it remains fully in place, which prevents it is ingested by the turbojet engine. In addition, the third broken attachment pin 13 remains trapped in the "box" delimited by the platform 3, so that it does not risk damaging elements located at the rear of the fan. In addition, this rotation of the platform 3 frees room for the blade 2 which has moved under the effect of the constraint, which prevents it from being badly damaged.

Afin de favoriser la rupture du troisième pion de fixation 13 en cas d'incident, celui-ci peut soit présenter des dimensions identiques à celles des premier 8 et deuxième 12 pions de fixation mais une résistance aux contraintes inférieure à la leur, soit présenter une section transverse inférieure à celle des premier 8 et deuxième 12 pions de fixation. Cette dernière solution est illustrée sur la figure 2.In order to promote the breaking of the third fastening pin 13 in the event of an incident, the latter may have dimensions that are identical to those of the first 8 and second 12 fixing pins, but have a resistance to stresses lower than their transverse section smaller than that of the first 8 and second 12 fixing pins. This last solution is illustrated in FIG.

Plus précisément, dans l'exemple illustré sur la figure 2, les premier 7 et second 10 orifices présentent des dimensions sensiblement identiques mais supérieures à celles du troisième orifice 11 afin de recevoir des premier 8 et deuxième 12 pions de fixation dont la section transverse est supérieure à celle du troisième pion de fixation 13.More precisely, in the example illustrated in FIG. 2, the first 7 and second 10 orifices have substantially identical dimensions but greater than those of the third orifice 11 in order to receive first 8 and second 12 fixing pins, the transverse section of which is greater than that of the third fixing pin 13.

On peut également envisager d'utiliser un troisième pion de fixation 13 présentant à la fois une résistance et une section transverse inférieures à celles des premier 8 et deuxième 12 pions de fixation.It is also conceivable to use a third fixing pin 13 having both a resistance and a cross section smaller than those of the first 8 and second 12 fixing pins.

Dans ces variantes de réalisation à troisième pion de fixation 13 "sécable", les premier 8 et deuxième 12 pions de fixation supportent donc les efforts centrifuges, tandis que ledit troisième pion de fixation 13 sert en fonctionnement normal à assurer l'isostatisme de la plate-forme 3 et en fonctionnement anormal à déclencher, en cas de rupture, le pivotement de ladite plate-forme 3.In these alternative embodiments with the third securing pin 13 "breakable", the first 8 and second 12 securing pins thus support the centrifugal forces, while said third pin attachment 13 serves in normal operation to ensure the isostatism of the plate -form 3 and abnormal operation to trigger, in case of rupture, the pivoting of said platform 3.

L'invention ne se limite pas aux modes de réalisation de plate-forme inter-aubes et de disque de support d'aubes décrits ci-avant, seulement à titre d'exemple, mais elle englobe toutes les variantes que pourra envisager l'homme de l'art dans le cadre des revendications ci-après.The invention is not limited to the embodiments of inter-blade platform and blade support disc described above, only by way of example, but encompasses all variants that may be considered by man of the art in the context of the claims below.

Ainsi, on a décrit une plate-forme dans laquelle la première patte de fixation, la moins haute et comportant un seul orifice destiné à recevoir un pion, était placée en amont de la seconde patte de fixation, la plus haute et comportant deux orifices destinés à recevoir chacun un pion. Mais, on peut envisager l'inverse, la première patte étant alors la plus haute, comportant toujours un seul orifice destiné à recevoir un pion, et étant placée en aval de la seconde patte de fixation, la moins haute et comportant toujours deux orifices destinés à recevoir chacun un pion.Thus, a platform has been described in which the first, and smaller, one-stud mounting flange is located upstream of the second, tallest and two-ported mounting bracket. to each receive a pawn. But, we can consider the opposite, the first tab then being the highest, always having a single hole for receiving a pin, and being placed downstream of the second bracket, the lowest and always having two holes for to each receive a pawn.

Claims (11)

  1. Inter-blade platform (3) for a support disk (1) for blades (2) of a turbine fan, comprising a deflector part (4) comprising a lower face (5) equipped with a first securing lug (6) provided with a first orifice (7), and a second securing lug (9) provided with a second orifice (10), characterised in that the second securing lug (9) is also provided with a third orifice (11), said orifices (7, 10, 11) being suitable for interacting with securing pins such as to render said securing lugs (6, 9) as one piece with said support disk (1).
  2. Platform according to Claim 1, characterised in that said first (7) and second (10) orifices are located in said first (6) and second (9) securing lugs substantially opposite one another, in such a way that the securing pins penetrating said first (7) and second (10) orifices are substantially aligned following the same axis (X).
  3. Platform according to Claim 1 or 2, characterised in that said first (7) and second (10) orifices have substantially identical dimensions, and in that said third (11) orifice has dimensions which are substantially smaller than those of said first (7) and second (10) orifices.
  4. Inter-blade platform according to any one of Claims 1 to 3, characterised in that it comprises first (8), second (12), and third (13) securing pins (8) which penetrate respectively said first (7), second (10), and third (11) orifices, and which are suitable for interaction with said orifices (7, 10, 11) such as to render said securing lugs (6, 9) as one piece with said support disk (1).
  5. Platform according to Claim 4, characterised in that said third securing pin (13) has a resistance to stress which is lower than that of said first (8) and second (12) securing pins.
  6. Platform according to either of Claims 4 or 5, characterised in that the first (8) and second (12) securing pins have a first chosen section, and in that the third securing pin (13) has a second section lower than said first section.
  7. Platform according to any one of Claims 4 to 6, characterised in that said third securing pin (13) is made of a material of which the resistance to stress is lower than that of the materials constituting said first (8) and second (12) securing pins.
  8. Platform according to any one of Claims 1 to 7, characterised in that said second (10) and third (11) orifices of the second securing lug (9) are located side by side, substantially at the same level.
  9. Platform according to any one of Claims 1 to 8, characterised in that it is made of a metallic material.
  10. Blade support disk (1), characterised in that it comprises a plurality of inter-blade platforms (3) according to any one of the preceding Claims, interlaced respectively between pairs of adjacent blades (2).
  11. Turbine, characterised in that it comprises a blade support disk (1) according to Claim 10 and a plurality of blades (2) secured on said blade support disk (1).
EP04291888A 2003-07-31 2004-07-23 Lightweight inter-blade platform for a blade support disk of a turbo engine Expired - Lifetime EP1503040B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0309452 2003-07-31
FR0309452A FR2858370B1 (en) 2003-07-31 2003-07-31 INTER-AUBES ALLEGEE PLATFORM FOR A TURBOREACTOR BLADE SUPPORT DISK

Publications (2)

Publication Number Publication Date
EP1503040A1 EP1503040A1 (en) 2005-02-02
EP1503040B1 true EP1503040B1 (en) 2007-02-14

Family

ID=33523037

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04291888A Expired - Lifetime EP1503040B1 (en) 2003-07-31 2004-07-23 Lightweight inter-blade platform for a blade support disk of a turbo engine

Country Status (9)

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US (1) US7163375B2 (en)
EP (1) EP1503040B1 (en)
JP (1) JP4216782B2 (en)
CA (1) CA2475145C (en)
DE (1) DE602004004700T2 (en)
ES (1) ES2277662T3 (en)
FR (1) FR2858370B1 (en)
RU (1) RU2343292C2 (en)
UA (1) UA77742C2 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2913734B1 (en) * 2007-03-16 2009-05-01 Snecma Sa TURBOMACHINE BLOWER
FR2926613B1 (en) * 2008-01-23 2010-03-26 Snecma TURBOMACHINE BLOWER DISK
FR2933887B1 (en) * 2008-07-18 2010-09-17 Snecma PROCESS FOR REPAIRING OR RETRIEVING A TURBOMACHINE DISK AND TURBOMACHINE DISK REPAIRED OR RECOVERED
US8939727B2 (en) 2011-09-08 2015-01-27 Siemens Energy, Inc. Turbine blade and non-integral platform with pin attachment
WO2014088673A2 (en) * 2012-09-20 2014-06-12 United Technologies Corporation Gas turbine engine fan spacer platform attachments
US9759226B2 (en) * 2013-02-15 2017-09-12 United Technologies Corporation Low profile fan platform attachment
US10584592B2 (en) * 2015-11-23 2020-03-10 United Technologies Corporation Platform for an airfoil having bowed sidewalls
US10458425B2 (en) 2016-06-02 2019-10-29 General Electric Company Conical load spreader for composite bolted joint
FR3089548B1 (en) * 2018-12-07 2021-03-19 Safran Aircraft Engines BLOWER INCLUDING AN INTER-BLADE PLATFORM FIXED UPSTREAM BY A VIROLE
FR3097904B1 (en) * 2019-06-26 2021-06-11 Safran Aircraft Engines Inter-vane platform with sacrificial box

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3455537A (en) * 1967-09-27 1969-07-15 Continental Aviat & Eng Corp Air-cooled turbine rotor self-sustaining shroud plate
US4621979A (en) * 1979-11-30 1986-11-11 United Technologies Corporation Fan rotor blades of turbofan engines
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
GB9405473D0 (en) * 1994-03-19 1994-05-04 Rolls Royce Plc A gas turbine engine fan blade assembly
US6447250B1 (en) * 2000-11-27 2002-09-10 General Electric Company Non-integral fan platform

Also Published As

Publication number Publication date
FR2858370B1 (en) 2005-09-30
CA2475145C (en) 2012-08-28
ES2277662T3 (en) 2007-07-16
UA77742C2 (en) 2007-01-15
CA2475145A1 (en) 2005-01-31
US7163375B2 (en) 2007-01-16
JP4216782B2 (en) 2009-01-28
DE602004004700T2 (en) 2007-11-22
EP1503040A1 (en) 2005-02-02
JP2005054785A (en) 2005-03-03
US20050276692A1 (en) 2005-12-15
RU2343292C2 (en) 2009-01-10
FR2858370A1 (en) 2005-02-04
DE602004004700D1 (en) 2007-03-29
RU2004123584A (en) 2006-01-27

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