EP2204546B1 - Bladed stator stage of a compressor, corresponding compressor and method of retention of vanes in such a stator stage - Google Patents

Bladed stator stage of a compressor, corresponding compressor and method of retention of vanes in such a stator stage Download PDF

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Publication number
EP2204546B1
EP2204546B1 EP08172916A EP08172916A EP2204546B1 EP 2204546 B1 EP2204546 B1 EP 2204546B1 EP 08172916 A EP08172916 A EP 08172916A EP 08172916 A EP08172916 A EP 08172916A EP 2204546 B1 EP2204546 B1 EP 2204546B1
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EP
European Patent Office
Prior art keywords
ring
openings
blade
stator stage
accordance
Prior art date
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Application number
EP08172916A
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German (de)
French (fr)
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EP2204546A1 (en
Inventor
Enrique Penalver Castro
Yves Culot
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
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Techspace Aero SA
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Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP08172916A priority Critical patent/EP2204546B1/en
Priority to AT08172916T priority patent/ATE548542T1/en
Priority to CA2688607A priority patent/CA2688607C/en
Priority to US12/644,101 priority patent/US8764392B2/en
Publication of EP2204546A1 publication Critical patent/EP2204546A1/en
Application granted granted Critical
Publication of EP2204546B1 publication Critical patent/EP2204546B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49947—Assembling or joining by applying separate fastener

Definitions

  • the invention relates to a rectifier stage of an axial turbomachine compressor, more particularly to a rectifier stage coming directly downstream of the inlet fan of a turbojet or turbine engine compressor.
  • the invention also relates to a compressor comprising such a rectifier and to a blade retention method of a rectifier stage of an axial turbine engine compressor, more particularly to a rectifier stage coming directly downstream of the fan. the input of a turbojet or turbine engine compressor.
  • the first stage turbojet or turbine engine rectifier must meet particular requirements with respect to the resistance of the blades to the impact or intrusion of a foreign body. Indeed, turbojets and turbine engines are likely to suck in flight different types of foreign bodies such as ice or birds.
  • the fan at the head of the machine is sized to withstand this kind of stress, but the fact remains that this type of foreign body may not be destroyed sufficiently by the fan to pass through the machine without causing other damage.
  • the rectifier stage directly downstream of the blower can also be subject to damage by this type of foreign body.
  • the blades of this stage can be deformed by the impact of the foreign body and potentially become detached especially at the level of the inner shell.
  • a detachment of a blade would cause the turbomachine very significant damage in comparison with a foreign body of the type mentioned above and must be prevented.
  • the fixing of the blades of the rectifier stage to the outer shell is usually made by welding, riveting or screwing.
  • This type of connection is quite rigid and resistant in comparison with the connection with the inner shell which is generally ensured by embedding and flooding the end of the blade in a damping material. It is therefore necessary to use locking systems at the foot of the blade.
  • the document GB 700.012 discloses a principle of attaching stator vanes to an outer shell and also to an inner shell where the ends of the vanes are inserted into respective slots in the inner and outer shells and where a hook wire is passed through openings in the ends of the blades.
  • This document does not specify the length of the wire and specifies how the wire is inserted into the openings. It appears from the teaching of this document that the insertion of the wire into the openings of several successive blades must be made very difficult because of the rigidity of the wire and the small clearance provided between the wire and the orifices.
  • the document GB 732,919 discloses a principle of stator vane attachment similar to that of the previous document.
  • the blade heads are inserted into respective slots of the stator and a latch wire is inserted into openings of the projecting blade heads.
  • the openings are spaced from the slots and the wire is held by a sheet rigidly fixed to the stator and folded over the wire.
  • the vanes may further be spot welded to the sheet in question.
  • This document does not specify the length of the wire or the number of blades held by a section of wire. Nor does it specify how the ends of adjacent wires are joined. It is however clear that the wire is held in place by the folding of the sheet metal ends extending between the blades.
  • the insertion of the wire into the openings of several successive blades must be made very difficult because of the rigidity of the wire and the small clearance provided between the wire and the orifices.
  • the document EP 1 213 484 B1 also discloses a similar principle of attaching blade heads and feet to the outer and inner rings where a strip or strip is inserted into corresponding openings of the blade heads and feet.
  • binding principles of these documents are limited to a lock, that is to say to prevent the release of a head or a blade root of its respective slot. They also require a final step of fixing the wire or the strip.
  • the object of the invention is to propose a principle of retention of the vanes of a rectifier stage which overcomes the aforementioned problems.
  • the invention consists of a rectifying stage of an axial turbomachine compressor, comprising an outer shell and an inner shell, both concentric; a series of blades arranged radially and fixed at their heads to the outer shell and at their feet to the inner shell, the inner shell comprising a series of openings each receiving the foot of a blade projecting from the inner face the inner ferrule, each blade root having at least one opening projecting from the inner face of the inner ferrule; wherein a spiral ring comprising at least two turns is housed in the openings so as to prevent the blade roots from protruding respective openings of the inner ferrule and so as to form a connection between the blade roots.
  • This arrangement has the advantage of ensuring the dual function of locking the blades relative to the inner ring and maintain the blades together while being particularly easy to implement. Indeed, the spiral ring will hold the blades and will be able to deform by sliding of its spirals with respect to each other. The installation requires no special tools and no closing operation of the ring is necessary.
  • the turns of the ring touch when the ring is at rest.
  • the turns of the ring are in pressure against each other when the ring is at rest.
  • the ring is made of metallic material, preferably spring steel.
  • the turns of the ring describe at least two complete turns.
  • the diameter of the ring at rest essentially corresponds to the diameter of the circle passing through the openings of the blade roots so that the ring is floating in the openings when it is in place.
  • the diameter of the ring at rest is slightly less than the diameter of the circle passing through the openings of the blade roots, preferably between 92 and 98%, so that the ring is in tension when it is in place. .
  • the blade roots comprise two rows of openings spaced from each other, each opening row receiving a respective spiral ring.
  • the openings of the blade roots are circular.
  • the circularity of the openings makes it possible to produce them in a simple manner, for example by simple drilling.
  • the invention also relates to an axial compressor comprising a fan at the compressor head and directly downstream of the fan a rectifier stage according to one of the preceding claims.
  • step a) comprises fixing the blade heads to an outer shell, and the diameter of the ring at rest essentially corresponds to the diameter of the circle passing through the openings of the blade roots so that the ring is floating in the openings when in place.
  • step a) comprises the attachment of the blade heads to an outer shell, and the diameter of the ring at rest is slightly less than the diameter of the circle passing through the openings of the blade roots, preferably between 92 and 98 %, so that the ring is in tension when in place.
  • FIG. figure 1 A turbojet axial compressor stator section is illustrated in FIG. figure 1 .
  • This is the rectifier intended to be placed directly downstream of the blower at the compressor inlet. It is composed of an outer shell 1, an inner shell 2 and a series of blades 3 arranged radially between the outer shell and the inner shell.
  • the blades 3 are rigidly fixed to the outer shell 1 via their heads 4. This attachment is made by welding, riveting, screwing or other means of attachment.
  • the inner ends or feet 5 of the blades 3 are inserted into openings or slots 7 (see figure 2 ) are practiced in the inner shell 2. The blades are free to slide in these openings.
  • the feet 5 of the blades 3 protruding from the inner ferrule are provided with holes or openings in which a spiral ring 6 or 6 'is inserted so as to lock the vanes in the inner ferrule and also to bind all vanes between them.
  • the figure 2 which is a bottom view of an inner ferrule section of the figure 1 further details the connection.
  • Slots or openings 7 are made in the inner shell 2 so that each slot receives the inner end 5 of a projecting blade.
  • Each projecting blade root has two holes or openings 8 and 8 '. Due to the constant position of the holes on the blades and the geometric arrangement of the blades, the holes 8, 8 'form two parallel circles.
  • a spiral ring 6, 6 ' is housed in each series of holes 8 and 8' forming a circle so as to lock the vanes with respect to the inner ferrule and to bind the blades together. As can be seen in the figure 2 each ring 6, 6 'is spiral and has two spirals.
  • the rings are of elastic material, preferably of spring steel, and formed so that the turns are in pressure on each other when they are at rest.
  • This type of ring may correspond to the rings marketed under the name Spirolox® and commonly used in mechanics as a stop ring on tree or boring grooves. In view of the large required diameter and other functional requirements, it is possible and even probable that such a ring is not available as a standard article and that it must be made to measure.
  • the supply may be provided in the form of a coil of the desired diameter and a large number of turns, from which the desired number of turns is cut.
  • the ends of the cut ring should then be rounded with a grinding wheel or other suitable tool.
  • a comfortable mechanical clearance is provided between the openings 8, 8 'and the section of the ring 6, 6' so as to make the mounting operation sufficiently easy.
  • the game will be, for example, of the order of 5% to 60%, more particularly of the order of 10% to 30% at the respective sections of the openings and the ring.
  • the installation is done as follows.
  • One end of the ring is detached from the neighboring turn and is inserted into a first hole 8 or 8 'of a blade and then into the following holes so as to thread the ring gradually, turn by turn, in the series of holes forming a circle. To do this the end must describe as many turns through the holes as there are turns in the ring.
  • the ring Once the other end of the ring is engaged in the holes, the ring returns to its original shape, namely that its different turns remain in contact with each other thus forming a compact and stable ring.
  • the assembly thus requires no special tools and even less any operation of fixing or stabilizing sections or ends of the ring.
  • the diameter of the ring at rest corresponds approximately to the diameter of the virtual circle passing through the holes or openings of the blade roots. Once mounted, the ring is relatively floating in the openings of the blades. Alternatively, it is possible to provide a slightly smaller diameter for the ring so as to put the vanes in tension via the ring. The mounting procedure of the ring remains the same except that the action of threading the ring through the openings will be a little more difficult, especially once the first turn engaged. In this case, the diameter of the ring at rest will be of the order of 92 to 98% of the nominal diameter of the virtual circle passing through the openings. Such a configuration provides the advantage that the ring is not floating and pulls all the blades evenly towards the center of the shell.
  • a minimum number of turns is necessary to ensure the function of automatic closure of the ring and holding its diameter. Indeed, a minimum of two turns seems required to ensure the stability of the ring.
  • the presence of two turns in practice means about two turns knowing that the last turn may not be complete. This is the case of some rings marketed under the name Spirolox® which include two turns but whose two ends do not overlap. It is clear that more turns or fractions of turns are possible depending on, inter alia, the section of the turns, the diameter of the ring and the desired stiffness for the ring.
  • the blade may deform in bending downstream of the flow and will be retained at the inner ring by the ring or rings.
  • the openings of the blade roots are positioned such that they are at a distance from the inner face of the ferrule. This gives a certain freedom to the blades to slide through the openings of the ferrule in case of impact by a foreign body. In case of deformation of the blade, it may retract a little of the inner ferrule until the ring comes into abutment against the inner face of the shell near the opening.
  • the ring Before reaching the stop, however, the ring will exert a growing restraining force with the retraction of the dawn.
  • the ring is indeed able to deform by sliding its turns relative to each other unlike a simple ring closed for example by welding.
  • the proposed construction is therefore able to guarantee a locking of the blades in the inner shell while ensuring an elastic retention of the blades. This construction is also very simple to implement.
  • the inner face of the inner ferrule is usually used to be lined with friable material ("abradable" according to the English expression more common) to cooperate in friction with one or more wipers of the rotor of the compressor.
  • friable material abradable according to the English expression more common

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

Abstract

The stage has series of vanes (3), whose heads (4) are fixed at an external shell (1), and feet (5) are fixed at an internal shell (2). The internal shell comprises a series of cutouts receiving the feet, where the feet are projected towards an internal face of the internal shell. Spiral rings (6, 6') are housed in an opening of the each vane to prevent the feet of the vane from being pulled out from the cutouts, respectively, and to form a connection between the feet, where the rings are made of spring steel. Independent claims are also included for the following: (1) a method for holding vanes of a rectifier stage of a compressor of an axial turbomachine (2) a method for fixing heads of vanes to an external shell.

Description

Domaine techniqueTechnical area

L'invention a trait à un étage redresseur d'un compresseur de turbomachine axiale, plus particulièrement à un étage redresseur venant directement en aval de la soufflante d'entrée d'un compresseur de turboréacteur ou de turbomoteur. L'invention a trait également à un compresseur comprenant un tel redresseur et à une méthode de rétention d'aubes d'un étage redresseur d'un compresseur de turbomachine axiale, plus particulièrement d'un étage redresseur venant directement en aval de la soufflante à l'entrée d'un compresseur de turboréacteur ou de turbomoteur.The invention relates to a rectifier stage of an axial turbomachine compressor, more particularly to a rectifier stage coming directly downstream of the inlet fan of a turbojet or turbine engine compressor. The invention also relates to a compressor comprising such a rectifier and to a blade retention method of a rectifier stage of an axial turbine engine compressor, more particularly to a rectifier stage coming directly downstream of the fan. the input of a turbojet or turbine engine compressor.

Etat de la techniqueState of the art

Le premier étage redresseur de turboréacteur ou de turbomoteur doit répondre à des exigences particulières en ce qui concerne la résistance des aubes à l'impact ou intrusion d'un corps étranger. En effet, les turboréacteurs et les turbomoteurs sont susceptibles d'aspirer en vol différents types de corps étrangers comme par exemple de la glace ou des oiseaux. La soufflante en tête de machine est dimensionnée pour résister à ce genre de contrainte mais il n'en reste pas moins que ce type de corps étranger peut ne pas être détruit suffisamment par la soufflante que pour passer au travers de la machine sans causer d'autres dégâts. En effet, l'étage redresseur directement en aval de la soufflante peut également être sujet à des dégâts par ce type de corps étranger. Les aubes de cet étage peuvent être déformées par l'impact du corps étranger et potentiellement se détacher en particulier au niveau de la virole interne. Un détachement d'une aube causerait à la turbomachine des dommages très importants en comparaison avec un corps étranger du type sus mentionné et doit être impérativement empêché. La fixation des aubes de l'étage redresseur à la virole externe est habituellement faite par soudure, rivetage ou vissage. Ce type de liaison est assez rigide et résistant en comparaison avec la liaison avec la virole interne qui est généralement assurée par un encastrement et un noyage de l'extrémité de l'aube dans un matériau amortisseur. Il est donc nécessaire d'utiliser des systèmes de verrouillage au niveau du pied de l'aube.The first stage turbojet or turbine engine rectifier must meet particular requirements with respect to the resistance of the blades to the impact or intrusion of a foreign body. Indeed, turbojets and turbine engines are likely to suck in flight different types of foreign bodies such as ice or birds. The fan at the head of the machine is sized to withstand this kind of stress, but the fact remains that this type of foreign body may not be destroyed sufficiently by the fan to pass through the machine without causing other damage. Indeed, the rectifier stage directly downstream of the blower can also be subject to damage by this type of foreign body. The blades of this stage can be deformed by the impact of the foreign body and potentially become detached especially at the level of the inner shell. A detachment of a blade would cause the turbomachine very significant damage in comparison with a foreign body of the type mentioned above and must be prevented. The fixing of the blades of the rectifier stage to the outer shell is usually made by welding, riveting or screwing. This type of connection is quite rigid and resistant in comparison with the connection with the inner shell which is generally ensured by embedding and flooding the end of the blade in a damping material. It is therefore necessary to use locking systems at the foot of the blade.

Le document GB 700,012 divulgue un principe de fixation d'aubes de stator à une virole externe et aussi à une virole interne où les extrémités des aubes sont insérées dans des fentes respectives dans les viroles interne et externe et où on fait passer un fil faisant crochet au travers d'ouvertures dans les extrémités des aubes. Ce document ne précise cependant pas la longueur du fil et ne précise par de quelle manière le fil est inséré dans les ouvertures. Il apparait au vu de l'enseignement de ce document que l'insertion du fil dans les ouvertures de plusieurs aubes successives doit être rendu très difficile en raison de la rigidité du fil et du faible jeu prévu entre le fil et les orifices.The document GB 700.012 discloses a principle of attaching stator vanes to an outer shell and also to an inner shell where the ends of the vanes are inserted into respective slots in the inner and outer shells and where a hook wire is passed through openings in the ends of the blades. This document, however, does not specify the length of the wire and specifies how the wire is inserted into the openings. It appears from the teaching of this document that the insertion of the wire into the openings of several successive blades must be made very difficult because of the rigidity of the wire and the small clearance provided between the wire and the orifices.

Le document GB 732,919 divulgue un principe de fixation d'aubes de stator similaire à celui du document précédent. Les têtes d'aubes sont insérées dans des fentes respectives du stator et un fil faisant verrou est inséré dans des ouvertures des têtes d'aubes faisant saillie. Les ouvertures sont à distances des fentes et le fil est maintenu par une tôle rigidement fixée au stator et repliée sur le fil. Les aubes peuvent de plus être soudées de manière ponctuelle à la tôle en question. Ce document ne précise pas la longueur du fil ou encore le nombre d'aubes maintenues par une section de fil. Il ne précise pas non plus de quelle manière les extrémités de fils adjacentes sont jointes. Il est cependant clair que le fil est maintenu en place par le pliage des bouts de tôle s'étendant entre les aubes. Tout comme pour l'enseignement du document précédent, il apparait que l'insertion du fil dans les ouvertures de plusieurs aubes successives doit être rendu très difficile en raison de la rigidité du fil et du faible jeu prévu entre le fil et les orifices.The document GB 732,919 discloses a principle of stator vane attachment similar to that of the previous document. The blade heads are inserted into respective slots of the stator and a latch wire is inserted into openings of the projecting blade heads. The openings are spaced from the slots and the wire is held by a sheet rigidly fixed to the stator and folded over the wire. The vanes may further be spot welded to the sheet in question. This document does not specify the length of the wire or the number of blades held by a section of wire. Nor does it specify how the ends of adjacent wires are joined. It is however clear that the wire is held in place by the folding of the sheet metal ends extending between the blades. As with the teaching of the previous document, it appears that the insertion of the wire into the openings of several successive blades must be made very difficult because of the rigidity of the wire and the small clearance provided between the wire and the orifices.

Le document EP 1 213 484 B1 divulgue également un principe similaire de fixation de têtes et pieds d'aubes aux viroles externe et interne où un feuillard ou bandeau est inséré dans des ouvertures correspondantes des têtes et pieds d'aubes.The document EP 1 213 484 B1 also discloses a similar principle of attaching blade heads and feet to the outer and inner rings where a strip or strip is inserted into corresponding openings of the blade heads and feet.

Les principes de liaison de ces documents se limitent à un verrouillage, c'est-à-dire à empêcher la sortie d'une tête ou d'un pied d'aube de sa fente respective. Ils requièrent de plus une étape finale de fixation du fil ou du feuillard.The binding principles of these documents are limited to a lock, that is to say to prevent the release of a head or a blade root of its respective slot. They also require a final step of fixing the wire or the strip.

Exposé de l'inventionPresentation of the invention

L'invention a pour objet de proposer un principe de rétention des aubes d'un étage redresseur palliant les problèmes sus mentionnés.The object of the invention is to propose a principle of retention of the vanes of a rectifier stage which overcomes the aforementioned problems.

L'invention consiste en un étage redresseur d'un compresseur de turbomachine axiale, comprenant une virole externe et une virole interne, toutes deux concentriques; une série d'aubes disposées radialement et fixées à leurs têtes à la virole externe et à leurs pieds à la virole interne, la virole interne comprenant une série d'ajours recevant, chacun, le pied d'une aube faisant saillie de la face interne de la virole interne, chaque pied d'aube présentant au moins une ouverture en saillie de la face interne de la virole interne; où un anneau spiralé comprenant au moins deux spires est logé dans les ouvertures de sorte à empêcher les pieds des aubes de sortir des ajours respectifs de la virole interne et de sorte à former une liaison entre les pieds d'aubes.The invention consists of a rectifying stage of an axial turbomachine compressor, comprising an outer shell and an inner shell, both concentric; a series of blades arranged radially and fixed at their heads to the outer shell and at their feet to the inner shell, the inner shell comprising a series of openings each receiving the foot of a blade projecting from the inner face the inner ferrule, each blade root having at least one opening projecting from the inner face of the inner ferrule; wherein a spiral ring comprising at least two turns is housed in the openings so as to prevent the blade roots from protruding respective openings of the inner ferrule and so as to form a connection between the blade roots.

Cet agencement a pour avantage d'assurer la double fonction de verrouiller les aubes par rapport à la virole interne et de maintenir les aubes entre elles tout en étant particulièrement facile à mettre en oeuvre. En effet, l'anneau spiralé va tenir les aubes et va pouvoir se déformer par glissement de ses spirales les unes par rapport aux autres. La mise en place ne requiert aucun outillage spécial et aucune opération de fermeture de l'anneau n'est nécessaire.This arrangement has the advantage of ensuring the dual function of locking the blades relative to the inner ring and maintain the blades together while being particularly easy to implement. Indeed, the spiral ring will hold the blades and will be able to deform by sliding of its spirals with respect to each other. The installation requires no special tools and no closing operation of the ring is necessary.

Préférentiellement les spires de l'anneau se touchent lorsque l'anneau est au repos.Preferably the turns of the ring touch when the ring is at rest.

Préférentiellement les spires de l'anneau sont en pression les unes contre les autres lorsque l'anneau est au repos.Preferably the turns of the ring are in pressure against each other when the ring is at rest.

Préférentiellement l'anneau est en matériau métallique, préférentiellement en acier à ressort.Preferably the ring is made of metallic material, preferably spring steel.

Préférentiellement les spires de l'anneau décrivent au moins deux tours complets.Preferably the turns of the ring describe at least two complete turns.

Préférentiellement le diamètre de l'anneau au repos correspond essentiellement au diamètre du cercle passant par les ouvertures des pieds d'aubes de sorte à ce que l'anneau soit flottant dans les ouvertures lorsqu'il est en place.Preferably, the diameter of the ring at rest essentially corresponds to the diameter of the circle passing through the openings of the blade roots so that the ring is floating in the openings when it is in place.

Préférentiellement le diamètre de l'anneau au repos est légèrement inférieur au diamètre du cercle passant par les ouvertures des pieds d'aubes, préférentiellement entre 92 et 98%, de sorte à ce que l'anneau soit en traction lorsqu'il est en place.Preferably, the diameter of the ring at rest is slightly less than the diameter of the circle passing through the openings of the blade roots, preferably between 92 and 98%, so that the ring is in tension when it is in place. .

Préférentiellement les pieds d'aubes comportent deux rangées d'ouvertures distantes l'une de l'autre, chaque rangée d'ouverture recevant un anneau spiralé respectif.Preferably the blade roots comprise two rows of openings spaced from each other, each opening row receiving a respective spiral ring.

Préférentiellement les ouvertures des pieds d'aubes sont circulaires. La circularité des ouvertures permet de les réaliser de manière simple comme par exemple par simple perçage.Preferably the openings of the blade roots are circular. The circularity of the openings makes it possible to produce them in a simple manner, for example by simple drilling.

L'invention concerne également un compresseur axial comprenant une soufflante en tête de compresseur et directement en aval de la soufflante un étage redresseur selon l'une des revendications précédentes.The invention also relates to an axial compressor comprising a fan at the compressor head and directly downstream of the fan a rectifier stage according to one of the preceding claims.

L'invention consiste également en une méthode de fixation d'aubes d'un étage redresseur d'un compresseur de turbomachine axiale à une virole interne comprenant les étapes suivantes :

  1. a) prévoir des aubes dont les pieds comprennent chacun une ouverture destinée à recevoir un moyen de blocage ;
  2. b) insérer le pied de chaque aube dans un ajour correspondant de la virole interne de sorte à ce que l'ouverture soit en saillie de la face interne de la virole;
  3. c) mettre en place un anneau spiralé comprenant au moins deux spires dans les ouvertures des pieds d'aubes en enfilant une extrémité de l'anneau successivement dans les ouvertures jusqu'à ce que toutes les spirales de l'anneau soient logées dans les ouvertures.
The invention also consists in a method for fixing vanes of a rectifying stage of an axial turbomachine compressor to an inner shell comprising the following steps:
  1. a) providing blades whose feet each comprise an opening for receiving a locking means;
  2. b) insert the foot of each blade into a corresponding aperture of the inner shell so that the opening is projecting from the inner face of the shell;
  3. c) setting up a spiral ring comprising at least two turns in the openings of the blade roots by threading one end of the ring successively in the openings until all the spirals of the ring are housed in the openings.

Préférentiellement l'étape a) comprend la fixation des têtes d'aubes à une virole externe, et le diamètre de l'anneau au repos correspond essentiellement au diamètre du cercle passant par les ouvertures des pieds d'aubes de sorte que l'anneau soit flottant dans les ouvertures lorsqu'il est en place.Preferably, step a) comprises fixing the blade heads to an outer shell, and the diameter of the ring at rest essentially corresponds to the diameter of the circle passing through the openings of the blade roots so that the ring is floating in the openings when in place.

Préférentiellement l'étape a) comprend la fixation des têtes d'aubes à une virole externe, et le diamètre de l'anneau au repos est légèrement inférieur au diamètre du cercle passant par les ouvertures des pieds d'aubes, préférentiellement entre 92 et 98%, de sorte que l'anneau soit en traction lorsqu'il est en place.Preferably, step a) comprises the attachment of the blade heads to an outer shell, and the diameter of the ring at rest is slightly less than the diameter of the circle passing through the openings of the blade roots, preferably between 92 and 98 %, so that the ring is in tension when in place.

Description sommaire des figuresBrief description of the figures

  • La figure 1 est une vue en perspective d'une section d'étage redresseur d'un compresseur axial, selon l'invention.The figure 1 is a perspective view of a rectifying stage section of an axial compressor, according to the invention.
  • La figure 2 est une vue en perspective agrandie du dessous de la figure 1.The figure 2 is an enlarged perspective view of the underside of the figure 1 .
Meilleure façon de réaliser l'inventionBest way to realize the invention

Une section de redresseur de compresseur axial de turboréacteur est illustrée à la figure 1. Il s'agit du redresseur destiné à être placé directement en aval de la soufflante à l'entrée du compresseur. Il est composé d'une virole externe 1, d'une virole interne 2 et d'une série d'aubes 3 disposées radialement entre la virole externe et la virole interne. Les aubes 3 sont rigidement fixées à la virole externe 1 via leurs têtes 4. Cette fixation est faite par soudure, rivetage, vissage ou tout autre moyen de fixation. Les extrémités internes ou encore pieds 5 des aubes 3 sont insérés dans des ajours ou fentes 7 (voir figure 2) pratiqués dans la virole interne 2. Les aubes sont donc libres de coulisser dans ces ajours. Les pieds 5 des aubes 3 faisant saillie par rapport à la virole interne sont pourvus de trous ou ouvertures dans lesquels un anneau spiralé 6 ou 6' est inséré de sorte à verrouiller les aubes dans la virole interne et également de sorte à lier toutes les aubes entre elles.A turbojet axial compressor stator section is illustrated in FIG. figure 1 . This is the rectifier intended to be placed directly downstream of the blower at the compressor inlet. It is composed of an outer shell 1, an inner shell 2 and a series of blades 3 arranged radially between the outer shell and the inner shell. The blades 3 are rigidly fixed to the outer shell 1 via their heads 4. This attachment is made by welding, riveting, screwing or other means of attachment. The inner ends or feet 5 of the blades 3 are inserted into openings or slots 7 (see figure 2 ) are practiced in the inner shell 2. The blades are free to slide in these openings. The feet 5 of the blades 3 protruding from the inner ferrule are provided with holes or openings in which a spiral ring 6 or 6 'is inserted so as to lock the vanes in the inner ferrule and also to bind all vanes between them.

La figure 2 qui est une vue de dessous d'une section de virole interne de la figure 1 détaille d'avantage la liaison. Des fentes ou ajours 7 sont pratiqués dans la virole interne 2 de sorte que chaque fente reçoive l'extrémité interne 5 d'une aube en saillie. Chaque pied d'aube en saillie comporte deux trous ou ouvertures 8 et 8'. De par la position constante des trous sur les aubes et l'agencement géométrique des aubes, les trous 8, 8' forment deux cercles parallèles. Un anneau spiralé 6, 6' est logé dans chaque série de trous 8 et 8' formant un cercle de sorte à verrouiller les aubes par rapport à la virole interne et à lier les aubes entre elles. Comme on peut le constater à la figure 2, chaque anneau 6, 6' est spiralé et comporte deux spirales. Ceci est d'autant plus visible pour l'anneau 6 dont on peut bien apercevoir les deux extrémités. Si l'on part de l'extrémité de l'anneau 6 en regard de l'autre anneau 6' on compte en fait deux spires dans le sens inverse des aiguilles d'une montre jusqu'à l'autre extrémité. Les deux extrémités se recouvrent sur une certaine distance de sorte à présenter une épaisseur correspondant à trois spires sur cette distance. Les anneaux sont en matériau élastique, préférentiellement en acier à ressort, et formés de sorte que les spires soient en pression les unes sur les autres lorsqu'ils sont au repos. Ce type d'anneau peut correspondre aux anneaux commercialisés sous le nom Spirolox® et couramment utilisés en mécanique comme bague d'arrêt sur des rainures d'arbres ou d'alésages. Au vu du diamètre requis important et à d'autres exigences fonctionnelles, il est possible voire même probable qu'un tel anneau ne soit pas disponible en tant qu'article standard et qu'il doive être fabriqué sur mesure.The figure 2 which is a bottom view of an inner ferrule section of the figure 1 further details the connection. Slots or openings 7 are made in the inner shell 2 so that each slot receives the inner end 5 of a projecting blade. Each projecting blade root has two holes or openings 8 and 8 '. Due to the constant position of the holes on the blades and the geometric arrangement of the blades, the holes 8, 8 'form two parallel circles. A spiral ring 6, 6 'is housed in each series of holes 8 and 8' forming a circle so as to lock the vanes with respect to the inner ferrule and to bind the blades together. As can be seen in the figure 2 each ring 6, 6 'is spiral and has two spirals. This is even more visible for the ring 6 which we can see the two ends. If we start from the end of the ring 6 facing the other ring 6 'there are in fact two turns in the opposite direction of clockwise to the other end. The two ends overlap for a certain distance so as to have a thickness corresponding to three turns over this distance. The rings are of elastic material, preferably of spring steel, and formed so that the turns are in pressure on each other when they are at rest. This type of ring may correspond to the rings marketed under the name Spirolox® and commonly used in mechanics as a stop ring on tree or boring grooves. In view of the large required diameter and other functional requirements, it is possible and even probable that such a ring is not available as a standard article and that it must be made to measure.

La fourniture peut être prévue sous forme de bobine du diamètre souhaité et d'un grand nombre de spires, dont on découpe le nombre de spires souhaité. Les extrémités de l'anneau découpé doivent ensuite être arrondies à l'aide d'une meule ou de tout autre outil adéquat.The supply may be provided in the form of a coil of the desired diameter and a large number of turns, from which the desired number of turns is cut. The ends of the cut ring should then be rounded with a grinding wheel or other suitable tool.

Un jeu mécanique confortable est prévu entre les ouvertures 8, 8' et la section de l'anneau 6, 6' de sorte à rendre l'opération de montage suffisamment aisée. Le jeu sera, à titre d'exemple, de l'ordre de 5% à 60%, plus particulièrement de l'ordre de 10% à 30% au niveau des sections respectives des ouvertures et de l'anneau.A comfortable mechanical clearance is provided between the openings 8, 8 'and the section of the ring 6, 6' so as to make the mounting operation sufficiently easy. The game will be, for example, of the order of 5% to 60%, more particularly of the order of 10% to 30% at the respective sections of the openings and the ring.

La mise en place se fait de la façon suivante. Une extrémité de l'anneau est décollée de la spire voisine et est insérée dans un premier trou 8 ou 8' d'une aube et ensuite dans les trous suivants de sorte à enfiler l'anneau progressivement, spire par spire, dans la série de trous formant un cercle. Pour ce faire l'extrémité doit décrire autant de tours au travers des trous qu'il y a de spires dans l'anneau. Une fois que l'autre extrémité de l'anneau est engagée dans les trous, l'anneau retrouve sa forme initiale, à savoir que ses différentes spires restent en contact les unes sur les autres formant ainsi un anneau compact et stable. Le montage ne requiert ainsi aucun outillage spécial et encore moins d'opération quelconque de fixation ou de stabilisation de tronçons ou des extrémités de l'anneau.The installation is done as follows. One end of the ring is detached from the neighboring turn and is inserted into a first hole 8 or 8 'of a blade and then into the following holes so as to thread the ring gradually, turn by turn, in the series of holes forming a circle. To do this the end must describe as many turns through the holes as there are turns in the ring. Once the other end of the ring is engaged in the holes, the ring returns to its original shape, namely that its different turns remain in contact with each other thus forming a compact and stable ring. The assembly thus requires no special tools and even less any operation of fixing or stabilizing sections or ends of the ring.

Le diamètre de l'anneau au repos correspond approximativement au diamètre du cercle virtuel passant par les trous ou ouvertures des pieds des aubes. Un fois monté, l'anneau est relativement flottant dans les ouvertures des aubes. Alternativement, on peut prévoir un diamètre légèrement inférieur pour l'anneau de sorte à mettre les aubes en tension via l'anneau. La procédure de montage de l'anneau reste la même à la différence près que l'action d'enfiler l'anneau au travers des ouvertures sera un peu plus difficile, en particulier une fois la première spire engagée. Dans ce cas de figure, le diamètre de l'anneau au repos sera de l'ordre de 92 à 98% du diamètre nominal du cercle virtuel passant par les ouvertures. Une telle configuration procure comme avantage que l'anneau ne soit pas flottant et tire toutes les aubes de manière égale vers le centre de la virole.The diameter of the ring at rest corresponds approximately to the diameter of the virtual circle passing through the holes or openings of the blade roots. Once mounted, the ring is relatively floating in the openings of the blades. Alternatively, it is possible to provide a slightly smaller diameter for the ring so as to put the vanes in tension via the ring. The mounting procedure of the ring remains the same except that the action of threading the ring through the openings will be a little more difficult, especially once the first turn engaged. In this case, the diameter of the ring at rest will be of the order of 92 to 98% of the nominal diameter of the virtual circle passing through the openings. Such a configuration provides the advantage that the ring is not floating and pulls all the blades evenly towards the center of the shell.

Un nombre de spires minimum est nécessaire afin d'assurer la fonction de fermeture automatique de l'anneau et de tenue de son diamètre. En effet, un minimum de deux spires semble requis pour assurer la stabilité de l'anneau. La présence de deux spires signifie en pratique environ deux tours sachant que le dernier tour peut ne pas être complet. C'est le cas de certains anneaux commercialisés sous le nom Spirolox® qui comprennent deux spires mais dont les deux extrémités ne se recouvrent pas. Il est clair que d'avantage de spires ou de fractions de tours sont envisageables en fonction, entre autres, de la section des spires, du diamètre de l'anneau et de la raideur voulue pour l'anneau.A minimum number of turns is necessary to ensure the function of automatic closure of the ring and holding its diameter. Indeed, a minimum of two turns seems required to ensure the stability of the ring. The presence of two turns in practice means about two turns knowing that the last turn may not be complete. This is the case of some rings marketed under the name Spirolox® which include two turns but whose two ends do not overlap. It is clear that more turns or fractions of turns are possible depending on, inter alia, the section of the turns, the diameter of the ring and the desired stiffness for the ring.

Dans l'exemple des figures 1 et 2, deux anneaux 6 et 6' égaux sont prévus afin d'assurer une double fixation des aubes sur la virole interne et entre elles. Il est à noter qu'il est envisageable de ne prévoir qu'un seul anneau ou encore de prévoir plus de deux anneaux en fonction des contraintes mécaniques à respecter et de contraintes d'encombrement. On pourrait par exemple envisager un seul anneau de section plus importante ou encore trois anneaux de sections plus petites.In the example of Figures 1 and 2 two rings 6 and 6 'equal are provided to ensure double attachment of the blades on the inner ring and between them. It should be noted that it is conceivable to provide only one ring or to provide more than two rings depending on the mechanical constraints to be met and space constraints. One could for example consider a single ring of larger section or three rings of smaller sections.

En cas d'impact sur une aube par un corps étranger comme de la glace ou un oiseau, l'aube pourra se déformer en flexion en direction aval de l'écoulement et sera retenue au niveau de la virole interne par le ou les anneaux. En effet, comme on peut le voir à la figure 1, les ouvertures des pieds d'aubes sont positionnées de telle sorte qu'elles sont à distance de la face interne de la virole. Ceci donne une certaine liberté aux aubes à coulisser au travers des ajours de la virole en cas d'impact par un corps étranger. En cas de déformation de l'aube, celle-ci pourra se rétracter un peu de la virole interne jusqu'à ce que l'anneau vienne en butée contre la face interne de la virole aux abords de l'ajour. Avant d'arriver en butée, l'anneau va cependant exercer un effort de retenue grandissant avec la rétraction de l'aube. L'anneau est en effet apte à se déformer par un glissement de ses spires les unes par rapport aux autres contrairement à un anneau simple fermé par exemple par soudure. La construction proposée est donc apte à garantir un verrouillage des aubes dans la virole interne tout en assurant une retenue élastique des aubes. Cette construction est de plus très simple à mettre oeuvre.In the event of an impact on a blade by a foreign body such as ice or a bird, the blade may deform in bending downstream of the flow and will be retained at the inner ring by the ring or rings. Indeed, as can be seen at figure 1 , the openings of the blade roots are positioned such that they are at a distance from the inner face of the ferrule. This gives a certain freedom to the blades to slide through the openings of the ferrule in case of impact by a foreign body. In case of deformation of the blade, it may retract a little of the inner ferrule until the ring comes into abutment against the inner face of the shell near the opening. Before reaching the stop, however, the ring will exert a growing restraining force with the retraction of the dawn. The ring is indeed able to deform by sliding its turns relative to each other unlike a simple ring closed for example by welding. The proposed construction is therefore able to guarantee a locking of the blades in the inner shell while ensuring an elastic retention of the blades. This construction is also very simple to implement.

La face interne de la virole interne est destinée de manière usuelle à être garnie de matériau friable (« abradable » selon l'expression anglaise plus courante) en vue de coopérer en frottement avec une ou plusieurs léchettes du rotor du compresseur. Les anneaux et les pieds d'aubes sont donc susceptibles d'être noyés dans une ou plusieurs couches de matériaux appliqués à l'état pâteux en vue d'assurer cette fonction ainsi qu'éventuellement une fonction d'amortissement.The inner face of the inner ferrule is usually used to be lined with friable material ("abradable" according to the English expression more common) to cooperate in friction with one or more wipers of the rotor of the compressor. The rings and the blade roots are therefore likely to be embedded in one or several layers of materials applied in the pasty state to ensure this function and possibly a damping function.

Claims (13)

  1. Stator stage of an axial turbomachine compressor, comprising an external shell and an internal shell, both being concentric
    a series of blades (3) arranged radially and attached at their tips (4) to the outer shell (1) and their roots (5) to the inner shell (2), the inner shell (2) having a series of cutouts (7) into each one of which a blade root (5) is fitted projecting from the inner face of the inner shell (2), each blade root (5) having at least one opening (8, 8') projecting from the inner face of the inner shell (2);
    wherein
    a spiral ring (6, 6') comprising at least two turns is housed in an opening (8, 8') of each blade (3) of the set of blades so as to prevent the blade roots (5) from coming out of their respective cutouts (7) in the inner shell (2) so as to connect the blade roots (5).
  2. Stator stage in accordance with the previous claim, wherein the turns of the ring (6, 6') are in contact with each other when the ring is at rest.
  3. Stator stage in accordance with the previous claim, wherein the turns of the ring (6, 6') are in compression against each other when the ring is at rest.
  4. Stator stage in accordance with the previous claim, wherein the ring (6, 6') is made of spring steel.
  5. Stator stage in accordance with the previous claim, wherein the turns of the ring (6, 6') make at least two complete circles.
  6. Stator stage in accordance with the previous claim, wherein the diameter of the ring (6, 6') at rest is equal to the diameter of the virtual circle passing through the openings (8, 8') of the blade roots (5) so that the ring floats in the openings when it is in place.
  7. Stator stage in accordance with claims 1 to 5, wherein the diameter of the ring (6, 6') at rest is slightly less than the diameter of the virtual circle passing through the openings (8, 8') of the blade roots (5), preferably between 92 % and 98 %, so that the ring is in tension when it is in place.
  8. Stator stage in accordance with one of the preceding claims, wherein the roots of the blades (5) have two sets of openings (8, 8') separated from each other, each set fitted with its own spiral ring (6, 6').
  9. Stator stage in accordance with one of the preceding claims, wherein the blade root openings (5) are circular.
  10. Axial compressor comprising a compressor blower head and, directly downstream from the blower, a stator stage in accordance with one of the preceding claims.
  11. Method for retaining blades in a compressor stator stage of an axial turbomachine with an internal shell containing the following steps:
    a) provide blades (3) whose roots (5) each have at least one opening (8, 8') for use as a means of locking;
    b) insert the root (5) of each blade in the corresponding cutout (7) of the inner shell (2) so that the opening (8, 8') is projecting from the inner face of the shell (2);
    wherein the following step is:
    c) insert a spiral ring (6, 6') comprising at least two turns in an opening (8, 8') of each blade root (5) by threading one end of the ring through the openings one after another until all the turns of the ring are housed in the openings.
  12. Fixing method in accordance with the previous claim, wherein step a) comprises fixing the tips of blades (4) into an external shell (1), and the diameter of the ring at rest is substantially the same as the diameter of the circle passing through the openings of the blade roots so that the ring floats in the openings when it is in place.
  13. Fixing method in accordance with the previous claim, wherein step a) comprises fixing the tips of blades (4) into an external shell (1), and the diameter of the ring at rest is slightly less, preferably between 92% to 98%, than the diameter of the circle passing through the openings of the blade roots so that the ring is in tension in the openings when it is in place.
EP08172916A 2008-12-24 2008-12-24 Bladed stator stage of a compressor, corresponding compressor and method of retention of vanes in such a stator stage Active EP2204546B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP08172916A EP2204546B1 (en) 2008-12-24 2008-12-24 Bladed stator stage of a compressor, corresponding compressor and method of retention of vanes in such a stator stage
AT08172916T ATE548542T1 (en) 2008-12-24 2008-12-24 VIDEO STAGE OF A COMPRESSOR, CORRESPONDING COMPRESSOR AND METHOD FOR SECURING BLADES IN SUCH A VIDEO STAGE
CA2688607A CA2688607C (en) 2008-12-24 2009-12-14 Blade retention at a compressor rectifier stage for impact resistance
US12/644,101 US8764392B2 (en) 2008-12-24 2009-12-22 Blade retention at a compressor rectifier stage for impact resistance

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08172916A EP2204546B1 (en) 2008-12-24 2008-12-24 Bladed stator stage of a compressor, corresponding compressor and method of retention of vanes in such a stator stage

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EP2204546A1 EP2204546A1 (en) 2010-07-07
EP2204546B1 true EP2204546B1 (en) 2012-03-07

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EP (1) EP2204546B1 (en)
AT (1) ATE548542T1 (en)
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Publication number Priority date Publication date Assignee Title
EP2735707B1 (en) * 2012-11-27 2017-04-05 Safran Aero Boosters SA Axial turbomachine guide nozzle with segmented inner shroud and corresponding compressor
EP3075960B1 (en) * 2015-03-31 2017-12-27 Ansaldo Energia IP UK Limited Multi-airfoil guide vane unit
US10472979B2 (en) * 2016-08-18 2019-11-12 United Technologies Corporation Stator shroud with mechanical retention
US20190078469A1 (en) * 2017-09-11 2019-03-14 United Technologies Corporation Fan exit stator assembly retention system
JP7264881B2 (en) * 2017-09-20 2023-04-25 スルザー ターボ サービシーズ フェンロー ベスローテン フェンノートシャップ Wing unit assembly

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE862158C (en) * 1943-10-05 1953-01-08 Brown Ag Vibration damper for the blades of turbo machines
FR998220A (en) 1949-10-26 1952-01-16 Soc D Const Et D Equipements M Advanced training in the assembly and fixing of fixed blades for turbomachines
NL179681B (en) * 1952-07-22 1955-12-15 Hitachi Shipbuilding Eng Co DEVICE FOR BURNING WASTE GASES.
GB732919A (en) 1953-07-15 1955-06-29 Rolls Royce Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines
FR1380241A (en) * 1963-02-01 1964-11-27 Ass Elect Ind Development of rotors for axial flow turbines
DE19507673C2 (en) * 1995-03-06 1997-07-03 Mtu Muenchen Gmbh Guide wheel for turbomachinery
DE60026687T2 (en) * 2000-12-06 2006-11-09 Techspace Aero S.A. Stator stage of a compressor
GB2410984B (en) * 2004-02-14 2006-03-08 Rolls Royce Plc Securing assembly

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US20110002787A1 (en) 2011-01-06
US8764392B2 (en) 2014-07-01
CA2688607C (en) 2017-03-28
ATE548542T1 (en) 2012-03-15
EP2204546A1 (en) 2010-07-07
CA2688607A1 (en) 2010-06-24

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