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EP1939459B1 - System with jaws for connecting two flanges, in particular for a compressor shroud - Google Patents

System with jaws for connecting two flanges, in particular for a compressor shroud Download PDF

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Publication number
EP1939459B1
EP1939459B1 EP06127255.5A EP06127255A EP1939459B1 EP 1939459 B1 EP1939459 B1 EP 1939459B1 EP 06127255 A EP06127255 A EP 06127255A EP 1939459 B1 EP1939459 B1 EP 1939459B1
Authority
EP
European Patent Office
Prior art keywords
flanges
connection system
jaw
jaws
pair
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP06127255.5A
Other languages
German (de)
French (fr)
Other versions
EP1939459A1 (en
Inventor
André Lhoest
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
Original Assignee
Safran Aero Boosters SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Priority to EP06127255.5A priority Critical patent/EP1939459B1/en
Priority to US11/964,380 priority patent/US8182216B2/en
Publication of EP1939459A1 publication Critical patent/EP1939459A1/en
Application granted granted Critical
Publication of EP1939459B1 publication Critical patent/EP1939459B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • Y10T29/53—Means to assemble or disassemble
    • Y10T29/53987—Tube, sleeve or ferrule

Definitions

  • the present invention relates to a connection system of two substantially tubular elements, in particular two ferrules of an axial compressor housing.
  • Axial compressors for example in turbojet engines, are generally formed by an axial succession of rotors and stators. Each rotor is a set of rotating blades attached to the drive shaft of the compressor. Each stator is a set of stationary straightening vanes attached to the compressor housing. Each rotor is followed by a stator, so as to form a compressor stage.
  • a turbojet may comprise a plurality of successive compressors, for example a low pressure compressor mounted in front of a high pressure compressor, where each comprises a different drive shaft.
  • an axial compressor casing is formed by a series of substantially tubular elements, or ferrules, successively connected.
  • Each ferrule generally surrounds a compressor stage, i.e. a rotor and a stator.
  • a ferrule will therefore normally comprise the set of stationary vanes forming the stator, or means for fixing said stationary vanes, as well as an abradable inner surface in order to avoid excessive friction with the vanes of the rotor.
  • the radial size of the expanded flanges also has other problems.
  • this size makes it difficult assembly and disassembly operations, because of interference between the flanges and elements external to the compressor, such as hoods.
  • the connecting flanges of the housings of the low pressure compressor housing are too bulky, they will abut against the intermediate casing placed generally at the rear of the low pressure compressor and used to support the entire turbojet engine.
  • the document EP 1 517 045 A2 discloses another fastener for the two flanges of a vacuum pump.
  • the object of the invention is to overcome the drawbacks of the state of the art by providing fastening elements making it possible to minimize the radial bulk of a connection system of substantially tubular elements, and particularly of compressor housing shrouds. axial.
  • a connection system as indicated at the beginning, wherein the fastening elements comprise at least one pair of jaws arranged to be connected by a set of traction elements, for example screws or bolts, each of the jaws of said pair being arranged to bear on the proximal face of one of the flanges, and a jaw of said pair further comprising means, such as substantially radial shoulders, arranged to form a positive connection with complementary means in the two flanges for a transmission of circumferential forces between the two flanges.
  • the fastening elements comprise at least one pair of jaws arranged to be connected by a set of traction elements, for example screws or bolts, each of the jaws of said pair being arranged to bear on the proximal face of one of the flanges, and a jaw of said pair further comprising means, such as substantially radial shoulders, arranged to form a positive connection with complementary means in the two flanges for a transmission of circumferential forces between the two flanges.
  • each of the two flanges comprises at least one substantially radial cut, and one of the jaws of said pair is arranged to form a positive connection with a cutout of each of the two flanges for said transmission of circumferential forces between the two flanges.
  • connection system further comprises centering means for taking up radial forces between the two flanges.
  • centering means for taking up radial forces between the two flanges. This makes it possible to decouple in turn the radial forces of the axial and circumferential forces and to size these centering means specifically for the recovery of the radial forces without influencing the bulk of the transmission means of other efforts.
  • the proximal face of at least one of said two flanges comprises an inclined or conical surface being intended to come into contact with one of said pair of jaws in order to retain it radially by a positive connection, and thus to prevent the The pair of jaws can slide to lose contact with the flanges, and thus the axial connection.
  • At least one of the jaws is arranged to support a hood or fairing external to the substantially tubular elements, for example a compressor nozzle in a double-flow turbojet engine, thus making it possible to simplify the support of such hoods or fairings and to facilitate the assembly and disassembly of the whole.
  • a hood or fairing external to the substantially tubular elements, for example a compressor nozzle in a double-flow turbojet engine
  • this support is arranged with a boss arranged in said jaw for receiving an insert or rivet nut for fixing said hood or fairing, thus allowing a solid but removable support without having to increase the radial size of the connection system.
  • said at least one jaw is integrated in said hood or fairing, thereby reducing the number of parts, with the advantages of reduced cost and greater reliability and simplicity.
  • the present invention also relates to an axial compressor casing, for example a low-pressure compressor of a turbojet or turboprop, comprising a plurality of ferrules, at least two of which are adjacent and connected by a connection system according to the invention, and than a method of using such a connection system in such a housing.
  • an axial compressor casing for example a low-pressure compressor of a turbojet or turboprop, comprising a plurality of ferrules, at least two of which are adjacent and connected by a connection system according to the invention, and than a method of using such a connection system in such a housing.
  • At least one of said two adjacent ferrules comprises a stator and / or an abradable inner surface, so as to integrate these elements of the compressor in the housing.
  • each of the rings 101 and 102 of a low-pressure compressor casing of a double-flow turbojet engine comprises a flange, respectively designated 103 and 104.
  • Each of these flanges 103, 104 has a face proximal, respectively designated 103p and 104p, and a distal face, respectively designated 103d and 104d.
  • a set of orifices respectively designated 105 and 106 connect the proximal face 103p, 104p to the distal face 103d, 104d.
  • the orifices 105 of the flange 103 are aligned with the orifices 106 of the flange 104, so as to be able to pass screws 107. By tightening these screws 107 with nuts 108, it is therefore possible to establish an axial connection between the ferrules 101 and 102.
  • each of the rings 201, 202 comprises a flange, respectively designated 203 and 204.
  • Each of the flanges 203, 204 comprises a distal face, designated respectively 203d and 204d, substantially perpendicular to the axis of the ferrule 201, 202 corresponding, and a proximal face, respectively designated 203p and 204p, substantially conical.
  • Each of the flanges 203, 204 also comprises a plurality of cutouts 205 distributed around the perimeter of each flange 203, 204.
  • Each cutout 205 has two substantially radial edges 206.
  • the cutouts 205 of the flange 203 are intended to be aligned with the cutouts 205 of the other flange 204 when the ferrules 201, 202 are connected.
  • the connection system illustrated further comprises a pair of jaws 207, 208 connected by screws 209 retained by nuts 210.
  • One jaw 207 bears on the proximal face 203p of a flange 203, while the other jaw 208 is supported on the proximal face 204p of the other flange 204.
  • This axial prestressing of the flanges 203, 204 makes it possible to transmit, via the distal faces 203d, 204d, the axial compressive forces between the ferrules 201, 202, and by the bolts 209 the axial tension forces.
  • the conical shape of the proximal faces 203p, 204p provides radial retention of the pair of jaws 207, 208 as the bolts 209 are tightened.
  • only one of the faces of the flanges 203 may have a conical shape corresponding to a single conical jaw 207, as shown in FIG. figure 2 .
  • the jaw 207 has an axial extension 211 such that the contact zone between the two flanges 203d, 204d is below this extension.
  • the axial extension 211 is housed in the aligned cutouts 205 of the two flanges 203, 204. In this way, this extension 211 forms a positive connection with the edges 206 of the two cutouts, making it possible to transmit the circumferential forces in torsion between the two flanges 203 204.
  • the jaw 207 provides a working section in shear greater than that of screws 107 of the state of the art without having to widen the diameter of the flanges 203, 204.
  • the screws 209 connecting the jaws 207, 208 are therefore substantially free of shear forces and can be dimensioned with a considerably reduced cross section relative to bolts 107 of the state of the art illustrated in FIG. figure 1 .
  • Circumferential torsional forces between the flanges 203, 204 could however, according to other embodiments, be transmitted by other positive connections.
  • the jaws 207, 208 could both have extensions, each of these extensions being accommodated in the cutout 205 of one of the flanges 203, 204, so that each forms a positive connection with the edges 206 of each cutout 205, and said extensions in turn present shoulders substantially radial and complementary so as to transmit the shear forces between the two jaws 207, 208.
  • the flats of the blanks 205 of the flanges may optionally have a radial clearance with the corresponding faces of the jaws 207 and / or 208, as shown in FIG. figure 2 for cutting the flange 204.
  • FIG 4 an alternative embodiment is illustrated where two rings 201, 202 of a low pressure compressor casing are also connected by flanges 203, 204.
  • the shell 201 serves as a support for the separation spout of the compressor, which is of axisymmetrical geometry. and is centered on the ferrule 201.
  • the flanges 203, 204 are retained by a pair of jaws 207, 208 connected by screws 209 and nuts 210.
  • the jaw 207 is integrated into a separating spout.
  • the separation spout of the compressor 401 which forms a shroud separating the primary flow from the secondary flow in a turbofan engine, can be supported by the low pressure compressor housing without resorting to a boss on the annulus 201 similar to the boss 402 formed on the shell 202 to support the hood 403 extending the compressor nozzle 401.
  • the shell 202 has bosses 402 to support the hood 403 extending the separation nozzle of the compressor 401.
  • bosses formed on the ferrules to support hoods or fairings have the disadvantage of widening the outer diameter of the ferrules, making more difficult to assemble and dismantle them because of possible interference with elements outside the compressor housing.
  • boss 402 of the embodiment shown in FIG. figure 4 by the means illustrated in the figure 5 .
  • a jaw 208 intended to replace the jaw 208 of the figure 4 , on which is formed a boss 501 provided with a hole 502 for receiving a bolt, screw, insert or rivet to support a hood or fairing.
  • This jaw and the flange 204 need not necessarily have a conical shape, because the radial retention of the jaw is ensured by its attachment to the axisymmetric part 207.
  • connection system can be mounted by temporarily connecting the ferrules 201, 202 by Colson collars before placing the jaws 207, 208, and / or disassembled by temporarily connecting the ferrules 201, 202 by Colson collars before removing the jaws 207, 208.

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

Description

La présente invention se rapporte à un système de raccordement de deux éléments sensiblement tubulaires, en particulier deux viroles d'un carter de compresseur axial.The present invention relates to a connection system of two substantially tubular elements, in particular two ferrules of an axial compressor housing.

Les compresseurs axiaux, par exemple dans des turboréacteurs, sont généralement formés par une succession axiale de rotors et stators. Chaque rotor est un ensemble d'aubes rotatives fixées à l'arbre d'entraînement du compresseur. Chaque stator est un ensemble d'aubes de redressement stationnaires fixées au carter du compresseur. Chaque rotor est suivi d'un stator, de manière à former un étage de compresseur.Axial compressors, for example in turbojet engines, are generally formed by an axial succession of rotors and stators. Each rotor is a set of rotating blades attached to the drive shaft of the compressor. Each stator is a set of stationary straightening vanes attached to the compressor housing. Each rotor is followed by a stator, so as to form a compressor stage.

Un turboréacteur peut comporter une pluralité de compresseurs successifs, par exemple un compresseur basse pression monté devant un compresseur haute pression, où chacun comporte un arbre d'entraînement différent.A turbojet may comprise a plurality of successive compressors, for example a low pressure compressor mounted in front of a high pressure compressor, where each comprises a different drive shaft.

Généralement, un carter de compresseur axial est formé par une série d'éléments sensiblement tubulaires, ou viroles, raccordés successivement. Chaque virole entoure généralement un étage de compresseur, c'est-à-dire un rotor et un stator. Une virole comportera donc normalement l'ensemble d'aubes stationnaires formant le stator, ou bien des moyens de fixation desdites aubes stationnaires, ainsi qu'une surface intérieure abradable afin d'éviter un frottement excessif avec les aubes du rotor.Generally, an axial compressor casing is formed by a series of substantially tubular elements, or ferrules, successively connected. Each ferrule generally surrounds a compressor stage, i.e. a rotor and a stator. A ferrule will therefore normally comprise the set of stationary vanes forming the stator, or means for fixing said stationary vanes, as well as an abradable inner surface in order to avoid excessive friction with the vanes of the rotor.

Les paires de viroles successives sont raccordées par des systèmes de raccordement comportant :

  1. a) deux brides, chacune étant sensiblement annulaire et comportant une face proximale destinée à être solidaire d'une des deux viroles successives, et une face distale, et
  2. b) des éléments de fixation pour serrer les faces distales des deux brides l'une contre l'autre, de manière à pouvoir transmettre des efforts axiaux de traction et de compression entre les deux brides.
The pairs of successive ferrules are connected by connection systems comprising:
  1. a) two flanges, each being substantially annular and having a proximal face intended to be integral with one of the two successive ferrules, and a distal face, and
  2. b) fastening elements for clamping the distal faces of the two flanges against each other, so as to transmit axial forces of traction and compression between the two flanges.

Par face distale, on entend la face plus éloignée du corps de la virole, par face proximale celle plus proche du corps de la virole. Dans l'état de la technique, on emploie comme éléments de fixation des boulons traversant des orifices agencés dans les brides. Toutefois cet arrangement présente plusieurs inconvénients :

  • Dans le cas d'une rupture d'aube de compresseur, des efforts circonférentiels non négligeables viennent s'ajouter aux efforts axiaux et radiaux entre les paires de viroles adjacentes. Ces efforts ont un effet de cisaillement sur les boulons du système de raccordement, ce qui oblige à utiliser un grand nombre de boulons ayant un diamètre considérable pour le raccordement des viroles. Afin de solutionner le problème de l'encombrement des boulons, il est nécessaire de surdimensionner les brides en augmentant le diamètre extérieur.
By distal face is meant the more distant face of the body of the ferrule, proximal face that closer to the body of the shell. In the state of the art, bolts passing through orifices arranged in the flanges are used as fixing elements. However, this arrangement has several disadvantages:
  • In the case of a compressor blade break, significant circumferential forces are added to the axial and radial forces between adjacent pairs of ferrules. These forces have a shearing effect on the bolts of the connection system, which makes it necessary to use a large number of bolts having a considerable diameter for connecting the ferrules. To solve the problem of the size of the bolts, it is necessary to oversize the flanges by increasing the outer diameter.

En plus des inconvénients de coût et poids inhérents à un tel surdimensionnement, l'encombrement radial des brides élargies présente aussi d'autres problèmes. Ainsi, dans de nombreuses applications, cet encombrement rend difficiles les opérations de montage et démontage, à cause d'interférences entre les brides et des éléments externes au compresseur, comme par exemple des capots. En particulier, dans le domaine des turboréacteurs, il peut être souhaitable de pouvoir démonter le compresseur basse pression vers l'arrière pour faciliter la maintenance. Toutefois, si les brides de raccordement des viroles du carter du compresseur basse pression sont trop encombrantes, elles vont buter contre le carter intermédiaire placé généralement à l'arrière du compresseur basse pression et servant à soutenir l'ensemble du turboréacteur.In addition to the disadvantages of cost and weight inherent in such oversizing, the radial size of the expanded flanges also has other problems. Thus, in many applications, this size makes it difficult assembly and disassembly operations, because of interference between the flanges and elements external to the compressor, such as hoods. In particular, in the field of turbojet engines, it may be desirable to be able to disassemble the low pressure compressor rearward to facilitate maintenance. However, if the connecting flanges of the housings of the low pressure compressor housing are too bulky, they will abut against the intermediate casing placed generally at the rear of the low pressure compressor and used to support the entire turbojet engine.

Le document EP 1 517 045 A2 décrit un autre dispositif de fixation pour les deux brides d'une pompe à vide. L'invention a pour but de pallier les inconvénients de l'état de la technique en procurant des éléments de fixation permettant de minimiser l'encombrement radial d'un système de raccordement d'éléments sensiblement tubulaires, et particulièrement de viroles de carter de compresseur axial.The document EP 1 517 045 A2 discloses another fastener for the two flanges of a vacuum pump. The object of the invention is to overcome the drawbacks of the state of the art by providing fastening elements making it possible to minimize the radial bulk of a connection system of substantially tubular elements, and particularly of compressor housing shrouds. axial.

Pour résoudre ce problème, il est prévu suivant l'invention, un système de raccordement tel qu'indiqué au début, dans lequel les éléments de fixation comportent au moins une paire de mâchoires agencées pour être connectées par un ensemble d'éléments de traction, par exemple des vis ou boulons, chacune des mâchoires de ladite paire étant agencée pour prendre appui sur la face proximale d'une des brides, et une mâchoire de ladite paire comportant en outre des moyens, tels que des épaulements sensiblement radiaux, agencés pour former une connexion positive avec des moyens complémentaires dans les deux brides pour une transmission des efforts circonférentiels entre les deux brides.To solve this problem, it is provided according to the invention, a connection system as indicated at the beginning, wherein the fastening elements comprise at least one pair of jaws arranged to be connected by a set of traction elements, for example screws or bolts, each of the jaws of said pair being arranged to bear on the proximal face of one of the flanges, and a jaw of said pair further comprising means, such as substantially radial shoulders, arranged to form a positive connection with complementary means in the two flanges for a transmission of circumferential forces between the two flanges.

Par ces moyens, on parvient à découpler les efforts axiaux en traction et compression des efforts circonférentiels en cisaillement entre les deux brides. Les éléments de traction reliant au moins une paire de mâchoires peuvent ainsi être dimensionnés purement en fonction des efforts axiaux en traction entre les deux brides, tandis que les efforts circonférentiels en cisaillement peuvent être repris sur une plus grande surface transversale par une de ladite paire de mâchoires sans devoir élargir excessivement le diamètre extérieur des brides. Selon l'invention, chacune des deux brides comporte au moins une découpe sensiblement radiale, et une des mâchoires de ladite paire est agencée pour former une connexion positive avec une découpe de chacune des deux brides pour ladite transmission des efforts circonférentiels entre les deux brides. Ceci permet d'agencer une connexion positive particulièrement efficace pour la transmission des efforts circonférentiels en cisaillement sans devoir excessivement élargir le diamètre des brides.By these means, it is possible to decouple the axial tensile and compressive forces shear circumferential forces between the two flanges. The traction elements connecting at least one pair of jaws can thus be dimensioned purely as a function of the axial tensile forces between the two flanges, whereas the circumferential shear forces can be taken over a larger transverse surface by one of said pair of jaws. jaws without having to excessively widen the outside diameter of the flanges. According to the invention, each of the two flanges comprises at least one substantially radial cut, and one of the jaws of said pair is arranged to form a positive connection with a cutout of each of the two flanges for said transmission of circumferential forces between the two flanges. This makes it possible to arrange a positive connection which is particularly effective for the transmission of circumferential shear forces without having to excessively widen the diameter of the flanges.

De préférence, le système de raccordement comporte en outre des moyens de centrage pour la reprise des efforts radiaux entre les deux brides. Ceci permet de découpler à leur tour les efforts radiaux des efforts axiaux et circonférentiels et de dimensionner ces moyens de centrage spécifiquement pour la reprise des efforts radiaux sans influencer l'encombrement des moyens de transmission des autres efforts.Preferably, the connection system further comprises centering means for taking up radial forces between the two flanges. This makes it possible to decouple in turn the radial forces of the axial and circumferential forces and to size these centering means specifically for the recovery of the radial forces without influencing the bulk of the transmission means of other efforts.

De préférence, la face proximale d'au moins une desdites deux brides comporte une surface inclinée ou conique étant destinée à entrer en contact avec une de ladite paire de mâchoires afin de la retenir radialement par une liaison positive, et donc d'éviter que la paire de mâchoires puisse glisser jusqu'à perdre le contact avec les brides, et donc le raccordement axial.Preferably, the proximal face of at least one of said two flanges comprises an inclined or conical surface being intended to come into contact with one of said pair of jaws in order to retain it radially by a positive connection, and thus to prevent the The pair of jaws can slide to lose contact with the flanges, and thus the axial connection.

De préférence, au moins une des mâchoires est agencée pour supporter un capot ou carénage extérieur aux éléments sensiblement tubulaires, par exemple un bec de compresseur dans un turboréacteur double-flux, permettant ainsi de simplifier le support de tels capots ou carénages extérieurs et de faciliter le montage et démontage de l'ensemble.Preferably, at least one of the jaws is arranged to support a hood or fairing external to the substantially tubular elements, for example a compressor nozzle in a double-flow turbojet engine, thus making it possible to simplify the support of such hoods or fairings and to facilitate the assembly and disassembly of the whole.

De préférence, ce support est arrangé avec un bossage agencé dans ladite mâchoire pour recevoir un insert ou écrou à rivet pour fixer ledit capot ou carénage, permettant ainsi un support solide mais démontable sans avoir à augmenter l'encombrement radial du système de raccordement.Preferably, this support is arranged with a boss arranged in said jaw for receiving an insert or rivet nut for fixing said hood or fairing, thus allowing a solid but removable support without having to increase the radial size of the connection system.

Alternativement, ladite au moins une mâchoire est intégrée dans ledit capot ou carénage, permettant ainsi de réduire le nombre de pièces, avec les avantages d'un coût réduit et de plus grandes fiabilité et simplicité.Alternatively, said at least one jaw is integrated in said hood or fairing, thereby reducing the number of parts, with the advantages of reduced cost and greater reliability and simplicity.

La présente invention se rapporte aussi à un carter de compresseur axial, par exemple de compresseur basse pression d'un turboréacteur ou turbopropulseur, comportant une pluralité de viroles dont au moins deux sont adjacentes et raccordées par un système de raccordement suivant l'invention, ainsi qu'à un procédé d'utilisation d'un tel système de raccordement dans un tel carter. Ceci fournit un carter de compresseur axial à faible encombrement radial et donc plus facilement démontable.The present invention also relates to an axial compressor casing, for example a low-pressure compressor of a turbojet or turboprop, comprising a plurality of ferrules, at least two of which are adjacent and connected by a connection system according to the invention, and than a method of using such a connection system in such a housing. This provides an axial compressor housing with small radial dimensions and therefore more easily removable.

De préférence, au moins une desdites deux viroles adjacentes comporte un stator et/ou une surface intérieure abradable, de manière à intégrer ces éléments du compresseur dans le carter.Preferably, at least one of said two adjacent ferrules comprises a stator and / or an abradable inner surface, so as to integrate these elements of the compressor in the housing.

Des détails concernant l'invention sont décrits ci-après faisant référence aux dessins.

  • La figure 1 est une coupe longitudinale de l'état de la technique.
  • La figure 2 est une coupe longitudinale d'un système de raccordement suivant un mode de réalisation de l'invention.
  • La figure 3 est une vue frontale du même système de raccordement.
  • La figure 4 est une coupe longitudinale d'un système de raccordement suivant un mode de réalisation alternatif.
  • La figure 5 est une vue en perspective d'une mâchoire d'un système de raccordement suivant un autre mode de réalisation alternatif.
Details of the invention are described below with reference to the drawings.
  • The figure 1 is a longitudinal section of the state of the art.
  • The figure 2 is a longitudinal section of a connection system according to one embodiment of the invention.
  • The figure 3 is a front view of the same connection system.
  • The figure 4 is a longitudinal section of a connection system according to an alternative embodiment.
  • The figure 5 is a perspective view of a jaw of a connection system according to another alternative embodiment.

Comme on peut voir dans la figure 1, dans l'état de la technique, chacune des viroles 101 et 102 d'un carter de compresseur basse pression d'un turboréacteur double-flux comporte une bride, respectivement désignée 103 et 104. Chacune de ces brides 103, 104 présente une face proximale, respectivement désignée 103p et 104p, et une face distale, respectivement désignée 103d et 104d. Dans chaque bride 103, 104, un ensemble d'orifices, respectivement désignés 105 et 106, relient la face proximale 103p, 104p à la face distale 103d, 104d. Les orifices 105 de la bride 103 sont alignés avec les orifices 106 de la bride 104, de manière à pouvoir y faire passer des vis 107. En serrant ces vis 107 avec des écrous 108, il est donc possible d'établir un raccordement axial entre les viroles 101 et 102.As can be seen in the figure 1 , in the state of the art, each of the rings 101 and 102 of a low-pressure compressor casing of a double-flow turbojet engine comprises a flange, respectively designated 103 and 104. Each of these flanges 103, 104 has a face proximal, respectively designated 103p and 104p, and a distal face, respectively designated 103d and 104d. In each flange 103, 104, a set of orifices respectively designated 105 and 106, connect the proximal face 103p, 104p to the distal face 103d, 104d. The orifices 105 of the flange 103 are aligned with the orifices 106 of the flange 104, so as to be able to pass screws 107. By tightening these screws 107 with nuts 108, it is therefore possible to establish an axial connection between the ferrules 101 and 102.

Tandis que la transmission des efforts radiaux est assurée par l'emboîtement de surfaces de centrage 109 des viroles 101, 102, les boulons 107 doivent reprendre, outre la traction axiale, la torsion circonférentielle entre les brides 103, 104. Une telle torsion soumet les boulons 107 à des efforts de cisaillement, ce qui force à augmenter leur section travaillante, et donc le diamètre des orifices 105, 106 et la hauteur des brides 103, 104.While the transmission of the radial forces is ensured by the interlocking of centering surfaces 109 of the ferrules 101, 102, the bolts 107 must resume, in addition to the axial tension, the circumferential torsion between the flanges 103, 104. Such a torsion submits the bolts 107 to shear forces, which forces to increase their working section, and therefore the diameter of the orifices 105, 106 and the height of the flanges 103, 104.

Dans le mode de réalisation de l'invention représenté dans la figure 2, chacune des viroles 201, 202 comporte une bride, désignée respectivement 203 et 204. Chacune des brides 203, 204 comporte une face distale, désignée respectivement 203d et 204d, sensiblement perpendiculaire à l'axe de la virole 201, 202 correspondante, et une face proximale, désignée respectivement 203p et 204p, sensiblement conique. Chacune des brides 203, 204 comporte aussi une pluralité de découpes 205 distribuées autour du périmètre de chaque bride 203, 204. Chaque découpe 205 comporte deux bords 206 sensiblement radiaux. Les découpes 205 de la bride 203 sont destinées à être alignées avec les découpes 205 de l'autre bride 204 quand les viroles 201, 202 sont raccordées.In the embodiment of the invention shown in the figure 2 , each of the rings 201, 202 comprises a flange, respectively designated 203 and 204. Each of the flanges 203, 204 comprises a distal face, designated respectively 203d and 204d, substantially perpendicular to the axis of the ferrule 201, 202 corresponding, and a proximal face, respectively designated 203p and 204p, substantially conical. Each of the flanges 203, 204 also comprises a plurality of cutouts 205 distributed around the perimeter of each flange 203, 204. Each cutout 205 has two substantially radial edges 206. The cutouts 205 of the flange 203 are intended to be aligned with the cutouts 205 of the other flange 204 when the ferrules 201, 202 are connected.

Le système de raccordement illustré comporte en outre une paire de mâchoires 207, 208 reliées par des vis 209 retenues par des écrous 210. L'une mâchoire 207 prend appui sur la face proximale 203p d'une bride 203, tandis que l'autre mâchoire 208 prend appui sur la face proximale 204p de l'autre bride 204. De cette manière, en serrant les vis 209 dans les écrous 210 on parvient à serrer les mâchoires 207, 208, prenant en étau les brides 203, 204. Cette précontrainte axiale des brides 203, 204 permet de transmettre par les faces distales 203d, 204d les efforts axiaux en compression entre les viroles 201, 202, et par les boulons 209 les efforts axiaux en tension. En même temps, la forme conique des faces proximales 203p, 204p assure la rétention radiale de la paire de mâchoires 207, 208 quand les boulons 209 sont serrés.The connection system illustrated further comprises a pair of jaws 207, 208 connected by screws 209 retained by nuts 210. One jaw 207 bears on the proximal face 203p of a flange 203, while the other jaw 208 is supported on the proximal face 204p of the other flange 204. In this way, by tightening the screws 209 in the nuts 210 it is possible to tighten the jaws 207, 208, clamping the flanges 203, 204. This axial prestressing of the flanges 203, 204 makes it possible to transmit, via the distal faces 203d, 204d, the axial compressive forces between the ferrules 201, 202, and by the bolts 209 the axial tension forces. At the same time, the conical shape of the proximal faces 203p, 204p provides radial retention of the pair of jaws 207, 208 as the bolts 209 are tightened.

Alternativement, une seule des faces des brides 203 peut présenter une forme conique correspondant à une seule mâchoire conique 207, comme représenté sur la figure 2.Alternatively, only one of the faces of the flanges 203 may have a conical shape corresponding to a single conical jaw 207, as shown in FIG. figure 2 .

La mâchoire 207 comporte une prolongation axiale 211 telle que la zone de contact entre les 2 brides 203d, 204d se situe sous cette prolongation. La prolongation axiale 211 est logée dans les découpes 205 alignées des deux brides 203, 204. De cette manière, cette prolongation 211 forme une connexion positive avec les bords 206 des deux découpes, permettant de transmettre les efforts circonférentiels en torsion entre les deux brides 203, 204. La mâchoire 207 offre une section travaillante en cisaillement supérieure à celle des vis 107 de l'état de la technique sans devoir élargir le diamètre des brides 203, 204. Les vis 209 reliant les mâchoires 207, 208 sont donc sensiblement exemptes d'efforts en cisaillement et peuvent être dimensionnés avec une section considérablement réduite relativement aux boulons 107 de l'état de la technique illustré dans la figure 1.The jaw 207 has an axial extension 211 such that the contact zone between the two flanges 203d, 204d is below this extension. The axial extension 211 is housed in the aligned cutouts 205 of the two flanges 203, 204. In this way, this extension 211 forms a positive connection with the edges 206 of the two cutouts, making it possible to transmit the circumferential forces in torsion between the two flanges 203 204. The jaw 207 provides a working section in shear greater than that of screws 107 of the state of the art without having to widen the diameter of the flanges 203, 204. The screws 209 connecting the jaws 207, 208 are therefore substantially free of shear forces and can be dimensioned with a considerably reduced cross section relative to bolts 107 of the state of the art illustrated in FIG. figure 1 .

Les efforts circonférentiels en torsion entre les brides 203, 204 pourraient toutefois, conformément à d'autres modes de réalisation, être transmis par d'autres connections positives. Par exemple, les mâchoires 207, 208 pourraient toutes les deux présenter des prolongations, chacune de ces prolongations être logée dans la découpe 205 d'une des brides 203, 204, de manière à ce que chacune forme une connexion positive avec les bords 206 de chaque découpe 205, et lesdites prolongations présenter à leur tour des épaulements sensiblement radiaux et complémentaires de manière à transmettre les efforts en cisaillement entre les deux mâchoires 207, 208. Les plats des découpes 205 des brides peuvent éventuellement présenter un jeu radial avec les faces correspondantes des mâchoires 207 et/ou 208, comme représenté sur la figure 2 pour la découpe de la bride 204.Circumferential torsional forces between the flanges 203, 204 could however, according to other embodiments, be transmitted by other positive connections. For example, the jaws 207, 208 could both have extensions, each of these extensions being accommodated in the cutout 205 of one of the flanges 203, 204, so that each forms a positive connection with the edges 206 of each cutout 205, and said extensions in turn present shoulders substantially radial and complementary so as to transmit the shear forces between the two jaws 207, 208. The flats of the blanks 205 of the flanges may optionally have a radial clearance with the corresponding faces of the jaws 207 and / or 208, as shown in FIG. figure 2 for cutting the flange 204.

La transmission des efforts radiaux est assurée, comme dans l'état de la technique illustré dans la figure 1, par l'emboîtement de surfaces de centrage 212 des viroles 101, 102.The transmission of the radial forces is ensured, as in the state of the art illustrated in the figure 1 by the interlocking of centering surfaces 212 of ferrules 101, 102.

De plus, lorsque les faces proximales des brides 203p, 204p sont coniques, l'effort radial est repris par les vis 209 sous forme d'effort axial.In addition, when the proximal faces of the flanges 203p, 204p are conical, the radial force is taken up by the screws 209 in the form of axial force.

Tournant maintenant vers la figure 4, un mode de réalisation alternatif est illustré où deux viroles 201, 202 d'un carter de compresseur basse pression sont aussi raccordées par des brides 203, 204. La virole 201 sert de support au bec de séparation du compresseur, qui est de géométrie axisymétrique et est centré sur la virole 201. Les brides 203, 204 sont retenues par une paire de mâchoires 207, 208 connectées par des vis 209 et des écrous 210. Dans ce mode de réalisation alternatif, la mâchoire 207 est intégrée dans un bec de séparation du compresseur 401. De cette manière, le bec de séparation du compresseur 401, qui forme un carénage séparant le flux primaire du flux secondaire dans un turboréacteur double flux, peut être soutenu par le carter de compresseur basse pression sans avoir recours à un bossage sur la virole 201 analogue au bossage 402 formé sur la virole 202 pour soutenir le capot 403 prolongeant le bec de compresseur 401.Turning now to the figure 4 , an alternative embodiment is illustrated where two rings 201, 202 of a low pressure compressor casing are also connected by flanges 203, 204. The shell 201 serves as a support for the separation spout of the compressor, which is of axisymmetrical geometry. and is centered on the ferrule 201. The flanges 203, 204 are retained by a pair of jaws 207, 208 connected by screws 209 and nuts 210. In this alternative embodiment, the jaw 207 is integrated into a separating spout. In this way, the separation spout of the compressor 401, which forms a shroud separating the primary flow from the secondary flow in a turbofan engine, can be supported by the low pressure compressor housing without resorting to a boss on the annulus 201 similar to the boss 402 formed on the shell 202 to support the hood 403 extending the compressor nozzle 401.

Sur la figure 4, la virole 202 comporte des bossages 402 pour soutenir le capot 403 prolongeant le bec de séparation du compresseur 401. De tels bossages formés sur les viroles pour soutenir des capots ou carénages ont l'inconvénient d'élargir le diamètre extérieur des viroles, rendant plus difficile leur montage et démontage à cause des possibles interférences avec des éléments extérieurs au carter de compresseur.On the figure 4 , the shell 202 has bosses 402 to support the hood 403 extending the separation nozzle of the compressor 401. Such bosses formed on the ferrules to support hoods or fairings have the disadvantage of widening the outer diameter of the ferrules, making more difficult to assemble and dismantle them because of possible interference with elements outside the compressor housing.

Il serait ainsi aussi avantageux de substituer le bossage 402 du mode de réalisation présenté dans la figure 4 par les moyens illustrés dans la figure 5. Dans cette figure 5 est illustrée une mâchoire 208, destinée à se substituer à la mâchoire 208 de la figure 4, sur laquelle est formé un bossage 501 pourvu d'un orifice 502 destiné à recevoir un boulon, vis, insert ou rivet pour soutenir un capot ou carénage. Cette mâchoire et la bride 204 ne doivent pas nécessairement présenter une forme conique, car la rétention radiale de la mâchoire est assurée par sa fixation à la pièce axisymétrique 207.It would thus also be advantageous to substitute boss 402 of the embodiment shown in FIG. figure 4 by the means illustrated in the figure 5 . In this figure 5 is illustrated a jaw 208, intended to replace the jaw 208 of the figure 4 , on which is formed a boss 501 provided with a hole 502 for receiving a bolt, screw, insert or rivet to support a hood or fairing. This jaw and the flange 204 need not necessarily have a conical shape, because the radial retention of the jaw is ensured by its attachment to the axisymmetric part 207.

Dans tous les modes de réalisation illustrés, le système de raccordement peut être monté en raccordant temporairement les viroles 201, 202 par des colliers Colson avant de placer les mâchoires 207, 208, et/ou démonté en raccordant temporairement les viroles 201, 202 par des colliers Colson avant de retirer les mâchoires 207, 208.In all the illustrated embodiments, the connection system can be mounted by temporarily connecting the ferrules 201, 202 by Colson collars before placing the jaws 207, 208, and / or disassembled by temporarily connecting the ferrules 201, 202 by Colson collars before removing the jaws 207, 208.

Quoique la présente invention ait été décrite en se référant à des exemples de réalisation spécifiques, il est évident que des différentes modifications et changements peuvent être effectués sur ces exemples sans sortir de la portée générale de l'invention telle que définie par les revendications. Par conséquent, la description et les dessins doivent être considérés dans un sens illustratif plutôt que descriptif.Although the present invention has been described with reference to specific exemplary embodiments, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. Therefore, the description and drawings should be considered in an illustrative rather than descriptive sense.

REFERENCES DES FIGURESREFERENCES OF THE FIGURES

101101
ViroleFerrule
102102
ViroleFerrule
103103
BrideFlange
103p103p
Face proximaleProximal face
103d103d
Face distaleDistal face
104104
BrideFlange
104p104p
Face proximaleProximal face
104d104d
Face distaleDistal face
105105
OrificeOrifice
106106
OrificeOrifice
107107
VisScrew
108108
ÉcrouNut
109109
Surfaces de centrageCentering surfaces
201201
ViroleFerrule
202202
ViroleFerrule
203203
BrideFlange
203p203P
Face proximaleProximal face
203d203d
Face distaleDistal face
204204
BrideFlange
204p204p
Face proximaleProximal face
204d204d
Face distaleDistal face
205205
Découpecutting
206206
BordEdge
207207
MâchoireJaw
208208
MâchoireJaw
209209
VisScrew
210210
ÉcrouNut
211211
ProlongationExtension
212212
Surfaces de centrageCentering surfaces
401401
Bec de séparation de compresseurCompressor separation nozzle
402402
Bossageboss
403403
Capothood
501501
Bossageboss
502502
OrificeOrifice

Claims (10)

  1. System for connecting two substantially tubular elements (201, 202), in particular two shells of an axial compressor case, comprising;
    a) two flanges (203, 204), each being substantially annular and comprising a proximal face (203p, 204p) adapted to be integral with one or both elements (203, 204) and a distal face (203d, 204d), and
    b) securing members for pressing the distal faces (203d, 204d) of the flanges (203, 204) into contact with each other, so as to be able to transmit tension and compression axial forces between the two flanges (203, 204).
    c) said securing members comprise at least one pair of jaws (207, 208) designed to be connected by a set of tension members (209), for example screws or bolts, each jaw (207, 208) of said pair being designed to abut against the proximal face (203p, 204p) of one of the flanges, and
    d) at least one jaw (207) of said pair also comprises means, such as substantially radial shoulders, designed to form a positive connection with complementary means in the two flanges (203, 204) for transmission of circumferential forces between the two flanges (203, 204),
    and characterised in that each of the two flanges (203, 204) comprises at least one substantially radial cutout (205), and in that one jaw (207) of said pair is arranged to form a positive connection with a cutout (205) in each of the two flanges (203, 204) for said transmission of circumferential forces between the two flanges (203, 204).
  2. Connection system according to the previous claim, also comprising centring means (212) for resisting radial forces between the two flanges (203, 204).
  3. Connection system according to one of the previous claims, in which the proximal face (203p, 204p) of at least one of said two flanges (203, 204) comprises a tilted or conical surface designed to come into contact with one of said pair of jaws (207, 208) in order to retain it radially by a positive link.
  4. Connection system according to one of the previous claims, in which at least one of the jaws (207, 208) is arranged to support a cowl or fairing (401, 403) external to the substantially tubular members (201, 202), for example a separation nose of the compressor (401) in a turbofan engine or an acoustic insulation panel (403).
  5. Connection system according to claim 4, in which said jaw (208) comprises a boss (501) arranged to accommodate an insert or a rivet and nut for securing said cowl or fairing (403).
  6. Connection system according to claim 4, in which said jaw (207) is integrated into said hood or fairing (401).
  7. Axial compressor case, for example of a low-pressure compressor of a turbojet or turboprop, comprising a plurality of shells (201, 202), of which two at least are adjacent and connected by a connection system according to one of the preceding claims.
  8. Axial compressor case according to claim 7, in which at least one of said two adjacent shells (201, 202) comprises a stator and/or an abradable inner surface.
  9. Use of a connection system according to one of claims 1 to 6, for connecting at least two adjacent shells (201, 202) of an axial compressor case, for example a low-pressure compressor of a turbojet or a turboprop.
  10. Use according to claim 9, in which at least one of said two adjacent shells (201, 202) comprises a stator and/or an abradable inner surface.
EP06127255.5A 2006-12-27 2006-12-27 System with jaws for connecting two flanges, in particular for a compressor shroud Not-in-force EP1939459B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06127255.5A EP1939459B1 (en) 2006-12-27 2006-12-27 System with jaws for connecting two flanges, in particular for a compressor shroud
US11/964,380 US8182216B2 (en) 2006-12-27 2007-12-26 Connecting system with jaws of two ferrules, including a compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06127255.5A EP1939459B1 (en) 2006-12-27 2006-12-27 System with jaws for connecting two flanges, in particular for a compressor shroud

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EP1939459A1 EP1939459A1 (en) 2008-07-02
EP1939459B1 true EP1939459B1 (en) 2018-04-25

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GB201103583D0 (en) 2011-03-03 2011-04-13 Rolls Royce Plc Fan casing for a turbofan engine
EP2733314B1 (en) * 2012-11-15 2017-04-05 Safran Aero Boosters SA Radial attachment and positioning flanges for axial turbomachine casing sections
US10100674B2 (en) 2012-11-15 2018-10-16 Safran Aero Boosters Sa Radial fixing and positioning flanges for shells of axial turbine compressor housings
ES2637944T3 (en) * 2014-06-06 2017-10-18 MTU Aero Engines AG Arrangement of the components of a gas turbine
ES2904551T3 (en) * 2016-02-16 2022-04-05 MTU Aero Engines AG Connection arrangement for the casing element of an intermediate casing of a turbine

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EP1517045A2 (en) * 2003-09-17 2005-03-23 Pfeiffer Vacuum GmbH Connecting element

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US8182216B2 (en) 2012-05-22
US20080159859A1 (en) 2008-07-03
EP1939459A1 (en) 2008-07-02

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