EP1308630B1 - Stator sector for a compressor of a turbomachine - Google Patents

Stator sector for a compressor of a turbomachine Download PDF

Info

Publication number
EP1308630B1
EP1308630B1 EP02292634A EP02292634A EP1308630B1 EP 1308630 B1 EP1308630 B1 EP 1308630B1 EP 02292634 A EP02292634 A EP 02292634A EP 02292634 A EP02292634 A EP 02292634A EP 1308630 B1 EP1308630 B1 EP 1308630B1
Authority
EP
European Patent Office
Prior art keywords
casing
rotation
fixed stator
stator according
parts
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.)
Expired - Lifetime
Application number
EP02292634A
Other languages
German (de)
French (fr)
Other versions
EP1308630A1 (en
Inventor
Jean-Louis Bertrand
Jean-Marc Claude Perrollaz
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1308630A1 publication Critical patent/EP1308630A1/en
Application granted granted Critical
Publication of EP1308630B1 publication Critical patent/EP1308630B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • 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
    • 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
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers

Definitions

  • the invention presented here concerns the high-pressure turbine of a turbomachine such as a turbojet engine used on an airplane. It relates more specifically to a sectorized fixed rectifier for a turbomachine compressor.
  • Document FR-A-2 728 015 discloses a stator distributor of a turbine comprising sectors each consisting of an inner segment and an outer segment connected by blades.
  • An integrated casing in the stator of the compressor is intended to support the abutting sectors to each other.
  • Anti-rotation means are provided to prevent rotation of the sectors supported by the housing.
  • the present invention has been designed to further improve the manufacture and cost of a fixed rectifier for a turbomachine compressor.
  • the housing is made of two or more parts, which facilitates the manufacture.
  • the parts of the housing and the rectifier sectors are associated by a system forming a slide and slider.
  • Anti-rotation means are provided to prevent rotation of the sectors relative to the housing.
  • the housing consists of two parts in the form of a semicircle.
  • the casing comprising two radial flanks facing each other, the slideway means comprise two opposite grooves formed in the flanks, the edges of the outer segments of the sectors constituting the slider means.
  • the anti-rotation means attached to the joint planes may then comprise at least one bar immobilized between the two grooves by said fixing means and forming a stop for a sliding sector in a slide of the housing.
  • This bar may be a pair of tweezers inserted by bringing the two branches together in receiving housings provided in the grooves, and immobilized in these housing by loosening the two branches, thereby achieving said fixing means.
  • the anti-rotation means attached to the joint planes may also include at least one anti-rotation lock constituted by an element comprising slider means adapted to the slide means of the housing parts, the element also comprising immobilization means on the housing.
  • These immobilization means may be of the tenon-mortise type, a tenon engaging in a mortise when the element is pushed in a direction perpendicular to the sliding direction of the element in the housing, thereby achieving said fastening means.
  • the outer segment of the sector adjacent to said element may have one of its ends which has a clearance so that when this adjacent sector is slid in contact with said element, the element can be pushed in said perpendicular direction.
  • the anti-rotation means blocked on the housing parts may then comprise at least one anti-rotation lock consisting of an element comprising slide means adapted to the slide means of the housing parts, the element also comprising immobilization means on the crankcase.
  • These immobilization means may be of the tenon-mortise type, a tenon engaging in a mortise when the element is pushed in a direction perpendicular to the direction of sliding of the element in the housing, thus realizing said locking means .
  • the outer segment of a sector adjacent to said element may have one of its ends which has a clearance so that when this adjacent sector is slid in contact with said element, the element can be pushed in said perpendicular direction.
  • Figure 1 is a partial sectional view of a compressor of a turbomachine using sectored fixed rectifiers 1, 2 and 3 according to the invention. These rectifiers are functionally identical.
  • the rectifier 1 will be described more precisely. It comprises a circular casing 4 integrated in the stator of the compressor and supporting sectors such as sector 5.
  • a sector 5 consists of an inner segment 7 and an outer segment 6 interconnected by vanes 8.
  • FIG. 2 is a partial and exploded view of the sectorized fixed rectifier 1. It comprises, for example, a two-part casing in the shape of a semicircle. Figure 2 partially shows one of the parts 11 of this housing with one of its joint planes 16 to be fixed on a corresponding joint plane of the other part of the housing. Three sectors 5 being edited are represented. For a sector 5, the outer segment 6, the inner segment 7 and the blades 8 which connect them are recognized.
  • the housing portion 11 comprises two radial flanks 12 and 13 facing each other and each provided with a groove.
  • the grooves are located vis-à-vis to form a slide.
  • the edges 21 and 22 of the outer segment 6 of the sector 5 project outwards to provide a sliding function with respect to the slide formed by the housing part 11.
  • an anti-rotation lock is installed at the joint plane 16 of the housing portion 11. It may be a bar or a lock such as the one shown in Figure 4.
  • FIG. 2 also shows an anti-rotation lock 30 disposed between two sectors 5.
  • This lock 30 is shown in a cavalier view in FIG. 3. It is formed of an element 31 which is placed between the two sides 12 and 13 of the housing portion 11 (see Figure 2).
  • the element 31 is in the shape of an arc of a circle and extended by an outer edge 32 and an inner edge 33.
  • the edges 32 and 33 are provided so that the latch 30 can slide in the grooves of the housing portion 11.
  • the outer edge 32 has a lug 34 projecting from the plane of the housing. element 31. The same applies to the lug 35 of the inner edge 33.
  • FIGs 5 and 6 illustrate two steps of the establishment of an anti-rotation lock 30 between two sectors 5.
  • FIG. 5 illustrates two steps of the establishment of an anti-rotation lock 30 between two sectors 5.
  • Only one of the sides of the housing portion 11 has been shown. We can see the groove 14 provided in this flank.
  • Figure 5 shows a first sector 5 already installed (left of the figure) and a second sector 5 being mounted (right of the figure). Between these two sectors was introduced by sliding a latch 30. Note that the height of the groove 14 allows the passage of the outer edge of the latch 30 with its lug 34.
  • the element 30 is slid up to abut on the first sector 5. This corresponds for the element 30 to a relative position relative to the housing portion 11 such that the lug 34 is vis-à-vis screw of a notch 15 machined in the housing portion 11. It is then sufficient to exert on the latch 30 upward thrust (for the representation of Figures 5 and 6) so that the lug 34 enters the notch 15, the latch 30 is then in raised position.
  • the second sector 5 can then be pushed towards the latch 30.
  • This second sector 5 present, at the end in contact with the latch 30, a clearance 23 such that a portion of the outer segment 6 passes under the latch 30.
  • the anti-rotation lock 40 of the joint plane shown in Figure 4 is mounted in the same manner as the lock of Figure 3. It is formed of an element 41 which is placed between the two sides of the housing part. The element 41 is extended by an outer edge 42 and an inner edge 43. The outer edge 42 has a lug 44 protruding from the plane of the element 41. The same goes for the lug 45 of the inner edge 43.

Landscapes

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

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention présentée ici concerne la turbine haute pression d'une turbomachine telle qu'un turboréacteur utilisé sur un avion. Elle concerne plus précisément un redresseur fixe sectorisé pour un compresseur de turbomachine.The invention presented here concerns the high-pressure turbine of a turbomachine such as a turbojet engine used on an airplane. It relates more specifically to a sectorized fixed rectifier for a turbomachine compressor.

ETAT DE LA TECHNIQUE ANTERIEURESTATE OF THE PRIOR ART

Il existe une très grande variété de compresseurs pour turbomachines. Les efforts des constructeurs portent sur l'amélioration des performances mais aussi sur l'amélioration de la fabrication, la réduction des coûts et la facilité de l'entretien.There is a very wide variety of turbomachine compressors. Manufacturers' efforts focus on improving performance, but also improving manufacturing, reducing costs and ease of maintenance.

Une amélioration connue a consisté à sectoriser le redresseur fixe d'un compresseur pour turbomachine. Les brevets US-A-4 126 405 et EP-1 104 836 divulguent un montage segmenté d'un distributeur de turbine.One known improvement has been to sectorise the fixed rectifier of a compressor for a turbomachine. US-A-4,126,405 and EP-1,104,836 disclose a segmented arrangement of a turbine distributor.

Le document FR-A-2 728 015 divulgue un distributeur de stator d'une turbine comprenant des secteurs constitués chacun d'un segment intérieur et d'un segment extérieur reliés par des aubes. Un carter intégré dans le stator du compresseur est destiné à supporter les secteurs aboutés les uns aux autres. Des moyens anti-rotation sont prévus pour empêcher la rotation des secteurs supportés par le carter.Document FR-A-2 728 015 discloses a stator distributor of a turbine comprising sectors each consisting of an inner segment and an outer segment connected by blades. An integrated casing in the stator of the compressor is intended to support the abutting sectors to each other. Anti-rotation means are provided to prevent rotation of the sectors supported by the housing.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

La présente invention a été conçue afin d'améliorer encore la fabrication et le coût d'un redresseur fixe pour compresseur de turbomachine. Pour cela le carter est réalisé en deux parties ou plus, ce qui facilite la fabrication. Les parties du carter et les secteurs de redresseur sont associés par un système formant glissière et coulisseau. Des moyens anti-rotation sont prévus pour éviter la rotation des secteurs par rapport au carter.The present invention has been designed to further improve the manufacture and cost of a fixed rectifier for a turbomachine compressor. For this the housing is made of two or more parts, which facilitates the manufacture. The parts of the housing and the rectifier sectors are associated by a system forming a slide and slider. Anti-rotation means are provided to prevent rotation of the sectors relative to the housing.

L'invention a donc pour objet un redresseur fixe sectorisé pour compresseur d'une turbomachine comprenant :

  • des secteurs en forme d'arc de cercle constitués chacun d'un segment intérieur et d'un segment extérieur reliés par des aubes,
  • un carter circulaire intégré dans le stator du compresseur et destiné à supporter les secteurs aboutés les uns aux autres,
  • des moyens anti-rotation destinés à empêcher la rotation des secteurs supportés par le carter,
caractérisé en ce que :
  • le carter est constitué d'au moins deux parties, aboutées et fixées entre elles selon des plans de joint, comprenant des moyens formant glissière,
  • les secteurs comprennent des moyens formant coulisseau adaptés aux moyens formant glissière des parties du carter,
  • les moyens anti-rotation comprennent des moyens anti-rotation fixés aux plans de joint des parties du carter par des moyens de fixation, et des moyens anti-rotation bloqués sur les parties du carter par des moyens de blocage au niveau de l'aboutement des secteurs entre eux.
The subject of the invention is therefore a sectorized fixed rectifier for a compressor of a turbomachine comprising:
  • arcuate sectors each consisting of an inner segment and an outer segment connected by vanes,
  • a circular casing integrated in the stator of the compressor and intended to support the abutting sectors with each other,
  • anti-rotation means for preventing the rotation of the sectors supported by the housing,
characterized in that
  • the casing consists of at least two parts, abutting and fixed together in joint planes, comprising slide means,
  • the sectors comprise slider means adapted to the slider means of the housing parts,
  • the anti-rotation means comprise anti-rotation means fixed to the joint planes of the parts of the casing by fastening means, and anti-rotation means blocked on the parts of the casing by locking means at the abutment of the sectors between them.

De préférence, le carter est constitué de deux parties en forme de demi-cercle.Preferably, the housing consists of two parts in the form of a semicircle.

Selon une variante de réalisation préférée, le carter comprenant deux flancs radiaux se faisant face, les moyens formant glissière comprennent deux gorges opposées réalisées dans les flancs, les bords des segments extérieurs des secteurs constituant les moyens formant coulisseau.According to a preferred embodiment, the casing comprising two radial flanks facing each other, the slideway means comprise two opposite grooves formed in the flanks, the edges of the outer segments of the sectors constituting the slider means.

Les moyens anti-rotation fixés aux plans de joint peuvent alors comprendre au moins une barrette immobilisée entre les deux gorges par lesdits moyens de fixation et formant butée pour un secteur coulissant dans une glissière du carter. Cette barrette peut être une pince à deux branches insérée par rapprochement des deux branches entre elles dans des logements de réception prévus dans les gorges, et immobilisée dans ces logements par relâchement des deux branches, réalisant ainsi lesdits moyens de fixation. Les moyens anti-rotation fixés aux plans de joint peuvent aussi comprendre au moins un verrou anti-rotation constitué par un élément comprenant des moyens formant coulisseau adaptés aux moyens formant glissière des parties du carter, l'élément comprenant également des moyens d'immobilisation sur le carter. Ces moyens d'immobilisation peuvent être du type tenon-mortaise, un tenon s'engageant dans une mortaise quand l'élément est poussé dans une direction perpendiculaire à la direction de glissement de l'élément dans le carter, réalisant ainsi lesdits moyens de fixation. Le segment extérieur du secteur adjacent audit élément peut avoir l'une de ses extrémités qui présente un dégagement afin que, lorsque ce secteur adjacent est glissé au contact dudit élément, l'élément puisse être poussé dans ladite direction perpendiculaire.The anti-rotation means attached to the joint planes may then comprise at least one bar immobilized between the two grooves by said fixing means and forming a stop for a sliding sector in a slide of the housing. This bar may be a pair of tweezers inserted by bringing the two branches together in receiving housings provided in the grooves, and immobilized in these housing by loosening the two branches, thereby achieving said fixing means. The anti-rotation means attached to the joint planes may also include at least one anti-rotation lock constituted by an element comprising slider means adapted to the slide means of the housing parts, the element also comprising immobilization means on the housing. These immobilization means may be of the tenon-mortise type, a tenon engaging in a mortise when the element is pushed in a direction perpendicular to the sliding direction of the element in the housing, thereby achieving said fastening means. The outer segment of the sector adjacent to said element may have one of its ends which has a clearance so that when this adjacent sector is slid in contact with said element, the element can be pushed in said perpendicular direction.

Les moyens anti-rotation bloqués sur les parties du carter peuvent alors comprendre au moins un verrou anti-rotation constitué par un élément comprenant des moyens formant coulisseau adaptés aux moyens formant glissière des parties du carter, l'élément comprenant également des moyens d'immobilisation sur le carter. Ces moyens d'immobilisation peuvent être du type tenon-mortaise, un tenon s'engageant dans une mortaise quand l'élément est poussé dans une direction perpendiculaire à la direction de glissement de l'élément dans le carter, réalisant ainsi lesdits moyens de blocage. Le segment extérieur d'un secteur adjacent audit élément peut avoir l'une de ses extrémités qui présente un dégagement afin que, lorsque ce secteur adjacent est glissé au contact dudit élément, l'élément puisse être poussé dans ladite direction perpendiculaire.The anti-rotation means blocked on the housing parts may then comprise at least one anti-rotation lock consisting of an element comprising slide means adapted to the slide means of the housing parts, the element also comprising immobilization means on the crankcase. These immobilization means may be of the tenon-mortise type, a tenon engaging in a mortise when the element is pushed in a direction perpendicular to the direction of sliding of the element in the housing, thus realizing said locking means . The outer segment of a sector adjacent to said element may have one of its ends which has a clearance so that when this adjacent sector is slid in contact with said element, the element can be pushed in said perpendicular direction.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

L'invention sera mieux comprise et d'autres avantages et particularités apparaîtront à la lecture de la description qui va suivre, donnée à titre d'exemple non limitatif, accompagnée des dessins annexés parmi lesquels :

  • la figure 1 est une vue partielle en coupe d'un compresseur d'un turbomachine utilisant un redresseur fixe sectorisé selon l'invention,
  • la figure 2 est une vue partielle et éclatée d'un redresseur fixe sectorisé selon l'invention,
  • la figure 3 est une vue cavalière d'un verrou anti-rotation pour plan de joint d'une partie de carter pour le redresseur fixe sectorisé de l'invention,
  • la figure 4 est une vue cavalière d'un verrou anti-rotation disposé entre deux secteurs d'un redresseur fixe sectorisé selon l'invention,
  • les figures 5 et 6 illustrent deux étapes de la mise en place d'un verrou anti-rotation entre deux secteurs d'un redresseur fixe sectorisé selon l'invention.
The invention will be better understood and other advantages and particularities will appear on reading the description which follows, given as a non-limiting example, accompanied by the appended drawings among which:
  • FIG. 1 is a partial sectional view of a compressor of a turbomachine using a sectored fixed rectifier according to the invention,
  • FIG. 2 is a fragmentary and exploded view of a sectored fixed rectifier according to the invention,
  • FIG. 3 is a side view of an anti-rotation latch for a joint plane of a housing part for the sectorized fixed rectifier of the invention,
  • FIG. 4 is a side view of an anti-rotation lock disposed between two sectors of a sectored fixed rectifier according to the invention,
  • Figures 5 and 6 illustrate two steps of the establishment of an anti-rotation lock between two sectors of a sectored fixed rectifier according to the invention.

DESCRIPTION DÉTAILLÉE DE MODES DE RÉALISATION DE L'INVENTIONDETAILED DESCRIPTION OF EMBODIMENTS OF THE INVENTION

La figure 1 est une vue partielle en coupe d'un compresseur d'une turbomachine utilisant des redresseurs fixes sectorisés 1, 2 et 3 selon l'invention. Ces redresseurs sont fonctionnellement identiques.Figure 1 is a partial sectional view of a compressor of a turbomachine using sectored fixed rectifiers 1, 2 and 3 according to the invention. These rectifiers are functionally identical.

Le redresseur 1 va être décrit plus précisément. Il comprend un carter circulaire 4 intégré dans le stator du compresseur et supportant des secteurs tel que le secteur 5.The rectifier 1 will be described more precisely. It comprises a circular casing 4 integrated in the stator of the compressor and supporting sectors such as sector 5.

Un secteur 5 est constitué d'un segment intérieur 7 et d'un segment extérieur 6 reliés entre eux par des aubes 8.A sector 5 consists of an inner segment 7 and an outer segment 6 interconnected by vanes 8.

La figure 2 est une vue partielle et éclatée du redresseur fixe sectorisé 1. Il comprend par exemple un carter en deux parties en forme de demi-cercle. La figure 2 montre partiellement l'une des parties 11 de ce carter avec l'un de ses plans de joint 16 destiné à être fixé sur un plan de joint correspondant de l'autre partie du carter. Trois secteurs 5 en cours de montage sont représentés. Pour un secteur 5, on reconnaît le segment extérieur 6, le segment intérieur 7 et les aubes 8 qui les relient.FIG. 2 is a partial and exploded view of the sectorized fixed rectifier 1. It comprises, for example, a two-part casing in the shape of a semicircle. Figure 2 partially shows one of the parts 11 of this housing with one of its joint planes 16 to be fixed on a corresponding joint plane of the other part of the housing. Three sectors 5 being edited are represented. For a sector 5, the outer segment 6, the inner segment 7 and the blades 8 which connect them are recognized.

La partie de carter 11 comprend deux flancs radiaux 12 et 13 se faisant face et pourvus chacun d'une gorge. Les gorges sont situées en vis-à-vis pour constituer une glissière. Les bords 21 et 22 du segment extérieur 6 du secteur 5 font saillie vers l'extérieur pour assurer une fonction de coulisseau par rapport à la glissière formée par la partie de carter 11.The housing portion 11 comprises two radial flanks 12 and 13 facing each other and each provided with a groove. The grooves are located vis-à-vis to form a slide. The edges 21 and 22 of the outer segment 6 of the sector 5 project outwards to provide a sliding function with respect to the slide formed by the housing part 11.

Avant d'engager un premier secteur 5 sur la partie de carter 11, un verrou anti-rotation est installé au plan de joint 16 de la partie de carter 11. Il peut s'agir d'une barrette ou d'un verrou tel que celui représenté à la figure 4.Before engaging a first sector 5 on the housing portion 11, an anti-rotation lock is installed at the joint plane 16 of the housing portion 11. It may be a bar or a lock such as the one shown in Figure 4.

La figure 2 montre aussi un verrou anti-rotation 30 disposé entre deux secteurs 5. Ce verrou 30 est montré en vue cavalière à la figure 3. Il est formé d'un élément 31 qui se place entre les deux flancs 12 et 13 de la partie de carter 11 (voir la figure 2). L'élément 31 est en forme d'arc de cercle et se prolonge par un bord extérieur 32 et un bord intérieur 33. Les bords 32 et 33 sont prévus pour que le verrou 30 puisse coulisser dans les gorges de la partie de carter 11. Le bord extérieur 32 comporte un ergot 34 faisant saillie du plan de l'élément 31. Il en va de même pour l'ergot 35 du bord intérieur 33.FIG. 2 also shows an anti-rotation lock 30 disposed between two sectors 5. This lock 30 is shown in a cavalier view in FIG. 3. It is formed of an element 31 which is placed between the two sides 12 and 13 of the housing portion 11 (see Figure 2). The element 31 is in the shape of an arc of a circle and extended by an outer edge 32 and an inner edge 33. The edges 32 and 33 are provided so that the latch 30 can slide in the grooves of the housing portion 11. The outer edge 32 has a lug 34 projecting from the plane of the housing. element 31. The same applies to the lug 35 of the inner edge 33.

Les figures 5 et 6 illustrent deux étapes de la mise en place d'un verrou anti-rotation 30 entre deux secteurs 5. Pour une meilleure compréhension, un seul des flancs de la partie de carter 11 a été représenté. On aperçoit la gorge 14 prévue dans ce flanc.Figures 5 and 6 illustrate two steps of the establishment of an anti-rotation lock 30 between two sectors 5. For better understanding, only one of the sides of the housing portion 11 has been shown. We can see the groove 14 provided in this flank.

La figure 5 montre un premier secteur 5 déjà installé (à gauche de la figure) et un deuxième secteur 5 en cours de montage (à droite de la figure). Entre ces deux secteurs a été introduit par glissement un verrou 30. On remarque que la hauteur de la gorge 14 permet le passage du bord extérieur du verrou 30 avec son ergot 34.Figure 5 shows a first sector 5 already installed (left of the figure) and a second sector 5 being mounted (right of the figure). Between these two sectors was introduced by sliding a latch 30. Note that the height of the groove 14 allows the passage of the outer edge of the latch 30 with its lug 34.

L'élément 30 est glissé jusqu'à venir en butée sur le premier secteur 5. Ceci correspond pour l'élément 30 à une position relative par rapport à la partie de carter 11 telle que l'ergot 34 se trouve en vis-à-vis d'une encoche 15 usinée dans la partie de carter 11. Il suffit alors d'exercer sur le verrou 30 une poussée vers le haut (pour la représentation des figures 5 et 6) pour que l'ergot 34 pénètre dans l'encoche 15, le verrou 30 se trouvant alors en position surélevée.The element 30 is slid up to abut on the first sector 5. This corresponds for the element 30 to a relative position relative to the housing portion 11 such that the lug 34 is vis-à-vis screw of a notch 15 machined in the housing portion 11. It is then sufficient to exert on the latch 30 upward thrust (for the representation of Figures 5 and 6) so that the lug 34 enters the notch 15, the latch 30 is then in raised position.

Le deuxième secteur 5 peut alors être poussé vers le verrou 30. Ce deuxième secteur 5 présente, à l'extrémité en contact avec le verrou 30, un dégagement 23 tel qu'une partie du segment extérieur 6 passe sous le verrou 30.The second sector 5 can then be pushed towards the latch 30. This second sector 5 present, at the end in contact with the latch 30, a clearance 23 such that a portion of the outer segment 6 passes under the latch 30.

Le verrou anti-rotation 40 de plan de joint représenté à la figure 4 se monte de la même manière que le verrou de la figure 3. Il est formé d'un élément 41 qui se place entre les deux flancs de la partie de carter. L'élément 41 se prolonge par un bord extérieur 42 et un bord intérieur 43. Le bord extérieur 42 comporte un ergot 44 faisant saillie du plan de l'élément 41. Il en va de même pour l'ergot 45 du bord intérieur 43.The anti-rotation lock 40 of the joint plane shown in Figure 4 is mounted in the same manner as the lock of Figure 3. It is formed of an element 41 which is placed between the two sides of the housing part. The element 41 is extended by an outer edge 42 and an inner edge 43. The outer edge 42 has a lug 44 protruding from the plane of the element 41. The same goes for the lug 45 of the inner edge 43.

Claims (11)

  1. Sectorized fixed stator for a compressor of a turbomachine comprising:
    - sectors (5) in the shape of an arc of a circle each consisting of an inner segment (7) and an outer segment (6) connected by blades (8),
    - a circular casing (4) incorporated into the stator of the compressor and designed to support the sectors (5) abutting one another,
    - anti-rotation means designed to prevent the rotation of the sectors supported by the casing,
    characterized in that:
    - the casing (4) consisting of at least two parts (11) abutting one another and attached together along parting lines, comprising means forming a slide,
    - the sectors (5) comprising means forming a runner adapted to the means forming a slide of the parts of the casing,
    - the anti-rotation means comprising anti-rotation means attached to the parting lines of the parts of the casing by attachment means,
    - the anti-rotation means comprise anti-rotation means locked onto the parts of the casing by locking means where the sectors abut one another.
  2. Sectorized fixed stator according to Claim 1, characterized in that the casing (4) consists of two parts (11) in the shape of a semicircle.
  3. Sectorized fixed stator according to one of Claims 1 or 2, characterized in that, the casing comprising two radial sides (12, 13) facing one another, the means forming a slide comprise two opposite grooves (14) made in the sides, the edges (21, 22) of the outer segments (6) of the sectors (5) being the means forming a runner.
  4. Sectorized fixed stator according to Claim 3, characterized in that the anti-rotation means attached to the parting lines comprise at least one bar immobilized between the two grooves by the said attachment means and forming a stop for a sector running in a slide of the casing.
  5. Sectorized fixed stator according to Claim 4, characterized in that the bar is a pincer with two branches inserted by bringing the two branches close to one another into receiving housings provided in the grooves, and immobilized in these housings by releasing the two branches, thus producing the said attachment means.
  6. Sectorized fixed stator according to Claim 3, characterized in that the anti-rotation means attached to the parting lines comprise at least one anti-rotation bolt (40) consisting of an element (41) comprising means forming a runner (42, 43) adapted to the means forming a slide of the parts of the casing, the element also comprising means (44, 45) of immobilization on the casing.
  7. Sectorized fixed stator according to Claim 6, characterized in that the immobilization means are of the mortice-tenon type, a tenon engaging in a mortice when the element (41) is pushed in a direction perpendicular to the direction of sliding of the element in the casing, thus forming the said attachment means.
  8. Sectorized fixed stator according to Claim 7, characterized in that the outer segment of the sector adjacent to the said element (41) has one of its ends that has a clearance so that, when this adjacent sector is slid into contact with the said element, the element can be pushed in the said perpendicular direction.
  9. Sectorized fixed stator according to Claim 3, characterized in that the anti-rotation means locked onto the parts of the casing comprise at least one anti-rotation bolt (30) consisting of an element (31) comprising means forming a runner (32, 33) adapted to the means forming a slide of the parts of the casing, the element also comprising means (34, 35) of immobilization on the casing.
  10. Sectorized fixed stator according to Claim 9, characterized in that the immobilization means are of the mortice-tenon type, a tenon engaging in a mortice when the element (31) is pushed in a direction perpendicular to the direction of sliding of the element in the casing, thus forming the said locking means.
  11. Sectorized fixed stator according to Claim 10, characterized in that the outer segment of a sector adjacent to the said element (31) has one of its ends that has a clearance so that, when this adjacent sector is slid into contact with the said element, the element can be pushed in the said perpendicular direction.
EP02292634A 2001-10-31 2002-10-24 Stator sector for a compressor of a turbomachine Expired - Lifetime EP1308630B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0114102A FR2831615B1 (en) 2001-10-31 2001-10-31 SECTORIZED FIXED RECTIFIER FOR A TURBOMACHINE COMPRESSOR
FR0114102 2001-10-31

Publications (2)

Publication Number Publication Date
EP1308630A1 EP1308630A1 (en) 2003-05-07
EP1308630B1 true EP1308630B1 (en) 2006-08-23

Family

ID=8868935

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02292634A Expired - Lifetime EP1308630B1 (en) 2001-10-31 2002-10-24 Stator sector for a compressor of a turbomachine

Country Status (9)

Country Link
US (1) US6890151B2 (en)
EP (1) EP1308630B1 (en)
JP (1) JP4181375B2 (en)
CA (1) CA2409972C (en)
DE (1) DE60214106T2 (en)
ES (1) ES2266430T3 (en)
FR (1) FR2831615B1 (en)
RU (1) RU2287090C2 (en)
UA (1) UA75069C2 (en)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2859509B1 (en) * 2003-09-10 2006-01-13 Snecma Moteurs ROTATION STOP OF AUBES AREAS OF RECTIFIERS BY BARRETTES IN THE SEAL PLANS OF THE CARTER
US7033135B2 (en) 2003-11-10 2006-04-25 General Electric Company Method and apparatus for distributing fluid into a turbomachine
US7144218B2 (en) * 2004-04-19 2006-12-05 United Technologies Corporation Anti-rotation lock
FR2878293B1 (en) * 2004-11-24 2009-08-21 Snecma Moteurs Sa MOUNTING DISTRIBUTOR SECTIONS IN AXIAL COMPRESSOR
JP4918263B2 (en) * 2006-01-27 2012-04-18 三菱重工業株式会社 Stator blade ring of axial compressor
US20080025838A1 (en) * 2006-07-25 2008-01-31 Siemens Power Generation, Inc. Ring seal for a turbine engine
US8128354B2 (en) * 2007-01-17 2012-03-06 Siemens Energy, Inc. Gas turbine engine
FR2913052B1 (en) * 2007-02-22 2011-04-01 Snecma CONTROL OF AUBES WITH VARIABLE SETTING ANGLE
EP2211023A1 (en) * 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Guide vane system for a turbomachine with segmented guide vane carrier
GB2468848B (en) * 2009-03-23 2011-10-26 Rolls Royce Plc An assembly for a turbomachine
FR2948736B1 (en) * 2009-07-31 2011-09-23 Snecma EXTERNAL VIROLE SECTOR FOR AIRBORNE TURBOMACHINE AIRBORNE STATOR CROWN, COMPRISING SHOCK ABSORBING MOUNTS
EP2339120B1 (en) * 2009-12-22 2015-07-08 Techspace Aero S.A. Turbomachine stator stage and corresponding compressor
US8454303B2 (en) * 2010-01-14 2013-06-04 General Electric Company Turbine nozzle assembly
US20110243725A1 (en) * 2010-03-31 2011-10-06 General Electric Company Turbine shroud mounting apparatus with anti-rotation feature
FR2975124B1 (en) 2011-05-09 2013-05-24 Snecma AIRCRAFT ENGINE ANNULAR VIRO COMPRISING AN AUBES INTRODUCTION WINDOW
US9074489B2 (en) 2012-03-26 2015-07-07 Pratt & Whitney Canada Corp. Connector assembly for variable inlet guide vanes and method
US10428832B2 (en) 2012-08-06 2019-10-01 United Technologies Corporation Stator anti-rotation lug
US10309235B2 (en) 2012-08-27 2019-06-04 United Technologies Corporation Shiplap cantilevered stator
US9353767B2 (en) 2013-01-08 2016-05-31 United Technologies Corporation Stator anti-rotation device
US9745864B2 (en) * 2014-04-16 2017-08-29 United Technologies Corporation Systems and methods for anti-rotational features
US10190434B2 (en) * 2014-10-29 2019-01-29 Rolls-Royce North American Technologies Inc. Turbine shroud with locating inserts
PL3215715T3 (en) * 2014-11-03 2021-03-08 Nuovo Pignone S.R.L. Sector for the assembly of a stage of a turbine and corresponding manufacturing method
BE1023619B1 (en) * 2015-06-26 2017-05-18 Safran Aero Boosters S.A. COMPRESSOR HOUSING OF AXIAL TURBOMACHINE
US20190309641A1 (en) * 2018-04-04 2019-10-10 United Technologies Corporation Gas turbine engine having cantilevered stators with sealing members

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2945290A (en) * 1957-09-16 1960-07-19 Gen Electric Stator vane half ring assemblies
US3365173A (en) * 1966-02-28 1968-01-23 Gen Electric Stator structure
US4126914A (en) 1976-06-22 1978-11-28 Cotton, Incorporated Process and apparatus for treating fibrous materials for subsequent processing
US4126405A (en) 1976-12-16 1978-11-21 General Electric Company Turbine nozzle
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
US5197856A (en) * 1991-06-24 1993-03-30 General Electric Company Compressor stator
US5141395A (en) * 1991-09-05 1992-08-25 General Electric Company Flow activated flowpath liner seal
FR2728015B1 (en) 1994-12-07 1997-01-17 Snecma SECTORIZED MONOBLOCK DISTRIBUTOR OF A TURBOMACHINE TURBINE STATOR
US5846050A (en) * 1997-07-14 1998-12-08 General Electric Company Vane sector spring
US6296443B1 (en) 1999-12-03 2001-10-02 General Electric Company Vane sector seating spring and method of retaining same

Also Published As

Publication number Publication date
US6890151B2 (en) 2005-05-10
DE60214106T2 (en) 2007-04-12
JP4181375B2 (en) 2008-11-12
UA75069C2 (en) 2006-03-15
CA2409972C (en) 2011-04-12
ES2266430T3 (en) 2007-03-01
CA2409972A1 (en) 2003-04-30
DE60214106D1 (en) 2006-10-05
FR2831615A1 (en) 2003-05-02
FR2831615B1 (en) 2004-01-02
EP1308630A1 (en) 2003-05-07
US20030082051A1 (en) 2003-05-01
JP2003161297A (en) 2003-06-06
RU2287090C2 (en) 2006-11-10

Similar Documents

Publication Publication Date Title
EP1308630B1 (en) Stator sector for a compressor of a turbomachine
EP2060750B1 (en) Stage of a turbine or compressor, in particular of a turbomachine
CA2554092C (en) Fan rotor blade locking system
CA2802821C (en) Angular stator sector for a turbomachine compressor, turbomachine stator and turbomachine comprising such a sector
EP0370899A1 (en) Turbine-bladed rotor disc
FR2501283A1 (en) METHOD AND DEVICE FOR LOCKING ROTOR BLADES ON A ROTOR DISC
CA2641017C (en) Improved turbojet stator blade spacing system control ring
FR2989724A1 (en) TURBINE STAGE FOR A TURBOMACHINE
FR2900437A1 (en) SYSTEM FOR RETENTING AUBES IN A ROTOR
EP3074638A1 (en) Fan for a turbomachine
FR3014151A1 (en) BLOWER, ESPECIALLY FOR A TURBOMACHINE
EP1524406B1 (en) Configuration of a turbomachine rotor blade
FR2971022A1 (en) COMPRESSOR RECTIFIER STAGE FOR A TURBOMACHINE
EP1662093B1 (en) Zusammenbau von Leitsegmente in einem axialen Kompressor
FR2729709A1 (en) Turbine rotor seal and retainer
CA2644312C (en) Turbine engine turbine or compressor stage
FR3106632A1 (en) STATOR BLADE FOR AN AIRCRAFT TURBOMACHINE
EP3683450A1 (en) Turbine engine rotor assembly
EP4359650A1 (en) Fan module impeller, and jet turbine engine equipped with such an impeller
EP4208626A1 (en) Turbine for a turbine engine comprising heat-shielding foils
FR2983247A1 (en) Rectifier-intermediate casing assembly for turboshaft engine e.g. turbojet, has blocking unit blocking rotation of internal ring with respect to casing, where unit is attached with internal ring by abutment in circumferential direction
FR3085994A1 (en) AXIAL RETENTION RING OF BLADES FOR MOBILE WHEEL OF TURBOMACHINE, PREFERABLY FOR AIRCRAFT

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20021108

AK Designated contracting states

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20060823

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 60214106

Country of ref document: DE

Date of ref document: 20061005

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20060928

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2266430

Country of ref document: ES

Kind code of ref document: T3

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20070524

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20121005

Year of fee payment: 11

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20150710

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20131025

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 17

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20210922

Year of fee payment: 20

Ref country code: IT

Payment date: 20210922

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20210922

Year of fee payment: 20

Ref country code: SE

Payment date: 20210921

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20210921

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 60214106

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20221023

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20221023