EP2053203A1 - Improvement of a ring for controlling the pitch of stator vanes of a turbomachine. - Google Patents

Improvement of a ring for controlling the pitch of stator vanes of a turbomachine. Download PDF

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Publication number
EP2053203A1
EP2053203A1 EP08166367A EP08166367A EP2053203A1 EP 2053203 A1 EP2053203 A1 EP 2053203A1 EP 08166367 A EP08166367 A EP 08166367A EP 08166367 A EP08166367 A EP 08166367A EP 2053203 A1 EP2053203 A1 EP 2053203A1
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EP
European Patent Office
Prior art keywords
ring
sections
turbomachine
turbomachine according
flanges
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08166367A
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German (de)
French (fr)
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EP2053203B1 (en
Inventor
Michel André Bouru
Jean-Christophe Leininger
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP2053203A1 publication Critical patent/EP2053203A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/79—Bearing, support or actuation arrangements therefor

Definitions

  • the invention relates to a turbomachine such as for example a compressor having at least one ring of rectifier blades with variable pitch. It relates more particularly to an improvement in the control ring of the orientation of the variable-pitch blades. The improvement makes it possible at the same time to improve the rigidity and the precision of operation of such a control ring of the positioning of these blades.
  • a turbomachine such as, for example, a high-pressure compressor of an aircraft turbojet, which comprises at least one stage of variable-pitch fixed vanes arranged circumferentially in a housing.
  • the compressor consists of a rotor comprising several stages of rotating blades, axially offset, between which are installed several stages of fixed blades variable pitch.
  • Each stage of fixed blades thus consists of a plurality of blades arranged radially and circumferentially in the casing forming a kind of crown, these blades are fixed but adjustable orientation.
  • the orientation of the blades must be identical for the entire crown of fixed vanes with variable pitch; it can be modified according to the operating conditions.
  • each blade comprises a control pivot projecting radially outside said housing and each pivot is connected by a lever to a common control ring, coaxial with said housing and rotatably mounted outside thereof.
  • the ring is slidably mounted on the outer surface of the casing and is actuated to be able to rotate about its own axis which coincides with that of the turbomachine.
  • the friction may represent up to 30% of the maneuvering force necessary to move the set of blades.
  • the behavior of the ring itself during these displacements can be the source of problems. There is sometimes an ovalization of the ring which is detrimental to the operation.
  • the ring consists of several sections, for example two half-rings, assembled around the housing.
  • FR-2-125,012 describes a control ring consisting of several sections assembled by bridge-shaped elements, to form a complete ring.
  • the bridge-shaped elements are bolted between distant ends of the sections of the ring.
  • the connection between two ring sections and a bridge-shaped element is made by radial bolting.
  • the bridge-shaped elements are relatively flexible and behave somewhat like soft hinges accentuating the deformation of the ring. This can result in a dispersion of blade angles of attack of up to two degrees or more. In the case where the compressor is part of a turboprop, this lack of precision increases the risk of pumping the engine.
  • the invention makes it possible at the same time to simplify and to stiffen the assembly of the sections constituting the control ring.
  • the invention relates to a turbomachine having a fixed blade stage variable pitch, arranged circumferentially in a housing, each blade having a control pivot projecting radially outside said housing and each pivot being connected by an arm a common control ring coaxial with said casing, rotatably mounted outside thereof, characterized in that said ring comprises two sections assembled by side connecting flanges fixed with recess on either side of said sections, to less in the vicinity of the ends thereof.
  • said sections have lateral recesses in which said connecting flanges are embedded.
  • such a connecting flange is a chamfered annular segment for defining frustoconical surfaces while the lateral recesses have a corresponding hollow profile, that is to say also having opposite frustoconical flanks.
  • such a connecting flange is an annular segment comprising a recess in which the end portions of said sections of the ring fit.
  • the sections of the ring may advantageously be chamfered to define four coaxially superposed two-by-two frustoconical surfaces and the aforementioned recess of each flange may comprise two corresponding frustoconical facets cooperating respectively with such two-by-two co-axial superimposed frustoconical surfaces. .
  • the frustoconical surfaces cooperating with the assembly during the tightening of the bolts, facilitate the positioning of the parts relative to each other.
  • the connecting flanges are bolted on either side of the adjacent end portions of said sections at the rate of at least one bolt for each end portion. Generally, two bolts are provided for each end portion.
  • a bolt screw is fitted to the hole of each end portion of the ring section in which it is engaged. If the assembly comprises more than one bolt per end portion of the ring section, the adjustment of a single bolt screw per ring section is generally sufficient to obtain the desired accuracy.
  • the ring comprises at least one actuating yoke or the like by which the actuating force causing its rotation is transmitted thereto.
  • the yoke has a base attached laterally with embedding to the ring, similarly to a lateral flange mentioned above.
  • the base itself forms one of said side flanges.
  • lateral recesses are defined on either side of the ring, considering its axial length, it is possible to proceed by practicing two truncated flank grooves on either side of a complete ring with radial section. rectangular or square, and then cutting the ring into several sections, for example and preferably into two half-rings and reconstituting the ring around the housing by assembling the sections by means of lateral connecting flanges bolted vis-à-vis at the ends of the sections.
  • the aforementioned lateral recesses extend over the entire circumference of the ring thus reconstituted.
  • a compressor 11 comprising, in a casing 13, a fixed blade ring 15 variable setting, adjustable by the rotation of a control ring 17 rotatably mounted outside the housing.
  • the control ring has two cylindrical faces 19, 20 coaxial.
  • the lower face 19 rests on the outer surface of the housing, by means of sliding pads (not visible in the drawings).
  • the center of the ring is located on the axis of rotation of the turbomachine. Only one dawn 15 is visible on the figure 1 .
  • Bores 23 oriented radially are made at regular intervals in the ring and open on its upper face 20 to receive axes 25 of control arm 27 of the blades 15.
  • the blades are arranged circumferentially and radially in the housing 13.
  • Each comprises a control pivot 29 projecting radially outside the housing, through a bore 31 thereof.
  • Each pivot is connected to the control ring by a specific arm 27. All this arrangement is classic.
  • the ring is manufactured in several sections 30a, 30b (at least two half-rings, for example) connected end to end.
  • the sections 30a, 30b of the ring are assembled by connecting flanges 33, 34 lateral fixed with embedding on either side of said sections, at least in the vicinity of the ends thereof.
  • said sections 30a, 30b comprise lateral recesses 35, 36 in which are embedded in said connecting flanges 33, 34.
  • Such a connecting flange is here an annular segment trapezoidal section that is to say having two frustoconical surfaces.
  • the lateral recesses 35, 36 have a corresponding recessed profile, that is to say they comprise two flanks with frustoconical surfaces complementary to those of the connecting flanges.
  • the lateral recesses 35, 36 are made at the ends of the sections 30a, 30b (half-rings) assembled by the connecting flanges described above. It suffices that these recesses have a sufficient length to accommodate the flanges of connection. However, in the embodiment shown, the lateral recesses 35, 36 extend over the entire circumference of the control ring. This results from an advantageous machining process of the ring. According to this method, a complete ring with a rectangular section is available and, by machining the flat annular surfaces (perpendicular to the axis of rotation) of this ring, two grooves with frustoconical sides.
  • the ring is then cut, for example in two equal parts, and holes 40 are made in the end portions of the sections thus formed. Corresponding holes 41 are made in the flanges 33, 34.
  • These sections are reassembled around the casing by means of bolts 44, at the rate of at least one bolt 44 per section, here two bolts 44 per section 30a or 30b, side to side. side.
  • an additional bolt 44a may be provided in the middle of the two flanges 33, 34, opposite the junction between the sections 30a, 30b.
  • connection is particularly rigid and the geometric and dimensional characteristics of the ring are particularly well controlled and stabilized over time.
  • the continuous lateral recesses 35 allow other elements to be connected to the control ring, with the same type of recessed assembly, for example for mounting at least one yoke 47 connected to an actuating jack of the ring.
  • the yoke has a base attached laterally with recess to the ring, in a manner similar to that shown for fixing the side flanges.
  • the base 48 forms one piece with one of the side flanges (the flange 34), as shown.
  • each connecting flange 133, 134 is an annular segment comprising a recess 135, 136 in which the end portions of the segments of the ring 17 are embedded.
  • the sections of the ring are chamfered to define four frustoconical surfaces 139a, 139b-140a, 140b two by two superimposed coaxially while the aforementioned hollow 135, 136 of each flange 133, 134 comprises two frustoconical facets 143a Corresponding 143b cooperating respectively with such two-by-two co-axial superimposed frustoconical surfaces.

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

Abstract

The turbomachine has a compressor (11) i.e. high pressure compressor, including fixed variable orientation blades arranged circumferentially in a casing (13), where each blade has a control pivot connected to a common control ring (17) by a blade orientation control arm (27). The ring is co-axial to the casing and rotatably mounted at the exterior of the casing. The ring has two sections (30a, 30b) i.e. semi-rings, assembled by lateral connecting flanges i.e. beveled annular segments, that are fitted on both sides of the sections and fitted nearer to ends of the sections by parallel bolting.

Description

L'invention se rapporte à une turbomachine telle que par exemple un compresseur présentant au moins une couronne d'aubes de redresseur à calage variable. Elle concerne plus particulièrement un perfectionnement à l'anneau de commande de l'orientation des aubes à calage variable. Le perfectionnement permet à la fois d'améliorer la rigidité et la précision de manoeuvre d'un tel anneau de commande du positionnement de ces aubes.The invention relates to a turbomachine such as for example a compressor having at least one ring of rectifier blades with variable pitch. It relates more particularly to an improvement in the control ring of the orientation of the variable-pitch blades. The improvement makes it possible at the same time to improve the rigidity and the precision of operation of such a control ring of the positioning of these blades.

On connaît une turbomachine telle que par exemple un compresseur haute pression d'un turboréacteur d'avion, qui comporte au moins un étage d'aubes fixes à calage variable agencées circonférentiellement dans un carter. Classiquement, le compresseur est constitué d'un rotor comprenant plusieurs étages de pales rotatives, décalés axialement, entre lesquels sont installés plusieurs étages d'aubes fixes à calage variable. Chaque étage d'aubes fixes est ainsi constitué d'une pluralité d'aubes agencées radialement et circonférentiellement dans le carter en formant une sorte de couronne, ces aubes sont fixes mais d'orientation réglable. L'orientation des pales doit être identique pour toute la couronne d'aubes fixes à calage variable ; elle peut être modifiée en fonction des conditions de fonctionnement.A turbomachine is known such as, for example, a high-pressure compressor of an aircraft turbojet, which comprises at least one stage of variable-pitch fixed vanes arranged circumferentially in a housing. Conventionally, the compressor consists of a rotor comprising several stages of rotating blades, axially offset, between which are installed several stages of fixed blades variable pitch. Each stage of fixed blades thus consists of a plurality of blades arranged radially and circumferentially in the casing forming a kind of crown, these blades are fixed but adjustable orientation. The orientation of the blades must be identical for the entire crown of fixed vanes with variable pitch; it can be modified according to the operating conditions.

Pour ce faire, chaque aube comporte un pivot de commande faisant saillie radialement à l'extérieur dudit carter et chaque pivot est relié par un levier à un anneau de commande commun, coaxial audit carter et monté rotatif à l'extérieur de celui-ci. Généralement, l'anneau est monté coulissant à la surface extérieure du carter et il est actionné pour pouvoir tourner autour de son propre axe qui est confondu avec celui de la turbomachine. Suivant la position des patins de coulissement entre l'anneau et le carter, et suivant l'emplacement des points d'accrochage des moyens de commande, les frottements peuvent représenter jusqu'à 30 % de l'effort de manoeuvre nécessaire pour déplacer l'ensemble des aubes. Le comportement de l'anneau lui-même pendant ces déplacements peut être la source de problèmes. On observe parfois une ovalisation de l'anneau qui est préjudiciable au fonctionnement.To do this, each blade comprises a control pivot projecting radially outside said housing and each pivot is connected by a lever to a common control ring, coaxial with said housing and rotatably mounted outside thereof. Generally, the ring is slidably mounted on the outer surface of the casing and is actuated to be able to rotate about its own axis which coincides with that of the turbomachine. Depending on the position of the sliding shoes between the ring and the casing, and depending on the location of the attachment points of the control means, the friction may represent up to 30% of the maneuvering force necessary to move the set of blades. The behavior of the ring itself during these displacements can be the source of problems. There is sometimes an ovalization of the ring which is detrimental to the operation.

Généralement, l'anneau est constitué de plusieurs tronçons, par exemple deux demi-anneaux, assemblés autour du carter. Ainsi, FR-2-125 012 décrit un anneau de commande constitué de plusieurs tronçons assemblés par des éléments en forme de pont, pour former un anneau complet. Les éléments en forme de pont sont boulonnés entre des extrémités éloignées des tronçons de l'anneau. L'assemblage entre deux tronçons d'anneau et un élément en forme de pont est fait par un boulonnage radial. Les éléments en forme de pont sont relativement flexibles et se comportent quelque peu comme des charnières souples accentuant la déformation de l'anneau. Il peut en résulter une dispersion des angles d'attaque des aubes pouvant atteindre deux degrés ou plus. Dans le cas où le compresseur fait partie d'un turbopropulseur, ce manque de précision augmente les risques de pompage du moteur.Generally, the ring consists of several sections, for example two half-rings, assembled around the housing. So, FR-2-125,012 describes a control ring consisting of several sections assembled by bridge-shaped elements, to form a complete ring. The bridge-shaped elements are bolted between distant ends of the sections of the ring. The connection between two ring sections and a bridge-shaped element is made by radial bolting. The bridge-shaped elements are relatively flexible and behave somewhat like soft hinges accentuating the deformation of the ring. This can result in a dispersion of blade angles of attack of up to two degrees or more. In the case where the compressor is part of a turboprop, this lack of precision increases the risk of pumping the engine.

L'invention permet à la fois de simplifier et rigidifier l'assemblage des tronçons constituant l'anneau de commande.The invention makes it possible at the same time to simplify and to stiffen the assembly of the sections constituting the control ring.

Plus particulièrement, l'invention concerne une turbomachine comportant un étage d'aubes fixes à calage variable, agencé circonférentiellement dans un carter, chaque aube comportant un pivot de commande faisant saillie radialement à l'extérieur dudit carter et chaque pivot étant relié par un bras à un anneau de commande commun coaxial audit carter, monté rotatif à l'extérieur de celui-ci, caractérisée en ce que ledit anneau comporte deux tronçons assemblés par des flasques de liaison latéraux fixés avec encastrement de part et d'autre desdits tronçons, au moins au voisinage des extrémités de ceux-ci.More particularly, the invention relates to a turbomachine having a fixed blade stage variable pitch, arranged circumferentially in a housing, each blade having a control pivot projecting radially outside said housing and each pivot being connected by an arm a common control ring coaxial with said casing, rotatably mounted outside thereof, characterized in that said ring comprises two sections assembled by side connecting flanges fixed with recess on either side of said sections, to less in the vicinity of the ends thereof.

Ainsi, le boulonnage radial des portions d'extrémité des tronçons, par l'intermédiaire d'un élément en forme de pont, est remplacé par un boulonnage parallèlement à l'axe, mettant en oeuvre deux flasques de liaison s'étendant de part et d'autre des tronçons. Il en résulte un assemblage d'une très grande rigidité et précision, pour un encombrement moindre.Thus, the radial bolting of the end portions of the sections, via a bridge-shaped element, is replaced by a bolting parallel to the axis, implementing two connecting flanges extending from one side to the other. other sections. This results in an assembly of great rigidity and precision, for less space.

Selon un mode de réalisation possible, lesdits tronçons présentent des creusures latérales dans lesquelles s'encastrent lesdits flasques de liaison.According to a possible embodiment, said sections have lateral recesses in which said connecting flanges are embedded.

Avantageusement, un tel flasque de liaison est un segment annulaire chanfreiné pour définir des surfaces tronconiques tandis que les creusures latérales ont un profil en creux correspondant, c'est-à-dire présentant aussi des flancs opposés tronconiques.Advantageously, such a connecting flange is a chamfered annular segment for defining frustoconical surfaces while the lateral recesses have a corresponding hollow profile, that is to say also having opposite frustoconical flanks.

Selon un mode de réalisation inverse, un tel flasque de liaison est un segment annulaire comportant une creusure dans laquelle s'encastrent les portions d'extrémité desdits tronçons de l'anneau.According to an inverse embodiment, such a connecting flange is an annular segment comprising a recess in which the end portions of said sections of the ring fit.

Dans ce cas, les tronçons de l'anneau peuvent être avantageusement chanfreinés pour définir quatre surfaces tronconiques deux à deux superposées coaxialement et la creusure précitée de chaque flasque peut comporter deux facettes tronconiques correspondantes, coopérant respectivement avec de telles surfaces tronconiques deux à deux superposées coaxialement.In this case, the sections of the ring may advantageously be chamfered to define four coaxially superposed two-by-two frustoconical surfaces and the aforementioned recess of each flange may comprise two corresponding frustoconical facets cooperating respectively with such two-by-two co-axial superimposed frustoconical surfaces. .

Les surfaces tronconiques, coopérant au montage pendant le serrage des boulons, facilitent le positionnement des pièces les unes par rapport aux autres.The frustoconical surfaces, cooperating with the assembly during the tightening of the bolts, facilitate the positioning of the parts relative to each other.

Les flasques de liaison sont boulonnés de part et d'autre des portions d'extrémité adjacentes desdits tronçons à raison d'au moins un boulon pour chaque portion d'extrémité. Généralement, on prévoit deux boulons pour chaque portion d'extrémité.The connecting flanges are bolted on either side of the adjacent end portions of said sections at the rate of at least one bolt for each end portion. Generally, two bolts are provided for each end portion.

Il est à noter que pour améliorer la précision de l'assemblage, une vis de boulon est ajustée au trou de chaque portion d'extrémité du tronçon d'anneau dans lequel elle est engagée. Si l'assemblage comporte plus d'un boulon par portion d'extrémité du tronçon d'anneau, l'ajustage d'une seule vis de boulon par tronçon d'anneau est généralement suffisant pour obtenir la précision recherchée.It should be noted that to improve the accuracy of the assembly, a bolt screw is fitted to the hole of each end portion of the ring section in which it is engaged. If the assembly comprises more than one bolt per end portion of the ring section, the adjustment of a single bolt screw per ring section is generally sufficient to obtain the desired accuracy.

Par ailleurs, l'anneau comporte au moins une chape de manoeuvre ou analogue par laquelle l'effort de manoeuvre entraînant sa rotation lui est transmis.Furthermore, the ring comprises at least one actuating yoke or the like by which the actuating force causing its rotation is transmitted thereto.

Selon une caractéristique avantageuse, la chape présente un socle fixé latéralement avec encastrement à l'anneau, de façon analogue à un flasque latéral précité. Par exemple, le socle forme lui-même l'un desdits flasques latéraux.According to an advantageous characteristic, the yoke has a base attached laterally with embedding to the ring, similarly to a lateral flange mentioned above. For example, the base itself forms one of said side flanges.

Dans le cas où des creusures latérales sont définies de part et d'autre de l'anneau, en considérant sa longueur axiale, on peut procéder en pratiquant deux gorges à flancs tronconiques de part et d'autre d'un anneau complet à section radiale rectangulaire ou carrée, puis en coupant cet anneau en plusieurs tronçons, par exemple et de préférence en deux demi-anneaux et en reconstituant l'anneau autour du carter en assemblant les tronçons au moyen de flasques de liaison latéraux en vis-à-vis boulonnés aux extrémités des tronçons. Dans ce cas, les creusures latérales précitées s'étendent sur toute la circonférence de l'anneau ainsi reconstitué.In the case where lateral recesses are defined on either side of the ring, considering its axial length, it is possible to proceed by practicing two truncated flank grooves on either side of a complete ring with radial section. rectangular or square, and then cutting the ring into several sections, for example and preferably into two half-rings and reconstituting the ring around the housing by assembling the sections by means of lateral connecting flanges bolted vis-à-vis at the ends of the sections. In this case, the aforementioned lateral recesses extend over the entire circumference of the ring thus reconstituted.

L'invention sera mieux comprise et d'autres avantages de celle-ci apparaîtront mieux à la lumière de la description qui va suivre donnée uniquement à titre d'exemple et faite en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue partielle en perspective d'une partie d'un compresseur du type comprenant une couronne d'aubes fixes à calage réglable, une seule aube et son bras étant représentés sur le dessin, pour plus de clarté ;
  • la figure 2 est une coupe II-II de la figure 1 ; et
  • la figure 3 est une vue analogue à la figure 2, illustrant une variante.
The invention will be better understood and other advantages thereof will appear better in the light of the following description given solely by way of example and with reference to the accompanying drawings in which:
  • the figure 1 is a partial perspective view of a portion of a compressor of the type comprising an adjustable blade ring crown, a single blade and its arm being shown in the drawing, for clarity;
  • the figure 2 is a II-II section of the figure 1 ; and
  • the figure 3 is a view similar to the figure 2 , illustrating a variant.

Sur les figures 1 et 2, on a représenté une partie d'une turbomachine, en l'occurrence un compresseur 11 comportant, dans un carter 13, une couronne d'aubes fixes 15 à calage variable , réglable par la rotation d'un anneau de commande 17 monté en rotation à l'extérieur du carter. L'anneau de commande comporte deux faces cylindriques 19, 20 coaxiales. La face inférieure 19 repose sur la surface extérieure du carter, par l'intermédiaire de patins de glissement (non visibles sur les dessins). Le centre de l'anneau se situe sur l'axe de rotation de la turbomachine. Une seule aube 15 est visible sur la figure 1.On the figures 1 and 2 , there is shown a part of a turbomachine, in this case a compressor 11 comprising, in a casing 13, a fixed blade ring 15 variable setting, adjustable by the rotation of a control ring 17 rotatably mounted outside the housing. The control ring has two cylindrical faces 19, 20 coaxial. The lower face 19 rests on the outer surface of the housing, by means of sliding pads (not visible in the drawings). The center of the ring is located on the axis of rotation of the turbomachine. Only one dawn 15 is visible on the figure 1 .

Des perçages 23 orientés radialement sont pratiqués à intervalle régulier dans l'anneau et débouchent sur sa face supérieure 20 pour recevoir des axes 25 de bras 27 de commande d'orientation des aubes 15. Les aubes sont agencés circonférentiellement et radialement dans le carter 13. Chacune comporte un pivot de commande 29 faisant saillie radialement à l'extérieur du carter, en traversant un alésage 31 de celui-ci. Chaque pivot est relié à l'anneau de commande par un bras 27 spécifique. Tout cet agencement est classique.Bores 23 oriented radially are made at regular intervals in the ring and open on its upper face 20 to receive axes 25 of control arm 27 of the blades 15. The blades are arranged circumferentially and radially in the housing 13. Each comprises a control pivot 29 projecting radially outside the housing, through a bore 31 thereof. Each pivot is connected to the control ring by a specific arm 27. All this arrangement is classic.

Pour pouvoir être monté à l'extérieur du carter, qui comporte des brides saillantes, l'anneau est fabriqué en plusieurs tronçons 30a, 30b (au moins deux demi-anneaux, par exemple) raccordés bout à bout.To be mounted outside the housing, which has projecting flanges, the ring is manufactured in several sections 30a, 30b (at least two half-rings, for example) connected end to end.

Selon une caractéristique importante, les tronçons 30a, 30b de l'anneau sont assemblés par des flasques de liaison 33, 34 latéraux fixés avec encastrement de part et d'autre desdits tronçons, au moins au voisinage des extrémités de ceux-ci. Dans l'exemple spécifiquement décrit, lesdits tronçons 30a, 30b comportent des creusures latérales 35, 36 dans lesquelles s'encastrent lesdits flasques de liaison 33, 34. Un tel flasque de liaison est ici un segment annulaire à section trapézoïdale c'est-à-dire comportant deux surfaces tronconiques. Dans ce cas, les creusures latérales 35, 36 ont un profil en creux correspondant, c'est-à-dire qu'elles comportent deux flancs à surfaces tronconiques complémentaires de celles des flasques de liaison.According to an important characteristic, the sections 30a, 30b of the ring are assembled by connecting flanges 33, 34 lateral fixed with embedding on either side of said sections, at least in the vicinity of the ends thereof. In the example specifically described, said sections 30a, 30b comprise lateral recesses 35, 36 in which are embedded in said connecting flanges 33, 34. Such a connecting flange is here an annular segment trapezoidal section that is to say having two frustoconical surfaces. In this case, the lateral recesses 35, 36 have a corresponding recessed profile, that is to say they comprise two flanks with frustoconical surfaces complementary to those of the connecting flanges.

Il est suffisant que les creusures latérales 35, 36 soient pratiquées aux extrémités des tronçons 30a, 30b (demi-anneaux) assemblées par les flasques de liaison décrit ci-dessus. Il suffit que ces creusures aient une longueur suffisante pour accueillir les flasques de liaison. Cependant, dans le mode de réalisation représenté, les creusures latérales 35, 36 s'étendent sur toute la circonférence de l'anneau de commande. Ceci résulte d'un procédé d'usinage avantageux de l'anneau. Selon ce procédé, on dispose d'un anneau complet à section rectangulaire et on pratique, en usinant les surfaces annulaires plates (perpendiculaires à l'axe de rotation) de cet anneau, deux gorges à flancs tronconiques. On coupe ensuite l'anneau, par exemple en deux parties égales et on pratique des trous 40 dans les portions d'extrémité des tronçons ainsi constitués. On pratique des trous 41 correspondants dans les flasques 33, 34. On réassemble ces tronçons autour du carter au moyen de boulons 44, à raison d'au moins un boulon 44 par tronçon, ici deux boulons 44 par tronçon 30a ou 30b, côte à côte.It is sufficient that the lateral recesses 35, 36 are made at the ends of the sections 30a, 30b (half-rings) assembled by the connecting flanges described above. It suffices that these recesses have a sufficient length to accommodate the flanges of connection. However, in the embodiment shown, the lateral recesses 35, 36 extend over the entire circumference of the control ring. This results from an advantageous machining process of the ring. According to this method, a complete ring with a rectangular section is available and, by machining the flat annular surfaces (perpendicular to the axis of rotation) of this ring, two grooves with frustoconical sides. The ring is then cut, for example in two equal parts, and holes 40 are made in the end portions of the sections thus formed. Corresponding holes 41 are made in the flanges 33, 34. These sections are reassembled around the casing by means of bolts 44, at the rate of at least one bolt 44 per section, here two bolts 44 per section 30a or 30b, side to side. side.

En outre, un boulon supplémentaire 44a peut être prévu au milieu des deux flasques 33, 34, en regard de la jonction entre les tronçons 30a, 30b.In addition, an additional bolt 44a may be provided in the middle of the two flanges 33, 34, opposite the junction between the sections 30a, 30b.

Avec ce mode d'assemblage, la liaison est particulièrement rigide et les caractéristiques géométriques et dimensionnelles de l'anneau sont particulièrement bien maîtrisées et stabilisées dans le temps.With this method of assembly, the connection is particularly rigid and the geometric and dimensional characteristics of the ring are particularly well controlled and stabilized over time.

De plus, les creusures latérales 35 continues permettent de raccorder d'autres éléments à l'anneau de commande, avec le même type d'assemblage à encastrement, par exemple pour le montage d'au moins une chape 47 reliée à un vérin de manoeuvre de l'anneau.In addition, the continuous lateral recesses 35 allow other elements to be connected to the control ring, with the same type of recessed assembly, for example for mounting at least one yoke 47 connected to an actuating jack of the ring.

Dans ce cas, la chape présente un socle fixé latéralement avec encastrement à l'anneau, d'une façon analogue à celle qui est représentée pour la fixation des flasques latéraux. Avantageusement, le socle 48 forme une seule pièce avec l'un des flasques latéraux (le flasque 34), comme représenté.In this case, the yoke has a base attached laterally with recess to the ring, in a manner similar to that shown for fixing the side flanges. Advantageously, the base 48 forms one piece with one of the side flanges (the flange 34), as shown.

Dans la variante de la figure 3, chaque flasque de liaison 133, 134 est un segment annulaire comportant une creusure 135, 136 dans laquelle s'encastrent les portions d'extrémité des tronçons de l'anneau 17.In the variant of the figure 3 each connecting flange 133, 134 is an annular segment comprising a recess 135, 136 in which the end portions of the segments of the ring 17 are embedded.

De préférence, comme représenté, les tronçons de l'anneau sont chanfreinés pour définir quatre surfaces tronconiques 139a, 139b - 140a, 140b deux à deux superposées coaxialement tandis que la creusure précitée 135, 136 de chaque flasque 133, 134 comporte deux facettes tronconiques 143a, 143b correspondantes coopérant respectivement avec de telles surfaces tronconiques deux à deux superposées coaxialement.Preferably, as shown, the sections of the ring are chamfered to define four frustoconical surfaces 139a, 139b-140a, 140b two by two superimposed coaxially while the aforementioned hollow 135, 136 of each flange 133, 134 comprises two frustoconical facets 143a Corresponding 143b cooperating respectively with such two-by-two co-axial superimposed frustoconical surfaces.

Claims (12)

Turbomachine comportant un étage d'aubes fixes à calage variable, agencé circonférentiellement dans un carter (13), chaque aube comportant un pivot de commande (29) faisant saillie radialement à l'extérieur dudit carter et chaque pivot étant relié par un bras (27) à un anneau de commande (17) commun coaxial audit carter, monté rotatif à l'extérieur de celui-ci, caractérisée en ce que ledit anneau (17) comporte deux tronçons (30a, 30b) assemblés par des flasques de liaison latéraux (33, 34) fixés avec encastrement de part et d'autre desdits tronçons, au moins au voisinage des extrémités de ceux-ci.A turbomachine comprising a variable-pitch fixed blade stage arranged circumferentially in a housing (13), each blade comprising a control pivot (29) projecting radially outside said housing and each pivot being connected by an arm (27). ) to a common control ring (17) coaxial with said casing, rotatably mounted outside thereof, characterized in that said ring (17) comprises two sections (30a, 30b) assembled by side connecting flanges ( 33, 34) fixed with recess on either side of said sections, at least in the vicinity of the ends thereof. Turbomachine selon la revendication 1, caractérisée en ce que lesdits tronçons comportent des creusures latérales (35, 36) dans lesquelles s'encastrent lesdits flasques de liaison (33, 34).Turbine engine according to claim 1, characterized in that said sections comprise lateral recesses (35, 36) in which said connecting flanges (33, 34) fit. Turbomachine selon la revendication 2, caractérisée en ce qu'un tel flasque de liaison (33, 34) est un segment annulaire chanfreiné pour définir des surfaces tronconiques et en ce que lesdites creusures latérales (35, 36) ont un profil en creux correspondant.Turbine engine according to claim 2, characterized in that such a connecting flange (33, 34) is a chamfered annular segment for defining frustoconical surfaces and in that said lateral recesses (35, 36) have a corresponding hollow profile. Turbomachine selon la revendication 1, caractérisée en ce qu'un tel flasque de liaison (133, 134) est un segment annulaire comportant une creusure (135, 136) dans laquelle s'encastrent les portions d'extrémité desdits tronçons.Turbine engine according to claim 1, characterized in that such a connecting flange (133, 134) is an annular segment comprising a recess (135, 136) in which the end portions of said sections fit. Turbomachine selon la revendication 4, caractérisée en ce que lesdits tronçons sont chanfreinés pour définir quatre surfaces tronconiques, (139a, 139b - 140a, 140b) deux à deux superposées coaxialement et en ce que la creusure précitée de chaque flasque latéral (133, 134) comprend deux facettes tronconiques correspondantes, coopérant respectivement avec de telles surfaces tronconiques deux à deux superposées coaxialement.Turbomachine according to claim 4, characterized in that said sections are chamfered to define four frustoconical surfaces, (139a, 139b-140a, 140b) coaxially superposed in pairs and in that said recess of each lateral flange (133, 134) comprises two corresponding frustoconical facets cooperating respectively with such two-by-two coaxially superposed frustoconical surfaces. Turbomachine selon l'une des revendications précédentes, caractérisée en ce que lesdits flasques de liaison sont boulonnés de part et d'autre des portions d'extrémité adjacente desdits tronçons, par au moins un boulon (44) pour chaque portion d'extrémité.Turbomachine according to one of the preceding claims, characterized in that said connecting flanges are bolted on either side of the adjacent end portions of said sections, by at least one bolt (44) for each end portion. Turbomachine selon la revendication 6, caractérisée en ce que les flasques de liaison sont boulonnés par deux boulons (44) pour chaque portion d'extrémité.Turbomachine according to claim 6, characterized in that the connecting flanges are bolted by two bolts (44) for each end portion. Turbomachine selon la revendication 6 ou 7, caractérisée en ce qu'une vis de boulon (44) est ajustée au trou (40) de chaque portion d'extrémité du tronçon d'anneau dans lequel elle est engagée.Turbomachine according to claim 6 or 7, characterized in that a bolt screw (44) is fitted to the hole (40) of each end portion of the ring section in which it is engaged. Turbomachine selon l'une des revendications 6 à 8, caractérisée en ce qu'un boulon supplémentaire (44a) est prévu au milieu des deux flasques.Turbomachine according to one of claims 6 to 8, characterized in that an additional bolt (44a) is provided in the middle of the two flanges. Turbomachine selon l'une des revendications précédentes, caractérisée en ce que ledit anneau comportant au moins une chape de manoeuvre (47) ou analogue, ladite chape présente un socle (48) fixé latéralement avec encastrement audit anneau, de façon analogue à un flasque latéral précité.Turbomachine according to one of the preceding claims, characterized in that said ring comprising at least one operating yoke (47) or the like, said yoke has a base (48) laterally fixed with recess in said ring, similarly to a lateral flange supra. Turbomachine selon la revendication 10, caractérisée en ce que ledit socle (48) forme une seule pièce avec l'un desdits flasques latéraux.Turbomachine according to claim 10, characterized in that said base (48) forms a single piece with one of said lateral flanges. Turbomachine selon l'une des revendications 2 à 11, caractérisée en ce que lesdites creusures latérales (35) s'étendent sur toute la circonférence dudit anneau.Turbomachine according to one of claims 2 to 11, characterized in that said lateral recesses (35) extend over the entire circumference of said ring.
EP08166367.6A 2007-10-12 2008-10-10 Improvement of a ring for controlling the pitch of stator vanes of a turbomachine. Active EP2053203B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0758244A FR2922257B1 (en) 2007-10-12 2007-10-12 IMPROVEMENT TO A CALIBRATION CONTROL RING OF THE FIXED AUBES OF A TURBOMACHINE

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EP2053203A1 true EP2053203A1 (en) 2009-04-29
EP2053203B1 EP2053203B1 (en) 2013-04-10

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US (1) US8226357B2 (en)
EP (1) EP2053203B1 (en)
JP (1) JP5420221B2 (en)
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FR3072719A1 (en) * 2017-10-20 2019-04-26 Safran Aircraft Engines CONTROL RING OF A VARIABLE SHIFT AUBRA STAGE FOR A TURBOMACHINE
FR3079870A1 (en) * 2018-04-06 2019-10-11 Safran Aircraft Engines DEVICE FOR CONTROLLING AN ANNULAR ROW OF VARIABLE-SETTING AUBES FOR AN AIRCRAFT ENGINE

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FR3029562B1 (en) * 2014-12-09 2016-12-09 Snecma CONTROL RING OF A VARIABLE SHIFT AUBRA STAGE FOR A TURBOMACHINE
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CA2641017A1 (en) 2009-04-12
RU2008140325A (en) 2010-04-20
JP2009097510A (en) 2009-05-07
CA2641017C (en) 2015-06-16
FR2922257B1 (en) 2014-03-28
FR2922257A1 (en) 2009-04-17
US20090116954A1 (en) 2009-05-07
EP2053203B1 (en) 2013-04-10
JP5420221B2 (en) 2014-02-19
US8226357B2 (en) 2012-07-24
RU2503823C2 (en) 2014-01-10

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