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EP2368017B1 - Positioning device for a ring segment - Google Patents

Positioning device for a ring segment Download PDF

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Publication number
EP2368017B1
EP2368017B1 EP09795477.0A EP09795477A EP2368017B1 EP 2368017 B1 EP2368017 B1 EP 2368017B1 EP 09795477 A EP09795477 A EP 09795477A EP 2368017 B1 EP2368017 B1 EP 2368017B1
Authority
EP
European Patent Office
Prior art keywords
arm
positioning member
ring
turbomachine according
casing
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.)
Active
Application number
EP09795477.0A
Other languages
German (de)
French (fr)
Other versions
EP2368017A1 (en
Inventor
Jean-Baptiste Arilla
Denis Chanteloup
Yvan Lameignere
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 Helicopter Engines SAS
Original Assignee
Turbomeca 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 Turbomeca SA filed Critical Turbomeca SA
Priority to PL09795477T priority Critical patent/PL2368017T3/en
Publication of EP2368017A1 publication Critical patent/EP2368017A1/en
Application granted granted Critical
Publication of EP2368017B1 publication Critical patent/EP2368017B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/70—Shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to the field of turbomachine turbines, and more particularly those found in gas turbines.
  • the present invention more specifically relates to a turbomachine comprising a member for positioning a ring segment for a turbine wheel rotatably mounted about an axis in a housing.
  • turbomachine turbine wheels such as helicopter gas turbine high pressure turbines
  • a ring concentric with the turbine wheel.
  • This ring as a constituent element of the stator of the turbomachine, forms an outer shell for the turbine stage.
  • the flue gases exiting the combustion chamber flow between the hub of the turbine wheel and the ring so as to drive the turbine wheel in rotation.
  • the ring is constituted by a plurality of ring segments, also called ring sectors, arranged contiguously next to each other.
  • ring segments are generally not fixed integrally to the casing of the turbomachine because they are likely to expand axially and radially due to the large heat carried by the flue gases.
  • the ring segments are held in the housing by one or more positioning members.
  • this cooling fluid can for example be taken from the compressed air that is generated by the compressor of the turbomachine .
  • the document US 5,988,975 proposes a solution which consists in producing a radial seal thanks to a ring which keeps the ring segments in radial support against the casing.
  • the document WO-A-99 30009 discloses a sealing member with an elastic bearing portion.
  • An object of the present invention is to provide a turbomachine comprising an alternating positioning member for sealing between a gas stream and the cooling circuit.
  • axial and radial are considered with reference to the axis and a radius of the turbine wheel, while the term “downstream” is referred to in the sense of flue gas flow in the turbine.
  • each ring segment is held axially against a portion normal to the axis of rotation (downstream or upstream) of the casing, thanks to the axial force exerted by the bearing portion of the positioning member, it follows that the seal is made between the cooling fluid circuit and the gas stream.
  • the positioning member being fixed to the housing by the fixing portion, the axial force generated by the elastic portion is transmitted to the bearing portion and the ring segment.
  • the latter being able, in the absence of the positioning member, to move slightly axially relative to the housing, it is conceivable that the bearing portion pushes the ring segment against the part of the housing, as a result of which it is pressed against said housing part.
  • the bearing portion pushes the ring segment against the downstream portion of the housing.
  • the fixing portion also bears against the ring segment.
  • the elastic portion is disposed between the fixing portion and the bearing portion.
  • the portion of the housing against which the ring segment is plated is normal to the axis of rotation of the turbine wheel.
  • the positioning member according to the invention comprises at least a first arm carrying the fixing portion.
  • this first arm is intended to extend preferably axially.
  • the attachment portion is in the form of a tab extending orthogonally with respect to a plane in which the first arm extends.
  • the tab when the positioning member is mounted, the tab extends radially. It is especially intended to be clamped between two constituent parts of the housing.
  • the fixing portion comprises a bore whose axis extends orthogonally with respect to a plane in which the first arm extends.
  • the attachment to the housing is carried out for example but not exclusively by means of a screw-nut system, so that the first arm of the positioning member is locked axially relative to the housing.
  • the elastic portion consists of a corrugated tongue, this tongue being for example a thin metal plate, for example a flexible sheet, having several successive folds.
  • this tongue being for example a thin metal plate, for example a flexible sheet, having several successive folds.
  • other types of elastic portion could be conceived.
  • the corrugation is preferably arranged between the fixing portion and the bearing portion.
  • the positioning member is in the form of a tongue whose first end, constituting the fixing portion, has an orthogonal tab, whose second end, constituting the bearing portion, is curved, and whose middle portion disposed between the first and second end is corrugated so as to constitute the elastic portion.
  • the positioning member comprises at least one first arm carrying the fixing portion, and at least one second arm comprising the elastic portion, the latter being preferably formed by a corrugation.
  • the first and second arms are parallel and extend from a plate, the attachment portion is located at one end of the first arm opposite the plate, while the support portion is located at the end of the second arm opposite the platen.
  • the positioning member further comprises a third arm similar to the second arm which extends from the plate, the arms being arranged so that the first arm extends between the second and third arms.
  • the positioning member has the shape of an "E", where the three branches are constituted by the first, second and third arm. More specifically, these three arms extend axially when the positioning member is mounted with the ring segment.
  • each of the ring segments is held in an azimuthal direction between the first arm of a first positioning member located at one end of the segment and the first arm of a second positioning member located at the end of the segment. other end of the segment.
  • the first arm further comprises, preferably, a second elastic portion disposed between the plate and the fixing portion, whereby the elasticity of the positioning member is further improved.
  • the first arm forms a wafer for covering a gap junction defined between two contiguous ring segments.
  • one of the ends of the wafer preferably carries the tab mentioned above to allow the fixing of the positioning member to the housing.
  • the wafer improves the seal by covering the gap that may exist between the two ends of two contiguous segments.
  • the elastic portion is constituted by a pair of "V" shaped arms extending from a plate.
  • the elastic portion is constituted by the pair of elastic arms which is able to return to its original shape after deformation.
  • the support portion is advantageously constituted by the ends of said arms, which are intended to bear axially against the ring segment so as to press the latter against the part (downstream or upstream) of the housing which is normal to the axis of rotation.
  • the present invention therefore relates to a turbomachine, for example but not necessarily for a helicopter, comprising a housing, a turbine wheel rotatably mounted about an axis in said housing, a ring concentric with the turbine wheel, said ring being composed of at least a first and a second ring segment, said turbomachine further comprising at least the positioning member described above, the latter being fixed to the casing while exerting an axial thrust on at least one of the segments of rings so as to axially press against a portion of the housing.
  • the positioning member has an attachment portion for attachment to the housing, which fastening portion is located near said portion of the housing to overcome the axial expansion of the ring segments.
  • said portion is a downstream portion of the housing.
  • the positioning member comprises a first arm fixed to the casing, a second elastic arm exerting an axial thrust on the first ring segment and a third elastic arm exerting an axial thrust on the second ring segment, so as to flatten the ring segments axially against a part crankcase.
  • the first and second ring segments are contiguous.
  • the turbomachine according to the invention further comprises at least one wafer covering the junction between the first and second contiguous ring segments, the wafer being held radially against the segments by the positioning member.
  • the positioning member comprises a resilient portion constituted by a tongue having a corrugation, the latter bearing in radial abutment against the plate to hold it radially against the contiguous ends of the first and second ring segments.
  • the corrugation has a radial flexibility to absorb the vibrations of the wafer. Moreover, this radial flexibility makes it possible to hold the wafer radially against the ends of the segments regardless of the differential pressure existing between the vein and the cavities internal to the casing.
  • Another advantage of the positioning member is that it absorbs the vibrations of the segments.
  • the positioning member can also, thanks to the corrugated portions, bear radially on the one hand the ring sector or the sealing tongue, and secondly on the housing part or ring support.
  • the contact on these two parts makes it possible to reduce or even cancel the clearance and radial clearance of the ring sectors, thus ensuring controlled radial positioning of the sectors: this is particularly advantageous as regards the control of the turbine games, and therefore of the performances of it.
  • a positioning member 10 is intended to position a ring segment for a turbine with respect to a casing of the turbomachine in which the turbine is rotatably mounted.
  • the positioning member 10 has the general shape of the letter "E". Indeed, it comprises a plate 12 from which orthogonally extend a first central arm 14 and second and third arms bearing the references 16 and 18, so that said arms constitute the three branches of the "E". Said arms are therefore substantially parallel to each other.
  • each of the arms is in the form of a corrugated tongue.
  • the positioning member 10 has an attachment portion 20 which, in this embodiment, is constituted by a bore 22 formed at the free end 14a of the first arm 14, that is to say say at the opposite end to the plate 12. similarly, the free ends of second and third arms 16,18 are referenced 16a and 18a.
  • This fixing portion 20 is intended to be fixed to the casing 62 of the turbomachine so as to fix the positioning member 10 to the casing of the turbomachine. This aspect will be described below.
  • Each of the first, second and third arms 14, 16 and 18 further comprises an elastic portion 24, 26 and 28 forming a spring.
  • each of these elastic portions 24,26 and 28 is in the form of a wave.
  • each of the arms 14, 16 and 18 has a succession of folds so as to form the corrugation, it being specified that the folding axes are transverse to said arms.
  • corrugations 24, 26, 28 may be deformed in the longitudinal direction of the arms 14,16 and 18 but then tend to resume their original forms.
  • These corrugations 26, 28 of the second and third arms constitute compression springs in that if one tends to bring the free ends of the plate closer together, the undulations thus deformed generate an opposite force, called compression. On the contrary, the corrugation 24 constitutes a tension spring. An interest of this effect will be explained below.
  • the positioning member 10 comprises two support portions 30, 32 constituted by the free ends 16 a, 18 a of the second and third arms 16, 18 .
  • the free ends 16a, 18a are bent to form a kind of hook.
  • the length of the second and third arms 16,18 is slightly larger than that of the first arm 14.
  • the ring of a turbine consists of a plurality of ring segments adjacently arranged side by side.
  • the figure 2 shows first and second ring segments 50, 50 ' end-to-end with their respective ends 50a and 50'a.
  • the geometry of the ring is such that it comprises an axial direction, a radial direction and an azimuthal direction, these three directions being orthogonal to each other.
  • the ring is, as already mentioned, intended to encircle the turbine wheel of the turbomachine.
  • a first interest of the positioning member 10 is to maintain the ends 50a, 50'a in order to prevent rotation of the ring segments 50, 50 ' around the axis of the turbine wheel.
  • each of the ring segments 50, 50 ' carries a rib 52, 52' extending in a transverse direction of the ring segment while projecting radially, so that when the positioning member 10 is mounted, the plate 12 extends in the azimuthal direction of the ring segments 50, 50 ' , while the first and second arms 14, 16 flank the rib 52' of one of the ring segments 50 ' , while the first and third arms 14, 18 of the member 10 flank the rib 52 of the other ring segment 50.
  • each segment 50, 50 ' is held at its two azimuthal ends by two members 10.
  • FIG. 3 details the assembly of the ring segments 50, 50 ' and the positioning member in the casing 62 of the turbomachine 60.
  • the ring segments 50, 50 ' are arranged around the high-pressure turbine wheel so as to cover the blades 64 of said turbine.
  • the arrows F indicate the direction of flow of the flue gases leaving a combustion chamber disposed upstream of the high pressure turbine.
  • the axial ends 50b, 50c of the ring segment 50 have axial swellings 66, 68 for cooperating with projections carried by upstream portions 62a and 62b downstream of the housing 62 so that the ring segment 50 is held radially. in the housing 62.
  • the ring segments 50 are mounted in the housing 62 with a slight axial clearance.
  • the casing 62 and the ring segments 50, 50 ' are arranged in such a way that they delimit an annular passage P for the circulation of a cooling fluid around the ring.
  • Orifices 70 are formed in the housing 62 to allow the supply of this cooling fluid in contact with the ring segments to cool them.
  • the positioning member 10 is fixed to the casing 62 by means of the fixing portion 20 , for example using a screw-nut or pin-type locking member 72.
  • the positioning member 10 When the positioning member 10 is in the mounted position, its arms 14, 16, 18 extend in the axial direction of the turbine wheel, while the plate 12 is housed between the upstream bulge 66 of the ring segment and the housing 62.
  • the point of attachment of the positioning member 10, that is to say here the nut 72 is arranged relative to the downstream projection 62b of the housing 62 so that the corrugations 24, 26, 28 of the member 10 are continuously compressed axially along the longitudinal direction thereof, whereby the free ends 16a and 18a of the second and third arms 16,18 exert on the peripheral edges 51, 51 'of the ring segments 50, 50 ', an axial thrust directed downstream.
  • the ring segments 50, 50 ' are pressed axially against a downstream part of the casing which is constituted here by the above-mentioned downstream projection 62b .
  • cooling fluid circulating in the annular passage also cools the corrugations 30, 32 which can be made to heat up. This makes it possible to control the service life of the corrugations, by optimizing their operating temperature.
  • the positioning member 10 more precisely the corrugation 24 of the first arm 14, allows to keep a wafer 54 radially against the adjacent ends of the first and second ring segments 50,50.
  • This wafer 54 covers the junction 56 defined between the ends 50a and 50'a of the two ring segments so as to improve the seal between the annular passage and the vein in which the blades 64 of the turbine wheel move.
  • the positioning member 10 axially pushes the ring segment at each of its azimuthal ends, which improves the contact between the ring segment 50 and the downstream portion 62b of the casing 62, and therefore the seal.
  • the support positioning at the ends of the segments 50, 50 ' also makes it possible to reduce the risk of jamming of the segments in the grooves of the casing 62.
  • the positioning member 110 is in the form of a single arm 114 constituted by a tongue.
  • the arm or tab 114 has a resilient portion 124 forming a compression spring, this elastic portion being constituted by a corrugation, the latter being made by folding the tab 114 several times .
  • the member 110 has an attachment portion 120 constituted by a tab extending orthogonally with respect to a plane in which the first arm 114 extends.
  • This tab 120 will be made for example by folding the tongue 114.
  • the member 110 has a plate 112 disposed between the tab 120 and the corrugation 124.
  • the tongue 114 has a bearing portion 130 formed by the end of the tab opposite the tab 120, which end is bent.
  • the figure 5 shows the mounting of the positioning member 110 in the turbomachine 60.
  • the positioning member 110 is fixed to the casing 110 by the lug 120. To do this, the latter is radially housed between the ring segment 50 and the casing 62.
  • the tongue 114 extends axially so that the free end 130 of the latter bears against the edge 51 of the ring segment 50.
  • the length of the tongue 114 is chosen so that when the ring segment is positioned axially against the downstream portion 62b of the housing, the corrugation 124 of the member 110 is compressed axially. It follows that the end 130 of the tongue exerts an axial thrust against the peripheral edge 51 of the ring segment 50, following which the latter is axially pressed against the downstream portion 62b of the housing 62, in the species according to contact zone C.
  • the positioning member 110 advantageously maintains the ring segment 50 in axial contact with the downstream part 62b of the casing 62.
  • the corrugation 124 of the member 110 enables the wafer 54 to be held radially against the ends of the ring segments.
  • the positioning member 210 has the general shape of an "E". As such, it comprises a first central arm 214 forming a non-corrugated straight plate intended to cover the junction between the two ends of the segments. ring. In other words, this positioning member advantageously allows to dispense with a wafer such as that described above since the first arm 214 fulfills precisely the role of said wafer.
  • At one end of the first arm 214 is a plate 212 carrying a fixing portion 220 constituted by a tab similar to that of the second embodiment.
  • Platen 212 extends second and third arms 216, 218 similar to those of the first embodiment. That is to say, they respectively carry a first elastic portion 226 and a second elastic portion 228 which form corrugations.
  • free ends 216a, 218b constitute support portions 230,232 similar to those of the first embodiment.
  • the figure 7 shows the positioning member 200 when it is mounted in the housing 60.
  • the tab 220 bears axially on the upstream portion 62a of the housing 62, while the free ends 216a and 218b of the second and third arms abut against the peripheral edge 51 of the ring segment 50 so as to axially press against the downstream edge 62b of the housing 62a.
  • the length of the second and third arms 216, 218 is slightly greater than the distance between the upstream portion 62a of the housing and the edge 51 so that the corrugations 226 and 228 are in compression.
  • this compression of the corrugations generates an axial thrust on the edge 51 of the contiguous ring segments, the downstream of the free ends 216a and 218a so that the ring segments 50, 50 ' are plated. axially against the downstream portion 62b of the casing 62.
  • the positioning member 310 comprises a plate 312 provided with a bore 314 constituting a fixing portion for attachment to the casing 62.
  • a pair of V- shaped arms 318, 320 extends in a bent portion 316 of this plate 312.
  • the positioning member 310 is made of a material having a certain rigidity so that each arm 318, 320 constitutes a portion elastic forming compression spring. Indeed, it is understood that if one tries to spread the arms of one another, they exert a restoring force tending to bring the arms back to their original position, at rest. In other words, the arms 318, 320 act as leaf springs.
  • the positioning member 310 When the positioning member 310 is mounted, as seen on the figure 9 It is fixed to the casing 62 by a nut 322 similar to the first embodiment.
  • Each arm is provided at its end 318a, 320a with a bearing portion in the form of a hook.
  • the ends 318a, 320a of the pairs of arms 318 and 320 are intended to bear against the peripheral edge 51 so as to come to press the ring segments 50 and 50 ' against the downstream portion 62b of the housing 62.
  • the arms 318, 320 are slightly deformed so as to maintain an axial pressure against the ring segment 50.
  • the position of the attachment point, that is to say the nut or pin 322 , or the length of the arms 318,320 are chosen so as to obtain this effect.

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

Description

La présente invention a trait au domaine des turbines de turbomachine, et plus particulièrement celles que l'on trouve dans les turbines à gaz.The present invention relates to the field of turbomachine turbines, and more particularly those found in gas turbines.

La présente invention concerne plus précisément une turbomachine comportant un organe de positionnement d'un segment d'anneau pour une roue de turbine montée rotative autour d'un axe dans un carter.The present invention more specifically relates to a turbomachine comprising a member for positioning a ring segment for a turbine wheel rotatably mounted about an axis in a housing.

Traditionnellement, les roues de turbines de turbomachines, telles les turbines à haute pression de turbine à gaz d'hélicoptères, sont encerclées par un anneau concentrique à la roue de turbine. Cet anneau, en tant qu'élément constitutif du stator de la turbomachine, forme une virole externe pour l'étage de la turbine. Autrement dit, les gaz brûlés qui sortent de la chambre de combustion s'écoulent entre le moyeu de la roue de turbine et l'anneau de manière à entrainer la roue de turbine en rotation.Traditionally, turbomachine turbine wheels, such as helicopter gas turbine high pressure turbines, are encircled by a ring concentric with the turbine wheel. This ring, as a constituent element of the stator of the turbomachine, forms an outer shell for the turbine stage. In other words, the flue gases exiting the combustion chamber flow between the hub of the turbine wheel and the ring so as to drive the turbine wheel in rotation.

Généralement, l'anneau est constitué par une pluralité de segments d'anneau, également appelés secteurs d'anneau, disposés de manière contiguë les uns à côtés des autres.Generally, the ring is constituted by a plurality of ring segments, also called ring sectors, arranged contiguously next to each other.

Ces segments d'anneaux ne sont généralement pas fixés solidairement du carter de la turbomachine car ils sont susceptibles de se dilater axialement et radialement en raison de l'importante chaleur véhiculée par les gaz brûlés.These ring segments are generally not fixed integrally to the casing of the turbomachine because they are likely to expand axially and radially due to the large heat carried by the flue gases.

En fait, les segments d'anneaux sont maintenus dans le carter grâce à un ou plusieurs organes de positionnement.In fact, the ring segments are held in the housing by one or more positioning members.

Par ailleurs, il est habituellement prévu de refroidir les segments d'anneau en faisant circuler un fluide de refroidissement autour de l'anneau, ce fluide de refroidissement pouvant par exemple être prélevé sur l'air comprimé qui est généré par le compresseur de la turbomachine.Furthermore, it is usually intended to cool the ring segments by circulating a cooling fluid around the ring, this cooling fluid can for example be taken from the compressed air that is generated by the compressor of the turbomachine .

Toutefois, un tel montage présente l'inconvénient de créer des zones de fuite et l'on conçoit que les gaz brûlés peuvent pénétrer dans le circuit de refroidissement ou bien à l'inverse, le fluide de refroidissement peut pénétrer dans la veine de gaz disposée en amont ou en aval de la roue de turbine, ce qui pénalise le rendement de la turbomachine, avec une pénalisation plus importante dans le cas de l'éjection à l'aval.However, such an arrangement has the disadvantage of creating leakage zones and it is conceivable that the burnt gases can enter the cooling circuit or conversely, the cooling fluid can enter the gas stream arranged. upstream or downstream of the turbine wheel, which penalizes the efficiency of the turbomachine, with a greater penalty in the case of ejection downstream.

Pour éviter les fuites, le document US 5 988 975 propose une solution qui consiste à réaliser une étanchéité radiale grâce à un anneau qui maintient les segments d'anneau en appui radial contre le carter. Le document WO-A-99 30009 décrit un organe d'étanchéité avec une portion d'appui élastique.To avoid leaks, the document US 5,988,975 proposes a solution which consists in producing a radial seal thanks to a ring which keeps the ring segments in radial support against the casing. The document WO-A-99 30009 discloses a sealing member with an elastic bearing portion.

Un but de la présente invention est de proposer une turbomachine comportant un organe de positionnement alternatif permettant d'assurer l'étanchéité entre une veine de gaz et le circuit de refroidissement.An object of the present invention is to provide a turbomachine comprising an alternating positioning member for sealing between a gas stream and the cooling circuit.

L'invention atteint son but par le fait que l'organe de positionnement présente :

  • une portion de fixation destinée à être fixée au carter ;
  • une portion élastique formant ressort;
  • une portion d'appui reliée à la portion élastique et destinée à venir en appui axialement contre le segment d'anneau, de sorte que, lorsque ledit organe est monté, le segment d'anneau est plaqué axialement contre une partie du carter par l'organe de positionnement.
The invention achieves its goal by the fact that the positioning member has:
  • an attachment portion for attachment to the housing;
  • an elastic portion forming a spring;
  • a bearing portion connected to the elastic portion and intended to abut axially against the ring segment, so that when said member is mounted, the ring segment is axially pressed against a portion of the housing by the positioning member.

Au sens de la présente invention, les termes « axial » et « radial » sont considérés en référence à l'axe et à un rayon de la roue de turbine, tandis que le terme « aval » l'est en référence au sens d'écoulement des gaz brûlés dans la turbine.For the purposes of the present invention, the terms "axial" and "radial" are considered with reference to the axis and a radius of the turbine wheel, while the term "downstream" is referred to in the sense of flue gas flow in the turbine.

Ainsi, dès lors que chaque segment d'anneau est maintenu axialement contre une partie normale à l'axe de rotation (aval ou amont) du carter, grâce à la force axiale exercée par la portion d'appui de l'organe de positionnement, il s'ensuit que l'étanchéité est réalisée entre le circuit de fluide de refroidissement et la veine de gaz.Thus, since each ring segment is held axially against a portion normal to the axis of rotation (downstream or upstream) of the casing, thanks to the axial force exerted by the bearing portion of the positioning member, it follows that the seal is made between the cooling fluid circuit and the gas stream.

En d'autres termes, l'organe de positionnement étant fixé au carter par la portion de fixation, la force axiale générée par la portion élastique est transmise à la portion d'appui puis au segment d'anneau. Ce dernier étant apte, en l'absence de l'organe de positionnement, à se déplacer légèrement axialement par rapport au carter, on conçoit que la portion d'appui pousse le segment d'anneau contre la partie du carter, en conséquence de quoi, il est plaqué contre ladite partie du carter. De préférence, la portion d'appui pousse le segment d'anneau contre la partie aval du carter.In other words, the positioning member being fixed to the housing by the fixing portion, the axial force generated by the elastic portion is transmitted to the bearing portion and the ring segment. The latter being able, in the absence of the positioning member, to move slightly axially relative to the housing, it is conceivable that the bearing portion pushes the ring segment against the part of the housing, as a result of which it is pressed against said housing part. Preferably, the bearing portion pushes the ring segment against the downstream portion of the housing.

Selon une autre variante, la portion de fixation vient également en appui contre le segment d'anneau.According to another variant, the fixing portion also bears against the ring segment.

De préférence, la portion élastique est disposée entre la portion de fixation et la portion d'appui.Preferably, the elastic portion is disposed between the fixing portion and the bearing portion.

De préférence, la partie du carter contre laquelle le segment d'anneau est plaqué est normale à l'axe de rotation de la roue de turbine.Preferably, the portion of the housing against which the ring segment is plated is normal to the axis of rotation of the turbine wheel.

Avantageusement, l'organe de positionnement selon l'invention comporte au moins un premier bras portant la portion de fixation.Advantageously, the positioning member according to the invention comprises at least a first arm carrying the fixing portion.

De préférence, ce premier bras est destiné à s'étendre de préférence axialement.Preferably, this first arm is intended to extend preferably axially.

Selon une première variante, la portion de fixation se présente sous la forme d'une patte s'étendant orthogonalement par rapport à un plan dans lequel s'étend le premier bras.According to a first variant, the attachment portion is in the form of a tab extending orthogonally with respect to a plane in which the first arm extends.

Ainsi, lorsque l'organe de positionnement est monté, la patte s'étend radialement. Elle est notamment destinée à être pincée entre deux parties constitutives du carter.Thus, when the positioning member is mounted, the tab extends radially. It is especially intended to be clamped between two constituent parts of the housing.

Selon une autre variante, la portion de fixation comporte un perçage dont l'axe s'étend orthogonalement par rapport à un plan dans lequel s'étend le premier bras. Dans cette variante, la fixation au carter est réalisée par exemple mais non exclusivement à l'aide d'un système vis-écrou, de sorte que le premier bras de l'organe de positionnement est bloqué axialement par rapport au carter.According to another variant, the fixing portion comprises a bore whose axis extends orthogonally with respect to a plane in which the first arm extends. In this variant, the attachment to the housing is carried out for example but not exclusively by means of a screw-nut system, so that the first arm of the positioning member is locked axially relative to the housing.

Avantageusement, la portion élastique est constituée d'une languette ondulée, cette languette étant par exemple une fine plaque métallique, par exemple une tôle souple, présentant plusieurs pliages successifs. On pourrait toutefois concevoir d'autres types de portion élastique.Advantageously, the elastic portion consists of a corrugated tongue, this tongue being for example a thin metal plate, for example a flexible sheet, having several successive folds. However, other types of elastic portion could be conceived.

Par ailleurs, l'ondulation est préférentiellement disposée entre la portion de fixation et la portion d'appui.Moreover, the corrugation is preferably arranged between the fixing portion and the bearing portion.

Selon un premier mode de réalisation, l'organe de positionnement se présente sous la forme d'une languette dont une première extrémité, constituant la portion de fixation, présente une patte orthogonale, dont la seconde extrémité, constituant la portion d'appui, est recourbée, et dont la partie médiane disposée entre les première et seconde extrémité est ondulée de manière à constituer la portion élastique.According to a first embodiment, the positioning member is in the form of a tongue whose first end, constituting the fixing portion, has an orthogonal tab, whose second end, constituting the bearing portion, is curved, and whose middle portion disposed between the first and second end is corrugated so as to constitute the elastic portion.

Selon un autre mode de réalisation, l'organe de positionnement comporte au moins un premier bras portant la portion de fixation, ainsi qu'au moins un deuxième bras comportant la portion élastique, cette dernière étant de préférence constituée par une ondulation.According to another embodiment, the positioning member comprises at least one first arm carrying the fixing portion, and at least one second arm comprising the elastic portion, the latter being preferably formed by a corrugation.

Selon un aspect avantageux de l'invention, les premier et deuxième bras sont parallèles et s'étendent depuis une platine, la portion de fixation est située à une extrémité du premier bras opposée à la platine, tandis que la portion d'appui se situe à l'extrémité du second bras opposée à la platine.According to an advantageous aspect of the invention, the first and second arms are parallel and extend from a plate, the attachment portion is located at one end of the first arm opposite the plate, while the support portion is located at the end of the second arm opposite the platen.

Un intérêt que la portion de fixation (notamment le point de fixation de l'organe de positionnement au carter) soit proche de la portion d'appui, est qu'on limite les effets de la déformation (sous effet thermique) du carter, des segments ou du système de positionnement entre la portion d'appui et la portion de fixation. Cela limite du reste les efforts appliqués aux segments et par conséquent améliore la tenue des segments d'anneau.An interest that the fastening portion (including the point of attachment of the positioning member to the housing) is close to the bearing portion, is that the effects of the deformation (thermal effect) of the housing, the segments or positioning system between the support portion and the attachment portion. This limits the efforts applied to the segments and consequently improves the holding of the ring segments.

De préférence, l'organe de positionnement comporte en outre un troisième bras similaire au deuxième bras qui s'étend depuis la platine, les bras étant arrangés de telle sorte que le premier bras s'étend entre les deuxième et troisième bras. Ainsi, l'organe de positionnement présente-t-il la forme d'un « E », où les trois branches sont constituées par les premier, second et troisième bras. Plus précisément, ces trois bras s'étendent axialement lorsque l'organe de positionnement est monté avec le segment d'anneau.Preferably, the positioning member further comprises a third arm similar to the second arm which extends from the plate, the arms being arranged so that the first arm extends between the second and third arms. Thus, the positioning member has the shape of an "E", where the three branches are constituted by the first, second and third arm. More specifically, these three arms extend axially when the positioning member is mounted with the ring segment.

Un intérêt de cet organe de positionnement est qu'il permet également de retenir azimutalement deux segments d'anneau consécutifs. Pour ce faire, chacun des segments d'anneau est maintenu selon une direction azimutale entre le premier bras d'un premier organe de positionnement situé à l'une des extrémités du segment et le premier bras d'un second organe de positionnement situé à l'autre extrémité du segment.An advantage of this positioning member is that it also makes it possible to azimuthally retain two consecutive ring segments. To do this, each of the ring segments is held in an azimuthal direction between the first arm of a first positioning member located at one end of the segment and the first arm of a second positioning member located at the end of the segment. other end of the segment.

Par ailleurs, le premier bras comporte en outre, de manière préférentielle, une seconde portion élastique disposée entre la platine et la portion de fixation, grâce à quoi on améliore encore l'élasticité de l'organe de positionnement.Furthermore, the first arm further comprises, preferably, a second elastic portion disposed between the plate and the fixing portion, whereby the elasticity of the positioning member is further improved.

Dans un autre mode de réalisation de l'invention, le premier bras forme une plaquette destinée à couvrir une jonction à interstice définie entre deux segments d'anneau contigus. Dans ce cas, l'une des extrémités de la plaquette porte préférentiellement la patte mentionnée ci-dessus pour permettre la fixation de l'organe de positionnement au carter. Ainsi, la plaquette permet d'améliorer l'étanchéité en recouvrant l'interstice pouvant exister entre les deux bouts de deux segments contigus.In another embodiment of the invention, the first arm forms a wafer for covering a gap junction defined between two contiguous ring segments. In this case, one of the ends of the wafer preferably carries the tab mentioned above to allow the fixing of the positioning member to the housing. Thus, the wafer improves the seal by covering the gap that may exist between the two ends of two contiguous segments.

Selon un autre mode de réalisation, la portion élastique est constituée par une paire de bras en forme de « V » s'étendant depuis une platine. Dans ce cas, la portion élastique est constituée par la paire de bras élastiques qui est apte à reprendre sa forme initiale après déformation.According to another embodiment, the elastic portion is constituted by a pair of "V" shaped arms extending from a plate. In this case, the elastic portion is constituted by the pair of elastic arms which is able to return to its original shape after deformation.

Dans ce mode de réalisation, la portion d'appui est avantageusement constituée par les extrémités desdits bras, qui sont destinées à venir en appui axial contre le segment d'anneau afin de plaquer ce dernier contre la partie (aval ou amont) du carter qui est normale à l'axe de rotation.In this embodiment, the support portion is advantageously constituted by the ends of said arms, which are intended to bear axially against the ring segment so as to press the latter against the part (downstream or upstream) of the housing which is normal to the axis of rotation.

La présente invention concerne donc une turbomachine, par exemple mais non nécessairement pour un hélicoptère, comportant un carter, une roue de turbine montée rotative autour d'un axe dans ledit carter, un anneau concentrique à la roue de turbine, ledit anneau étant composé d'au moins un premier et un deuxième segments d'anneaux, ladite turbomachine comportant en outre au moins l'organe de positionnement décrit ci-dessus, ce dernier étant fixé au carter tout en exerçant une poussée axiale sur au moins l'un des segments d'anneaux de manière à le plaquer axialement contre une partie du carter.The present invention therefore relates to a turbomachine, for example but not necessarily for a helicopter, comprising a housing, a turbine wheel rotatably mounted about an axis in said housing, a ring concentric with the turbine wheel, said ring being composed of at least a first and a second ring segment, said turbomachine further comprising at least the positioning member described above, the latter being fixed to the casing while exerting an axial thrust on at least one of the segments of rings so as to axially press against a portion of the housing.

De manière préférentielle, l'organe de positionnement présente une portion de fixation pour sa fixation au carter, laquelle portion de fixation est située à proximité de ladite partie du carter afin de s'affranchir de la dilatation axiale des segments d'anneau.Preferably, the positioning member has an attachment portion for attachment to the housing, which fastening portion is located near said portion of the housing to overcome the axial expansion of the ring segments.

De préférence, ladite partie est une partie aval du carter.Preferably, said portion is a downstream portion of the housing.

Avantageusement, l'organe de positionnement comporte un premier bras fixé au carter, un deuxième bras élastique exerçant une poussée axiale sur le premier segment d'anneau et un troisième bras élastique exerçant une poussée axiale sur le deuxième segment d'anneau, de manière à plaquer les segments d'anneau axialement contre une partie du carter. De préférence, les premier et deuxième segments d'anneaux sont contigus.Advantageously, the positioning member comprises a first arm fixed to the casing, a second elastic arm exerting an axial thrust on the first ring segment and a third elastic arm exerting an axial thrust on the second ring segment, so as to flatten the ring segments axially against a part crankcase. Preferably, the first and second ring segments are contiguous.

De manière préférentielle, la turbomachine selon l'invention comporte en outre au moins une plaquette recouvrant la jonction entre les premier et deuxième segments d'anneau contigus, la plaquette étant maintenue radialement contre les segments par l'organe de positionnement.Preferably, the turbomachine according to the invention further comprises at least one wafer covering the junction between the first and second contiguous ring segments, the wafer being held radially against the segments by the positioning member.

De préférence, l'organe de positionnement comporte une portion élastique constituée par une languette présentant une ondulation, cette dernière venant en appui radial contre la plaquette pour la maintenir radialement contre les extrémités contigües des premier et deuxième segments d'anneau.Preferably, the positioning member comprises a resilient portion constituted by a tongue having a corrugation, the latter bearing in radial abutment against the plate to hold it radially against the contiguous ends of the first and second ring segments.

De préférence, l'ondulation présente une souplesse radiale afin d'absorber les vibrations de la plaquette. Par ailleurs, cette souplesse radiale permet de maintenir radialement la plaquette contre les extrémités des segments quel que soit le différentiel de pression existant entre la veine et les cavités internes au carter.Preferably, the corrugation has a radial flexibility to absorb the vibrations of the wafer. Moreover, this radial flexibility makes it possible to hold the wafer radially against the ends of the segments regardless of the differential pressure existing between the vein and the cavities internal to the casing.

Un autre avantage de l'organe de positionnement est qu'il permet d'absorber les vibrations des segments.Another advantage of the positioning member is that it absorbs the vibrations of the segments.

L'organe de positionnement peut aussi, grâce aux parties ondulées, venir en appui radial sur, d'une part le secteur d'anneau ou la languette d'étanchéité, et d'autre part sur la partie carter ou support d'anneau. Le contact sur ces deux pièces permet de réduire, voire annuler, le jeu et débattement radial des secteurs d'anneaux, assurant ainsi un positionnement radial contrôlé des secteurs : ceci est particulièrement avantageux quant à la maîtrise des jeux de turbine, et donc des performances de celle-ci.The positioning member can also, thanks to the corrugated portions, bear radially on the one hand the ring sector or the sealing tongue, and secondly on the housing part or ring support. The contact on these two parts makes it possible to reduce or even cancel the clearance and radial clearance of the ring sectors, thus ensuring controlled radial positioning of the sectors: this is particularly advantageous as regards the control of the turbine games, and therefore of the performances of it.

L'invention sera mieux comprise et ses avantages apparaîtront mieux à la lecture de la description qui suit, de modes de réalisation indiqués à titre d'exemples non limitatifs. La description se réfère aux dessins annexés sur lesquels :

  • La figure 1 est une vue en perspective d'un premier mode de réalisation de l'organe de positionnement de la turbomachine selon l'invention ;
  • La figure 2 est une vue en perspective partielle d'un anneau de turbine, montrant deux segments d'anneau maintenus ensemble par un l'organe de positionnement de la figure 1 ;
  • la figure 3 est une vue en coupe axiale partielle d'une turbomachine montrant l'organe de positionnement de la figure 1 lorsqu'il est monté ;
  • la figure 4 est une vue en perspective d'un deuxième mode de réalisation de l'organe de positionnement selon l'invention ;
  • la figure 5 est une vue en coupe axiale partielle d'une turbomachine dans laquelle est monté l'organe de positionnement de la figure 4 ;
  • la figure 6 est une vue en perspective d'un troisième mode de réalisation de l'organe de positionnement de la turbomachine selon l'invention ;
  • la figure 7 est une vue en coupe axiale partielle d'une turbomachine dans laquelle est monté l'organe de positionnement de la figure 6 ;
  • la figure 8 est une vue en perspective d'un quatrième mode de réalisation de l'organe de positionnement de la turbomachine selon l'invention ; et
  • la figure 9 est une vue en coupe axiale partielle d'une turbomachine dans laquelle est monté l'organe de positionnement de la figure 8 .
The invention will be better understood and its advantages will appear better on reading the following description of embodiments given by way of non-limiting examples. The description refers to the accompanying drawings in which:
  • The figure 1 is a perspective view of a first embodiment of the positioning member of the turbomachine according to the invention;
  • The figure 2 is a partial perspective view of a turbine ring, showing two ring segments held together by a positioning member of the figure 1 ;
  • the figure 3 is a view in partial axial section of a turbomachine showing the positioning member of the figure 1 when mounted
  • the figure 4 is a perspective view of a second embodiment of the positioning member according to the invention;
  • the figure 5 is a view in partial axial section of a turbomachine in which is mounted the positioning member of the figure 4 ;
  • the figure 6 is a perspective view of a third embodiment of the positioning member of the turbomachine according to the invention;
  • the figure 7 is a view in partial axial section of a turbomachine in which is mounted the positioning member of the figure 6 ;
  • the figure 8 is a perspective view of a fourth embodiment of the positioning member of the turbomachine according to the invention; and
  • the figure 9 is a view in partial axial section of a turbomachine in which is mounted the positioning member of the figure 8 .

A l'aide de figures 1 à 3 , on va tout d'abord décrire un premier mode de réalisation de l'invention.Using Figures 1 to 3 First of all there will be described a first embodiment of the invention.

Selon l'invention, un organe de positionnement 10 est destiné à positionner un segment d'anneau pour une turbine par rapport à un carter de la turbomachine dans lequel est montée rotative la turbine.According to the invention, a positioning member 10 is intended to position a ring segment for a turbine with respect to a casing of the turbomachine in which the turbine is rotatably mounted.

Comme on le voit sur la figure 1 , l'organe de positionnement 10 présente la forme générale de la lettre « E ». En effet, il comporte une platine 12 d'où s'étendent orthogonalement un premier bras central 14 ainsi que des deuxième et troisième bras portant les références 16 et 18, de sorte que lesdits bras constituent les trois branches du « E ». Lesdits bras sont donc sensiblement parallèles les uns aux autres.As we see on the figure 1 , the positioning member 10 has the general shape of the letter "E". Indeed, it comprises a plate 12 from which orthogonally extend a first central arm 14 and second and third arms bearing the references 16 and 18, so that said arms constitute the three branches of the "E". Said arms are therefore substantially parallel to each other.

Par ailleurs, l'organe de positionnement 10 présente une épaisseur fine par rapport à ses autres dimensions. Plus précisément, chacun des bras se présente sous la forme d'une languette ondulée.Furthermore, the positioning member 10 has a thin thickness relative to its other dimensions. More specifically, each of the arms is in the form of a corrugated tongue.

Conformément à l'invention, l'organe de positionnement 10 présente une portion de fixation 20 qui, dans ce mode de réalisation, est constituée par un perçage 22 réalisé à l'extrémité libre 14a du premier bras 14, c'est-à-dire à l'extrémité opposée à la platine 12. De manière similaire, les extrémités libres des deuxième et troisième bras 16,18 sont référencées 16a et 18a. According to the invention, the positioning member 10 has an attachment portion 20 which, in this embodiment, is constituted by a bore 22 formed at the free end 14a of the first arm 14, that is to say say at the opposite end to the plate 12. similarly, the free ends of second and third arms 16,18 are referenced 16a and 18a.

Cette portion de fixation 20 est destinée à être fixée au carter 62 de la turbomachine de manière à fixer l'organe de positionnement 10 au carter de la turbomachine. Cet aspect sera décrit ci-après.This fixing portion 20 is intended to be fixed to the casing 62 of the turbomachine so as to fix the positioning member 10 to the casing of the turbomachine. This aspect will be described below.

Chacun des premier, deuxième et troisième bras 14, 16 et 18 comporte en outre une portion élastique 24, 26 et 28 formant ressort.Each of the first, second and third arms 14, 16 and 18 further comprises an elastic portion 24, 26 and 28 forming a spring.

Chacune de ces portions élastiques 24,26 et 28 se présente sous la forme d'une ondulation. Autrement dit, chacun des bras 14,16 et 18 présente une succession de pliages de manière à former l'ondulation, étant précisé que les axes de pliage sont transversaux auxdits bras.Each of these elastic portions 24,26 and 28 is in the form of a wave. In other words, each of the arms 14, 16 and 18 has a succession of folds so as to form the corrugation, it being specified that the folding axes are transverse to said arms.

Ces ondulations 24, 26, 28 peuvent être déformées selon la direction longitudinale des bras 14,16 et 18 mais tendent alors à reprendre leurs formes originaires. Ces ondulations 26, 28 des deuxième et troisième bras constituent des ressorts de compression en ce sens que si l'on tend à rapprocher les extrémités libres de la platine, les ondulations ainsi déformées génèrent une force opposée, dite de compression. Au contrario, l'ondulation 24 constitue un ressort de tension. Un intérêt de cet effet sera explicité ci-après.These corrugations 24, 26, 28 may be deformed in the longitudinal direction of the arms 14,16 and 18 but then tend to resume their original forms. These corrugations 26, 28 of the second and third arms constitute compression springs in that if one tends to bring the free ends of the plate closer together, the undulations thus deformed generate an opposite force, called compression. On the contrary, the corrugation 24 constitutes a tension spring. An interest of this effect will be explained below.

Au surplus, l'organe de positionnement 10 comporte deux portions d'appui 30,32 constituées par les extrémités libres 16a, 18a des deuxième et troisième bras 16,18. Comme on le voit sur la figure 1 , les extrémités libres 16a, 18a sont recourbées pour former une sorte de crochet.In addition, the positioning member 10 comprises two support portions 30, 32 constituted by the free ends 16 a, 18 a of the second and third arms 16, 18 . As we see on the figure 1 , the free ends 16a, 18a are bent to form a kind of hook.

Par ailleurs, de préférence, la longueur des deuxième et troisième bras 16,18 est légèrement plus grande que celle du premier bras 14. Furthermore, preferably, the length of the second and third arms 16,18 is slightly larger than that of the first arm 14.

Grâce aux figures 2 et 3 , on va maintenant expliquer le montage de l'organe de positionnement 10. Thanks to figures 2 and 3 , we will now explain the mounting of the positioning member 10.

Classiquement, l'anneau d'une turbine est constitué d'une pluralité de segments d'anneau disposés côte à côte de manière contiguë. La figure 2 montre des premier et deuxième segments d'anneau 50, 50' mis bout à bout par leurs extrémités respectives 50a et 50'a. Conventionally, the ring of a turbine consists of a plurality of ring segments adjacently arranged side by side. The figure 2 shows first and second ring segments 50, 50 ' end-to-end with their respective ends 50a and 50'a.

La géométrie de l'anneau est telle qu'il comporte une direction axiale, une direction radiale et une direction azimutale, ces trois directions étant orthogonales les unes aux autres. L'anneau est, comme on l'a déjà mentionné, destiné à encercler la roue de turbine de la turbomachine.The geometry of the ring is such that it comprises an axial direction, a radial direction and an azimuthal direction, these three directions being orthogonal to each other. The ring is, as already mentioned, intended to encircle the turbine wheel of the turbomachine.

Un premier intérêt de l'organe de positionnement 10 est de maintenir les extrémités 50a,50'a afin d'empêcher la rotation des segments d'anneau 50, 50' autour de l'axe de la roue de turbine. Pour ce faire, chacun des segments d'anneau 50,50' porte une nervure 52,52' s'étendant selon une direction transversale du segment d'anneau tout en faisant saillie radialement, de telle sorte que, lorsque l'organe de positionnement 10 est monté, la platine 12 s'étend selon la direction azimutale des segments d'anneau 50,50', tandis que les premier et deuxième bras 14,16 flanquent la nervure 52' de l'un des segments d'anneau 50', alors que les premier et troisième bras 14,18 de l'organe 10 flanquent la nervure 52 de l'autre segment d'anneau 50. Par suite, on comprend que l'organe de positionnement 10 empêche le déplacement azimutal des extrémités 50a, 50'a de chaque segment d'anneau 50 et 50'. De préférence, chaque segment 50, 50' est tenu à ses deux extrémités azimutales grâce à deux organes 10. A first interest of the positioning member 10 is to maintain the ends 50a, 50'a in order to prevent rotation of the ring segments 50, 50 ' around the axis of the turbine wheel. To do this, each of the ring segments 50, 50 ' carries a rib 52, 52' extending in a transverse direction of the ring segment while projecting radially, so that when the positioning member 10 is mounted, the plate 12 extends in the azimuthal direction of the ring segments 50, 50 ' , while the first and second arms 14, 16 flank the rib 52' of one of the ring segments 50 ' , while the first and third arms 14, 18 of the member 10 flank the rib 52 of the other ring segment 50. As a result, it is understood that the positioning member 10 prevents the azimuth displacement of the ends 50a, 50'a of each ring segment 50 and 50 '. Preferably, each segment 50, 50 ' is held at its two azimuthal ends by two members 10.

Comme on le voit sur la figure 2 , les portions d'appui 30, 32 de l'organe de positionnement 10, c'est-à-dire ici les extrémités libres 16a et 18a des deuxième et troisième bras 16,18 viennent en appui axial contre un bord périphérique 51, 51' des premier et deuxième segments d'anneau 50,50'. Un intérêt de ce montage sera explicité ci-après.As we see on the figure 2 , The bearing portions 30, 32 of the positioning member 10, that here is to say the free ends 16a and 18a of the second and third arms 16,18 come to bear axially against a peripheral edge 51, 51 'first and second ring segments 50,50. An interest of this assembly will be explained below.

Un autre intérêt de la présente invention se comprend mieux à l'aide de la figure 3 qui détaille le montage des segments d'anneau 50, 50' et de l'organe de positionnement dans le carter 62 de la turbomachine 60. Another advantage of the present invention is better understood by means of the figure 3 which details the assembly of the ring segments 50, 50 ' and the positioning member in the casing 62 of the turbomachine 60.

Comme on l'a déjà mentionné ci-dessus, les segments d'anneau 50, 50' sont disposés autour de la roue de turbine haute pression de manière à recouvrir les pales 64 de ladite turbine. Les flèches F indiquent le sens d'écoulement des gaz brûlés sortant d'une chambre de combustion disposée en amont de la turbine haute pression.As already mentioned above, the ring segments 50, 50 ' are arranged around the high-pressure turbine wheel so as to cover the blades 64 of said turbine. The arrows F indicate the direction of flow of the flue gases leaving a combustion chamber disposed upstream of the high pressure turbine.

Comme on le comprend à l'aide de la figure 3 , les extrémités axiales 50b, 50c du segment d'anneau 50 présentent des renflements axiaux 66,68 destinés à coopérer avec des saillies portées par des parties amont 62a et aval 62b du carter 62 de sorte que le segment d'anneau 50 soit maintenu radialement dans le carter 62. Toutefois, les segments d'anneau 50 sont montés dans le carter 62 avec un léger jeu axial.As can be understood by using the figure 3 , the axial ends 50b, 50c of the ring segment 50 have axial swellings 66, 68 for cooperating with projections carried by upstream portions 62a and 62b downstream of the housing 62 so that the ring segment 50 is held radially. in the housing 62. However, the ring segments 50 are mounted in the housing 62 with a slight axial clearance.

Par ailleurs, on voit que le carter 62 et les segments d'anneau 50, 50' sont arrangés de telle sorte qu'ils délimitent un passage annulaire P pour la circulation d'un fluide de refroidissement autour de l'anneau. Des orifices 70 sont ménagés dans le carter 62 pour permettre l'amenée de ce fluide de refroidissement au contact des segments d'anneau afin de refroidir ces derniers.Furthermore, it can be seen that the casing 62 and the ring segments 50, 50 ' are arranged in such a way that they delimit an annular passage P for the circulation of a cooling fluid around the ring. Orifices 70 are formed in the housing 62 to allow the supply of this cooling fluid in contact with the ring segments to cool them.

Conformément à l'invention, l'organe de positionnement 10 est fixé au carter 62 par le biais de la portion de fixation 20 en utilisant par exemple un organe de verrouillage de type vis-écrou ou pion 72. According to the invention, the positioning member 10 is fixed to the casing 62 by means of the fixing portion 20 , for example using a screw-nut or pin-type locking member 72.

Lorsque l'organe de positionnement 10 est en position montée, ses bras 14, 16, 18 s'étendent selon la direction axiale de la roue de turbine, tandis que la platine 12 est logée entre le renflement amont 66 du segment d'anneau et le carter 62. When the positioning member 10 is in the mounted position, its arms 14, 16, 18 extend in the axial direction of the turbine wheel, while the plate 12 is housed between the upstream bulge 66 of the ring segment and the housing 62.

Qui plus est, le point de fixation de l'organe de positionnement 10, c'est-à-dire ici l'écrou 72 est disposé par rapport à la saillie aval 62b du carter 62 de telle sorte que les ondulations 24, 26, 28 de l'organe 10 sont continuellement comprimées axialement selon leur direction longitudinale, en conséquence de quoi les extrémités libres 16a et 18a des deuxième et troisième bras 16,18 exercent sur les bords périphérique 51, 51' des segments d'anneau 50, 50', une poussée axiale dirigée vers l'aval. Il en résulte que les segments d'anneau 50, 50' sont plaqués axialement contre une partie aval du carter qui est constituée ici par la saillie aval 62b précitée. Le contact entre les segments d'anneau 50, 50' et la partie aval du carter 62b, qui a lieu selon une zone de contact portant la référence C, permet de réaliser l'étanchéité entre le passage annulaire P et une veine aval V, grâce à quoi le fluide de refroidissement circulant dans le passage annulaire ne peut pas s'écouler dans cette veine aval V. Moreover, the point of attachment of the positioning member 10, that is to say here the nut 72 is arranged relative to the downstream projection 62b of the housing 62 so that the corrugations 24, 26, 28 of the member 10 are continuously compressed axially along the longitudinal direction thereof, whereby the free ends 16a and 18a of the second and third arms 16,18 exert on the peripheral edges 51, 51 'of the ring segments 50, 50 ', an axial thrust directed downstream. As a result, the ring segments 50, 50 ' are pressed axially against a downstream part of the casing which is constituted here by the above-mentioned downstream projection 62b . The contact between the ring segments 50, 50 ' and the downstream part of the casing 62b, which takes place along a contact zone with the reference C, makes it possible to seal between the annular passage P and a downstream duct V, whereby the cooling fluid circulating in the annular passage can not flow into this downstream vein V.

Un autre avantage est que le fluide de refroidissement circulant dans le passage annulaire vient également refroidir les ondulations 30, 32 qui peuvent être amenées à s'échauffer. Ceci permet de piloter la durée de vie des ondulations, en optimisant leur température de fonctionnement.Another advantage is that the cooling fluid circulating in the annular passage also cools the corrugations 30, 32 which can be made to heat up. This makes it possible to control the service life of the corrugations, by optimizing their operating temperature.

Enfin, sur cette figure 3 , on voit que l'organe de positionnement 10, et plus précisément l'ondulation 24 du premier bras 14, permet de maintenir radialement une plaquette 54 contre les extrémités contiguës des premier et deuxième segments d'anneau 50,50'. Cette plaquette 54 recouvre la jonction 56 définie entre les extrémités 50a et 50'a des deux segments d'anneau de manière à améliorer l'étanchéité entre le passage annulaire et la veine dans laquelle se déplacent les pales 64 de la roue de turbine.Finally, on this figure 3 It is seen that the positioning member 10, more precisely the corrugation 24 of the first arm 14, allows to keep a wafer 54 radially against the adjacent ends of the first and second ring segments 50,50. This wafer 54 covers the junction 56 defined between the ends 50a and 50'a of the two ring segments so as to improve the seal between the annular passage and the vein in which the blades 64 of the turbine wheel move.

Un autre avantage de l'organe de positionnement 10 est qu'il pousse axialement le segment d'anneau à chacune de ses extrémités azimutales, ce qui améliore le contact entre le segment d'anneau 50 et la partie aval 62b du carter 62, et donc l'étanchéité. Le positionnement d'appui aux extrémités des segments 50, 50' permet aussi de réduire les risques de grippage des segments dans les gorges du carter 62. Another advantage of the positioning member 10 is that it axially pushes the ring segment at each of its azimuthal ends, which improves the contact between the ring segment 50 and the downstream portion 62b of the casing 62, and therefore the seal. The support positioning at the ends of the segments 50, 50 ' also makes it possible to reduce the risk of jamming of the segments in the grooves of the casing 62.

A l'aide des figures 4 et 5 , on va maintenant décrire un deuxième mode de réalisation d'un organe de positionnement 110 conforme à la présente invention. Dans ce mode de réalisation, les éléments identiques à ceux du premier mode de réalisation portent les mêmes références numériques augmentées de la valeur cent.With the help of Figures 4 and 5 , Will now be described a second embodiment of a positioning device 110 according to the present invention. In this embodiment, the elements identical to those of the first embodiment bear the same numerical references increased by the value cent.

L'organe de positionnement 110 se présente sous la forme d'un bras unique 114 constitué par une languette. A l'instar du premier mode de réalisation, le bras ou languette 114 présente une portion élastique 124 formant ressort de compression, cette portion élastique étant constituée par une ondulation, cette dernière étant réalisée en pliant plusieurs fois la languette 114. The positioning member 110 is in the form of a single arm 114 constituted by a tongue. Like the first embodiment, the arm or tab 114 has a resilient portion 124 forming a compression spring, this elastic portion being constituted by a corrugation, the latter being made by folding the tab 114 several times .

De plus, l'organe 110 présente une portion de fixation 120 constituée par une patte s'étendant orthogonalement par rapport à un plan dans lequel s'étend le premier bras 114. Cette patte 120 sera par exemple réalisée par pliage de la languette 114. In addition, the member 110 has an attachment portion 120 constituted by a tab extending orthogonally with respect to a plane in which the first arm 114 extends. This tab 120 will be made for example by folding the tongue 114.

Pour être cohérent avec le premier mode de réalisation, on peut définir que l'organe 110 présente une platine 112 disposée entre la patte 120 et l'ondulation 124. To be consistent with the first embodiment, it can be defined that the member 110 has a plate 112 disposed between the tab 120 and the corrugation 124.

Enfin, la languette 114 comporte une portion d'appui 130 constituée par l'extrémité de la languette opposée à la patte 120, laquelle extrémité est recourbée.Finally, the tongue 114 has a bearing portion 130 formed by the end of the tab opposite the tab 120, which end is bent.

La figure 5 montre le montage de l'organe de positionnement 110 dans la turbomachine 60. The figure 5 shows the mounting of the positioning member 110 in the turbomachine 60.

L'organe de positionnement 110 est fixé au carter 110 par la patte 120. Pour ce faire, cette dernière est radialement logée entre le segment d'anneau 50 et le carter 62. The positioning member 110 is fixed to the casing 110 by the lug 120. To do this, the latter is radially housed between the ring segment 50 and the casing 62.

La languette 114 s'étend axialement de sorte que l'extrémité libre 130 de cette dernière vienne en appui contre le bord 51 du segment d'anneau 50. The tongue 114 extends axially so that the free end 130 of the latter bears against the edge 51 of the ring segment 50.

Par ailleurs, la longueur de la languette 114 est choisie de sorte que lorsque le segment d'anneau est positionné axialement contre la partie aval 62b du carter, l'ondulation 124 de l'organe 110 est comprimée axialement. Il s'ensuit que l'extrémité 130 de la languette exerce une poussée axiale contre le bord périphérique 51 du segment d'anneau 50, à la suite de quoi ce dernier est plaqué axialement contre la partie aval 62b du carter 62, en l'espèce selon la zone de contact C. Furthermore, the length of the tongue 114 is chosen so that when the ring segment is positioned axially against the downstream portion 62b of the housing, the corrugation 124 of the member 110 is compressed axially. It follows that the end 130 of the tongue exerts an axial thrust against the peripheral edge 51 of the ring segment 50, following which the latter is axially pressed against the downstream portion 62b of the housing 62, in the species according to contact zone C.

On comprend donc que l'organe de positionnement 110 maintient avantageusement le segment d'anneau 50 en contact axial avec la partie aval 62b du carter 62. It is therefore understood that the positioning member 110 advantageously maintains the ring segment 50 in axial contact with the downstream part 62b of the casing 62.

De surcroît, l'ondulation 124 de l'organe 110 permet de maintenir radialement la plaquette 54 contre les extrémités des segments d'anneau.In addition, the corrugation 124 of the member 110 enables the wafer 54 to be held radially against the ends of the ring segments.

A l'aide des figures 6 et 7 , on va décrire un troisième mode de réalisation de l'invention.With the help of Figures 6 and 7 Will be described a third embodiment of the invention.

Dans ce mode de réalisation, les éléments identiques à ceux du premier mode de réalisation portent les mêmes références numériques augmentées de la valeur deux cents.In this embodiment, the elements identical to those of the first embodiment carry the same numerical references increased by the value two hundred.

L'organe de positionnement 210 selon le troisième mode de réalisation présente la forme générale d'un « E ». A ce titre, il comporte un premier bras central 214 formant une plaquette droite non ondulée destinée à recouvrir la jonction entre les deux extrémités des segments d'anneau. Autrement dit, cet organe de positionnement permet avantageusement de se dispenser d'une plaquette telle que celle décrite précédemment puisque le premier bras 214 remplit précisément le rôle de ladite plaquette.The positioning member 210 according to the third embodiment has the general shape of an "E". As such, it comprises a first central arm 214 forming a non-corrugated straight plate intended to cover the junction between the two ends of the segments. ring. In other words, this positioning member advantageously allows to dispense with a wafer such as that described above since the first arm 214 fulfills precisely the role of said wafer.

A l'une des extrémités du premier bras 214 se trouve une platine 212 portant une portion de fixation 220 constituée par une patte similaire à celle du deuxième mode de réalisation.At one end of the first arm 214 is a plate 212 carrying a fixing portion 220 constituted by a tab similar to that of the second embodiment.

De la platine 212 s'étendent des deuxième et troisième bras 216, 218 similaires à ceux du premier mode de réalisation. C'est-à-dire qu'ils portent respectivement une première portion élastique 226 et une seconde portion élastique 228 qui forment des ondulations.Platen 212 extends second and third arms 216, 218 similar to those of the first embodiment. That is to say, they respectively carry a first elastic portion 226 and a second elastic portion 228 which form corrugations.

Par ailleurs, les extrémités libres 216a, 218b constituent des portions d'appui 230,232 similaires à celles du premier mode de réalisation.Furthermore, the free ends 216a, 218b constitute support portions 230,232 similar to those of the first embodiment.

La figure 7 montre l'organe de positionnement 200 lorsqu'il est monté dans le carter 60. La patte 220 prend appui axialement sur la partie amont 62a du carter 62, tandis que les extrémités libres 216a et 218b des deuxième et troisième bras viennent en appui contre le bord périphérique 51 du segment d'anneau 50 de manière à le plaquer axialement contre le bord aval 62b du carter 62a. Pour ce faire, la longueur des deuxième et troisième bras 216, 218 est légèrement plus grande que la distance entre la partie amont 62a du carter et le bord 51 de sorte que les ondulations 226 et 228 sont en compression. Comme dans le premier mode de réalisation, cette compression des ondulations génère une poussée axiale sur le bord 51 des segments d'anneau contigus, l'aval des extrémités libres 216a et 218a de sorte que les segments d'anneau 50, 50' sont plaqués axialement contre la partie aval 62b du carter 62. The figure 7 shows the positioning member 200 when it is mounted in the housing 60. The tab 220 bears axially on the upstream portion 62a of the housing 62, while the free ends 216a and 218b of the second and third arms abut against the peripheral edge 51 of the ring segment 50 so as to axially press against the downstream edge 62b of the housing 62a. To do this, the length of the second and third arms 216, 218 is slightly greater than the distance between the upstream portion 62a of the housing and the edge 51 so that the corrugations 226 and 228 are in compression. As in the first embodiment, this compression of the corrugations generates an axial thrust on the edge 51 of the contiguous ring segments, the downstream of the free ends 216a and 218a so that the ring segments 50, 50 ' are plated. axially against the downstream portion 62b of the casing 62.

A l'aide des figures 8 et 9 , on va maintenant décrire un quatrième mode de réalisation de l'invention. L'organe de positionnement 310 comporte une platine 312 pourvue d'un perçage 314 constituant une portion de fixation pour la fixation au carter 62. With the help of Figures 8 and 9 , Will be described a fourth embodiment of the invention. The positioning member 310 comprises a plate 312 provided with a bore 314 constituting a fixing portion for attachment to the casing 62.

Une paire de bras 318, 320 en forme de « V » s'étend dans une portion recourbée 316 de cette platine 312. L'organe de positionnement 310 est réalisé dans un matériau présentant une certaine rigidité de sorte que chaque bras 318, 320 constitue une portion élastique formant ressort de compression. En effet, on comprend que si l'on tente d'écarter les bras l'un de l'autre, ils exercent une force de rappel tendant à ramener les bras dans leur position d'origine, au repos. Autrement dit, les bras 318, 320 agissent comme des lames-ressorts.A pair of V- shaped arms 318, 320 extends in a bent portion 316 of this plate 312. The positioning member 310 is made of a material having a certain rigidity so that each arm 318, 320 constitutes a portion elastic forming compression spring. Indeed, it is understood that if one tries to spread the arms of one another, they exert a restoring force tending to bring the arms back to their original position, at rest. In other words, the arms 318, 320 act as leaf springs.

Lorsque l'organe de positionnement 310 est monté, comme on le voit sur la figure 9 , il est fixé au carter 62 par un écrou 322 similaire à celui du premier mode de réalisation.When the positioning member 310 is mounted, as seen on the figure 9 It is fixed to the casing 62 by a nut 322 similar to the first embodiment.

Chaque bras est muni à son extrémité 318a, 320a d'une portion d'appui présentant la forme d'un crochet.Each arm is provided at its end 318a, 320a with a bearing portion in the form of a hook.

Dans ce mode de réalisation, les extrémités 318a, 320a des paires de bras 318 et 320 sont destinées à venir en appui contre le bord périphérique 51 de manière à venir plaquer les segments d'anneau 50 et 50' contre la partie aval 62b du carter 62. Dans cette position, les bras 318, 320 sont légèrement déformés de manière à maintenir une pression axiale contre le segment d'anneau 50. La position du point de fixation, c'est-à-dire de l'écrou ou pion 322, ou la longueur des bras 318,320 sont choisies de manière à obtenir cet effet.In this embodiment, the ends 318a, 320a of the pairs of arms 318 and 320 are intended to bear against the peripheral edge 51 so as to come to press the ring segments 50 and 50 ' against the downstream portion 62b of the housing 62. In this position, the arms 318, 320 are slightly deformed so as to maintain an axial pressure against the ring segment 50. The position of the attachment point, that is to say the nut or pin 322 , or the length of the arms 318,320 are chosen so as to obtain this effect.

Claims (14)

  1. A turbomachine comprising a casing (62), a turbine wheel rotatably mounted about an axis within said casing, a ring mounted concentrically around the turbine wheel, said ring being made up of at least first (50) and second (50') ring segments, said turbomachine further comprising at least one positioning member (10, 110, 210, 310) presenting:
    · a fastener portion (20, 120, 220, 314) fastened to the casing (62);
    · a resilient portion (24, 26, 28, 124, 226, 228, 318, 320) forming a spring; and
    · a bearing portion (30, 32, 130, 230, 232, 318a, 320a) connected to the resilient portion and bearing axially against the ring segment, said positioning member being fastened to the casing while exerting axial thrust on at least one of the ring segments in such a manner as to press it axially against a portion of the casing.
  2. A turbomachine according to claim 1, characterized in that the positioning member includes at least a first arm (14, 114, 214, 312) carrying the fastener portion (20, 120, 220, 314).
  3. A turbomachine according to claim 2, characterized in that the fastener portion (320) is in the form of a tab extending orthogonally relative to a plane in which the first arm extends.
  4. A turbomachine according to claim 2, characterized in that the fastener portion (20, 314) comprises a hole, the axis of which extending orthogonally relative to a plane in which the first arm (14, 312) extends.
  5. A turbomachine according to any one of claims 1 to 4, characterized in that the resilient portion (24, 26, 28, 124, 226, 228) is constituted by a corrugated tongue.
  6. A turbomachine according to any one of claims 1 to 5, characterized in that the positioning member comprises at least a first arm (14, 214) carrying the fastener portion, together with at least a second arm (16, 216) including the resilient portion.
  7. A turbomachine according to claim 6, characterized in that the first arm (14, 214) and second arm (16, 216) are parallel and extend from a plate (12, 212), and in that the fastener portion (20, 220) is situated at one end of the first arm remote from the plate, while the bearing portion is situated at the end of the second arm that is remote from the plate.
  8. A turbomachine according to claim 6 or claim 7, characterized in that the positioning member further includes a third arm (18, 218) similar to the second arm (16, 216) extending from the plate (12, 212), the first arm extending between the second and third arms.
  9. A turbomachine according to any one of claims 6 to 8, characterized in that the first arm (14) further includes a second resilient portion (24) disposed between the plate (12) and the fastener portion (20).
  10. A turbomachine according to any one of claims 6 to 8, characterized in that the first arm (214) forms a plate for covering a junction between two contiguous ring segments (50, 50').
  11. A turbomachine according to any one of claims 1 to 4, characterized in that the resilient portion (318, 320) is constituted by a pair of arms in a V-shape extending from a plate (312).
  12. A turbomachine according to claim 11, characterized in that the bearing portion is constituted by the ends (318a, 320a) of said arms.
  13. A turbomachine according to claim 1, characterized in that the positioning member includes a portion (20, 120, 220, 314) fastened to the casing, a resilient second arm (16, 216, 318) exerting axial thrust on the first ring segment (50), and a resilient third arm (18, 218, 310) exerting axial thrust on the second ring segment (50'), thereby pressing the ring segment (50, 50') axially against a portion (62b) of the casing (62).
  14. A turbomachine according to any one of claims 1 to 13, characterized in that it further includes at least one plate (54, 214) covering the junction between the first and second ring segments (50, 50'), said plate being held radially against the ring segments by the positioning member (10, 110, 210).
EP09795477.0A 2008-11-21 2009-11-20 Positioning device for a ring segment Active EP2368017B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09795477T PL2368017T3 (en) 2008-11-21 2009-11-20 Positioning device for a ring segment

Applications Claiming Priority (2)

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FR0857904A FR2938873B1 (en) 2008-11-21 2008-11-21 POSITIONING DEVICE FOR RING SEGMENT
PCT/FR2009/052235 WO2010058137A1 (en) 2008-11-21 2009-11-20 Positioning member for ring segment

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EP2368017A1 EP2368017A1 (en) 2011-09-28
EP2368017B1 true EP2368017B1 (en) 2013-05-29

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US (1) US9051846B2 (en)
EP (1) EP2368017B1 (en)
JP (1) JP5628190B2 (en)
KR (1) KR101723366B1 (en)
CN (1) CN102224323B (en)
CA (1) CA2744413C (en)
ES (1) ES2423794T3 (en)
FR (1) FR2938873B1 (en)
PL (1) PL2368017T3 (en)
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WO (1) WO2010058137A1 (en)

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Also Published As

Publication number Publication date
EP2368017A1 (en) 2011-09-28
US9051846B2 (en) 2015-06-09
CN102224323A (en) 2011-10-19
US20110236203A1 (en) 2011-09-29
CN102224323B (en) 2014-12-10
PL2368017T3 (en) 2013-09-30
FR2938873A1 (en) 2010-05-28
KR101723366B1 (en) 2017-04-05
ES2423794T3 (en) 2013-09-24
FR2938873B1 (en) 2014-06-27
RU2516992C2 (en) 2014-05-27
CA2744413A1 (en) 2010-05-27
WO2010058137A1 (en) 2010-05-27
JP5628190B2 (en) 2014-11-19
JP2012509435A (en) 2012-04-19
KR20110084994A (en) 2011-07-26
RU2011125322A (en) 2012-12-27
CA2744413C (en) 2016-05-24

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