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EP3341570B1 - Device for attaching manifolds for cooling the casing of a turbine-engine turbine by air jets - Google Patents

Device for attaching manifolds for cooling the casing of a turbine-engine turbine by air jets Download PDF

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Publication number
EP3341570B1
EP3341570B1 EP16770056.6A EP16770056A EP3341570B1 EP 3341570 B1 EP3341570 B1 EP 3341570B1 EP 16770056 A EP16770056 A EP 16770056A EP 3341570 B1 EP3341570 B1 EP 3341570B1
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EP
European Patent Office
Prior art keywords
support
manifolds
cooling
support element
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
EP16770056.6A
Other languages
German (de)
French (fr)
Other versions
EP3341570A1 (en
Inventor
Jacques Marcel Arthur Bunel
Emeric D'HERBIGNY
Alain Paul Madec
Pierre TINCELIN
Benjamin VILLENAVE
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Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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Publication date
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Publication of EP3341570A1 publication Critical patent/EP3341570A1/en
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Publication of EP3341570B1 publication Critical patent/EP3341570B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
    • 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
    • F05D2240/90—Mounting on supporting structures or systems
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the invention lies in the field of cooling a turbine casing, in particular a low pressure turbine, a turbomachine.
  • the present invention more specifically relates to a device for fixing air jet cooling ramps of the casing of a turbine of a turbomachine.
  • the invention also relates to a turbomachine equipped with such a device.
  • the low-pressure turbine of a turbomachine is protected by a housing C generally flared, substantially frustoconical. This housing is cooled using impact cooling technology.
  • the casing C is equipped with one or more box (es) B of pressurized air supply, connected to several cooling ramps R.
  • the housing C is equipped with two housings B, positioned at about 180 ° from each other (only one being visible on the figure 2 ).
  • Each box B is equipped with five ramps R, with two tubes T by ramps, each tube extending about 90 °.
  • the tubes T are pierced with a series of small openings opening to the right of the outer surface of the housing. The pressurized air passing through these orifices ensures impact ventilation of the casing C.
  • the air gap E between an air outlet orifice formed in a tube T and the outer surface of the casing C (or “housing skin” PC) is of the order of 5 to 6 mm.
  • the metal casing C tends to expand radially but especially longitudinally.
  • the upstream flanges BAM and downstream BAV remain colder and do not expand in the same way as the skin of the PC casing. It follows that cooling ramps R tend to approach or even touch the skin of the PC housing in places.
  • the air gap E cold is important, it is insufficient hot.
  • the ramp must be located very close to the skin of the PC housing and therefore keep a constant air gap E.
  • the positioning of the hot ramp is not correct, and the ramp may be either too far or too close (or even in contact) with the housing skin during operation of the turbines. It is therefore necessary to find a fixing means to maintain a constant air gap regardless of the temperature.
  • the invention therefore aims to solve the aforementioned drawbacks of the state of the art.
  • the invention particularly aims to provide a device for fixing air jet cooling ramps of the casing of a turbomachine turbine, which avoids the air gap variations between said ramps and the outer wall of the housing, and this, even hot, that is to say during the use of the turbine.
  • the invention relates to a device for fixing air jet cooling ramps of the casing of a turbine, preferably a low-pressure turbine, a turbomachine comprising a support for said ramps, shaped to maintain said ramps spaced between they and several support elements of said ramp support, each support element being fixed to said housing and connected to said ramp support by connecting means.
  • the device comprises N cooling ramps and N-1 support elements, each support element being disposed between two contiguous cooling ramps.
  • the gap between the ramps and the outer wall of the housing remains constant, even during hot use.
  • the integral support elements of the ramp support are disposed between two adjacent cooling ramps, and retain them at a constant distance from the skin of the housing.
  • these support elements being attached to the housing, they are subject to the same temperature changes as the housing and expand according to the deformations thereof.
  • the invention also relates to a turbomachine which comprises a device for fixing said cooling ramps as mentioned above.
  • cooling ramps 1 on the casing 2 of a turbine, preferably a low pressure turbine, a turbomachine.
  • the cooling ramps 1 and the casing 2 have the same shapes and structures as those described previously in connection with the Figures 1 and 2 for the state of the art.
  • the cooling ramps 1 are formed of tubes of cross section, preferably circular and have a curved shape in a circular arc, matching the outer shape of the housing 2.
  • the latter has a flared shape and comprises a surface 21, an upstream end 22 and a downstream end 23.
  • the fixing device bears the general reference 3. It comprises a support 4 of said ramps 1 and several elements 5 for supporting said support 4.
  • This support 4 comprises two blades, respectively called inner blade 41 and outer blade 42.
  • the inner blade 41 is intended to be disposed near the outer surface 21 of the housing, it comprises a series of parallel grooves 411, perpendicular to the blade and separated from each other by an intermediate flat area 412.
  • Each groove 411 is shaped to surround at least a portion of the circumference of one of said ramps 1.
  • the inner radius of the groove 411 substantially corresponds to the outer radius of a cooling ramp 1.
  • each groove surrounds half of the circumference of a ramp.
  • the outer blade 42 intended to be disposed outside the ramps 1, also has a series of parallel grooves 421 spaced apart from each other by a flat zone 422 (see FIG. figure 1 ).
  • the inner blade 41 and the inner blade 42 are assembled on either side of the cooling ramps 1, so that their respective grooves 411, 412 are opposite one another and surround said ramps, as can be seen in FIG. see him on the figures 6 and 7 .
  • the support 4 of ramps thus makes it possible to keep the ramps 1 spaced apart from each other, in the axial direction of the casing 2.
  • the support element 5 has the shape of a bridge as can be seen on the figure 3 .
  • Each bridge comprises two ends 51 and a projecting central portion 52.
  • the ends 51 are fixed to the casing 2, more precisely on the outer surface 21 thereof (also known as the "skin of the casing"), more precisely still on the portion of the outer surface 21 that extends between the upstream ends 22 and downstream 23.
  • This fixing is carried out by any appropriate means, for example by welding, brazing, bonding, riveting or bolting.
  • Each support element 5 is connected to the support 4, that is to say to the two blades 41 and 42 by so-called “fixed” 6 or “mobile” connecting means 6 '.
  • the central portion 52 of the bridge is pierced with a circular orifice 53.
  • the assembly of the various elements constituting the fixing device 3 is carried out as follows.
  • the various support elements 5 are fixed on the housing 2.
  • the inner blade 41 is then fixed on these support elements 5, so that its planar zones 412 are positioned facing the projecting central flat part 52 of the bridge 5 (see figure 4 ).
  • the outer blade 42 is positioned on the ramps 1, so that the grooves 421 enclose the ramps 1 and that the flat areas 422 are positioned opposite the planar zones 412 of the inner blade 41.
  • the support elements 5 are N-1 and are arranged between the two cooling ramps 1 of each pair of ramps.
  • At least one additional support element 5 may be further provided at at least one of the two ends of the ramp support 4.
  • the connecting means 6 are said to be “fixed” in that they do not allow any relative displacement between the ramp support 4 and a support element 5. This solution is represented in FIG. figure 8 and in the lower left corner of Figures 4 to 7 .
  • the two blades 41 and 42 and the bridge 5 are assembled by means of a screw 7 passing through said orifices 53, 413 and 423 and a nut 8 screwed onto the screw.
  • the screw 7 being circular and the orifices 413 and 423 also and of the same diameter, there is no possibility of relative movement of the blades of the support 4 relative to the elements 5 of this support.
  • the connecting means 6 ' are said to be “mobile” in that they allow relative movement between the ramp support blades 41, 42 and a support element 5.
  • the orifices arranged in the blades 41 and 42 are oblong and are respectively referenced 413 'and 423'.
  • the assembly is carried out with a stepped pin 7 'and a washer 8'.
  • the blades 41 and 42 can slide axially relative to the stepped pin 7 ', so that the blades 41 and 42 can follow the expansion movement of the housing 2, including its axial expansion movement.
  • the fixed connection means 6 are used near the upstream end of the casing and the mobile connection means 6 'in the center and near the downstream end of the casing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

DOMAINE TECHNIQUE GENERALGENERAL TECHNICAL FIELD

L'invention se situe dans le domaine du refroidissement d'un carter de turbine, notamment une turbine basse pression, d'une turbomachine.The invention lies in the field of cooling a turbine casing, in particular a low pressure turbine, a turbomachine.

La présente invention concerne plus précisément un dispositif de fixation des rampes de refroidissement par jets d'air du carter d'une turbine d'une turbomachine.The present invention more specifically relates to a device for fixing air jet cooling ramps of the casing of a turbine of a turbomachine.

L'invention concerne également une turbomachine équipée d'un tel dispositif.The invention also relates to a turbomachine equipped with such a device.

ETAT DE L'ARTSTATE OF THE ART

Comme on peut le voir sur les figures 1 et 2 jointes, qui représentent l'état de la technique, la turbine basse pression d'une turbomachine est protégée par un carter C de forme générale évasée, sensiblement tronconique. Ce carter est refroidi en utilisant la technologie du refroidissement par impact.As can be seen on the Figures 1 and 2 Attached, which represent the state of the art, the low-pressure turbine of a turbomachine is protected by a housing C generally flared, substantially frustoconical. This housing is cooled using impact cooling technology.

Le carter C est équipé d'un ou plusieurs boitier(s) B d'alimentation en air sous pression, raccordé à plusieurs rampes de refroidissement R.The casing C is equipped with one or more box (es) B of pressurized air supply, connected to several cooling ramps R.

Dans l'exemple de réalisation représenté sur les figures, le carter C est équipé de deux boitiers B, positionnés à environ 180° l'un de l'autre, (un seul étant visible sur la figure 2). Chaque boitier B est équipé de cinq rampes R, avec deux tubes T par rampes, chaque tube s'étendant sur environ 90°. Les tubes T sont percés d'une série de petits orifices débouchant au droit de la surface extérieure du carter. L'air sous pression transitant au travers de ces orifices assure une ventilation par impact du carter C.In the embodiment shown in the figures, the housing C is equipped with two housings B, positioned at about 180 ° from each other (only one being visible on the figure 2 ). Each box B is equipped with five ramps R, with two tubes T by ramps, each tube extending about 90 °. The tubes T are pierced with a series of small openings opening to the right of the outer surface of the housing. The pressurized air passing through these orifices ensures impact ventilation of the casing C.

Sur la figure 1, on peut voir que les supports S des rampes R de refroidissement sont fixés au carter par une bride amont BAM et par une bride aval BAV. Bien que cela ne soit pas représenté, les boitiers B sont fixés sur le carter de la même façon.On the figure 1 it can be seen that the supports S of the cooling ramps R are fixed to the casing by an upstream flange BAM and a downstream flange BAV. Although not shown, the boxes B are fixed on the housing in the same way.

A froid, c'est-à-dire lorsque les turbines sont à l'arrêt, l'entrefer E entre un orifice de sortie d'air ménagé dans un tube T et la surface extérieure du carter C (ou « peau du carter » PC) est de l'ordre de 5 à 6 mm.In cold, that is to say when the turbines are stopped, the air gap E between an air outlet orifice formed in a tube T and the outer surface of the casing C (or "housing skin" PC) is of the order of 5 to 6 mm.

A chaud, c'est-à-dire pendant le fonctionnement des turbines, le carter métallique C tend à se dilater radialement mais surtout longitudinalement. Or, les brides amont BAM et aval BAV restent plus froides et ne se dilatent pas de la même façon que la peau du carter PC. Il s'en suit que les rampes R de refroidissement ont tendance à se rapprocher, voire même à toucher par endroits la peau du carter PC. Bien que l'entrefer E à froid soit important, il s'avère insuffisant à chaud.At hot, that is to say during operation of the turbines, the metal casing C tends to expand radially but especially longitudinally. However, the upstream flanges BAM and downstream BAV remain colder and do not expand in the same way as the skin of the PC casing. It follows that cooling ramps R tend to approach or even touch the skin of the PC housing in places. Although the air gap E cold is important, it is insufficient hot.

Il est difficile d'anticiper la dilatation de la peau du carter PC par rapport aux brides amont et aval. En effet, pour que le refroidissement par impact de jets d'air soit efficace, la rampe doit être située très près de la peau du carter PC et donc garder un entrefer E constant. Le positionnement de la rampe à chaud n'est donc pas correct, et la rampe risque d'être soit trop loin soit trop proche (ou même en contact) avec la peau du carter, lors du fonctionnement des turbines. Il est par conséquent nécessaire de trouver un moyen de fixation permettant de conserver un entrefer constant quelle que soit la température.It is difficult to anticipate the expansion of the skin of the PC casing with respect to the upstream and downstream flanges. Indeed, for air jet impact cooling to be effective, the ramp must be located very close to the skin of the PC housing and therefore keep a constant air gap E. The positioning of the hot ramp is not correct, and the ramp may be either too far or too close (or even in contact) with the housing skin during operation of the turbines. It is therefore necessary to find a fixing means to maintain a constant air gap regardless of the temperature.

On connaît déjà d'après le document US 2014/0030066 un dispositif de refroidissement par jets d'air de la paroi d'un carter de turbine à gaz. Ce dispositif comprend plusieurs rampes de refroidissement montées sur un distributeur d'air qui les maintient espacées entre-elles. Ce distributeur d'air est lui-même raccordé au carter mais par des brides 300, 302 fixées sur les extrémités du carter, de sorte que les rampes situées dans sa partie médiane risquent de se retrouver plus proche du carter en cas de dilatation de celui-ci.We already know from the document US 2014/0030066 an air jet cooling device for the wall of a gas turbine casing. This device comprises several cooling ramps mounted on an air distributor which holds them spaced apart. This air distributor is itself connected to the housing but by flanges 300, 302 fixed on the ends of the housing, so that the ramps in its middle portion may be closer to the housing in case of expansion of that -this.

PRESENTATION DE L'INVENTIONPRESENTATION OF THE INVENTION

L'invention a pour donc but de résoudre les inconvénients précités de l'état de la technique.The invention therefore aims to solve the aforementioned drawbacks of the state of the art.

L'invention a notamment pour objectif de fournir un dispositif de fixation des rampes de refroidissement par jets d'air du carter d'une turbine d'une turbomachine, qui évite les variations d'entrefer entre lesdites rampes et la paroi extérieure du carter, et ce, même à chaud, c'est-à-dire pendant l'utilisation de la turbine.The invention particularly aims to provide a device for fixing air jet cooling ramps of the casing of a turbomachine turbine, which avoids the air gap variations between said ramps and the outer wall of the housing, and this, even hot, that is to say during the use of the turbine.

A cet effet, l'invention concerne un dispositif de fixation des rampes de refroidissement par jets d'air du carter d'une turbine, de préférence basse pression, d'une turbomachine comprenant un support desdites rampes, conformé pour maintenir lesdites rampes espacées entre elles et plusieurs éléments de soutien dudit support de rampes, chaque élément de soutien étant fixé audit carter et lié audit support de rampes par des moyens de liaison.To this end, the invention relates to a device for fixing air jet cooling ramps of the casing of a turbine, preferably a low-pressure turbine, a turbomachine comprising a support for said ramps, shaped to maintain said ramps spaced between they and several support elements of said ramp support, each support element being fixed to said housing and connected to said ramp support by connecting means.

Conformément à l'invention, le dispositif comprend N rampes de refroidissement et N-1 éléments de soutien, chaque élément de soutien étant disposé entre deux rampes de refroidissement contigües.According to the invention, the device comprises N cooling ramps and N-1 support elements, each support element being disposed between two contiguous cooling ramps.

Grâce à ces caractéristiques de l'invention, l'entrefer entre les rampes et la paroi extérieure du carter reste constant, et ce, même pendant l'utilisation à chaud. En effet, les éléments de soutien solidaires du support de rampe sont disposés entre deux rampes de refroidissement contiguës, et retiennent celles-ci à distance constante de la peau du carter. En outre, ces éléments de soutien étant fixés au carter, ils sont soumis aux mêmes variations de température que le carter et se dilatent en suivant les déformations de celui-ci.Thanks to these features of the invention, the gap between the ramps and the outer wall of the housing remains constant, even during hot use. Indeed, the integral support elements of the ramp support are disposed between two adjacent cooling ramps, and retain them at a constant distance from the skin of the housing. In addition, these support elements being attached to the housing, they are subject to the same temperature changes as the housing and expand according to the deformations thereof.

L'entrefer étant maintenu constant, le refroidissement du carter de turbine est amélioré et la durée de vie de celui-ci est accrue.As the gap is kept constant, the cooling of the turbine casing is improved and the service life of the latter is increased.

Selon d'autres caractéristiques avantageuses et non limitatives de l'invention, prises seules ou en combinaison :

  • ledit support des rampes comprend deux lames dites « lame intérieure » et lame extérieure dont chacune comprend une série de gorges parallèles, séparées par une zone plane, chaque gorge étant conformée pour entourer une partie de la circonférence de l'une desdites rampes, de préférence la moitié, la lame intérieure et la lame extérieure étant assemblées de part et d'autres des rampes de refroidissement, de façon que leurs gorges respectives soient en face l'une de l'autre et entourent lesdites rampes ;
  • au moins certains des moyens de liaison sont des moyens dits "fixes", qui n'autorisent pas de déplacement relatif entre ledit support de rampes et un élément de soutien ;
  • au moins certains des moyens de liaison sont des moyens dits "mobiles", qui autorisent un déplacement relatif entre ledit support de rampes et un élément de soutien ;
  • l'élément de soutien est percé d'un orifice circulaire, les zones planes des lames du support de rampes sont percées d'un orifice circulaire et l'élément de soutien et les deux lames sont assemblés par une vis traversant les deux orifices circulaires et coopérant avec un écrou, les orifices circulaires, la vis et l'écrou constituant lesdits moyens de liaison fixe ;
  • l'élément de soutien est percé d'un orifice circulaire, les zones planes des lames du support de rampes sont percées d'un orifice oblong et l'élément de soutien et les deux lames sont assemblés par un pion épaulé traversant l'orifice circulaire et les deux orifices oblongs et coopérant avec une rondelle, l'assemblage étant fait de façon à autoriser le coulissement axial desdites lames par rapport au pion épaulé au niveau des orifices oblongs de façon à réaliser une liaison mobile ;
  • l'élément de soutien est un pontet, fixé à ses deux extrémités au carter et dont la partie centrale en saillie est liée audit support de rampes.
According to other advantageous and nonlimiting features of the invention, taken alone or in combination:
  • said support of the ramps comprises two blades called "inner blade" and outer blade each of which comprises a series of parallel grooves, separated by a flat area, each groove being shaped to surround part of the circumference of one of said ramps, preferably half, the inner blade and the outer blade being assembled on both sides of the cooling ramps, so that their respective grooves face each other and surround said ramps;
  • at least some of the connecting means are so-called "fixed" means, which do not allow relative movement between said ramp support and a support element;
  • at least some of the connecting means are so-called "mobile" means, which allow relative movement between said ramp support and a support element;
  • the support element is pierced with a circular orifice, the flat areas of the blades of the ramp support are pierced with a circular orifice and the support element and the two blades are assembled by a screw passing through the two circular orifices and cooperating with a nut, the circular orifices, the screw and the nut constituting said fixed connection means;
  • the support element is pierced with a circular orifice, the flat areas of the ramp support blades are pierced with an oblong orifice and the support element and the two blades are assembled by a stepped pin passing through the circular orifice. and the two orifices oblong and cooperating with a washer, the assembly being made so as to allow axial sliding of said blades relative to the stepped pin at the oblong orifices so as to achieve a movable connection;
  • the support element is a bridge, fixed at both ends to the housing and whose projecting central portion is connected to said ramp support.

L'invention concerne également une turbomachine qui comprend un dispositif de fixation desdites rampes de refroidissement tel que précité.The invention also relates to a turbomachine which comprises a device for fixing said cooling ramps as mentioned above.

PRESENTATION DES FIGURESPRESENTATION OF FIGURES

D'autres caractéristiques et avantages de l'invention apparaîtront de la description qui va maintenant en être faite, en référence aux dessins annexés, qui en représentent, à titre indicatif mais non limitatif, deux modes de réalisation possible.Other features and advantages of the invention will appear from the description which will now be made, with reference to the accompanying drawings, which represent, by way of indication but not limitation, two possible embodiments.

Sur ces dessins :

  • la figure 1 est une vue en perspective d'une partie d'un carter d'une turbine d'une turbomachine, équipé de rampes de refroidissement selon l'état de la technique,
  • la figure 2 est une vue en perspective d'un boitier d'alimentation en air et des rampes de refroidissement selon l'état de la technique,
  • les figures 3 à 6 sont des vues en perspective représentant deux modes de réalisation des différents éléments constitutifs du dispositif de fixation des rampes de refroidissement conforme à l'invention,
  • la figure 7 est une vue en coupe transversale du dispositif conforme à l'invention représentant deux modes de réalisation,
  • les figures 8 et 9 sont des vues de détail des zones référencées VIII et IX sur la figure 7.
On these drawings:
  • the figure 1 is a perspective view of a portion of a casing of a turbomachine turbine, equipped with cooling ramps according to the state of the art,
  • the figure 2 is a perspective view of an air supply box and cooling ramps according to the state of the art,
  • the Figures 3 to 6 are perspective views showing two embodiments of the different elements constituting the device for fixing the cooling ramps according to the invention,
  • the figure 7 is a cross-sectional view of the device according to the invention showing two embodiments,
  • the Figures 8 and 9 are detailed views of the zones referenced VIII and IX on the figure 7 .

DESCRIPTION DETAILLEEDETAILED DESCRIPTION

Le dispositif de fixation des rampes de refroidissement conforme à l'invention va maintenant être décrit en liaison avec les figures 3 à 7.The device for fixing the cooling ramps according to the invention will now be described in connection with the Figures 3 to 7 .

Il permet la fixation de rampes de refroidissement 1, sur le carter 2 d'une turbine, de préférence une turbine basse pression, d'une turbomachine. Les rampes de refroidissement 1 et le carter 2 présentent les mêmes formes et structures que celles décrites précédemment en liaison avec les figures 1 et 2 pour l'état de la technique.It allows the attachment of cooling ramps 1, on the casing 2 of a turbine, preferably a low pressure turbine, a turbomachine. The cooling ramps 1 and the casing 2 have the same shapes and structures as those described previously in connection with the Figures 1 and 2 for the state of the art.

En d'autres termes, les rampes de refroidissement 1 sont formées de tubes de section transversale, de préférence circulaire et présentent une forme incurvée en arc de cercle, épousant la forme extérieure du carter 2. Ce dernier présente une forme évasée et comprend une surface extérieure 21, une extrémité amont 22 et une extrémité aval 23.In other words, the cooling ramps 1 are formed of tubes of cross section, preferably circular and have a curved shape in a circular arc, matching the outer shape of the housing 2. The latter has a flared shape and comprises a surface 21, an upstream end 22 and a downstream end 23.

Le dispositif de fixation porte la référence générale 3. Il comprend un support 4 desdites rampes 1 et plusieurs éléments 5 de soutien dudit support 4.The fixing device bears the general reference 3. It comprises a support 4 of said ramps 1 and several elements 5 for supporting said support 4.

Un mode de réalisation possible du support 4 de rampes va maintenant être décrit.A possible embodiment of the support 4 of ramps will now be described.

Ce support 4 comprend deux lames, dites respectivement lame intérieure 41 et lame extérieure 42.This support 4 comprises two blades, respectively called inner blade 41 and outer blade 42.

Comme cela apparaît mieux sur la figure 4, la lame intérieure 41 est destinée à être disposée à proximité de la surface extérieure 21 du carter, elle comprend une série de gorges parallèles 411, perpendiculaires à la lame et séparées les unes des autres par une zone plane intermédiaire 412.As it appears better on the figure 4 , the inner blade 41 is intended to be disposed near the outer surface 21 of the housing, it comprises a series of parallel grooves 411, perpendicular to the blade and separated from each other by an intermediate flat area 412.

Chaque gorge 411 est conformée pour entourer au moins une partie de la circonférence de l'une desdites rampes 1. En d'autres termes, dans le cas où le tube d'une rampe de refroidissement est de section circulaire, le rayon intérieur de la gorge 411 correspond sensiblement au rayon extérieur d'une rampe de refroidissement 1. De préférence, chaque gorge entoure la moitié de la circonférence d'une rampe.Each groove 411 is shaped to surround at least a portion of the circumference of one of said ramps 1. In other words, in the case where the tube of a cooling ramp is of circular section, the inner radius of the groove 411 substantially corresponds to the outer radius of a cooling ramp 1. Preferably, each groove surrounds half of the circumference of a ramp.

De façon similaire, la lame extérieure 42, destinée à être disposée à l'extérieur des rampes 1, présente également une série de gorges parallèles 421, espacées entre-elles d'une zone plane 422, (voir figure 1).Similarly, the outer blade 42, intended to be disposed outside the ramps 1, also has a series of parallel grooves 421 spaced apart from each other by a flat zone 422 (see FIG. figure 1 ).

La lame intérieure 41 et la lame intérieure 42 sont assemblées de part et d'autre des rampes de refroidissement 1, de façon que leurs gorges respectives 411, 412 soient en regard l'une de l'autre et entourent lesdites rampes, comme on peut le voir sur les figures 6 et 7.The inner blade 41 and the inner blade 42 are assembled on either side of the cooling ramps 1, so that their respective grooves 411, 412 are opposite one another and surround said ramps, as can be seen in FIG. see him on the figures 6 and 7 .

Le support 4 de rampes permet ainsi de maintenir les rampes 1 espacées entre-elles, selon la direction axiale du carter 2.The support 4 of ramps thus makes it possible to keep the ramps 1 spaced apart from each other, in the axial direction of the casing 2.

Selon un mode de réalisation possible, l'élément de soutien 5 présente la forme d'un pontet comme on peut le voir sur la figure 3. Chaque pontet comprend deux extrémités 51 et une partie centrale en saillie 52.According to a possible embodiment, the support element 5 has the shape of a bridge as can be seen on the figure 3 . Each bridge comprises two ends 51 and a projecting central portion 52.

Les extrémités 51 sont fixées au carter 2, plus précisément sur la surface extérieure 21 de celui-ci (également connue sous le terme de « peau du carter »), plus précisément encore sur la portion de la surface extérieure 21 qui s'étend entre les extrémités amont 22 et aval 23. Cette fixation est réalisée par tout moyen approprié, par exemple par soudage, brasage, collage, rivetage ou boulonnage.The ends 51 are fixed to the casing 2, more precisely on the outer surface 21 thereof (also known as the "skin of the casing"), more precisely still on the portion of the outer surface 21 that extends between the upstream ends 22 and downstream 23. This fixing is carried out by any appropriate means, for example by welding, brazing, bonding, riveting or bolting.

Ces éléments de soutien 5 suivent donc la déformation du carter 2 due à la dilatation de celui-ci, tant sur le plan radial que sur le plan axial.These support elements 5 thus follow the deformation of the casing 2 due to the expansion thereof, both radially and axially.

Ceci n'était pas le cas dans l'état de la technique décrit dans le document US 2014/0030066 où le distributeur d'air qui soutient les rampes de refroidissement est fixé par des brides, elles-mêmes fixées à leur tour aux deux extrémités du carter donc dans une région où la dilatation est moindre que dans la partie centrale du carter.This was not the case in the state of the art described in the document US 2014/0030066 where the air distributor supporting the cooling ramps is fixed by flanges, themselves fixed in turn at both ends of the housing so in a region where the expansion is less than in the central part of the housing.

Chaque élément de soutien 5 est lié au support 4, c'est-à-dire aux deux lames 41 et 42 par des moyens de liaison dits « fixes » 6 ou « mobiles » 6'.Each support element 5 is connected to the support 4, that is to say to the two blades 41 and 42 by so-called "fixed" 6 or "mobile" connecting means 6 '.

La partie centrale 52 du pontet est percée d'un orifice circulaire 53.The central portion 52 of the bridge is pierced with a circular orifice 53.

L'assemblage des différents éléments constituant le dispositif de fixation 3 est réalisé comme suit.The assembly of the various elements constituting the fixing device 3 is carried out as follows.

Comme représenté sur la figure 3, les différents éléments de soutien 5 sont fixés sur le carter 2. La lame intérieure 41 est ensuite fixée sur ces éléments de soutien 5, de façon que ses zones planes 412 soient positionnées en regard de la partie centrale plane en saillie 52 du pontet 5 (voir figure 4).As shown on the figure 3 , the various support elements 5 are fixed on the housing 2. The inner blade 41 is then fixed on these support elements 5, so that its planar zones 412 are positioned facing the projecting central flat part 52 of the bridge 5 (see figure 4 ).

Ensuite, et comme représenté sur la figure 5, les rampes 1 sont disposées dans les gorges 411.Then, and as shown on the figure 5 the ramps 1 are arranged in the grooves 411.

Enfin, comme on peut le voir sur la figure 6, la lame extérieure 42 est positionnée sur les rampes 1, de façon que les gorges 421 enserrent les rampes 1 et que les zones planes 422 soient positionnées en regard des zones planes 412 de la lame intérieure 41.Finally, as we can see on the figure 6 , the outer blade 42 is positioned on the ramps 1, so that the grooves 421 enclose the ramps 1 and that the flat areas 422 are positioned opposite the planar zones 412 of the inner blade 41.

Conformément à l'invention, et comme représenté par exemple sur la figure 4, si les rampes de refroidissement 1 sont au nombre de N, alors les éléments de soutien 5 conformes à l'invention sont au nombre de N-1 et sont disposés entre les deux rampes de refroidissement 1 de chaque paire de rampes.According to the invention, and as represented for example on the figure 4 , if the cooling ramps 1 are N, then the support elements 5 according to the invention are N-1 and are arranged between the two cooling ramps 1 of each pair of ramps.

Ainsi, l'entrefer entre chaque rampe de refroidissement 1 et la surface extérieure du carter 2 est maintenu constant.Thus, the air gap between each cooling ramp 1 and the outer surface of the casing 2 is kept constant.

Au moins un élément de soutien 5 additionnel peut en outre être prévu au moins à l'une des deux extrémités du support de rampe 4.At least one additional support element 5 may be further provided at at least one of the two ends of the ramp support 4.

Les moyens de liaison 6 sont dits « fixes », en ce sens qu'ils n'autorisent aucun déplacement relatif entre le support de rampes 4 et un élément de soutien 5. Cette solution est représentée en figure 8 et dans le coin inférieur gauche des figures 4 à 7.The connecting means 6 are said to be "fixed" in that they do not allow any relative displacement between the ramp support 4 and a support element 5. This solution is represented in FIG. figure 8 and in the lower left corner of Figures 4 to 7 .

Dans ce cas, les zones planes 412, 422 des lames 41, respectivement 42, sont percées d'un orifice circulaire 413, respectivement 423.In this case, the flat areas 412, 422 of the blades 41, respectively 42, are pierced with a circular hole 413, respectively 423.

Les deux lames 41 et 42 et le pontet 5 sont assemblés à l'aide d'une vis 7 traversant lesdits orifices 53, 413 et 423 et d'un écrou 8 vissé sur la vis. La vis 7 étant circulaire et les orifices 413 et 423 également et de même diamètre, il n'existe aucune possibilité de mouvement relatif des lames du support 4 par rapport aux éléments 5 de ce support.The two blades 41 and 42 and the bridge 5 are assembled by means of a screw 7 passing through said orifices 53, 413 and 423 and a nut 8 screwed onto the screw. The screw 7 being circular and the orifices 413 and 423 also and of the same diameter, there is no possibility of relative movement of the blades of the support 4 relative to the elements 5 of this support.

Toutefois, cette liaison fixe permet aux éléments de soutien 5 de suivre le mouvement de dilatation radiale du carter.However, this fixed connection allows the support elements 5 to follow the radial expansion movement of the housing.

Les moyens de liaison 6' sont dits « mobiles », en ce sens qu'ils autorisent un déplacement relatif entre les lames 41, 42 de support de rampes 4 et un élément de soutien 5. Dans ce cas, et comme représenté sur les parties centrales et supérieures droites des figures 4 à 7 et sur la figure 9, les orifices aménagés dans les lames 41 et 42 sont oblongs et sont référencées respectivement 413' et 423'.The connecting means 6 'are said to be "mobile" in that they allow relative movement between the ramp support blades 41, 42 and a support element 5. In this case, and as shown on the parts central and superior right of Figures 4 to 7 and on the figure 9 , the orifices arranged in the blades 41 and 42 are oblong and are respectively referenced 413 'and 423'.

Le montage s'effectue avec un pion épaulé 7' et une rondelle 8'. Toutefois dans ce cas, les lames 41 et 42 peuvent coulisser axialement par rapport au pion épaulé 7', de sorte que les lames 41 et 42 peuvent suivre le mouvement de dilatation du carter 2, notamment son mouvement de dilatation axiale.The assembly is carried out with a stepped pin 7 'and a washer 8'. However in this case, the blades 41 and 42 can slide axially relative to the stepped pin 7 ', so that the blades 41 and 42 can follow the expansion movement of the housing 2, including its axial expansion movement.

On notera que, de préférence, on utilise les moyens de liaison fixes 6 à proximité de l'extrémité amont de carter et les moyens de liaison mobiles 6' au centre et à proximité de l'extrémité aval du carter.It should be noted that, preferably, the fixed connection means 6 are used near the upstream end of the casing and the mobile connection means 6 'in the center and near the downstream end of the casing.

Toutefois, il est possible d'utiliser exclusivement l'un ou l'autre desdits moyens de liaison.However, it is possible to use exclusively one or the other of said connecting means.

Claims (8)

  1. A device (3) for attaching manifolds (1) for cooling by air jets the casing (2) of a turbine, preferably a low-pressure turbine, of a turbine engine, comprising a support (4) of said manifolds, shaped to hold said manifolds spaced from one another and several support elements (5) of said manifold support (4), each support element (5) being attached to said casing (2) and connected to said manifold support (4) by connecting means (6, 6'), characterized in that it comprises N cooling manifolds (1) and N-1 support elements (5), each support element (5) being disposed between two contiguous cooling manifolds.
  2. The device according to claim 1, characterized in that said manifold support (4) comprises two blades so-called "interior blade" (41) and "exterior blade" (42), each one of which comprises a series of parallel grooves (411, 421), separated by a planar area (412, 422), each groove (411, 421) being shaped to surround a portion of the circumference of one of said manifolds (1), preferably half, the interior blade (41) and the exterior blade (42) being assembled on either side of the cooling manifolds (1), so that their respective grooves (411, 421) are facing one another and surround said manifolds.
  3. The device according to claim 1 or 2, characterized in that at least some of the connecting means (6) are so-called "fixed" means (53, 413, 423, 7, 8), which do not allow relative movement between said manifold support (4) and a support element (5).
  4. The device according to claim 1 or 2, characterized in that at least some of the connecting means (6') are so-called "moving" means (53, 413', 423', 7, 8), which allow relative movement between said manifold support (4) and a support element (5).
  5. The device according to claims 2 and 3, characterized in that the support element (5) is pierced with a circular opening (53), in that the planar areas (412, 422) of the blades (41, 42) of the manifold support are pierced with a circular opening (413, 423) and in that the support element (5) and the two blades (41, 42) are assembled by a screw (7) passing through the two circular openings and cooperating with a nut (8), the circular openings, the screw and the nut constituting said fixed connecting means (6).
  6. The device according to claims 2 and 4, characterized in that the support element (5) is pierced with a circular opening (53), in that the planar areas (412, 422) of the blades (41, 42) of the manifold support are pierced with an oblong opening (413', 423') and in that the support element (5) and the two blades (41, 42) are assembled by a shoulder pin (7') passing through the circular opening and the two oblong openings and cooperating with a washer (8'), the assembly being accomplished so as to allow the axial sliding of said blades (41, 42) with respect to the shoulder pin at the oblong openings so as to accomplish a moving connection (6').
  7. The device according to one of the preceding claims, characterized in that the support element (5) is a saddle, attached at its two ends (51) to the casing (2) and the protruding central portion (52) whereof is connected to said manifold support (4).
  8. A turbine engine comprising a turbine, particularly a low-pressure turbine, surrounded by a casing (2), equipped with cooling manifolds using air jets (1), characterized in that it comprises a device (3) for attaching said cooling manifolds (1) according to any one of said preceding claims.
EP16770056.6A 2015-08-27 2016-08-25 Device for attaching manifolds for cooling the casing of a turbine-engine turbine by air jets Active EP3341570B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1557978A FR3040429B1 (en) 2015-08-27 2015-08-27 DEVICE FOR FASTENING AIR COOLED COOLING RAMPS OF A TURBOMACHINE TURBINE
PCT/FR2016/052120 WO2017032952A1 (en) 2015-08-27 2016-08-25 Device for attaching manifolds for cooling the casing of a turbine-engine turbine by air jets

Publications (2)

Publication Number Publication Date
EP3341570A1 EP3341570A1 (en) 2018-07-04
EP3341570B1 true EP3341570B1 (en) 2019-05-01

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US (1) US10619511B2 (en)
EP (1) EP3341570B1 (en)
CN (1) CN107923259B (en)
FR (1) FR3040429B1 (en)
WO (1) WO2017032952A1 (en)

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FR3077097B1 (en) 2018-01-22 2020-08-07 Safran Aircraft Engines COOLING DEVICE FOR A TURBINE OF A TURBOMACHINE
FR3082872B1 (en) * 2018-06-25 2021-06-04 Safran Aircraft Engines TURBOMACHINE CASE COOLING SYSTEM
FR3085719B1 (en) * 2018-09-06 2021-04-16 Safran Aircraft Engines PRESSURIZED AIR SUPPLY BOX OF AN AIR JET COOLING DEVICE
FR3089560B1 (en) * 2018-12-06 2021-01-22 Safran Aircraft Engines Device for maintaining a cooling tube for a turbomachine casing
FR3093129B1 (en) 2019-02-25 2021-01-29 Safran Aircraft Engines Device for holding at least one cooling tube to a turbomachine casing and its mounting method
FR3099800B1 (en) * 2019-08-09 2021-07-09 Safran Aircraft Engines Device for attaching an air supply unit to a cooling device for a turbomachine casing
FR3099798B1 (en) * 2019-08-09 2021-12-03 Safran Aircraft Engines Set for a turbomachine turbine
FR3114346B1 (en) * 2020-09-24 2022-10-28 Safran Aircraft Engines Turbojet turbine casing equipped with cooling tube mounting bracket

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US20180216488A1 (en) 2018-08-02
CN107923259A (en) 2018-04-17
FR3040429B1 (en) 2019-06-07
FR3040429A1 (en) 2017-03-03
WO2017032952A1 (en) 2017-03-02
US10619511B2 (en) 2020-04-14
CN107923259B (en) 2020-09-29
EP3341570A1 (en) 2018-07-04

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