EP0824048A1 - Method of making a hollow blade for a turbomachine having a release material after welding - Google Patents

Method of making a hollow blade for a turbomachine having a release material after welding Download PDF

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Publication number
EP0824048A1
EP0824048A1 EP97401926A EP97401926A EP0824048A1 EP 0824048 A1 EP0824048 A1 EP 0824048A1 EP 97401926 A EP97401926 A EP 97401926A EP 97401926 A EP97401926 A EP 97401926A EP 0824048 A1 EP0824048 A1 EP 0824048A1
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EP
European Patent Office
Prior art keywords
blade
diffusion
gas
parts
dawn
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.)
Granted
Application number
EP97401926A
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German (de)
French (fr)
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EP0824048B1 (en
Inventor
Gilles Michel Georges Louis Calle
Gilles Charles Klein
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/021—Deforming sheet bodies
    • B21D26/027—Means for controlling fluid parameters, e.g. pressure or temperature
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/053—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure characterised by the material of the blanks
    • B21D26/055—Blanks having super-plastic properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D53/00—Making other particular articles
    • B21D53/78—Making other particular articles propeller blades; turbine blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage

Definitions

  • the present invention relates to a manufacturing process of a turbomachine hollow blade assembled by diffusion-welding and formed under gas pressure by forming superplastic. It also relates to a device used in a step of said method comprising an operation of cold separation of components of the blade.
  • FR N ° 95.11300 also provides before starting inflation at step (f) above to detach the parts cold primers, taking into account the state of compaction of diffusion barriers previously deposited.
  • This operation is indeed necessary to ensure in step (f) the correct inflation cycle and superplastic forming ensuring regular supply with neutral gas through cavities delimited by the welds and coated with anti-diffusion barrier coating.
  • This takeoff operation of the dawn parts between the welded areas alone can control deformation rates from the start of the forming cycle to step (f) avoiding provoking during the inflation of overpressures due to local sticking of a part of dawn on the other which would cause inflation excessive unwanted and risk of rupture.
  • the method of manufacturing a hollow turbomachine blade comprising the steps recalled above comprises a step additional detachment of the areas of the blade parts coated with an anti-diffusion barrier coating during which, in accordance with the invention, a conduit gas supply is formed in a dawn area where inter-cavity communication holes are provided in the intermediate sheet of dawn by means of controlled injections gas under pressure while providing localized heating from said dawn area.
  • said operation hot forming of a gas supply pipe and separation of the areas of the blade parts coated with a anti-diffusion barrier coating is carried out either on a flat blade assembly welded by diffusion, or on a blade assembly welded by diffusion and shaped by twisting / bending, either during the setting operation twist shape of the welded blade assembly.
  • the device according to the invention used during said hot forming operation of a supply pipe in gas and delamination of the areas of the coated blade parts of a coating forming an anti-diffusion barrier comprises jaws fitted with heating elements and having a surface to the shapes of the imprint of the duct to be produced, a mobile table containing the gas supply system, the temperature and pressure regulation equipment and a workpiece support fitted with sensors capable of detecting micro-displacements.
  • a hollow 1 blade of turbomachine including a large-rope fan blade intended for example for a turbofan is consisting of a lower surface skin 2, an upper surface skin 3 and a central plate 4, intended to form the stiffeners from dawn.
  • a manufacturing process known per se in its principle at least one of the surfaces facing the parts constituting the dawn receives a coating deposit forming an anti-diffusion barrier, according to a predefined pattern then a metallurgical bond in the unpaved areas of the anti-diffusion product is then obtained by welding-diffusion thanks to an isostatic pressurization.
  • the manufacturing process according to the invention involves a remarkable peeling operation 2, 3 and sheet 4 between the welded areas.
  • the blade 1 is disposed on a support carried by a movable table 96, as shown in Figure 3.
  • channels supply tube 17 and 18 connect the blade 1 on the one hand to a reservoir 92 supplied by a distribution source of neutral gas 91, pressure sensors 93 and 94 being placed on either side of the reservoir 92 as well as of the valves 98 and 99 and on the other hand to a trigger volume 100 preceded also of a valve 101 and of a pressure sensor 102.
  • a specific area 90 of dawn 1 in which the central sheet 4 has holes 5 which connect the cavities formed between the zones welded from dawn 1 is arranged between jaws of tooling 97 comprising heating elements 103. temperature sensors 104 are further connected to said dawn area 1.
  • the operation consists of heating in the area where the material constituting the blade is plastic said zone 90 of dawn 1. As soon as the temperature is reached, injections high pressure gas are sent by the way supply 17. Under gas pressure the skin becomes gradually deforms from one cavity to another to form a persistent duct 90 between supply lines 17-18 subsequently allowing a balanced gas distribution in each of the cavities.
  • the tank 92 of defined capacity was filled from neutral gas distribution source 91 until you get the working pressure.
  • the sensors pressure 93-94 provide information on the conditions of operation. As soon as the set pressure is reached upstream of the tank, the supply is cut off, allowing discharge to tube 17. Then the gas seeps into dawn 1 until the meeting of the heated zone 90 where a peeling of skin starts under pressure and deforms plastically said skins to form a portion of the conduit corresponding to the volume of gas introduced into the tank 92. This operation is repeated as many times that it will be necessary to permanently form the conduit 90. As soon as the conduit 90 is definitively formed, the heating is cut off and new gas pulses are sent to take off all of the cavities.
  • sensors 95 measure at the level of said cavities micro-deformations caused by gas infiltration and inform about the end takeoff.
  • the range of temperatures used for heating of zone 90 of dawn 1 is between 880 ° C and 940 ° C and this temperature is reached in a few seconds.
  • the internal surface of the jaws 97 present in a preferential embodiment the shape of the conduit 90 formed at hot on dawn 1 after plastic deformation of the skins 2 and 3.
  • the constant gas injection pressure through the channel supply 17 is preferably between 1 MPa and 6 MPa. The injection continues until the equipression between channels 18 and 17. At this time the heating is cut and the takeoff cycle can begin.
  • gas injections regulated both in pressure and flow initiate peeling of the skins, which causes a pressure drop in 94 to reach the threshold authorizing a new injection. The cycle repeats until all the detectors 95 detect microdeformation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Arc Welding In General (AREA)

Abstract

The procedure for fabricating a blade for a turbine engine involves using computer assistance, for providing a digital simulation to construct the flat components of the blade. The elementary pieces of the blade are forged and machined. A diffusion barrier layer is then applied to the blade, in order to determine the final internal geometry of the blade, and the components are assembled using a diffusion welding process under iso-static pressure. The components are then inflated under gas pressure in order to form the blade shape, in a super-plastic mode, prior to final machining. The process also includes an additional complementary stage of un-gluing parts of the blade structure internally, with this region being defined by the diffusion barrier layer applied previously. The un-gluing process enables the formation of internal cavities in the blade structure.

Description

La présente invention concerne un procédé de fabrication d'une aube creuse de turbomachine assemblée par soudage-diffusion et formée sous pression de gaz par formage superplastique. Elle concerne également un dispositif utilisé dans une étape dudit procédé comportant une opération de décollement à froid de parties constitutives de l'aube.The present invention relates to a manufacturing process of a turbomachine hollow blade assembled by diffusion-welding and formed under gas pressure by forming superplastic. It also relates to a device used in a step of said method comprising an operation of cold separation of components of the blade.

Les avantages découlant de l'utilisation d'aubes à grande corde pour les turbomachines sont apparus notamment dans le cas des aubes de rotor de soufflante des turboréacteurs à double flux. Ces aubes doivent répondre à des conditions sévères d'utilisation et posséder notamment des caractéristiques mécaniques suffisantes associées à des propriétés antivibratoires et de résistance aux impacts de corps étranger. L'objectif de vitesses suffisantes en bout d'aube a en outre amené à rechercher une réduction des masses. Ce but est notamment atteint par l'utilisation d'aubes creuses.The benefits of using large blades rope for turbomachinery appeared especially in the case of the fan rotor blades of turbojet engines double flow. These blades must meet conditions severe use and in particular have sufficient mechanical characteristics associated with anti-vibration and impact resistance properties of foreign body. The objective of sufficient speeds at the end dawn has also led to the search for a reduction in masses. This goal is notably achieved by the use hollow blades.

EP-A-0 700 738 décrit un procédé de fabrication d'une aube creuse de turbomachine, notamment une aube de rotor de soufflante à grande corde. Ledit procédé prévoit le découlé opératoire général selon les étapes suivantes :

  • (b) forgeage sur presse des pièces primaires constituant l'aube par matriçage ;
  • (c) usinage des pièces primaires ;
  • (d) dépôt de barrières de diffusion suivant un motif prédéfini, déterminant la géométrie interne finale de l'aube;
  • (e) assemblage des pièces primaires suivi du soudage-diffusion en pression isostatique ;
  • (f) gonflage sous pression de gaz et formage superplastique ;
  • (g) usinage final.
    • EP-A-0 700 738 describes a method for manufacturing a hollow blade of a turbomachine, in particular a blade rotor of a large-rope fan. Said method provides for the general operating flow according to the following steps:
  • (b) forging on the press of the primary parts constituting the blade by stamping;
  • (c) machining of primary parts;
  • (d) depositing diffusion barriers according to a predefined pattern, determining the final internal geometry of the dawn;
  • (e) assembly of the primary parts followed by welding-diffusion under isostatic pressure;
  • (f) inflation under gas pressure and superplastic forming;
  • (g) final machining.

    • FR N°95.11300 prévoit en outre avant démarrage du gonflage à l'étape (f) ci-dessus de réaliser un décollement des pièces primaires à froid, compte-tenu de l'état de compactage des barrières de diffusion précédemment déposées. Cette opération est en effet nécessaire pour assurer à l'étape (f) le bon déroulement d'un cycle de gonflage et formage superplastique en garantissant une alimentation régulière par un gaz neutre au travers des cavités délimitées par les soudures et enduites du revêtement formant barrière anti-diffusion. Cette opération de décollage des parties constituées de l'aube entre les zones soudées permet seule de maítriser les vitesses de déformation dès le début du cycle de formage à l'étape (f) en évitant de provoquer au cours du cycle de gonflage des surpressions dues à un collage local d'une partie d'aube sur l'autre qui entrainerait un gonflage excessif indésiré et des risques de rupture.FR N ° 95.11300 also provides before starting inflation at step (f) above to detach the parts cold primers, taking into account the state of compaction of diffusion barriers previously deposited. This operation is indeed necessary to ensure in step (f) the correct inflation cycle and superplastic forming ensuring regular supply with neutral gas through cavities delimited by the welds and coated with anti-diffusion barrier coating. This takeoff operation of the dawn parts between the welded areas alone can control deformation rates from the start of the forming cycle to step (f) avoiding provoking during the inflation of overpressures due to local sticking of a part of dawn on the other which would cause inflation excessive unwanted and risk of rupture.

    Les mises en oeuvre connues de ladite opération de décollement n'ont toutefois pas donné entière satisfaction et un des buts de l'invention est de prévoir une mise en oeuvre améliorée sans les inconvénients antérieurs et également d'utiliser un dispositif particulièrement adapté à cet effet.The known implementations of said operation of detachment, however, were not entirely satisfactory and one of the aims of the invention is to provide an implementation improved without the prior drawbacks and also to use a device particularly suitable for this purpose.

    Le procédé de fabrication d'une aube creuse de turbomachine comportant les étapes rappelées ci-dessus comporte une étape complémentaire de décollement des zones des parties d'aube enduites d'un revêtement formant barrière anti-diffusion au cours de laquelle, conformément à l'invention, un conduit d'alimentation en gaz est formé dans une zone de l'aube où des trous de communication inter-cavités sont ménagés dans la tôle intermédiaire de l'aube au moyen d'injections contrôlées de gaz sous pression tout en assurant un chauffage localisé de ladite zone de l'aube.The method of manufacturing a hollow turbomachine blade comprising the steps recalled above comprises a step additional detachment of the areas of the blade parts coated with an anti-diffusion barrier coating during which, in accordance with the invention, a conduit gas supply is formed in a dawn area where inter-cavity communication holes are provided in the intermediate sheet of dawn by means of controlled injections gas under pressure while providing localized heating from said dawn area.

    En fonction des applications particulières, ladite opération de formage à chaud d'un conduit d'alimentation en gaz et de décollement des zones des parties d'aube enduites d'un revêtement formant barrière anti-diffusion est effectuée soit sur un ensemble plat d'aube soudé par diffusion, soit sur un ensemble d'aube soudé par diffusion et mis en forme par vrillage/cambrage, soit au cours de l'opération de mise en forme par vrillage de l'ensemble soudé d'aube.Depending on the specific applications, said operation hot forming of a gas supply pipe and separation of the areas of the blade parts coated with a anti-diffusion barrier coating is carried out either on a flat blade assembly welded by diffusion, or on a blade assembly welded by diffusion and shaped by twisting / bending, either during the setting operation twist shape of the welded blade assembly.

    Le dispositif conforme à l'invention utilisé lors de ladite opération de formage à chaud d'un conduit d'alimentation en gaz et de décollement des zones des parties d'aube enduites d'un revêtement formant barrière anti-diffusion comporte des mâchoires munies d'éléments chauffants et présentant une surface aux formes de l'empreinte du conduit à réaliser, une table mobile regroupant le système d'alimentation en gaz, les équipements de régulation de températures et de pressions et un support de pièce muni de capteurs susceptibles de détecter des micro-déplacements.The device according to the invention used during said hot forming operation of a supply pipe in gas and delamination of the areas of the coated blade parts of a coating forming an anti-diffusion barrier comprises jaws fitted with heating elements and having a surface to the shapes of the imprint of the duct to be produced, a mobile table containing the gas supply system, the temperature and pressure regulation equipment and a workpiece support fitted with sensors capable of detecting micro-displacements.

    D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'un mode de réalisation de l'invention, en référence aux dessins annexés sur lesquels :

    • la figure 1 représente une vue schématique de la mise en oeuvre d'une opération de décollement des zones des parties d'aube enduites d'un revêtement formant barrière anti-diffusion dans le procédé de fabrication d'une aube creuse de turbomachine conforme à l'invention;
    • la figure 2 représente une vue schématique en coupe de l'ensemble soudé d'aube en cours de fabrication ;
    • la figure 3 représente une vue schématique de l'ensemble du dispositif utilisé pour ladite mise en oeuvre.
    Other characteristics and advantages of the invention will be better understood on reading the following description of an embodiment of the invention, with reference to the appended drawings in which:
    • FIG. 1 represents a schematic view of the implementation of a separation operation of the zones of the blade parts coated with a coating forming an anti-diffusion barrier in the process for manufacturing a hollow blade of a turbomachine conforming to l 'invention;
    • 2 shows a schematic sectional view of the welded blade assembly during manufacture;
    • Figure 3 shows a schematic view of the entire device used for said implementation.

    Comme schématiquement représenté sur les figures 1 à 3, à un stade intermédiaire de fabrication, une aube 1 creuse de turbomachine, notamment une aube de soufflante à grande corde destinée par exemple à un turboréacteur à double flux est constituée d'une peau d'intrados 2, d'une peau d'extrados 3 et d'une tôle centrale 4, destinée à former les raidisseurs de l'aube. Selon un procédé de fabrication connu en soi dans son principe, au moins une des surfaces en regard des parties constitutives de l'aube reçoit un dépôt d'un revêtement formant barrière anti-diffusion, suivant un motif prédéfini puis une liaison métallurgique dans les zones non revêtues du produit d'anti-diffusion est ensuite obtenue par soudage-diffusion grâce à une mise sous pression isostatique.As shown schematically in Figures 1 to 3, at a intermediate stage of manufacture, a hollow 1 blade of turbomachine, including a large-rope fan blade intended for example for a turbofan is consisting of a lower surface skin 2, an upper surface skin 3 and a central plate 4, intended to form the stiffeners from dawn. According to a manufacturing process known per se in its principle, at least one of the surfaces facing the parts constituting the dawn receives a coating deposit forming an anti-diffusion barrier, according to a predefined pattern then a metallurgical bond in the unpaved areas of the anti-diffusion product is then obtained by welding-diffusion thanks to an isostatic pressurization.

    Avant d'obtenir ensuite la formation de cavités internes dans l'aube 1 par gonflage sous pression de gaz neutre et par formage superplastique des différentes parties 2, 3 et 4 de l'aube 1, le procédé de fabrication conforme à l'invention comporte une opération remarquable de décollement des peaux 2, 3 et tôle 4 entre les zones soudées.Before then obtaining the formation of internal cavities in vane 1 by inflation under pressure of neutral gas and by superplastic forming of the different parts 2, 3 and 4 of dawn 1, the manufacturing process according to the invention involves a remarkable peeling operation 2, 3 and sheet 4 between the welded areas.

    A ce stade de fabrication, l'aube 1 est disposée sur un support porté par une table mobile 96, telle que représentée sur la figure 3. Comme montré sur la figure 2, des voies d'alimentation par tube 17 et 18 relient l'aube 1 d'une part à un réservoir 92 alimenté par une source de distribution de gaz neutre 91, des capteurs de pression 93 et 94 étant placés de part et d'autre du réservoir 92 ainsi que des vannes 98 et 99 et d'autre part à un volume de détente 100 précédé également d'une vanne 101 et d'un capteur de pression 102. Sur la table mobile 96 une zone déterminée 90 de l'aube 1 dans laquelle la tôle centrale 4 comporte des perçages 5 qui mettent en communication les cavités formées entre les zones soudées de l'aube 1 est disposée entre des machoires d'outillage 97 comportant des éléments chauffants 103. Des capteurs de température 104 sont en outre reliés à ladite zone de l'aube 1.At this stage of manufacture, the blade 1 is disposed on a support carried by a movable table 96, as shown in Figure 3. As shown in Figure 2, channels supply tube 17 and 18 connect the blade 1 on the one hand to a reservoir 92 supplied by a distribution source of neutral gas 91, pressure sensors 93 and 94 being placed on either side of the reservoir 92 as well as of the valves 98 and 99 and on the other hand to a trigger volume 100 preceded also of a valve 101 and of a pressure sensor 102. On the movable table 96 a specific area 90 of dawn 1 in which the central sheet 4 has holes 5 which connect the cavities formed between the zones welded from dawn 1 is arranged between jaws of tooling 97 comprising heating elements 103. temperature sensors 104 are further connected to said dawn area 1.

    L'opération consiste à chauffer dans le domaine où le matériau constituant l'aube est plastique ladite zone 90 de l'aube 1. Dès que la température est atteinte, des injections contrôlées de gaz à haute pression sont envoyées par la voie d'alimentation 17. Sous la pression gazeuse la peau se déforme progressivement d'une cavité à l'autre pour former un conduit persistant 90 entre les voies d'alimentation 17-18 permettant par la suite une distribution de gaz équilibrée dans chacune des cavités. The operation consists of heating in the area where the material constituting the blade is plastic said zone 90 of dawn 1. As soon as the temperature is reached, injections high pressure gas are sent by the way supply 17. Under gas pressure the skin becomes gradually deforms from one cavity to another to form a persistent duct 90 between supply lines 17-18 subsequently allowing a balanced gas distribution in each of the cavities.

    Préalablement, le réservoir 92 de capacité définie a été rempli à partir de la source de distribution de gaz neutre 91 jusqu'à obtenir la pression de travail. Les capteurs de pression 93-94 renseignent sur les conditions de fonctionnement. Dès que la pression de consigne est atteinte en amont du réservoir, l'alimentation est coupée, autorisant la décharge vers le tube 17. Alors le gaz s'infiltre dans l'aube 1 jusqu'à la rencontre de la zone chauffée 90 où un décollement d'une peau s'amorce sous la pression et déforme plastiquement lesdites peaux pour former une portion du conduit correspondant au volume de gaz introduit dans le réservoir 92. Cette opération est réitérée autant de fois qu'il sera nécessaire pour former définitivement le conduit 90. Dès que le conduit 90 est définitivement formé, le chauffage est coupé et de nouvelles impulsions de gaz sont envoyées pour effectuer le décollement de l'ensemble des cavités. En effet le gaz débité s'infiltre progressivement sous les peaux et provoque ainsi le décollage de toutes les parties enduites du revêtement d'anti-diffusion. A l'extrémité opposée des alimentations en gaz, des capteurs 95 mesurent au droit desdites cavités les micro-déformations provoquées par l'infiltration du gaz et informent sur la fin de décollage.Beforehand, the tank 92 of defined capacity was filled from neutral gas distribution source 91 until you get the working pressure. The sensors pressure 93-94 provide information on the conditions of operation. As soon as the set pressure is reached upstream of the tank, the supply is cut off, allowing discharge to tube 17. Then the gas seeps into dawn 1 until the meeting of the heated zone 90 where a peeling of skin starts under pressure and deforms plastically said skins to form a portion of the conduit corresponding to the volume of gas introduced into the tank 92. This operation is repeated as many times that it will be necessary to permanently form the conduit 90. As soon as the conduit 90 is definitively formed, the heating is cut off and new gas pulses are sent to take off all of the cavities. Indeed the gas delivered gradually infiltrates under the skins and thus causes the takeoff of all parts coated with anti-diffusion coating. AT the opposite end of the gas supplies, sensors 95 measure at the level of said cavities micro-deformations caused by gas infiltration and inform about the end takeoff.

    Selon un mode avantageux de réalisation, dans l'application à une aube de soufflante à grande corde en alliage de titane de type TA6V, la gamme de températures retenues pour le chauffage de la zone 90 de l'aube 1 se situe entre 880°C et 940°C et cette température est atteinte en quelques secondes. La surface interne des machoires 97 présente dans une réalisation préférentielle la forme du conduit 90 formé à chaud sur l'aube 1 après déformation plastique des peaux 2 et 3. La pression constante d'injection du gaz par la voie d'alimentation 17 est comprise préférentiellement entre 1 MPa et 6 MPa. L'injection se poursuit jusqu'à obtenir l'équipression entre les voies 18 et 17. A ce moment le chauffage est coupé et le cycle de décollage peut débuter. Au moyen du réservoir 92, des injections de gaz régulées à la fois en pression et débit amorcent le décollement des peaux, ce qui provoque une baisse de pression en 94 pour atteindre le seuil autorisant une nouvelle injection. Le cycle se réitère jusqu'au moment où tous les détecteurs 95 décèlent une microdéformation.According to an advantageous embodiment, in the application to a large titanium alloy blower blade from type TA6V, the range of temperatures used for heating of zone 90 of dawn 1 is between 880 ° C and 940 ° C and this temperature is reached in a few seconds. The internal surface of the jaws 97 present in a preferential embodiment the shape of the conduit 90 formed at hot on dawn 1 after plastic deformation of the skins 2 and 3. The constant gas injection pressure through the channel supply 17 is preferably between 1 MPa and 6 MPa. The injection continues until the equipression between channels 18 and 17. At this time the heating is cut and the takeoff cycle can begin. By means of reservoir 92, gas injections regulated both in pressure and flow initiate peeling of the skins, which causes a pressure drop in 94 to reach the threshold authorizing a new injection. The cycle repeats until all the detectors 95 detect microdeformation.

    Claims (5)

    Procédé de fabrication d'une aube creuse de turbomachine, notamment une aube de rotor de soufflante à grande corde, comportant les étapes suivantes : (a) à partir de la définition d'une aube (1) à obtenir, étude en utilisant les moyens de Conception et Fabrication Assistés par Ordinateur/CFAO et réalisation d'une simulation numérique de la mise à plat des pièces constitutives de l'aube ; (b) forgeage sur presse des pièces primaires par matriçage ; (c) usinage des pièces primaires ; (d) dépôt de barrières de diffusion suivant un motif prédéfini, déterminant la géométrie interne finale de l'aube; (e) assemblage des pièces primaires 2,3,4) suivi du soudage-diffusion en pression isostatique ; (f) gonflage sous pression de gaz et formage superplastique ; (g) usinage final, comportant en outre une étape complémentaire (f1) après le soudage-diffusion, réalisant le décollement des zones des parties d'aube enduites d'un revêtement formant barrière pour l'anti-diffusion au cours de laquelle un conduit d'alimentation en gaz (90) est formé dans une zone de l'aube où des trous (5) de communication inter-cavités sont ménagés dans la tôle intermédiaire (4) de l'aube (1) au moyen d'injections contrôlées de gaz sous pression tout en assurant un chauffage localisé de ladite zone de l'aube.Method for manufacturing a hollow turbomachine blade, in particular a large-rope fan rotor blade, comprising the following steps: (a) from the definition of a dawn (1) to be obtained, study using the Computer Aided Design / Manufacturing / CAD / CAM means and realization of a digital simulation of the flattening of the constituent parts of the dawn; (b) press forging of primary parts by stamping; (c) machining of primary parts; (d) depositing diffusion barriers according to a predefined pattern, determining the final internal geometry of the dawn; (e) assembly of the primary parts 2,3,4) followed by welding-diffusion under isostatic pressure; (f) inflation under gas pressure and superplastic forming; (g) final machining, further comprising a complementary step (f1) after welding-diffusion, carrying out the separation of the areas of the blade parts coated with a coating forming a barrier for anti-diffusion during which a gas supply duct ( 90) is formed in an area of the blade where inter-cavity communication holes (5) are formed in the intermediate sheet (4) of the blade (1) by means of controlled injections of pressurized gas while providing localized heating of said dawn area. Procédé de fabrication d'une aube creuse de turbomachine selon la revendication 1 dans lequel ladite opération (f1) de formage à chaud d'un conduit permanent (90) d'alimentation en gaz et de décollement des zones des parties d'aube enduites d'un revêtement formant barrière d'anti-diffusion est effectuée sur un ensemble plat d'aube (1) soudé par diffusion.Method for manufacturing a hollow turbomachine blade according to claim 1 wherein said operation (f1) of hot forming of a permanent supply pipe (90) gas and delamination of the areas of the coated blade parts of an anti-diffusion barrier coating is performed on a flat blade assembly (1) welded by diffusion. Procédé de fabrication d'une aube creuse de turbomachine selon la revendication 1 dans lequel ladite opération (f1) de formage à chaud d'un conduit permanent (90) d'alimentation en gaz et de décollement des zones des parties d'aube enduites d'un revêtement formant barrière pour l'anti-diffusion est effectuée sur un ensemble d'aube soudé par diffusion et préalablement mis en forme par vrillage/cambrage.Method for manufacturing a hollow turbomachine blade according to claim 1 wherein said operation (f1) of hot forming of a permanent supply pipe (90) gas and delamination of the areas of the coated blade parts of a barrier coating for anti-diffusion is performed on a diffusion welded blade assembly and previously shaped by twisting / bending. Procédé de fabrication d'une aube creuse de turbomachine selon la revendication 1, dans lequel ladite opération (fl) de formage à chaud d'un conduit permanent (90) d'alimentation en gaz et de décollement des zones des parties d'aube enduites d'un revêtement formant barrière pour l'anti-diffusion est effectuée au cours d'une opération de mise en forme par vrillage de l'ensemble d'aube soudé par diffusion.Method for manufacturing a hollow turbomachine blade according to claim 1, wherein said operation (fl) for hot forming a permanent supply duct (90) in gas and detachment of the areas of the blade parts coated with a barrier coating for anti-diffusion is performed during a setting operation twist shape of the diffusion welded blade assembly. Dispositif de réalisation d'une opération de formage à chaud d'un conduit (90) d'alimentation en gaz et de décollement des zones des parties d'aube (1) enduites d'un revêtement formant barrière d'anti-diffusion effectuée sur un ensemble d'aube (1) dans un procédé de fabrication d'une aube creuse de turbomachine suivant l'une quelconque des revendications 1 à 4 caractérisé en ce qu'il comporte des machoires (97) munies d'éléments chauffants (103) et présentant une surface aux formes de l'empreinte du conduit (90) à réaliser, une table mobile (96) regroupant le système d'alimentation en gaz (91, 92, 17, 18), les équipements de régulation de températures (104) et de pressions (93, 94, 102) et un support de pièce muni de capteurs (95) susceptibles de détecter des micro-déplacements.Device for carrying out a forming operation at hot of a gas supply pipe (90) and separation of the areas of the blade parts (1) coated with a coating forming an anti-diffusion barrier carried out on a blade assembly (1) in a method of manufacturing a blade turbomachine hollow according to any one of claims 1 to 4 characterized in that it comprises jaws (97) provided with heating elements (103) and having a surface with the shapes of the imprint of the duct (90) to be produced, a mobile table (96) grouping the system gas supply (91, 92, 17, 18), the equipment regulation of temperatures (104) and pressures (93, 94, 102) and a workpiece support with sensors (95) likely to detect micro-displacements.
    EP97401926A 1996-08-14 1997-08-13 Method of making a hollow blade for a turbomachine having a release material after welding Expired - Lifetime EP0824048B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    FR9610194A FR2752388B1 (en) 1996-08-14 1996-08-14 PROCESS FOR THE MANUFACTURE OF A HOLLOW BLADE OF A TURBOMACHINE COMPRISING A TAKE-OFF AFTER WELDING
    FR9610194 1996-08-14

    Publications (2)

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    EP0824048A1 true EP0824048A1 (en) 1998-02-18
    EP0824048B1 EP0824048B1 (en) 2001-01-10

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    US (1) US5946802A (en)
    EP (1) EP0824048B1 (en)
    JP (1) JP3477036B2 (en)
    CA (1) CA2207828C (en)
    DE (1) DE69703866T2 (en)
    ES (1) ES2153640T3 (en)
    FR (1) FR2752388B1 (en)
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    US6264880B1 (en) * 1998-07-22 2001-07-24 The Regents Of The University Of California Manifold free multiple sheet superplastic forming
    GB2360236B (en) * 2000-03-18 2003-05-14 Rolls Royce Plc A method of manufacturing an article by diffusion bonding and superplastic forming
    FR2820062B1 (en) * 2001-02-01 2003-03-07 Snecma Moteurs INSTALLATION FOR FORMING A WORKPIECE AND APPLICATION TO HOT FORMING
    FR2867096B1 (en) * 2004-03-08 2007-04-20 Snecma Moteurs METHOD FOR MANUFACTURING A REINFORCING LEAK OR RELEASING EDGE FOR A BLOWER BLADE
    WO2015070409A1 (en) * 2013-11-14 2015-05-21 深圳智慧能源技术有限公司 Method for manufacturing a hollow structure
    GB201809397D0 (en) * 2018-06-07 2018-07-25 Group Rhodes Ltd Super plastic forming apparatus and method
    US10808550B2 (en) * 2018-12-13 2020-10-20 Raytheon Technologies Corporation Fan blade with integral metering device for controlling gas pressure within the fan blade
    CN114669970A (en) * 2022-05-06 2022-06-28 北京航空航天大学 Forming method of composite blade titanium alloy wrapping edge

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    EP0500458A1 (en) * 1991-02-20 1992-08-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Method for fabricating a hollow blade for a turbomachine
    EP0700738A1 (en) * 1994-09-07 1996-03-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Method of producing a hollow turbine blade

    Also Published As

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    IL121600A0 (en) 1998-02-08
    EP0824048B1 (en) 2001-01-10
    FR2752388B1 (en) 1998-09-18
    FR2752388A1 (en) 1998-02-20
    DE69703866D1 (en) 2001-02-15
    JP3477036B2 (en) 2003-12-10
    ES2153640T3 (en) 2001-03-01
    JPH10103005A (en) 1998-04-21
    CA2207828A1 (en) 1998-02-14
    US5946802A (en) 1999-09-07
    IL121600A (en) 2004-03-28
    CA2207828C (en) 2005-02-22
    DE69703866T2 (en) 2001-05-23

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