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EP0761978B1 - Rotor aus thermostrukturellem Verbundmaterial, insbesondere mit grossem Diameter und sein Herstellungsverfahren - Google Patents

Rotor aus thermostrukturellem Verbundmaterial, insbesondere mit grossem Diameter und sein Herstellungsverfahren Download PDF

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Publication number
EP0761978B1
EP0761978B1 EP96401836A EP96401836A EP0761978B1 EP 0761978 B1 EP0761978 B1 EP 0761978B1 EP 96401836 A EP96401836 A EP 96401836A EP 96401836 A EP96401836 A EP 96401836A EP 0761978 B1 EP0761978 B1 EP 0761978B1
Authority
EP
European Patent Office
Prior art keywords
blades
hub
turbine
composite material
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP96401836A
Other languages
English (en)
French (fr)
Other versions
EP0761978A1 (de
Inventor
Jean-Pierre Maumus
Guy Martin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Br Construction De Moteurs D A
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Br Construction De Moteurs D A, Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Br Construction De Moteurs D A
Publication of EP0761978A1 publication Critical patent/EP0761978A1/de
Application granted granted Critical
Publication of EP0761978B1 publication Critical patent/EP0761978B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2261—Carbides of silicon
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • 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
    • Y10T29/4932—Turbomachine making
    • 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
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the present invention relates to turbines, and more particularly those intended to operate at high temperatures, typically higher at 1000 ° C.
  • these turbines are made of metal, generally made up of several elements assembled by welding.
  • the use of metal has several drawbacks. So the high mass of the rotating parts requires large shaft lines and very powerful motors and requires anyway a limitation of the speed of rotation. There is a limitation in temperature due to the risk of metal creep.
  • the sensitivity of the metal to thermal shock can cause formation of cracks or deformations. This results in imbalances in the rotating mass favoring a reduction in the service life of the turbines and their drive motors.
  • significant thermal shock can occur, especially when injected massive cold gas, to quickly lower the temperature inside an oven to reduce the duration of treatment cycles.
  • thermostructural composite materials are used for temperature use high. These materials generally consist of a fibrous reinforcement texture, or preform, densified by a matrix and are characterized by their properties mechanical which make them suitable for constituting structural elements and by their ability to maintain these properties up to high temperatures.
  • thermostructural composite materials are composites carbon-carbon (C-C) consisting of a carbon fiber reinforcement and a carbon matrix, and ceramic matrix composites (CMC) consisting of carbon fiber or ceramic reinforcement and a ceramic matrix.
  • thermostructural composite materials Compared to metals, thermostructural composite materials have the essential advantages of much lower density and high stability at high temperatures. The reduction in mass and the elimination of risk of creep can allow high speeds of rotation and, thereby, very high ventilation rates without requiring oversizing of the drive bodies. In addition, thermostructural composite materials have a very high resistance to thermal shock.
  • Thermostructural composite materials therefore have important performance advantages, but their use is limited in because of their fairly high cost. In addition to the materials used, the cost comes from essentially difficulties encountered in making fibrous preforms, especially when the parts to be manufactured have complex shapes, which is the case of turbines, and the duration of the densification cycles.
  • an object of the present invention is to propose an architecture turbine particularly suitable for its production in composite material thermostructural in order to benefit from the advantages of this material but at a cost manufacturing as reduced as possible.
  • Another object of the present invention is to propose an architecture turbine suitable for making large turbines, that is to say whose diameter can greatly exceed 1 m.
  • the turbine is produced by assembly of parts having a simple shape, for example annular plates planes making up the hub, or parts made from preforms fibrous in a simple shape (two-dimensional plate or sheet), by example blades and flanges.
  • parts having a simple shape for example annular plates planes making up the hub, or parts made from preforms fibrous in a simple shape (two-dimensional plate or sheet), by example blades and flanges.
  • the swollen blade root is formed by placing an insert in a slot in the texture fiber used to make the preform of a blade.
  • the plates are assembled constituting the hub with at least one annular plate, constituting a first flange closing the passages between blades at one end of the turbine, by axial clamping on a shaft on which the turbine is mounted.
  • the second flange which forms an annular zone with the hub fluid inlet for suction through the passages between blades, is mounted on the blades, for example by engagement in notches of the flange of heels formed on the adjacent edges of the blades, and / or by gluing.
  • this second flange can be static.
  • the invention relates to a turbine in thermostructural composite material comprising a plurality of blades arranged around a hub, between two flanges, the turbine being characterized in that it includes flat annular plates of thermostructural composite material stacked along the same axis, immobilized with respect to each other in rotation around the axis and forming a hub, and the blades of composite material thermostructural are individually connected to the hub by a part forming blade root.
  • said flat annular plates of material thermostructural composite form an assembly comprising the hub and a first flange closing the passages between blades at one end of the turbine.
  • FIGS 1 and 2 illustrate a turbine comprising a plurality of blades 10 regularly arranged around a hub 20, between two flanges end 30, 40. These various components of the turbine are in one thermostructural composite material, for example a composite material carbon-carbon (C-C) or a ceramic matrix composite material such as C-SiC composite material (carbon fiber reinforcement and carbide matrix silicon).
  • C-C composite material carbon-carbon
  • SiC composite material carbon fiber reinforcement and carbide matrix silicon
  • the blades 10 define between them passages 11 for circulation of fluid.
  • the passages 11 are closed by the annular flange 30 which extends from the hub 20 to the edge free outside 12 of the blades 10.
  • the flange 40 of shape substantially annular, extends over only part of the length of the blades 10, from their outer edge 12.
  • the free space between the internal edge 41 of the flange 40 and the hub 20 defines an entry zone from which a fluid can be sucked through the passages 11, to be ejected at the outer ring of the turbine, like the show the arrows F in Figure 2.
  • the hub 20 is formed of annular plates 21 which are stacked along the axis A of the turbine.
  • the plates 21 have the same internal diameter defining the central passage of the hub. In each plate, the outside diameter gradually increases from the face closest to the fluid entry zone to the opposite face, and the contacting faces of two neighboring plates have the same outer diameter, so that the set of plates 21 forms a hub of regularly increasing thickness between the flange 40 and the flange 30, without discontinuity.
  • Dovetail-shaped grooves 23 are formed at the periphery of the hub 20 in order to receive the feet of the blades 10 and ensure the connection of these with the hub as shown in more detail later in the description.
  • the grooves 23 extend axially over the entire length of the hub 20 by being regularly distributed around it. In plates 21 more large outside diameter, the grooves 23 communicate with the outside through grooves 23a, the width of which corresponds substantially to the thickness of a blade.
  • Each annular plate 21 is made individually of material thermostructural composite.
  • a fibrous structure can be used in form of plate in which an annular preform is cut.
  • Such a structure is produced for example by flat stacking of texture layers two-dimensional fibrous material, such as web of threads or cables, fabric, etc., and bonding of the strata together by needling, as described for example in the document FR-A-2 584 106.
  • the annular preform cut from this plate is densified by the constituent material of the matrix of the thermostructural composite material to achieve. Densification is carried out in a manner known per se by infiltration chemical in the vapor phase, or by liquid, i.e. impregnation with a matrix precursor in the liquid state and transformation of the precursor. After densification, the annular plate is machined to be brought to its dimensions final and to form the notches which, after stacking the plates, constitute the grooves 23 and grooves 23a.
  • the plates 21 are secured in rotation about the axis A of the turbine by means of screws 26 which extend axially through all the plates.
  • the screws 26 are machined from a block of thermostructural composite material.
  • the flange 30, which closes the passages 11 opposite the entry area of fluid, is made of thermostructural composite material by densification of a fibrous preform.
  • the preform is produced for example by stacking at flat of two-dimensional strata and bonding of the strata together by needling.
  • the flange 30 has a thickness which increases by continuously from its periphery to its internal circumference.
  • a plate annular intermediate 31 can be interposed between the hub 20 proper and the flange 30 proper, this plate 31 having an external profile such that it allows the face of the flange 30 facing the inside of the turbine to be connected without discontinuity on the outer surface of the hub 20.
  • the plate 31 is secured in rotation with the plates 21 by means of screws 26 of material thermostructural composite.
  • the profile of the flange 30 may be obtained from a preform produced by stacking annular layers of which the outside diameter gradually decreases.
  • machining of the flange to its dimensions definitive is achieved.
  • the internal annular face 37 is given flange 30 a frustoconical shape for mounting the turbine on a shaft.
  • the attachment of the flange 30 with the hub 20 rotating around the axis A is made by means of screws 36 of thermostructural composite material which connect the flange 30 to plate 31.
  • Each blade 10 is in the form of a thin plate with a surface curved whose outline is shown very schematically in Figure 3. From internal side intended to be connected to the hub 20, each blade 10 has a bulging part forming blade root 13 whose shape and dimensions correspond to those of the grooves 23 of the hub.
  • the edge of the blade 10 located on the side of the fluid entry zone has, from the foot 13, a first part convex curve 14a which ends in a radial projection forming heel 16. The latter is connected to the end edge 12 by a second convex part 14b.
  • the edge of the blade opposite the fluid entry zone present, from the foot 13, a radial part 15a extended by a concave part 15b which follows the profile of the adjacent faces of the intermediate plate 31 and the flange 30.
  • the fibrous structure is cut to roughly reproduce the contour of the blade (step 100), then the edge corresponding to the location of the leg is split in order to introduce an insert I around which the parts of the structure fibrous located on either side of the slot are folded (step 101).
  • the structure fibrous is then pre-impregnated with a resin and shaped in a tool T in order to give it a shape close to that of the blade to be produced (step 102).
  • a preform P of the blade After crosslinking of the resin in the tooling, a preform P of the blade.
  • the resin is then pyrolyzed leaving a residue, for example carbon sufficiently binding the fibers together so that the preform P retains its shape. Densification can then be continued outside the tooling, either by continuing with liquid route, either by chemical vapor infiltration (step 103).
  • step 104 After densification, a precise machining of the contour of the blade in particular to form the heel 16 and the edges 12, 14, 15 (step 104).
  • the annular flange 40 has a curved profile corresponding to that of the edge portion 14b of the blades. It is made by densification of a fibrous texture in the form of a sheet or plate, in the same way as the blades 10. After densification, the flange 40 is machined to be brought to its final dimensions and to form notches 46 intended to receive the heels 16 of the blades 10.
  • the assembly of the turbine is carried out as follows.
  • the blades 10 are hung on the flange 40 by engagement of the heels 16 in the notches 46. Then, the hub 20 is formed by setting places plates 21 one after the other, while inserting feet 13 of blades in the grooves 23. The plate 31 is put in place then the plates 21 are linked together and with the plate 31 by the screws 26. The flange 30 is then put in place, as well as the screws 36. It will be noted that grooves respectively 44, 35 can be formed on the internal faces of the flanges 40 and 30 in which the edges respectively 24b and 25b of the blades can be inserted to ensure a more effective blade retention.
  • a ring 53 is disposed on the plate 21 at the end of the hub opposite the flange 30, the ring 53 having a diameter sufficient to close off the grooves 23.
  • the mutual tightening of the plates 21, 31 and the flange 30 is ensured by a nut 55 engaged on the threaded part 52 and exerting a force on the ring 53 by through another ring 56, the rings 53 and 56 being in mutual support by frustoconical surfaces.
  • Maintaining the flange 40 is ensured simply by hanging on the heels 16 of the blades.
  • the attachment of the flange 40 on the blades may alternatively be carried out by gluing, with or without mechanical attachment of the heels of the blades in notches on the flange. After bonding, it may be advantageous to carry out a cycle chemical vapor infiltration to densify the adhesive joint and establish continuity of the matrix at the interfaces between the glued parts.
  • the flange 40 may be constituted by a static part, that is to say not linked in rotation to the rest of the turbine.
  • a turbine as illustrated in FIGS. 1 and 2 was produced from CC composite having a diameter of 950 mm and a width, in the axial direction, of 250 mm. It was used to carry out a gas suction with a temperature of 1200 ° C at a rotation speed of 3000 rpm ensuring a flow rate of 130,000 m 3 / h.
  • the gain of mass is about 5, i.e. about 40 kg for the turbine composite C-C against 200 kg for the metal turbine.
  • the mass of the turbine metal means that its speed of rotation cannot in practice exceed approximately 800 rpm.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Composite Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Moulding By Coating Moulds (AREA)

Claims (12)

  1. Verfahren zur Herstellung einer Turbine, die eine Mehrzahl von Schaufeln aufweist, die um eine Nabe herum zwischen zwei Scheiben angeordnet sind, wobei die Schaufeln, die Nabe und die Scheiben aus einem thermostrukturellen Verbundwerkstoff bestehen, wobei gemäß diesem Verfahren:
    (a) die Nabe durch eine einer gleichen Achse folgenden Stapelung von ringförmigen, ebenen Platten aus thermostrukturellem Verbundwerkstoff und durch Festlegung der Platten gegenseitig bei Rotation um die Achse hergestellt wird,
    (b) jede Schaufel mit einem inneren Randbereich hergestellt wird, der einen Fuß mit verdickter Gestalt bildet, indem die folgenden Schritte durchgeführt werden:
    Formen eines im Wesentlichen zweidimensionalen, plattenförmigen oder tafelförmigen Fasergebildes, um einen Vorformling der Schaufel zu erhalten,
    Verdichten des Vorformlings durch eine Matrix, um einen Rohling der Schaufel aus thermostrukturellem Verbundwerkstoff zu erhalten, und
    Bearbeiten des Umrisses des verdichteten Vorformlings,
    (c) jede Scheibe hergestellt wird, indem die folgenden Schritte durchgeführt werden:
    Herstellen eines ringförmigen oder im Wesentlichen ringförmigen Vorformlings mit Hilfe eines im Wesentlichen zweidimensionalen Fasergebildes in Gestalt einer Platte oder Tafel und
    Verdichten des Vorformlings durch eine Matrix, um ein Teil aus einem thermostrukturellen Verbundwerkstoff zu erhalten, und
    (d) die Schaufeln mit der Nabe zwischen den Scheiben zusammengebaut werden, wobei jede Schaufel mit der Nabe durch Einsetzen des Fußes der Schaufel in eine Vertiefung mit entsprechender Gestalt, die in der Nabe ausgebildet ist, verbunden wird.
  2. Verfahren nach Anspruch 1,
    dadurch gekennzeichnet, dass
    der Vorformling jeder Schaufel durch Formen eines vorimprägnierten Fasergebildes hergestellt wird.
  3. Verfahren nach einem der Ansprüche 1 und 2,
    dadurch gekennzeichnet, dass
    ein Schaufelfuß dadurch gebildet wird, dass ein Einsatzteil in einen Schlitz eingebracht wird, der in dem Fasergebilde ausgebildet ist, das dazu verwendet wird, um den Vorformling einer Schaufel herzustellen.
  4. Verfahren nach einem der Ansprüche 1 bis 3,
    dadurch gekennzeichnet, dass
    die die Nabe bildenden Platten mit wenigstens einer ringförmigen Platte zusammengebaut werden, die eine die Passagen zwischen Schaufeln an dem einen Ende der Turbine schließende, erste Scheibe bildet, mit der die Schaufeln durch axiales Spannen auf einer Welle verbunden werden, auf der die Turbine angebracht wird.
  5. Verfahren nach Anspruch 4,
    dadurch gekennzeichnet, dass
    die zweite Scheibe, die mit der Nabe eine ringförmige Fluideintrittszone zum Ansaugen durch die Passagen zwischen Schaufeln hindurch bildet, an den Schaufeln angebracht wird.
  6. Verfahren nach Anspruch 5,
    dadurch gekennzeichnet, dass
    die zweite Scheibe Vertiefungen aufweist, in welche Ansätze eingreifen, die an den an die Schaufeln angrenzenden Rändern gebildet sind.
  7. Verfahren nach einem der Ansprüche 5 und 6,
    dadurch gekennzeichnet, dass
    die zweite Scheibe an die an die Schaufeln angrenzenden Ränder geklebt wird.
  8. Verfahren nach einem der Ansprüche 5 bis 7,
    dadurch gekennzeichnet, dass
    ein Zyklus einer chemischen Infiltration in der Dampfphase nach Anbringen der zweiten Scheibe an den Schaufeln durchgeführt wird.
  9. Turbine aus einem thermostrukturellen Verbundwerkstoff, die eine Mehrzahl von Schaufeln (10) aufweist, die um eine Nabe (20) herum zwischen zwei Scheiben (30, 40) angeordnet sind, wobei die Turbine ringförmige, ebene Platten (21) aus thermostrukturellem Verbundwerkstoff aufweist, die gemäß einer gleichen Achse gestapelt sind, gegenseitig bei Rotation um die Achse festgelegt sind und eine Nabe (20) bilden, wobei die Schaufeln (10) aus thermostrukturellem Verbundwerkstoff einzeln mit der Nabe durch einen inneren Randbereich, der einen Schaufelfuß mit verdickter Gestalt bildet, verbunden sind, der in eine in der Nabe gebildete Vertiefung mit entsprechender Gestalt eingreift.
  10. Turbine nach Anspruch 9,
    dadurch gekennzeichnet, dass
    die ebenen, ringförmigen Platten (21, 31, 30) aus thermostrukturellem Verbundwerkstoff eine Anordnung bilden, die die Nabe (20) und eine erste Scheibe (30) aufweist, die die Passagen zwischen Schaufeln an einem Ende der Turbine schließt.
  11. Turbine nach einem der Ansprüche 9 und 10,
    dadurch gekennzeichnet, dass
    die zweite Scheibe (40), die mit der Nabe (20) eine ringförmige Fluideintrittszone zum Ansaugen durch die Passagen (11) zwischen Schaufeln hindurch bildet, an den Schaufeln fixiert ist.
  12. Turbine nach einem der Ansprüche 9 und 10,
    dadurch gekennzeichnet, dass
    die zweite Scheibe, die mit der Nabe eine ringförmige Fluideintrittszone zum Ansaugen durch die Passagen zwischen Schaufeln hindurch bildet, statisch ist.
EP96401836A 1995-08-30 1996-08-28 Rotor aus thermostrukturellem Verbundmaterial, insbesondere mit grossem Diameter und sein Herstellungsverfahren Expired - Lifetime EP0761978B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9510206A FR2738304B1 (fr) 1995-08-30 1995-08-30 Turbine en materiau composite thermostructural, en particulier a grand diametre, et procede pour sa fabrication
FR9510206 1995-08-30

Publications (2)

Publication Number Publication Date
EP0761978A1 EP0761978A1 (de) 1997-03-12
EP0761978B1 true EP0761978B1 (de) 2001-10-31

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EP96401836A Expired - Lifetime EP0761978B1 (de) 1995-08-30 1996-08-28 Rotor aus thermostrukturellem Verbundmaterial, insbesondere mit grossem Diameter und sein Herstellungsverfahren

Country Status (10)

Country Link
US (2) US5845398A (de)
EP (1) EP0761978B1 (de)
JP (1) JPH09105304A (de)
CN (1) CN1148673A (de)
CA (1) CA2184522A1 (de)
DE (1) DE69616460T2 (de)
ES (1) ES2165964T3 (de)
FR (1) FR2738304B1 (de)
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FR2738304A1 (fr) 1997-03-07
US5944485A (en) 1999-08-31
US5845398A (en) 1998-12-08
EP0761978A1 (de) 1997-03-12
CN1148673A (zh) 1997-04-30
UA28035C2 (uk) 2000-10-16
ES2165964T3 (es) 2002-04-01
JPH09105304A (ja) 1997-04-22
RU2135779C1 (ru) 1999-08-27
CA2184522A1 (en) 1997-03-01
DE69616460D1 (de) 2001-12-06
DE69616460T2 (de) 2002-07-18
FR2738304B1 (fr) 1997-11-28

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