[go: up one dir, main page]

WO2010026179A1 - Method for making a circular revolution thermomechanical part including a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method - Google Patents

Method for making a circular revolution thermomechanical part including a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method Download PDF

Info

Publication number
WO2010026179A1
WO2010026179A1 PCT/EP2009/061381 EP2009061381W WO2010026179A1 WO 2010026179 A1 WO2010026179 A1 WO 2010026179A1 EP 2009061381 W EP2009061381 W EP 2009061381W WO 2010026179 A1 WO2010026179 A1 WO 2010026179A1
Authority
WO
WIPO (PCT)
Prior art keywords
titanium
steel
alloy
superalloy
compressor
Prior art date
Application number
PCT/EP2009/061381
Other languages
French (fr)
Inventor
Laurent Ferrer
Claude Marcel Mons
Original Assignee
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 Snecma filed Critical Snecma
Priority to US13/060,719 priority Critical patent/US20110211945A1/en
Publication of WO2010026179A1 publication Critical patent/WO2010026179A1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • 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
    • B21D39/00—Application of procedures in order to connect objects or parts, e.g. coating with sheet metal otherwise than by plating; Tube expanders
    • B21D39/04—Application of procedures in order to connect objects or parts, e.g. coating with sheet metal otherwise than by plating; Tube expanders of tubes with tubes; of tubes with rods
    • B21D39/042—Application of procedures in order to connect objects or parts, e.g. coating with sheet metal otherwise than by plating; Tube expanders of tubes with tubes; of tubes with rods using explosives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
    • B21J1/04—Shaping in the rough solely by forging or pressing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
    • B32B15/013—Layered products comprising a layer of metal all layers being exclusively metallic one layer being formed of an iron alloy or steel, another layer being formed of a metal other than iron or aluminium
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F02C7/25—Fire protection or prevention
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/26—Manufacture essentially without removing material by rolling
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to the manufacture of a thermomechanical part of circular revolution comprising a titanium-based carrier substrate coated with steel or superalloy.
  • It relates more particularly to the production of a titanium fire resistant compressor casing.
  • a high-pressure axial compressor comprising such a housing and an aircraft engine, such as an aircraft turbojet engine equipped with such a housing.
  • titanium fire results from the fact that undesired friction occurs between a moving part, for example a moving blade, made of titanium of the compressor and a fixed titanium part of the compressor. This unwanted friction can result in local overheating of at least one of the parts in contact: moving blade or fixed part, which results in a volume combustion of the titanium alloy.
  • the temperature of the liquid material (titanium or titanium alloy) in combustion can reach 2700 ° C. either locally at the level of the friction zone or inside the combustion titanium particles which have been projected into the compressor's vein since the friction zone.
  • crankcase thermal protection techniques are either draconian
  • the object of the invention is then to propose a solution that makes it possible to protect a turbomachine compressor casing against any titanium fire that may occur, while largely preserving the advantages of titanium or its components.
  • conventional alloys high mechanical strength and low density).
  • the subject of the invention is a method for manufacturing a thermomechanical part of circular revolution comprising a titanium or titanium alloy substrate coated with a steel or superalloy, characterized in that the following steps are carried out: : a / production of a rough blank titanium or titanium alloy in a generally circular shape at the ready of the shape and outer sides of the workpiece, b / realization of a rough blank of steel or alloy of incombustible titanium steel or incombustible superalloy in combustion in a generally circular shape of smaller diameter (s) than the circular blank made of titanium or titanium alloy and at most close to the shape and inside ribs of the part to be manufactured, c / machining, at the inner edges of the part to be manufactured, the inner surface of the blank of steel or alloy steel or superalloy, d / assembly with interlocking of the blank steel or alli age of steel or superalloy in the blank in titanium or titanium alloy, e / explosion plating of the blank of steel or alloy steel or superalloy on the
  • a plating is carried out using explosives whose load and location are judiciously chosen to create corrugations resistant to thermomechanical cycles suffered by the part subsequently.
  • the technique used is that of an explosion plating of two plates but suitably adapted to blanks of generally circular shape and with a titanium or titanium alloy bearing material and a plating material made of steel or alloy steel or superalloy.
  • the usual technique of explosion plating is described for example in the publication entitled “Recent Developments in Characterization of a Titanium-Steel Explosion Bond Interface” published in “Processings of reactive Metals in Corrosive Applications” OR, Sept. 1999, pp 89-98 and made by the authors Wah Chang, Albany.
  • the technique used can also be a DETACLAD0 explosion plating process.
  • the solution according to the invention is an effective response to titanium fire while retaining the majority of the intrinsic advantage of titanium, namely a low density and a high mechanical strength, for the carrier structure.
  • the superalloy (s) according to the invention may advantageously be based on cobalt or nickel.
  • step a / is carried out by beta or alpha-beta forging of a titanium alloy.
  • step b / is carried out by pre-rolling or rolling a sheet or by a spun-welded technique of steel or alloy steel or superalloy.
  • the invention also relates to a casing comprising at least one part constituting the supporting structure of rows of stationary blades and an inner wall delimiting the outer contour of a compressor stream in which are rotated rows of blades interposed individually.
  • thermal protection means against burning titanium characterized in that it comprises over at least a part of its length, as a bearing structure, a piece of titanium or titanium alloy on which is plated a thickness of steel or alloy steel or incombustible superalloy to burning titanium, the thickness of steel or alloy steel or superalloy constituting the thermal protection means and the inner wall delimiting the outer contour of the compressor stream.
  • the preferred material for the inner thickness of steel or steel alloy is selected from Inconel® 909 or Inconel® 783.
  • a particularly advantageous titanium alloy is selected from Ti 6 4, Ti 6242 or Ti 6246.
  • the plated part may have a length corresponding to only a portion of the annular length of the housing.
  • a wear material adapted to define the external contour of the vein may be fixed on a titanium or titanium alloy portion.
  • This wear material constitutes the abradable blades, that is to say a material capable of being leveled or eroded by the friction of the blade heads rotating against the housing.
  • the invention also relates to a high-pressure axial compressor comprising, as a stator, a housing as defined above.
  • the length of the casing constitutes only the upstream part of the compressor, the inner wall delimiting the external contour of the downstream vein being made of titanium or titanium alloy.
  • the invention finally relates to an aircraft engine comprising a compressor referred to above.
  • FIG. 1 is a longitudinal sectional view of a high-pressure axial compressor of an aircraft turbojet according to the invention
  • FIG. 2 is a perspective view of a step of the method of manufacturing a thermomechanical part of circular revolution according to the invention
  • FIG. 3 is a diagrammatic cross-sectional view of a compressor casing obtained according to FIG. method of the invention.
  • FIG. 1 shows a high-pressure compressor 1 of a new-generation turbojet, that is to say at high pressures at the inlet E.
  • This type of compressor 1 comprises a first row of stationary vanes 2 for rectifying the gas upstream of a first row of moving blades 3. All the blades 2, 3 are made of titanium or titanium alloy. During operation of the turbojet engine, there remains a risk of severe contact by friction between the foot 20 of the blades 2 and the blade. foot 30 of the blades 3 in the zone Z illustrated in FIG.
  • This risk of severe contact by friction can lead to the combustion of titanium in this zone Z. It is then necessary to prevent burning titanium particles from propagating the combustion to the outer casing 10. Indeed, such particles can be expelled in the vein of the gases 4 and consequently come into contact with the outer casing 10.
  • the risk of contact is greater with the upstream part thereof which extends over a certain length L.
  • This length L is the distance between two points, one of which marks the inversion of the slopes in the profile of the casing and the other is a joint plane with the downstream structure of the HP compressor which becomes a gas-veined superalloy structure.
  • this outer casing 10 is made exclusively of titanium or titanium alloy, a titanium fire can be created and therefore spread to all other parts constituting the turbojet engine.
  • an outer casing 10 is produced from a part whose external thickness 11 is made of titanium or titanium alloy and on which is plated an internal thickness 12 made of steel or steel alloy. or incombustible superalloy with burning titanium.
  • the internal thickness 12 made of steel or steel alloy or incombustible incombustible superalloy with burning titanium thus constitutes a kind of thermal barrier to the supporting structure against any titanium particle in question. combustion likely to come in this part L of the housing 10.
  • the inner wall 12 of the casing delimiting the outer contour 40 of the compressor stream 4 is thus constituted by the thickness of steel or steel alloy or superalloy.
  • the outer thickness 11 is titanium alloy Ti 6.4.
  • the internal plating thickness 12 is made of a low coefficient of expansion alloy such as inconelE 909 or 783.
  • a hot conversion is preferably carried out by beta or alpha-beta forging of a rough blank 11 'of titanium alloy Ti 6.4 by placing it in the form of a truncated cone.
  • the internal surface of the cone frustum 12 'of steel alloy or alloy steel or superalloy is then machined to the inner ribs of the casing 10 to be obtained.
  • the truncated cone 12 ' is then made of alloy steel or alloy steel or superalloy in the truncated cone 11 'titanium alloy.
  • the two cone frustums 11 ', 12' are then nested one in the other, for example, according to the assembly step of the DETACLAD0 explosion cladding technique. This assembly is performed in order to allow optimized operating conditions for the subsequent explosion plating.
  • a number of suitable explosive beads 13 are then placed on the inner surface of the cone frustum of steel alloy or steel alloy or superalloy 12 '.
  • the tooling 14 is reusable as desired for other embodiments of explosive cladding.
  • thermomechanical piece of circular revolution is obtained whose density is between
  • the outer casing 10 plated according to the invention makes it possible to maintain a carrier structure 11 made of titanium alloy (Ti 6 4, 6242 or 6246, for example) protected from the risks of titanium fire by the internal thickness 12.
  • the internal thickness of steel or steel alloy or superalloy is a kind of part of the carrier structure and also contributes to the mechanical strength of the housing. Indeed, the circumferential corrugations due to the shock waves of the explosion at the interface between the titanium alloy thickness and the alloy steel or alloy steel or superalloy thickness improves the mechanical strength of the housing in the axial direction.
  • the invention as described makes it possible to: A / protect the vein of the high-pressure compressors by means of a non-combustible titanium fire alloy, B / make the external part or bearing structure with a titanium alloy out of the zone potentially affected by titanium fire,
  • C / maintain a much lower mass compared to crankcase solutions made completely of steel or alloy steel or superalloy.
  • a outer casing 10 using as internal plated thickness of the InconelE 909 of the order of 1 to 2 mm, as performed on the length L in the illustrated embodiment, having a weight of less than about 10 kg compared to a casing of identical shape and dimensions completely made of InconelE 909.
  • the "average" density of the casing according to the invention is equivalent to that of a casing of titanium-derived alloys known to be anti-fire.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a novel method for making a compressor casing that is resistant to titanium fire (burning titanium). The method of the invention comprises carrying out a plating by exploding a circular preform (12’), made of steel or a steel alloy or a superalloy that is incombustible to titanium fire, against a circular preform (H’) made of titanium or a titanium alloy.

Description

PROCEDE DE FABRICATION D'UNE PIECE THERMOMECANIQUE DE REVOLUTION CIRCULAIRE COMPORTANT UN SUBSTRAT PORTEUR METHOD FOR MANUFACTURING A CIRCULAR REVOLUTION THERMOMECHANICAL PIECE COMPRISING A CARRIER SUBSTRATE
A BASE DE TITANE REVETU D'ACIER OU SUPERALLIAGE, CARTER DE COMPRESSEUR DE TURBOMACHINE RESISTANT AU FEU DE TITANE OBTENU SELON CE PROCEDEBASED ON TITANIUM COATED WITH STEEL OR SUPERALLIATION, TITANIUM FIRE RESISTANT TURBOMACHINE COMPRESSOR CASING OBTAINED ACCORDING TO SAID METHOD
DESCRIPTIONDESCRIPTION
DOMAINE TECHNIQUETECHNICAL AREA
L'invention concerne la fabrication d'une pièce thermomécanique de révolution circulaire comportant un substrat porteur à base de titane revêtu d'acier ou superalliage.The invention relates to the manufacture of a thermomechanical part of circular revolution comprising a titanium-based carrier substrate coated with steel or superalloy.
Elle concerne plus particulièrement la réalisation d'un carter de compresseur résistant au feu de titane.It relates more particularly to the production of a titanium fire resistant compressor casing.
Elle concerne également un compresseur axial haute-pression comprenant un tel carter et un moteur d'aéronef, tel qu'un turboréacteur d'avion équipé d'un tel carter.It also relates to a high-pressure axial compressor comprising such a housing and an aircraft engine, such as an aircraft turbojet engine equipped with such a housing.
ART ANTÉRIEURPRIOR ART
Dans une turbomachine telle qu'un turboréacteur d'avion, les carters de compresseur haute-pression doivent montrer leur capacité à résister au feu dit « feu de titane ». Un tel feu de titane provient du fait qu'un frottement non souhaité apparaît entre une pièce mobile, par exemple une aube mobile, en titane du compresseur et une partie fixe en titane du compresseur. Ce frottement non souhaité peut entraîner une surchauffe locale au moins de l'une des parties en contacts : aube mobile ou partie fixe, qui se traduit par une combustion volumique de l'alliage de titane. La température du matériau liquide (titane ou alliage de titane) en combustion peut atteindre les 27000C soit localement au niveau de la zone de frottement, soit à l'intérieur des particules de titane en combustion qui sont projetées dans la veine du compresseur depuis la zone de frottement. En conséquence, les points de fusion de la matière environnante mise en contact avec le titane liquide sont dépassés, ce qui génère ainsi du combustible à la structure. Ce phénomène est entretenu par des pressions et des débits d'oxygène importants, qui sont rencontrés dès l'entrée de veine pour des compresseurs haute pression modernes. Ainsi, dans le cas de turboréacteurs nouvelles génération nécessitant des fortes pressions à l'entrée du compresseur axial haute-pression, le risque potentiel de frottement pouvant conduire à la combustion de titane existe, par exemple entre la première rangée d'aubes fixes et le bec formé par la partie inférieure des aubes mobiles. Par la suite, les particules en combustion peuvent être projetées dans la veine de compresseur et atteindre le carter externe. Dans le passé, des feux de titane ont été jusqu'à traverser des parois entières de carters avec les conséquences dommageables qui s'en suivent. Ces conséquences sont d' autant plus dommageables que le feu de titane ne peut s'éteindre que de lui-même lors du fonctionnement d'un turboréacteur en fonctionnement. Pour protéger les carters de compresseur des feux de titane, différentes solutions ont déjà été proposées.In a turbomachine such as an aircraft turbojet engine, the high-pressure compressor casings must show their ability to withstand the fire called "titanium fire". Such a titanium fire results from the fact that undesired friction occurs between a moving part, for example a moving blade, made of titanium of the compressor and a fixed titanium part of the compressor. This unwanted friction can result in local overheating of at least one of the parts in contact: moving blade or fixed part, which results in a volume combustion of the titanium alloy. The temperature of the liquid material (titanium or titanium alloy) in combustion can reach 2700 ° C. either locally at the level of the friction zone or inside the combustion titanium particles which have been projected into the compressor's vein since the friction zone. As a result, the melting points of the surrounding material contacted with the liquid titanium are exceeded, thereby generating fuel to the structure. This phenomenon is maintained by high pressures and oxygen flow rates, which are encountered at the vein inlet for modern high-pressure compressors. Thus, in the case of new-generation turbojet engines requiring high pressures at the inlet of the high-pressure axial compressor, the potential risk of friction that may lead to the combustion of titanium exists, for example between the first row of blades and the blade. beak formed by the lower part of the blades. Subsequently, the burning particles can be thrown into the compressor vein and reach the outer casing. In the past, titanium fires have gone through entire casing walls with the damaging consequences that follow. These consequences are all the more damaging that the titanium fire can only extinguish itself when operating a turbojet engine in operation. To protect the compressor housings of titanium fires, various solutions have already been proposed.
Certaines techniques de protection thermique de carter utilisées sont soit draconiennesSome crankcase thermal protection techniques used are either draconian
(suppression des alliages à base de titane et remplacement par des acier ou alliage d'acier ou superalliages ou des bases nickel ou d'autres matériaux) , soit sophistiquées (mise en places de liners spécifiques sur le carter à base de titane ou d'alliage en titane, protections thermiques réalisées par plasma, traitement des surfaces potentiellement en contact au cours du fonctionnement moteur) . On peut citer en tant que couches-liners de protections thermiques les solutions décrites dans les brevets FR 2 560 640 et FR 2 560 641. Quoi qu'il en soit, ces solutions s'avèrent lourdes, encombrantes et parfois limitées dans le temps, c'est-à-dire non compatibles avec les durées de vie de turbomachine, telles qu'un turboréacteur d'avion.(removal of titanium-based alloys and replacement with steel or alloy steel or super alloys or nickel bases or other materials), or sophisticated (placement of specific liners on the housing based on titanium or titanium alloy, thermal protections made by plasma, treatment of surfaces potentially in contact during engine operation). As thermal barrier layers, the solutions described in patents FR 2 560 640 and FR 2 560 641 may be mentioned. However, these solutions prove to be cumbersome, cumbersome and sometimes limited in time, that is to say, not compatible with the life of the turbomachine, such as an aircraft turbojet.
La littérature fait aussi état d'alliages de titane peu combustible, mais de masse volumique plus élevée que celle des alliages standards. Aucun des ces solutions à base d'alliage dit peu combustible n'a réellement été validée aujourd'hui.The literature also reports titanium alloys that are not very combustible but have a higher density than standard alloys. None of these low-alloy alloy solutions has actually been validated today.
Le but de l'invention est alors de proposer une solution qui permette de protéger un carter de compresseur de turbomachine de tout feu de titane susceptible de se produire, tout en conservant en grande partie les avantages du titane ou de ses alliages conventionnels (résistance mécanique importante et faible masse volumique) .The object of the invention is then to propose a solution that makes it possible to protect a turbomachine compressor casing against any titanium fire that may occur, while largely preserving the advantages of titanium or its components. conventional alloys (high mechanical strength and low density).
EXPOSÉ DE L' INVENTIONSTATEMENT OF THE INVENTION
A cet effet, l'invention a pour objet un procédé de fabrication d'une pièce thermomécanique de révolution circulaire comprenant un substrat porteur en titane ou alliage de titane revêtu d'un acier ou superalliage, caractérisé en ce qu'on réalise les étapes suivantes : a/ réalisation d'une ébauche brute en titane ou alliage de titane sous une forme générale circulaire au plus prêt de la forme et des côtes extérieures de la pièce à fabriquer, b/ réalisation d'une ébauche brute en acier ou alliage d'acier ou superalliage incombustible au titane en combustion sous une forme générale circulaire de diamètre (s) inférieur (s) à l'ébauche circulaire en titane ou alliage de titane et au plus prêt de la forme et des côtes intérieures de la pièce à fabriquer, c/ usinage, aux côtes intérieures de la pièce à fabriquer, de la surface intérieure de l'ébauche en acier ou alliage d'acier ou superalliage, d/ assemblage avec emboitement de l'ébauche en acier ou alliage d'acier ou superalliage dans l'ébauche en titane ou alliage de titane, e/ placage par explosion de l'ébauche en acier ou alliage d'acier ou superalliage sur l'ébauche en titane ou alliage de titane dans des conditions opératoires telles que les ondulations créées à l'interface sont dépourvues de phases fragiles au cours des cycles thermomécaniques subis ultérieurement par la pièce .For this purpose, the subject of the invention is a method for manufacturing a thermomechanical part of circular revolution comprising a titanium or titanium alloy substrate coated with a steel or superalloy, characterized in that the following steps are carried out: : a / production of a rough blank titanium or titanium alloy in a generally circular shape at the ready of the shape and outer sides of the workpiece, b / realization of a rough blank of steel or alloy of incombustible titanium steel or incombustible superalloy in combustion in a generally circular shape of smaller diameter (s) than the circular blank made of titanium or titanium alloy and at most close to the shape and inside ribs of the part to be manufactured, c / machining, at the inner edges of the part to be manufactured, the inner surface of the blank of steel or alloy steel or superalloy, d / assembly with interlocking of the blank steel or alli age of steel or superalloy in the blank in titanium or titanium alloy, e / explosion plating of the blank of steel or alloy steel or superalloy on the titanium or titanium alloy blank under operating conditions such as that the ripples created at the interface are devoid of fragile phases during thermomechanical cycles subsequently suffered by the part.
Selon l'invention, on réalise un placage à l'aide d'explosifs dont la charge et l'emplacement sont judicieusement choisis pour créer des ondulations résistantes aux cycles thermomécaniques subis par la pièce ultérieurement .According to the invention, a plating is carried out using explosives whose load and location are judiciously chosen to create corrugations resistant to thermomechanical cycles suffered by the part subsequently.
La technique utilisée est celle d'un plaquage par explosion de deux plaques mais adaptée judicieusement à des ébauches de forme générale circulaire et avec un matériau porteur en titane ou alliage de titane et un matériau de placage en acier ou alliage d'acier ou superalliage. La technique usuelle de plaquage par explosion est décrite par exemple dans la publication intitulée « Récent Developments in Characterization of a Titanium-Steel Explosion Bond Interface » publiée dans « Processings of reactive Metals in Corrosive Applications » OR, Sept. 1999, pp 89-98 et faite par les auteurs Wah Chang, Albany. La technique utilisée peut également être un procédé de placage par explosion DETACLAD0.The technique used is that of an explosion plating of two plates but suitably adapted to blanks of generally circular shape and with a titanium or titanium alloy bearing material and a plating material made of steel or alloy steel or superalloy. The usual technique of explosion plating is described for example in the publication entitled "Recent Developments in Characterization of a Titanium-Steel Explosion Bond Interface" published in "Processings of reactive Metals in Corrosive Applications" OR, Sept. 1999, pp 89-98 and made by the authors Wah Chang, Albany. The technique used can also be a DETACLAD0 explosion plating process.
La solution selon l'invention constitue une réponse efficace au feu de titane tout en conservant la majorité de l'avantage intrinsèque du titane, à savoir une faible masse volumique et une résistance mécanique importante, pour la structure porteuse.The solution according to the invention is an effective response to titanium fire while retaining the majority of the intrinsic advantage of titanium, namely a low density and a high mechanical strength, for the carrier structure.
Le (s) superalliage (s) selon l'invention pourront être avantageusement à base de cobalt ou de nickel . Selon une caractéristique avantageuse de l'invention, on réalise l'étape a/ par forgeage béta ou alpha-béta d'un alliage de titane.The superalloy (s) according to the invention may advantageously be based on cobalt or nickel. According to an advantageous characteristic of the invention, step a / is carried out by beta or alpha-beta forging of a titanium alloy.
Selon une autre caractéristique avantageuse, on réalise l'étape b/ par prélaminage ou par roulage d'une tôle ou par une technique de filé- roulé-soudé d'acier ou alliage d'acier ou superalliage.According to another advantageous characteristic, step b / is carried out by pre-rolling or rolling a sheet or by a spun-welded technique of steel or alloy steel or superalloy.
Ainsi, selon l'invention, on peut utiliser des aciers ou alliages d'acier ou superalliages déjà existants et qui sont incombustibles au titane en combustion. Ces acier ou alliages d'acier ou superalliages sont par ailleurs compatibles thermiquement (compatibilité de traitement thermique et coefficient de dilatation proches) avec le titane ou les alliages à base de titane également déjà existants dans la réalisation de carters de compresseurs, en particulier les compresseurs haute-pression de turboréacteur .Thus, according to the invention, it is possible to use existing steels or alloys of steel or superalloys that are incombustible with burning titanium. These steel or alloys of steel or superalloys are moreover thermally compatible (heat treatment compatibility and expansion coefficient close) with titanium or titanium-based alloys already already existing in the production of compressor housings, in particular compressors. high-pressure turbojet.
L' invention concerne également un carter comprenant au moins une partie constituant la structure porteuse de rangées d' aubes fixes et une paroi interne délimitant le contour externe d'une veine de compresseur dans laquelle sont montées en rotation des rangées d'aubes mobiles intercalées individuellement avec les rangées d'aubes fixes et, des moyens de protection thermique contre du titane en combustion caractérisé en ce qu' il comprend sur au moins une partie de sa longueur, en tant que structure porteuse, une pièce en titane ou alliage de titane sur laquelle est plaquée une épaisseur en acier ou alliage d'acier ou superalliage incombustible au titane en combustion, l'épaisseur d'acier ou alliage d'acier ou superalliage constituant les moyens de protection thermique et la paroi interne délimitant le contour externe de la veine de compresseur. Le matériau préféré pour l'épaisseur interne en acier ou alliage d'acier est choisi parmi l'Inconel® 909 ou l'Inconel® 783.The invention also relates to a casing comprising at least one part constituting the supporting structure of rows of stationary blades and an inner wall delimiting the outer contour of a compressor stream in which are rotated rows of blades interposed individually. with the rows of vanes and, thermal protection means against burning titanium characterized in that it comprises over at least a part of its length, as a bearing structure, a piece of titanium or titanium alloy on which is plated a thickness of steel or alloy steel or incombustible superalloy to burning titanium, the thickness of steel or alloy steel or superalloy constituting the thermal protection means and the inner wall delimiting the outer contour of the compressor stream. The preferred material for the inner thickness of steel or steel alloy is selected from Inconel® 909 or Inconel® 783.
Un alliage de titane particulièrement avantageux est choisi parmi le Ti 6 4, Ti 6242 ou Ti 6246.A particularly advantageous titanium alloy is selected from Ti 6 4, Ti 6242 or Ti 6246.
Selon une variante, la pièce plaquée peut avoir une longueur correspondant à seulement à une partie de la longueur annulaire du carter.Alternatively, the plated part may have a length corresponding to only a portion of the annular length of the housing.
Sur le diamètre interne de la pièce plaquée ou en aval de la longueur sur laquelle elle est fixée, un matériau d'usure adapté pour définir le contour externe de la veine peut être fixé sur une partie en titane ou en alliage de titane. Ce matériau d'usure constitue l'abradable des aubes mobiles, c'est-à-dire un matériau susceptible d'être arasé ou érodé par le frottement des têtes d'aubes en rotation contre le carter .On the internal diameter of the plated piece or downstream of the length on which it is fixed, a wear material adapted to define the external contour of the vein may be fixed on a titanium or titanium alloy portion. This wear material constitutes the abradable blades, that is to say a material capable of being leveled or eroded by the friction of the blade heads rotating against the housing.
L' invention concerne également un compresseur axial haute-pression comprenant, en tant que stator, un carter tel que défini précédemment.The invention also relates to a high-pressure axial compressor comprising, as a stator, a housing as defined above.
Selon un mode de réalisation avantageux, la longueur du carter constitue uniquement la partie amont du compresseur, la paroi interne délimitant le contour externe de la veine en aval étant réalisée en titane ou alliage de titane. L' invention concerne enfin un moteur d'aéronef comprenant un compresseur visé ci-dessus.According to an advantageous embodiment, the length of the casing constitutes only the upstream part of the compressor, the inner wall delimiting the external contour of the downstream vein being made of titanium or titanium alloy. The invention finally relates to an aircraft engine comprising a compressor referred to above.
BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS
D'autres caractéristiques et avantages de l'invention ressortiront mieux à la lecture de la description détaillée ci-dessous faite en référence aux figures suivantes parmi lesquelles :Other characteristics and advantages of the invention will emerge more clearly on reading the detailed description below made with reference to the following figures among which:
- la figure 1 est une vue en coupe longitudinale d'un compresseur axial haute-pression d'un turboréacteur d'avion selon l'invention,FIG. 1 is a longitudinal sectional view of a high-pressure axial compressor of an aircraft turbojet according to the invention,
- la figure 2 est une vue en perspective d'une étape du procédé de fabrication d'une pièce thermomécanique de révolution circulaire selon 1' invention, - la figure 3 est une vue schématique en coupe transversale d'un carter de compresseur obtenu selon le procédé de l'invention.FIG. 2 is a perspective view of a step of the method of manufacturing a thermomechanical part of circular revolution according to the invention; FIG. 3 is a diagrammatic cross-sectional view of a compressor casing obtained according to FIG. method of the invention.
EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERSDETAILED PRESENTATION OF PARTICULAR EMBODIMENTS
Sur la figure 1, on a représenté un compresseur haute-pression 1 d'un turboréacteur de nouvelle génération, c'est-à-dire à fortes pressions à l'entrée E.FIG. 1 shows a high-pressure compressor 1 of a new-generation turbojet, that is to say at high pressures at the inlet E.
Ce type de compresseur 1 comprend une première rangée d'aubes fixes 2 de redressement du gaz en amont d'une première rangée d'aubes mobiles 3. Toutes les aubes 2, 3 sont réalisées en titane ou alliage de titane. Lors du fonctionnement du turboréacteur, il subsiste un risque de contact sévère par frottement entre le pied 20 des aubes fixes 2 et le pied 30 des aubes mobiles 3 dans la zone Z illustrée en figure 1.This type of compressor 1 comprises a first row of stationary vanes 2 for rectifying the gas upstream of a first row of moving blades 3. All the blades 2, 3 are made of titanium or titanium alloy. During operation of the turbojet engine, there remains a risk of severe contact by friction between the foot 20 of the blades 2 and the blade. foot 30 of the blades 3 in the zone Z illustrated in FIG.
Ce risque de contact sévère par frottement peut conduire à la mise en combustion du titane dans cette zone Z. Il faut alors éviter que des particules de titane en combustion viennent propager la combustion au carter externe 10. En effet, de telles particules peuvent être expulsées dans la veine des gaz 4 et en conséquence venir en contact avec le carter externe 10. Le risque de contact est plus grand avec la partie amont de celui-ci 10 qui s'étend sur une certaine longueur L. Cette longueur L est la distance entre deux points dont l'un marque l'inversion des pentes dans le profil du carter et l'autre est un plan de joint avec la structure aval du compresseur HP qui devient une structure en superalliage en veine gazeuse.This risk of severe contact by friction can lead to the combustion of titanium in this zone Z. It is then necessary to prevent burning titanium particles from propagating the combustion to the outer casing 10. Indeed, such particles can be expelled in the vein of the gases 4 and consequently come into contact with the outer casing 10. The risk of contact is greater with the upstream part thereof which extends over a certain length L. This length L is the distance between two points, one of which marks the inversion of the slopes in the profile of the casing and the other is a joint plane with the downstream structure of the HP compressor which becomes a gas-veined superalloy structure.
Si ce carter externe 10 est constitué exclusivement en titane ou en alliage de titane, un feu de titane peut donc être créé et donc se propager à l'ensemble des autres pièces constituant le turboréacteur .If this outer casing 10 is made exclusively of titanium or titanium alloy, a titanium fire can be created and therefore spread to all other parts constituting the turbojet engine.
Pour éviter cela, selon l'invention, on réalise un carter externe 10 à partir d'une pièce dont l'épaisseur externe 11 est en titane ou alliage de titane et sur laquelle est plaquée une épaisseur interne 12 en acier ou alliage d'acier ou superalliage incombustible au titane en combustion. L'épaisseur interne 12 en acier ou alliage d'acier ou superalliage incombustible au titane en combustion constitue ainsi en quelque sorte une barrière thermique à la structure porteuse contre n' importe quelle particule du titane en combustion susceptible de venir dans cette partie L du carter 10.To avoid this, according to the invention, an outer casing 10 is produced from a part whose external thickness 11 is made of titanium or titanium alloy and on which is plated an internal thickness 12 made of steel or steel alloy. or incombustible superalloy with burning titanium. The internal thickness 12 made of steel or steel alloy or incombustible incombustible superalloy with burning titanium thus constitutes a kind of thermal barrier to the supporting structure against any titanium particle in question. combustion likely to come in this part L of the housing 10.
La paroi interne 12 du carter délimitant le contour externe 40 de la veine de compresseur 4 est ainsi constituée par l'épaisseur en acier ou alliage d'acier ou superalliage.The inner wall 12 of the casing delimiting the outer contour 40 of the compressor stream 4 is thus constituted by the thickness of steel or steel alloy or superalloy.
Dans le mode de réalisation illustré, l'épaisseur externe 11 est en alliage de titane Ti 6.4.In the illustrated embodiment, the outer thickness 11 is titanium alloy Ti 6.4.
L'épaisseur interne 12 de plaquage est en alliage à bas coefficient de dilatation tel que l'inconelE 909 ou le 783.The internal plating thickness 12 is made of a low coefficient of expansion alloy such as inconelE 909 or 783.
Selon l'invention, pour obtenir le carterAccording to the invention, to obtain the housing
10 selon l'invention, on procède comme suit :According to the invention, the procedure is as follows:
Tout d'abord, on réalise une transformation à chaud de préférence par forgeage beta ou alpha-beta d'une ébauche brute 11' en alliage de titane Ti 6.4 en le mettant sous la forme d'un tronc de cône. L'ébaucheFirst of all, a hot conversion is preferably carried out by beta or alpha-beta forging of a rough blank 11 'of titanium alloy Ti 6.4 by placing it in the form of a truncated cone. The draft
11' est réalisée au plus prêt de la forme extérieure et des côtes extérieures du carter 10. On réalise en parallèle une ébauche brute11 'is made closer to the outer shape and outer sides of the housing 10. In parallel a rough rough
12' en alliage d'acier InconelE 909 sous la forme également d'un tronc de cône de diamètre inférieur à la à celui 11' en Ti 6.4. L'ébauche 12' est réalisée au plus prêt de la forme intérieure et des côtes intérieures du carter 10.12 'steel alloy InconelE 909 also in the form of a truncated cone diameter smaller than that 11' Ti 6.4. The blank 12 'is made closer to the inner shape and inner sides of the housing 10.
On usine alors la surface interne du tronc de cône 12' en alliage d'acier ou alliage d'acier ou superalliage aux côtes intérieures du carter 10 à obtenir . On emboite alors le tronc de cône 12' en alliage d'acier ou alliage d'acier ou superalliage dans le tronc de cône 11' en alliage de titane. On assemble alors les deux troncs de cône 11', 12' emboités l'un dans l'autre par exemple selon l'étape d'assemblage de la technique de placage par explosion DETACLAD0. Cet assemblage est réalisé afin de permettre des conditions opératoires optimisées pour le placage par explosion ultérieur .The internal surface of the cone frustum 12 'of steel alloy or alloy steel or superalloy is then machined to the inner ribs of the casing 10 to be obtained. The truncated cone 12 'is then made of alloy steel or alloy steel or superalloy in the truncated cone 11 'titanium alloy. The two cone frustums 11 ', 12' are then nested one in the other, for example, according to the assembly step of the DETACLAD0 explosion cladding technique. This assembly is performed in order to allow optimized operating conditions for the subsequent explosion plating.
Comme montré sur la figure 2, on place alors un certain nombre de cordons d'explosifs 13 appropriés sur la surface intérieure du tronc de cône en alliage d'acier ou alliage d'acier ou superalliage 12' .As shown in FIG. 2, a number of suitable explosive beads 13 are then placed on the inner surface of the cone frustum of steel alloy or steel alloy or superalloy 12 '.
On enferme le tout dans un outillage 13 de forme adaptée à la forme extérieure du carter 10 et susceptible de résister à l'explosion ultérieureIt encloses the whole in a tool 13 of shape adapted to the outer shape of the housing 10 and likely to withstand the subsequent explosion
(figure 2) . L'outillage 14 est réutilisable à souhait pour d'autres réalisations de placage par explosion.(Figure 2). The tooling 14 is reusable as desired for other embodiments of explosive cladding.
On procède alors à l'étape proprement dite de placage par explosion de l'alliage d'acier ou alliage d'acier ou superalliage sur l'épaisseur de titane. Cette étape est avantageusement réalisée conformément au procédé DETACLAD0.This is followed by the actual step of exploding the alloy steel or alloy steel or superalloy on the titanium thickness. This step is advantageously carried out in accordance with the DETACLAD0 process.
Grâce au procédé selon l'invention, on obtient une pièce thermomécanique de révolution circulaire dont la masse volumique est comprise entreWith the method according to the invention, a thermomechanical piece of circular revolution is obtained whose density is between
4,7 et 5,8 kg/dm3.4.7 and 5.8 kg / dm 3 .
Pour l'application au carter de turboréacteur, on peut réaliser grâce au procédé, un carter 10 d'épaisseur finale de l'ordre de 1 à 2 mm. Pour finir la pièce thermomécanique de révolution circulaire 11', 12' obtenue selon le procédé de l'invention et parvenir au carter 10, on procède aux étapes de contrôles et de finition utilisées classiquement dans la fabrication des carters de compresseur de turboréacteur. Le carter externe 10 plaqué selon l'invention permet de conserver une structure porteuse 11 en alliage de titane (Ti 6 4 ,6242 ou 6246, par exemple) protégée des risques de feu de titane par l'épaisseur interne 12. En outre, grâce au procédé de plaquage par explosion circulaire selon l'invention, l'épaisseur interne en acier ou alliage d' acier ou superalliage constitue en quelque sorte une partie de la structure porteuse et participe également à la tenue mécanique du carter. En effet, les ondulations circonférentielles dues aux ondes de choc de l'explosion à l'interface entre l'épaisseur en alliage de titane et l'épaisseur en alliage d'acier ou alliage d'acier ou superalliage améliore la tenue mécanique du carter dans le sens axial.For the application to the turbojet casing, it is possible by means of the method to produce a casing 10 with a final thickness of the order of 1 to 2 mm. To finish the thermomechanical part of circular revolution 11 ', 12' obtained according to the method of the invention and to reach the casing 10, one proceeds to the control and finishing steps conventionally used in the manufacture of turbojet compressor casings. The outer casing 10 plated according to the invention makes it possible to maintain a carrier structure 11 made of titanium alloy (Ti 6 4, 6242 or 6246, for example) protected from the risks of titanium fire by the internal thickness 12. In the circular explosion plating method according to the invention, the internal thickness of steel or steel alloy or superalloy is a kind of part of the carrier structure and also contributes to the mechanical strength of the housing. Indeed, the circumferential corrugations due to the shock waves of the explosion at the interface between the titanium alloy thickness and the alloy steel or alloy steel or superalloy thickness improves the mechanical strength of the housing in the axial direction.
L' invention telle que décrite permet de : A/ protéger la veine des compresseurs haute-pression grâce à un alliage incombustible au feu de titane, B/ réaliser la partie externe ou structure porteuse avec un alliage de titane hors de la zone potentiellement concernée par le feu de titane,The invention as described makes it possible to: A / protect the vein of the high-pressure compressors by means of a non-combustible titanium fire alloy, B / make the external part or bearing structure with a titanium alloy out of the zone potentially affected by titanium fire,
C/ conserver une masse bien inférieure par rapport à des solutions de carter réalisées complètement en acier ou alliage d'acier ou superalliage. Par exemple, il est permis d'envisager un carter externe 10, utilisant comme épaisseur interne plaquée de l' InconelE 909 de l'ordre de 1 à 2 mm, tel que réalisé sur la longueur L dans le mode de réalisation illustré, ayant un poids moindre d'environ 10 kg par rapport à un carter de forme et de dimensions identiques réalisé totalement en InconelE 909. Ainsi, la masse volumique « moyenne » du carter selon l'invention est équivalente à celle d'un carter en alliages dérivés du titane réputés anti feu. C / maintain a much lower mass compared to crankcase solutions made completely of steel or alloy steel or superalloy. For example, it is permissible to consider a outer casing 10, using as internal plated thickness of the InconelE 909 of the order of 1 to 2 mm, as performed on the length L in the illustrated embodiment, having a weight of less than about 10 kg compared to a casing of identical shape and dimensions completely made of InconelE 909. Thus, the "average" density of the casing according to the invention is equivalent to that of a casing of titanium-derived alloys known to be anti-fire.

Claims

REVENDICATIONS
1. Procédé de fabrication d'une pièce thermomécanique de révolution circulaire comprenant un substrat porteur en titane ou alliage de titane revêtu d'un acier ou superalliage, caractérisé en ce qu'on réalise les étapes suivantes : a/ réalisation d'une ébauche brute en titane ou alliage de titane sous une forme générale circulaire (H') au plus prêt de la forme et des côtes extérieures de la pièce à fabriquer, b/ réalisation d'une ébauche brute en acier ou alliage d'acier ou superalliage incombustible au titane en combustion sous une forme générale circulaire (12') de diamètre (s) inférieur (s) à l'ébauche circulaire en titane ou alliage de titane et au plus prêt de la forme et des côtes intérieures de la pièce à fabriquer, c/ usinage, aux côtes intérieures de la pièce à fabriquer, de la surface intérieure de l'ébauche en acier ou alliage d'acier ou superalliage, d/ assemblage avec emboitement de l'ébauche en acier ou alliage d'acier ou superalliage dans l'ébauche en titane ou alliage de titane, e/ placage par explosion de l'ébauche (12') en acier ou alliage d'acier ou superalliage sur l'ébauche en titane ou alliage de titane (H') dans des conditions opératoires telles que les ondulations créées à l'interface sont dépourvues de phases fragiles au cours des cycles thermomécaniques subis ultérieurement par la pièce. 1. A method of manufacturing a thermomechanical part of circular revolution comprising a titanium-bearing substrate or titanium alloy coated with a steel or superalloy, characterized in that the following steps are carried out: a / production of a rough blank in titanium or titanium alloy in a generally circular shape (H ') in the shape of the outer ribs of the part to be manufactured, b / production of a rough blank of steel or steel alloy or non-combustible superalloy burning titanium in a generally circular shape (12 ') of smaller diameter (s) than the circular blank made of titanium or titanium alloy and at most close to the shape and internal ribs of the part to be manufactured, c / machining, at the inner edges of the workpiece, the inner surface of the steel or alloy steel blank or superalloy, d / assembly with interlocking of the steel or alloy steel blank or superalloy in the blank made of titanium or titanium alloy, e / exploding of the blank (12 ') of steel or alloy steel or superalloy on the blank of titanium or titanium alloy (H') under conditions such as the ripples created at the interface are devoid of fragile phases during the thermomechanical cycles subsequently suffered by the part.
2. Procédé selon la revendication 1, caractérisé en qu'on réalise l'étape a/ par forgeage béta ou alpha-béta d'un alliage de titane.2. Method according to claim 1, characterized in that step a / is carried out by beta or alpha-beta forging of a titanium alloy.
3. Procédé selon la revendication 1 ou 2, caractérisé en qu'on réalise l'étape b/ par prélaminage ou par roulage d'une tôle ou par une technique de filé- roulé-soudé d'un alliage d'acier ou alliage d'acier ou superalliage .3. Method according to claim 1 or 2, characterized in that step b / by pre-rolling or by rolling of a sheet or by a wire-rolled-welded technique of a steel or alloy alloy is carried out. steel or superalloy.
4. Carter (10) comprenant au moins une partie constituant la structure porteuse de rangées d'aubes fixes et une paroi interne délimitant le contour externe (40) d'une veine (4) de compresseur (1) dans laquelle sont montées en rotation des rangées d'aubes mobiles (3) intercalées individuellement avec les rangées d'aubes fixes (2) et, des moyens de protection thermique contre du titane en combustion caractérisé en ce qu' il comprend sur au moins une partie de sa longueur, en tant que structure porteuse, une pièce (11) en titane ou alliage de titane sur laquelle est plaquée une épaisseur (12) en acier ou alliage d'acier ou superalliage incombustible au titane en combustion, l'épaisseur d'acier ou alliage d'acier ou superalliage constituant les moyens de protection thermique et la paroi interne délimitant le contour externe (40) de la veine (4) de compresseur.4. Housing (10) comprising at least one part constituting the structure carrying fixed blade rows and an inner wall delimiting the outer contour (40) of a stream (4) compressor (1) in which are rotatably mounted rows of blades (3) interposed individually with the rows of vanes (2) and thermal protection means against burning titanium characterized in that it comprises over at least a part of its length, in as supporting structure, a piece (11) of titanium or titanium alloy on which is plated a thickness (12) of steel or alloy steel or incombustible superalloy to burning titanium, the thickness of steel or alloy of steel or superalloy constituting the thermal protection means and the inner wall delimiting the outer contour (40) of the compressor stream (4).
5. Carter (10) selon la revendication précédente, caractérisé en ce que l'acier ou alliage d'acier est choisi parmi l'Inconel® 909 ou l'Inconel® 783.5. Carter (10) according to the preceding claim, characterized in that the steel or alloy steel is selected from Inconel® 909 or Inconel® 783.
6. Carter (10) selon la revendication 4 ou 5, caractérisé en ce que l'alliage de titane est choisi parmi le Ti 6 4, Ti 6242 ou Ti 6246.6. Housing (10) according to claim 4 or 5, characterized in that the titanium alloy is selected from Ti 6 4, Ti 6242 or Ti 6246.
7. Carter (10) selon l'une quelconque des revendications 4 à 6, caractérisé en ce que la pièce plaquée a une longueur correspondant à seulement à une partie de la longueur annulaire du carter.7. Carter (10) according to any one of claims 4 to 6, characterized in that the plated part has a length corresponding to only a portion of the annular length of the housing.
8. Carter (10) selon l'une des revendications 4 à 7, caractérisé en ce que sur le diamètre interne de la pièce plaquée ou en aval de la longueur sur laquelle elle est fixée, un matériau d'usure adapté pour définir le contour externe de la veine est fixé sur une partie en titane ou en alliage de titane.8. Carter (10) according to one of claims 4 to 7, characterized in that on the inner diameter of the plated part or downstream of the length on which it is fixed, a wear material adapted to define the contour outer of the vein is attached to a titanium or titanium alloy part.
9. Compresseur axial haute-pression (1) comprenant, en tant que stator, un carter (10) selon l'une quelconque des revendications 4 à 8.9. High-pressure axial compressor (1) comprising, as a stator, a housing (10) according to any one of claims 4 to 8.
10. Compresseur haute-pression (1) selon la revendication précédente, caractérisé en ce que la longueur du carter (L) constitue uniquement la partie amont (10) du compresseur, la paroi interne (14) délimitant le contour externe (40) de la veine (4) en aval étant réalisée en titane ou alliage de titane.10. High-pressure compressor (1) according to the preceding claim, characterized in that the length of the housing (L) is only the upstream portion (10) of the compressor, the inner wall (14) defining the outer contour (40) of the vein (4) downstream being made of titanium or titanium alloy.
11. Moteur d'aéronef comprenant un compresseur selon la revendication 9 ou 10. Aircraft engine comprising a compressor according to claim 9 or 10.
PCT/EP2009/061381 2008-09-05 2009-09-03 Method for making a circular revolution thermomechanical part including a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method WO2010026179A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US13/060,719 US20110211945A1 (en) 2008-09-05 2009-09-03 Method for the manufacture of a circular revolution thermomechanical part including a titanium-based load-bearing substrate lined with steel or superalloy, a turbomachine compressor housing which is resistant to titanium fire obtained according to this method

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0855963 2008-09-05
FR0855963A FR2935625B1 (en) 2008-09-05 2008-09-05 METHOD FOR MANUFACTURING A CIRCULAR REVOLUTION THERMAMECHANICAL PART COMPRISING A STEEL-COATED OR SUPERALLIATION TITANIUM-BASED CARRIER SUBSTRATE, TITANIUM-FIRE RESISTANT TURBOMACHINE COMPRESSOR CASE

Publications (1)

Publication Number Publication Date
WO2010026179A1 true WO2010026179A1 (en) 2010-03-11

Family

ID=40551056

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2009/061381 WO2010026179A1 (en) 2008-09-05 2009-09-03 Method for making a circular revolution thermomechanical part including a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method

Country Status (3)

Country Link
US (1) US20110211945A1 (en)
FR (1) FR2935625B1 (en)
WO (1) WO2010026179A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2978077A1 (en) * 2011-07-22 2013-01-25 Snecma Method for assembling metal shells for high pressure compressor casing of turboshaft engine, involves heating titanium alloy shells to specific temperature to deform one shell such that face of one shell follows face of other shell
FR2978075A1 (en) * 2011-07-22 2013-01-25 Snecma Method for assembling metal shells for high pressure compressor casing of turboshaft engine, involves heating titanium alloy shell to deform shell such that face of shell follows face of another titanium alloy shell
WO2013014369A1 (en) * 2011-07-22 2013-01-31 Snecma Method for assembling a titanium shell and a titanium fire-resistant alloy shell
US11982236B2 (en) 2017-12-22 2024-05-14 General Electric Company Titanium alloy compressor case

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2951198B1 (en) 2009-10-12 2013-05-10 Snecma THERMAL TREATMENTS OF STAINLESS STEEL MARTENSITIC STEELS AFTER REFUSION UNDER DAIRY
FR2951197B1 (en) 2009-10-12 2011-11-25 Snecma HOMOGENIZATION OF STAINLESS STEEL MARTENSITIC STEELS AFTER REFUSION UNDER DAIRY
FR2951196B1 (en) 2009-10-12 2011-11-25 Snecma DEGASTING STAINLESS STEEL MARTENSITIC STEELS BEFORE REFUSAL UNDER DICE
CN106078112B (en) * 2016-07-21 2018-07-20 滁州南钢盛达实业有限公司 A kind of production technology of H profile steel
US11033992B2 (en) * 2018-10-05 2021-06-15 Pratt & Whitney Canada Corp. Double row compressor stators
GB2627785B (en) * 2023-03-01 2025-04-30 Gkn Aerospace Sweden Ab Bimetallic case

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3798011A (en) * 1969-01-31 1974-03-19 Du Pont Multilayered metal composite
US4155680A (en) * 1977-02-14 1979-05-22 General Electric Company Compressor protection means
FR2560640A1 (en) * 1984-03-03 1985-09-06 Mtu Muenchen Gmbh METHOD AND MEANS FOR PREVENTING THE BIRTH OF TITANIUM FIRE
FR2560641A1 (en) * 1984-03-03 1985-09-06 Mtu Muenchen Gmbh INSTALLATION FOR PREVENTING THE EXTENSION OF "TITANIUM FIRE" IN TURBOMACHINES, ESPECIALLY GAS TURBINES OR GAS TURBINES OR TURBOREACTORS
EP0305113A2 (en) * 1987-08-27 1989-03-01 Imi Titanium Limited Rotating or moving metal components and methods of manufacturing such components
EP1002882A1 (en) * 1998-11-11 2000-05-24 Rolls-Royce Plc A beta titanium alloy
EP1059420A1 (en) * 1999-06-10 2000-12-13 Snecma Moteurs Housing for a high pressure compressor
WO2004071763A2 (en) * 2003-02-17 2004-08-26 Sigmabond Technologies Corporation Method of producing metal composite materials comprising incompatible metals
EP1643011A1 (en) * 2004-09-30 2006-04-05 General Electric Company Erosion and wear resistant protective structures for turbine components

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3137937A (en) * 1960-10-26 1964-06-23 Du Pont Explosive bonding
US3434197A (en) * 1964-08-03 1969-03-25 Singer General Precision Explosive welding
US3403889A (en) * 1966-04-07 1968-10-01 Gen Electric Frame assembly having low thermal stresses
US3360848A (en) * 1966-10-17 1968-01-02 Du Pont Process for explosion-bonding metals
US3728780A (en) * 1970-01-24 1973-04-24 Inst Science And Technology Explosive cladding on geometrically non-uniform metal material
US3854891A (en) * 1972-09-25 1974-12-17 Allegheny Ludlum Ind Inc Titanium composite
EP0003078A1 (en) * 1978-01-17 1979-07-25 Imperial Chemical Industries Plc Improvements in and relating to explosive cladding
DE3263845D1 (en) * 1981-03-05 1985-07-04 Asahi Chemical Ind Titanium clad steel plate
DE3926151C1 (en) * 1989-02-28 1990-05-10 Mtu Muenchen Gmbh
US5074970A (en) * 1989-07-03 1991-12-24 Kostas Routsis Method for applying an abrasive layer to titanium alloy compressor airfoils
US5210945A (en) * 1991-05-22 1993-05-18 Ngk Spark Plug Co., Ltd. Method of assembly of a rotary shaft in a ball-bearing type turbocharger
GB9121147D0 (en) * 1991-10-04 1991-11-13 Ici Plc Method for producing clad metal plate
AU1875595A (en) * 1994-02-16 1995-09-04 Sohl, Charles E. Coating scheme to contain molten material during gas turbine engine fires
GB9823267D0 (en) * 1998-10-24 1998-12-16 Hardwick Roy Method of producing a metal composites which can be processed at high temperatures
GB0116988D0 (en) * 2000-08-11 2001-09-05 Rolls Royce Plc A gas turbine engine blade containment assembly
GB0300014D0 (en) * 2003-01-02 2003-02-05 Hardwick Roy Method of producing explosively bonded interfaces which are waveless when using explosives of higher detonation velocity which normally produce waves
WO2005068845A1 (en) * 2004-01-14 2005-07-28 Ishikawajima-Harima Heavy Industries Co., Ltd. Compressor, titanium-made rotor blade, jet engine and titanium-made rotor blade producing method
US7530485B1 (en) * 2006-02-07 2009-05-12 High Energy Metals, Inc. Method for explosive bonding of tubular metal liners
US8950069B2 (en) * 2006-12-29 2015-02-10 Rolls-Royce North American Technologies, Inc. Integrated compressor vane casing
DE102008019296A1 (en) * 2008-04-16 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Process for producing a fire protection for titanium component bodies of an aircraft gas turbine and titanium component body for an aircraft gas turbine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3798011A (en) * 1969-01-31 1974-03-19 Du Pont Multilayered metal composite
US4155680A (en) * 1977-02-14 1979-05-22 General Electric Company Compressor protection means
FR2560640A1 (en) * 1984-03-03 1985-09-06 Mtu Muenchen Gmbh METHOD AND MEANS FOR PREVENTING THE BIRTH OF TITANIUM FIRE
FR2560641A1 (en) * 1984-03-03 1985-09-06 Mtu Muenchen Gmbh INSTALLATION FOR PREVENTING THE EXTENSION OF "TITANIUM FIRE" IN TURBOMACHINES, ESPECIALLY GAS TURBINES OR GAS TURBINES OR TURBOREACTORS
EP0305113A2 (en) * 1987-08-27 1989-03-01 Imi Titanium Limited Rotating or moving metal components and methods of manufacturing such components
EP1002882A1 (en) * 1998-11-11 2000-05-24 Rolls-Royce Plc A beta titanium alloy
EP1059420A1 (en) * 1999-06-10 2000-12-13 Snecma Moteurs Housing for a high pressure compressor
WO2004071763A2 (en) * 2003-02-17 2004-08-26 Sigmabond Technologies Corporation Method of producing metal composite materials comprising incompatible metals
EP1643011A1 (en) * 2004-09-30 2006-04-05 General Electric Company Erosion and wear resistant protective structures for turbine components

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2978077A1 (en) * 2011-07-22 2013-01-25 Snecma Method for assembling metal shells for high pressure compressor casing of turboshaft engine, involves heating titanium alloy shells to specific temperature to deform one shell such that face of one shell follows face of other shell
FR2978075A1 (en) * 2011-07-22 2013-01-25 Snecma Method for assembling metal shells for high pressure compressor casing of turboshaft engine, involves heating titanium alloy shell to deform shell such that face of shell follows face of another titanium alloy shell
WO2013014369A1 (en) * 2011-07-22 2013-01-31 Snecma Method for assembling a titanium shell and a titanium fire-resistant alloy shell
GB2507430A (en) * 2011-07-22 2014-04-30 Snecma Method for assembling a titanium shell and a titanium fire-resistant alloy shell
US11982236B2 (en) 2017-12-22 2024-05-14 General Electric Company Titanium alloy compressor case

Also Published As

Publication number Publication date
FR2935625A1 (en) 2010-03-12
FR2935625B1 (en) 2011-09-09
US20110211945A1 (en) 2011-09-01

Similar Documents

Publication Publication Date Title
WO2010026179A1 (en) Method for making a circular revolution thermomechanical part including a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method
FR2935623A1 (en) METHOD FOR MANUFACTURING CIRCULAR REVOLUTION THERMOMECHANICAL PIECE COMPRISING STEEL-COATED OR SUPERALLIATION TITANIUM-BASED CARRIER SUBSTRATE, TITANIUM-FIRE RESISTANT TURBOMACHINE COMPRESSOR CASE
WO2010026182A1 (en) Method for making a circular revolution thermomechanical part comprising a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method
EP2326845B1 (en) Compressor casing resistant to titanium fire, high pressure compressor including such a casing, and aircraft engine including such a compressor
EP1785651B1 (en) Annular knife edge seal for a labyrinth sealing and its manufacturing method
EP3429784B1 (en) Method for manufacturing a turbine shroud for a turbomachine
EP3429787B1 (en) Process to produde and repair an abradable layer of a turbine ring
EP2418387A1 (en) Shroud ring of an axial turbomachine compressor
FR3059323A1 (en) ASSEMBLY OF A CMC PIECE ASSEMBLED ON A METALLIC ELEMENT, METHOD OF MANUFACTURING SUCH AN ASSEMBLY
EP3469206B1 (en) Rocket motor combustion chamber having variable-composition fins
FR3101642A1 (en) Sealing of a turbine
FR3055820A1 (en) METHOD OF ASSEMBLING METAL SHELLS ONE OF WHICH IS REALIZED BY LASER DEPOT
FR2996475A1 (en) Manufacturing e.g. rotor of turboshaft engine, comprises filling housing with abradable material, heating material, maintaining material at specific temperature until sintering occurs between particles of material, and lowering temperature
EP3466567A1 (en) Method for making a part comprising two different superalloys
FR2979664A1 (en) Annular part for stator of e.g. high-pressure turbine of turboshaft engine of aircraft, has porous abradable material coating covered with additional layer of non-porous refractory material, where additional layer includes lower thickness
EP2903763B1 (en) Method of manufacturing a component covered with an abradable coating
EP3568574B1 (en) Turbine ring assembly
EP4127265B1 (en) Method for manufacturing a titanium fire-resistant metal component by additive manufacturing
FR2996477A1 (en) Manufacturing e.g. casing of compressor in turbojet, comprises providing blank of piece with housing, filling housing with abradable material, plating material in housing by explosion, and subjecting material to thermal heat treatment
FR3151873A1 (en) LABYRINTH SEALING DEVICE FOR A TURBOMACHINE COMPRISING A RETOUCHING LAYER MADE OF CERAMIC MATERIAL
FR3152533A1 (en) CASING FOR AN AIRCRAFT TURBINE OR TURBOMACHINE
FR2978077A1 (en) Method for assembling metal shells for high pressure compressor casing of turboshaft engine, involves heating titanium alloy shells to specific temperature to deform one shell such that face of one shell follows face of other shell
FR3027959A1 (en) FIRE PROTECTION OF A COMPOSITE MATERIAL PART OF A GAS TURBINE
FR3042997A1 (en) PROCESS FOR MAKING A SEALING PART WITH SUPERALLY BODY AND BRASE COATING

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 09811123

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 13060719

Country of ref document: US

122 Ep: pct application non-entry in european phase

Ref document number: 09811123

Country of ref document: EP

Kind code of ref document: A1