EP0513407B1 - Procédé de fabrication d' une aube de turbine - Google Patents

Procédé de fabrication d' une aube de turbine Download PDF

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Publication number
EP0513407B1
EP0513407B1 EP91107707A EP91107707A EP0513407B1 EP 0513407 B1 EP0513407 B1 EP 0513407B1 EP 91107707 A EP91107707 A EP 91107707A EP 91107707 A EP91107707 A EP 91107707A EP 0513407 B1 EP0513407 B1 EP 0513407B1
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EP
European Patent Office
Prior art keywords
hot
process according
blade
casting
carried out
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
EP91107707A
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German (de)
English (en)
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EP0513407A1 (fr
Inventor
Mohamed Dr. Nazmy
Markus Staubli
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.)
ABB Asea Brown Boveri Ltd
ABB AB
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ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Publication date
Priority to EP91107707A priority Critical patent/EP0513407B1/fr
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to DE59106047T priority patent/DE59106047D1/de
Priority to US07/880,036 priority patent/US5299353A/en
Priority to JP4116420A priority patent/JPH07166802A/ja
Priority to CA002068504A priority patent/CA2068504A1/fr
Priority to PL92294502A priority patent/PL168950B1/pl
Priority to KR1019920008009A priority patent/KR920021236A/ko
Priority to SU925011799A priority patent/RU2066253C1/ru
Priority to CN92103469A priority patent/CN1025358C/zh
Publication of EP0513407A1 publication Critical patent/EP0513407A1/fr
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Publication of EP0513407B1 publication Critical patent/EP0513407B1/fr
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
    • 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
    • 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
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the invention is based on a method for producing a turbine blade, comprising an airfoil, a blade root and, if appropriate, a casting body having a blade cover band and made of an alloy based on a dopant-containing gamma-titanium aluminide.
  • Gamma-titanium aluminides have properties which favor their use as a material for turbine blades exposed to high temperatures. This includes, among other things, their low density compared to commonly used superalloys, which is more than twice as large, for example, in Ni superalloys.
  • turbine blades made of niobium-doped gamma titanium aluminide are known. Such blades have high heat resistance, but their ductility at room temperature is low, so that damage to parts subject to bending stresses cannot be ruled out with certainty.
  • FR-A-2 136 170 describes a method for producing a turbine blade, consisting of a cast body made of an alloy containing aluminum or titanium and having a blade blade and a blade root.
  • a melt of the alloy is first poured into a precision casting mold.
  • the mold, with its part located above the blade root, is then brought into an inductively heatable graphite container.
  • the one above The part of the casting body located in the casting mold of the blade root is then melted inductively and solidified by slowly moving the graphite container away towards the tip of the blade.
  • crystals are formed in the airfoil parallel to the longitudinal axis of the airfoil, which give the airfoil a high tensile and creep resistance.
  • the blade root however, consists of non-directional, ductile alloy material. This method is not suitable for producing a turbine blade made of gamma-titanium aluminide, which can withstand high thermal and mechanical loads.
  • the invention is based on the object of specifying a method of the type mentioned, with which a turbine blade consisting of doped gamma-titanium aluminide and having a high thermal and mechanical strength and in a simple and suitable manner for series production high creep rupture strength can be produced.
  • the method according to the invention provides a thermally and mechanically highly resilient turbine blade which is characterized by a long service life even when subjected to bending loads. This is made possible by the fact that the differently stressed parts of the turbine blade have differently specified modifications of the doped gamma titanium aluminide used as the material. It proves to be particularly advantageous from a manufacturing point of view that the turbine blade is merely molded out of an inexpensive, one-piece cast body. In addition, this method can be designed for series production in a simple manner by using conventional means, such as casting molds, ovens, seizing and mechanical and electrochemical processing devices.
  • the annealed, hot-isostatically pressed, thermoformed and heat-treated cast body shown in the figure has the essential material and shape properties of the turbine blade produced by the method according to the invention. It contains an elongated airfoil 1, a blade root 2 formed on one end of the airfoil 1 and a blade cover band 3 molded on the opposite end of the airfoil.
  • the turbine blade is produced from this cast body by slight material-lifting processing.
  • the material-lifting processing essentially consists in adapting the dimensions of the cast body to the desired dimensions of the turbine blade. With blade root 2 and blade cover band 3, this is advantageously done by grinding and polishing.
  • the fastening grooves 4 of the blade root 2 which are shown in dashed lines in the figure, can also be formed.
  • the airfoil is preferably adapted to the desired airfoil shape by electrochemical processing.
  • the cast body shown in the figure consists essentially of an alloy based on a dopant-containing gamma titanium aluminide. At least in Parts of the airfoil 1 is present in the form of a material with a coarse-grained structure and with a structure that leads to high tensile and creep strength. At least in parts of the blade root 2 and the blade shroud 3, the alloy is in the form of a material with a fine-grained structure and with a higher ductility than the material in the blade 1. This ensures a long service life for the airfoil.
  • the turbine blade according to the invention can be used advantageously at medium and high temperatures, i. H. Use at temperatures between 200 and 1000 ° C, especially in gas turbines and in compressors.
  • the blade cover sheet 3 may be present or omitted.
  • Suitable alloys are gamma titanium aluminides in which at least one or more of the elements B, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W and Zr are contained as dopant.
  • the amount of dopant added is preferably 0.5 to 8 atomic percent.
  • the melt is poured into a mold corresponding to the turbine blade to be manufactured.
  • the cast body formed can then advantageously be annealed at approximately 1100 ° C. for 10 hours in an argon atmosphere and cooled to room temperature for the purposes of its homogenization.
  • the cast skin and scale layer are then removed by, for example, removing a surface layer approximately 1 mm thick by mechanical or chemical means.
  • the descaled cast body is inserted into a suitable capsule made of soft carbon steel and the latter welded gas-tight.
  • the encapsulated cast body is then hot isostatically pressed and cooled at a temperature of 1260 ° C. for 3 hours under a pressure of 120 MPa.
  • the annealing of the alloy should be carried out at temperatures between 1000 and 1100 ° C for at least half and for a maximum of thirty hours.
  • hot isostatic pressing which should advantageously be carried out at temperatures between 1200 and 1300 ° C and a pressure between 100 and 150 MPa for at least one and at most five hours.
  • thermoforming of the part of the annealed and hot-isostatically pressed cast body corresponding to the blade root 2 and / or the blade cover band 3, forming the material with a fine-grained structure, and heat treating at least the part of the annealed and hot corresponding to the airfoil 1 -isostatically pressed cast body before or after the isothermal thermoforming to form the material with a coarse-grained structure.
  • the annealed and hot-isostatically pressed cast body is heat-treated prior to the isothermal thermoforming to form the material with a coarse-grained structure
  • the part of the annealed and hot-isostatically pressed cast body after the isothermal thermoforming is heat-treated to form the material with a coarse-grained structure. It has proven to be expedient to heat the annealed and hot-isostatically pressed cast body to the temperature required for hot-working at a rate of between 10 and 50 ° C./min before the isothermal hot-working.
  • the parts to be thermoformed such as the blade root 2 and possibly also the blade cover band 3, can advantageously be kneaded in the forging press by upsetting in at least two directions transverse to the longitudinal axis of the turbine blade and then pressed to the final shape.
  • the finished pressed parts have a fine-grained structure with one compared to that in the airfoil located material on increased ductility.
  • the tensile strength or the ductility of the material in the airfoil 1 is 390 MPa or 0.3% and in the blade root 2 and in the blade cover band 3 is 370 MPa or 1.3%.
  • the cast body is heated to 1100 ° C., for example, at a heating rate of 10 to 50 ° C./min and is kept at this temperature.
  • the blade root 2 and / or the blade shroud 3 are then isothermally forged at 1100 ° C. in accordance with the previously described method.
  • the forged parts also have a fine-grained structure with an increased ductility compared to the material located in the airfoil 1.
  • the airfoil is then heated to a temperature of 1200 to 1400 ° C. and, depending on the heating temperature and alloy composition, heat-treated for between 0.5 and 25 hours. When cooling, another 1 to 5 h heat treatment can be carried out. After the heat treatment, the airfoil predominantly has a coarse-grained structure and a structure that leads to high tensile and creep resistance. In such a turbine blade manufactured in this way, the tensile strength and ductility of the material in the airfoil 1 or in the blade root 2 and in the blade shroud 3 have almost the same values as in the turbine blade produced by the previously described method.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Forging (AREA)
  • Powder Metallurgy (AREA)

Claims (14)

  1. Procédé pour la fabrication d'une aube de turbine, comprenant un corps moulé comportant une pale (1), un pied d'aube (2) et éventuellement une bande de recouvrement de l'aube (3), en un alliage à base d'un aluminiure de titane-gamma contenant des matières de dopage, caractérisé en ce que l'on effectue les opérations suivantes :
    - fusion de l'alliage,
    - coulée du bain fondu en un corps moulé à la forme de l'aube de turbine,
    - compression isostatique à chaud du corps moulé,
    - déformation à chaud isotherme, unique ou répétée, de la partie du corps moulé comprimé isostatiquement à chaud correspondant au pied de l'aube (2) et/ou à la bande de recouvrement de l'aube (3) avec formation d'une matière ayant une texture à grain fin et une ductilité accrue par rapport à la matière se trouvant dans la pale (1),
    - traitement thermique au moins de la partie du corps moulé comprimé isostatiquement à chaud correspondant à la pale (1), avant ou après la déformation à chaud isotherme, avec formation d'une matière ayant une texture à gros grain et une structure conduisant à une haute résistance à la traction et au fluage, et
    - usinage par enlèvement de matière du corps moulé comprimé isostatiquement à chaud, déformé à chaud et traité thermiquement, en une aube de turbine.
  2. Procédé suivant la revendication 1, caractérisé en ce que l'on utilise dans l'alliage, comme matière de dopage, au moins un ou plusieurs des éléments B, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W ainsi que Zr.
  3. Procédé suivant la revendication 2, caractérisé en ce que l'alliage présente au moins 0,5 et au plus 8 pour-cent atomiques de matière de dopage.
  4. Procédé suivant l'une des revendications 1 à 3, caractérisé en ce que le corps moulé comprimé isostatiquement à chaud est traité thermiquement avant la déformation à chaud isotherme, avec formation de la matière ayant une texture à gros grain.
  5. Procédé suivant l'une des revendications 1 à 3, caractérisé en ce que la partie du corps moulé comprimé isostatiquement à chaud comprenant la pale (1) est traitée thermiquement après la déformation à chaud isotherme, avec formation de la matière ayant une texture à gros grain.
  6. Procédé suivant la revendication 5, caractérisé en ce que le traitement thermique est effectué avec une bobine d'induction.
  7. Procédé suivant l'une des revendications 1 à 6, caractérisé en ce que le traitement thermique est effectué entre 1200 et 1400°C.
  8. Procédé suivant la revendication 7, caractérisé en ce qu'un traitement thermique supplémentaire est effectué ultérieurement entre 800 et 1000°C.
  9. Procédé suivant l'une des revendications 1 à 8, caractérisé en ce que la déformation à chaud est effectuée entre 1050 et 1200°C avec une vitesse de déformation comprise entre 5·10⁻⁵ s⁻¹ et 10⁻² s⁻¹ jusqu'à un taux de déformation ε = 1,6, avec
    Figure imgb0004
        où
    h₀ =   hauteur initiale de la pièce, et
    h =   hauteur de la pièce après formage.
  10. Procédé suivant la revendication 9, caractérisé en ce que la déformation à chaud est effectuée dans une presse de forge.
  11. Procédé suivant la revendication 10, caractérisé en ce que les parties à déformer à chaud sont d'abord corroyées dans la presse de forge par refoulement dans au moins deux directions orientées transversalement à l'axe longitudinal de l'aube de turbine et sont ensuite forgées à leur forme finale.
  12. Procédé suivant l'une des revendications 1 à 11, caractérisé en ce que le corps moulé comprimé isostatiquement à chaud est refroidi à la température ambiante avant la déformation à chaud isotherme et est ensuite chauffé à la température réglée pour la déformation à chaud avec une vitesse comprise entre 10 et 50°C/min.
  13. Procédé suivant l'une des revendications 1 à 12, caractérisé en ce que le corps moulé est homogénéisé à des températures comprises entre 1000 et 1100°C avant la déformation à chaud et le traitement thermique.
  14. Procédé suivant l'une des revendications 1 à 13, caractérisé en ce que la compression isostatique à chaud est effectuée à des températures comprises entre 1200 et 1300°C et sous une pression comprise entre 100 et 150 MPa.
EP91107707A 1991-05-13 1991-05-13 Procédé de fabrication d' une aube de turbine Expired - Lifetime EP0513407B1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
DE59106047T DE59106047D1 (de) 1991-05-13 1991-05-13 Verfahren zur Herstellung einer Turbinenschaufel.
EP91107707A EP0513407B1 (fr) 1991-05-13 1991-05-13 Procédé de fabrication d' une aube de turbine
JP4116420A JPH07166802A (ja) 1991-05-13 1992-05-08 タービンブレイドとこのタービンブレイドを作製する方法
CA002068504A CA2068504A1 (fr) 1991-05-13 1992-05-08 Aube de turbine et procede de fabrication
US07/880,036 US5299353A (en) 1991-05-13 1992-05-08 Turbine blade and process for producing this turbine blade
PL92294502A PL168950B1 (pl) 1991-05-13 1992-05-11 Sposób wytwarzania lopatki turbiny PL PL
KR1019920008009A KR920021236A (ko) 1991-05-13 1992-05-12 터빈 블레이드 및 그 제조방법
SU925011799A RU2066253C1 (ru) 1991-05-13 1992-05-12 Способ изготовления турбинных лопаток
CN92103469A CN1025358C (zh) 1991-05-13 1992-05-12 制造涡轮叶片的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP91107707A EP0513407B1 (fr) 1991-05-13 1991-05-13 Procédé de fabrication d' une aube de turbine

Publications (2)

Publication Number Publication Date
EP0513407A1 EP0513407A1 (fr) 1992-11-19
EP0513407B1 true EP0513407B1 (fr) 1995-07-19

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EP91107707A Expired - Lifetime EP0513407B1 (fr) 1991-05-13 1991-05-13 Procédé de fabrication d' une aube de turbine

Country Status (9)

Country Link
US (1) US5299353A (fr)
EP (1) EP0513407B1 (fr)
JP (1) JPH07166802A (fr)
KR (1) KR920021236A (fr)
CN (1) CN1025358C (fr)
CA (1) CA2068504A1 (fr)
DE (1) DE59106047D1 (fr)
PL (1) PL168950B1 (fr)
RU (1) RU2066253C1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
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DE19756354A1 (de) * 1997-12-18 1999-06-24 Asea Brown Boveri Schaufel und Verfahren zur Herstellung der Schaufel
US7048507B2 (en) 2003-03-26 2006-05-23 Alstom Technology Ltd. Axial-flow thermal turbomachine
WO2010149141A2 (fr) 2009-06-25 2010-12-29 Mtu Aero Engines Gmbh Procédé de fabrication et/ou de réparation d'une pale pour une turbomachine
DE10305912B4 (de) * 2003-02-13 2014-01-30 Alstom Technology Ltd. Hybrid- Schaufel für thermische Turbomaschinen

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DE4219470A1 (de) * 1992-06-13 1993-12-16 Asea Brown Boveri Bauteil für hohe Temperaturen, insbesondere Turbinenschaufel, und Verfahren zur Herstellung dieses Bauteils
DE4219469A1 (de) * 1992-06-13 1993-12-16 Asea Brown Boveri Hohen Temperaturen aussetzbares Bauteil, insbesondere Turbinenschaufel, und Verfahren zur Herstellung dieses Bauteils
DE4301880A1 (de) * 1993-01-25 1994-07-28 Abb Research Ltd Verfahren zur Herstellung eines Werkstoffes auf der Basis einer dotierten intermetallischen Verbindung
US5350466A (en) * 1993-07-19 1994-09-27 Howmet Corporation Creep resistant titanium aluminide alloy
GB9413631D0 (en) * 1994-07-06 1994-09-14 Inco Engineered Prod Ltd Manufacture of forged components
GB9419712D0 (en) * 1994-09-30 1994-11-16 Rolls Royce Plc A turbomachine aerofoil and a method of production
EP0852164B1 (fr) * 1995-09-13 2002-12-11 Kabushiki Kaisha Toshiba Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane
US6551064B1 (en) * 1996-07-24 2003-04-22 General Electric Company Laser shock peened gas turbine engine intermetallic parts
US5873703A (en) * 1997-01-22 1999-02-23 General Electric Company Repair of gamma titanium aluminide articles
US6158961A (en) * 1998-10-13 2000-12-12 General Electric Compnay Truncated chamfer turbine blade
US6115917A (en) * 1998-10-20 2000-09-12 General Electric Company Single position turbine rotor repair method
RU2164180C2 (ru) * 1999-06-17 2001-03-20 Институт проблем сверхпластичности металлов РАН СПОСОБ ПРОКАТКИ ЗАГОТОВОК ИЗ ЗАЭВТЕКТОИДНЫХ γ+α2СПЛАВОВ И СПОСОБ ПОЛУЧЕНИЯ ЗАГОТОВОК ДЛЯ ОСУЩЕСТВЛЕНИЯ ПЕРВОГО СПОСОБА
RU2164263C2 (ru) * 1999-06-17 2001-03-20 Институт проблем сверхпластичности металлов РАН СПОСОБ ОБРАБОТКИ ЗАГОТОВОК ИЗ ЗАЭВТЕКТОИДНЫХ γ+α2 СПЛАВОВ
KR100340806B1 (ko) * 1999-10-27 2002-06-20 윤행순 고온등압 압축기술을 이용한 가스터빈 고온부품 수명연장방법
DE10255346A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Verfahren zum Herstellen einer Turbinenschaufel
US6910859B2 (en) * 2003-03-12 2005-06-28 Pcc Structurals, Inc. Double-walled annular articles and apparatus and method for sizing the same
DE10313490A1 (de) * 2003-03-26 2004-10-14 Alstom Technology Ltd Axial durchströmte thermische Turbomaschine
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CN1025358C (zh) 1994-07-06
US5299353A (en) 1994-04-05
RU2066253C1 (ru) 1996-09-10
CN1066706A (zh) 1992-12-02
KR920021236A (ko) 1992-12-18
EP0513407A1 (fr) 1992-11-19
PL294502A1 (en) 1992-11-30
PL168950B1 (pl) 1996-05-31
DE59106047D1 (de) 1995-08-24
CA2068504A1 (fr) 1992-11-14
JPH07166802A (ja) 1995-06-27

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