EP0574708B1 - Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément - Google Patents

Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément Download PDF

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Publication number
EP0574708B1
EP0574708B1 EP93107926A EP93107926A EP0574708B1 EP 0574708 B1 EP0574708 B1 EP 0574708B1 EP 93107926 A EP93107926 A EP 93107926A EP 93107926 A EP93107926 A EP 93107926A EP 0574708 B1 EP0574708 B1 EP 0574708B1
Authority
EP
European Patent Office
Prior art keywords
alloys
section
component
alloy
press
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
EP93107926A
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German (de)
English (en)
Other versions
EP0574708A1 (fr
Inventor
Joachim Dr. Rösler
Manfred Dr. Thumann
Christoph Tönnes
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
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0574708A1 publication Critical patent/EP0574708A1/fr
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Publication of EP0574708B1 publication Critical patent/EP0574708B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12021—All metal or with adjacent metals having metal particles having composition or density gradient or differential porosity
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/1216—Continuous interengaged phases of plural metals, or oriented fiber containing
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/1216—Continuous interengaged phases of plural metals, or oriented fiber containing
    • Y10T428/12174—Mo or W containing

Definitions

  • the invention is based on a component for high Temperatures, especially a turbine blade, after the Preamble of claim 1.
  • the invention also relates a method for producing such a component.
  • Such a component and a method for producing a such component are state of the art and for example in US-A-4 825 522.
  • This patent document is a high-temperature resistant component made of a nickel-based alloy removable. Certain sections of this component are covered by Modification of the base material with different Alloy additions to different material-specific Adjusted requirements. Further relevant state of the art is also FR-A-2 317 502, US-A-4 787 821 and US-A-4 529 452 to remove.
  • a gas turbine blade is in FR-A1-2.136.170 described.
  • This scoop has one of a eutectic Alloy cast, airfoil and airfoil containing blade body.
  • the blade root is from one ductile cast body with non-directional structure formed.
  • the airfoil consists of a matrix and parallel aligned with each other and in the longitudinal direction of the blade, fibrous crystals, which are embedded in the matrix and which by directional solidification from an inductive heated melt are formed.
  • the airfoil excels at significantly reduced Ductility from a much greater creep resistance. Especially when manufacturing a large airfoil however, it is difficult to find one for directional solidification sufficiently large temperature gradients and thus the desired Achieve high creep resistance in the airfoil.
  • the invention as specified in claims 1 and 3 is based on the task of a component, in particular a Turbine blade, of the type mentioned at the beginning, which when used in a medium and high temperature operated device, such as in particular a turbine features a long service life, and at the same time a way to point, which enables such a component in simple and suitable for mass production.
  • the component according to the invention stands out comparable components according to the prior art by a long service life. This is due to the choice of gamma titanium aluminide as base material and of suitable Dopants, which in predetermined quantities the base material are added, determined. With the selected base material it is possible in a particularly simple manner to alloy define which sections have different stresses of the component are adjusted. Since these are local differently stressed component sections, such as Turbine blade or turbine base, adapted alloys contain a common base material occur in Border area of the sections none chemical reaction products. The sections therefore go without a sharp transition into each other, so that the component according to the invention when operating a thermal Machine, such as a gas turbine or one in particular Compressor, high thermal and graded can easily absorb mechanical loads.
  • a thermal Machine such as a gas turbine or one in particular Compressor
  • the method used is characterized by the fact that large components with high thermal and mechanical Resilience through common process steps, such as in particular by hot isostatic pressing or by Sintering, easier and for mass production can be produced in a suitable manner.
  • FIG. 1 and 2 and each as Turbine blade 1 each contain components an elongated airfoil 2 and one at one end of the airfoil 2 molded blade root 3.
  • Reference numeral 4 denotes a press can.
  • This Press can encloses in the embodiment according to Fig. 1 the blade root 3 and has one from the airfoil 2 filled opening 5, which preferably through Welding or soldering the press jug 4 to the Blade 2 is sealed gas-tight.
  • the press can 4 the entire turbine blade 1.
  • the turbine blade 1 shown in FIG. 1 is produced as follows: A cast body designed as an airfoil 2 is guided with its one end through the opening 5 into the press can 4.
  • the press can 4 which is preferably made of steel, is soldered or welded to the cast body in a gas-tight manner in the region of the opening 5.
  • a cavity of the press can 4 receiving the blade root of the turbine blade 1 is filled with alloy powder.
  • the press can 4 is then evacuated and sealed gas-tight.
  • the materials for the cast body and the powder included one of two each on a common base material based alloys of different chemical Compositions which differ from one another by the Presence and / or the amount of at least one of them Distinguish the base material of the alloyed dopant.
  • An intermetallic is preferably used as the base material Phase, such as in particular a gamma titanium aluminide, is used.
  • At least one of the two containing gamma titanium aluminide Alloys have a share of at least 0.2 and at most 8 atomic percent of dopant, such as one or more of the elements B, C, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W and Zr.
  • the gas-tight closing of the press jug 4 Completed sample is placed in a press device and hot isostatic at temperatures between 900 and 1200 ° C condensed.
  • a typical pressing process at approx. 1070 ° C took about 3 at a pressure of about 250 MPa Hours.
  • the two alloys, without the Borderline chemical reaction products were formed non-porous with a gradual transition from the airfoil 2 compressed to the blade root 3.
  • Turbine blade 1 was extended in the longitudinal direction and the entire turbine blade 1 receiving press can 4 used.
  • jug 4 was the first Shovel blade 2 entered and cast below according to the previously described Embodiment filled the alloy powder.
  • the Press can 4 was then evacuated and gas-tight locked.
  • the test specimen thus produced was according to the previously described embodiment treated.
  • the alloys used were the same Composition on as described above Embodiment.
  • a cast body forming the airfoil 2 can also be a body from a hot isostatic in the press jug 4 compacted powder are introduced.
  • a another alternative embodiment of the invention that used to form the airfoil Alloy powder with 48 atomic percent Al, 3 atomic percent Cr, Balance Ti and small amounts of impurities in a Temperature of approx. 1070 ° C and a pressure of approx. 250 MPa hot isostatically compressed for approx. 3 hours.
  • the structure and the are from the micrograph according to FIG Microstructure of a part indicated by a border in Fig. 2 one - as described above - exclusively Alloy powders produced turbine blade after the Invention to see. It can be seen from this that the airfoil 2 forming alloy a coarse and the alloy forming the blade root 3 is a fine-grained one Has microstructure, and that at the transition zone no undesirable reaction zone between the two alloys with chemical reaction products or with excretions occurs. Both alloys go coarser with the teeth and fine crystallite gradually overlap.
  • the alloy forming the airfoil 2 has Room temperature to a ductility of about 0.5%, which the Alloy forming blade root 3 is one of 2.1%. At a temperature of approx. 700 ° C Blade 2 has a creep resistance, which corrected considerably above the creep resistance of the usually used in this temperature range Nickel-based superalloys.
  • the whole Turbine blade 1 shows the material of the Blade 2 corresponding ductility of 0.5%. Your mechanical and thermal properties are due to the No transition zone between the two alloys impaired.
  • the turbine blade 1 according to the invention is characterized by a blade root 3 with high Ductility and a brittle one at room temperature high temperatures, however, a high creep resistance having blade 2. The strength in Transitional area is because of the two alloys common base material and the lack of brittle Reaction products large enough to be safe Operation of the turbine blade 1 at high temperatures guarantee.
  • a press can 4 as a form for receiving the Alloys use a sintered mold, and compacting to achieve the turbine blade in a sintering process.
  • the invention is not limited to turbine blades. It also applies to others at high temperatures mechanically heavily loaded components, such as in one piece trained turbine wheels of turbochargers.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • General Engineering & Computer Science (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

  1. Elément pour températures élevées, en particulier, aube de turbine (1) comprenant un corps d'élément comportant au moins une première (pied d'ailette 3) et une deuxième sections (pale 2) dans lequel la première section (3) est formée d'un matériau ductile, et la deuxième section (2) comprend un matériau cassant en comparaison du matériau ductile, dans lequel chacun des deux matériaux contient l'un de deux alliages qui sont formés d'un matériau de base commun et ont des compositions chimiques différentes, et qui se distinguent l'un de l'autre par la présence et/ou la quantité d'au moins une substance de dopage alliée au matériau de base, caractérisé en ce que le matériau de base est l'aluminiure de titane gamma, que la teneur en matériau de dopage dans au moins l'un des deux alliages est au moins de 0,2 et au maximum de 0,8 atomes/%, et qu'au moins un ou plusieurs des éléments B, C, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W ainsi que Zr sont contenus comme substances de dopage.
  2. Elément suivant la revendication 1, caractérisé en ce qu'un premier des deux alliages formant la première section (3) contient une substance de dopage favorisant l'établissement d'un joint finement cristallin comme, en particulier, un ou plusieurs des éléments Cr, Mn, V, Si et un deuxième des deux alliages formant la deuxième section (2) contient une substance de dopage favorisant un joint grossièrement cristallin et augmentant la résistance au fluage, comme, en particulier, un ou plusieurs des éléments Nb, Ta, W.
  3. Procédé de fabrication de l'élément suivant la revendication 1, caractérisé en ce que les deux alliages pour le corps d'élément sont densifiés à chaud, et en ce qu'avant la densification à chaud, un premier des deux alliages formant la première section (3) est introduit à l'état de poudre dans une forme.
  4. Procédé suivant la revendication 3, caractérisé en ce qu'un deuxième des deux alliages formant la deuxième section (2) est utilisé sous la forme d'un corps coulé ou d'un corps formé à partir d'une poudre densifiée à chaud, et en ce que ce corps coulé ou le corps formé de la poudre densifiée à chaud est introduit par au moins une extrémité dans la forme constituée par une enceinte de pressage (4) et mis en contact avec la poudre dans l'enceinte de pressage (4).
  5. Procédé suivant la revendication 4, caractérisé en ce que l'enceinte de pressage (4) présente une ouverture (5) obturée par le corps introduit, laquelle est scellée, de préférence, sur le corps par soudage ou brasage de l'enceinte de pressage (4).
  6. Procédé suivant la revendication 5, caractérisé en ce qu'avant la densification à chaud un deuxième des deux alliages formant la deuxième section (2) est introduit sous forme de poudre dans la forme.
  7. Procédé suivant l'une quelconque des revendications 3 à 6, caractérisé en ce que la densification à chaud est exécutée à des températures comprises entre 900 et 1200°C.
  8. Procédé suivant l'une quelconque des revendications 4 à 7, caractérisé en ce que le matériau obtenu par densification à chaud est soumis à un traitement thermique à des températures supérieures à 700°C.
EP93107926A 1992-06-13 1993-05-14 Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément Expired - Lifetime EP0574708B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4219470A DE4219470A1 (de) 1992-06-13 1992-06-13 Bauteil für hohe Temperaturen, insbesondere Turbinenschaufel, und Verfahren zur Herstellung dieses Bauteils
DE4219470 1992-06-13

Publications (2)

Publication Number Publication Date
EP0574708A1 EP0574708A1 (fr) 1993-12-22
EP0574708B1 true EP0574708B1 (fr) 1998-09-16

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EP93107926A Expired - Lifetime EP0574708B1 (fr) 1992-06-13 1993-05-14 Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément

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Country Link
US (1) US5409781A (fr)
EP (1) EP0574708B1 (fr)
DE (2) DE4219470A1 (fr)

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Also Published As

Publication number Publication date
EP0574708A1 (fr) 1993-12-22
DE4219470A1 (de) 1993-12-16
DE59308980D1 (de) 1998-10-22
US5409781A (en) 1995-04-25

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