EP0574727A1 - Méthode de production d'un élément réfractaire à partir de deux matériaux différents - Google Patents

Méthode de production d'un élément réfractaire à partir de deux matériaux différents Download PDF

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Publication number
EP0574727A1
EP0574727A1 EP93108243A EP93108243A EP0574727A1 EP 0574727 A1 EP0574727 A1 EP 0574727A1 EP 93108243 A EP93108243 A EP 93108243A EP 93108243 A EP93108243 A EP 93108243A EP 0574727 A1 EP0574727 A1 EP 0574727A1
Authority
EP
European Patent Office
Prior art keywords
section
alloy
press
alloys
titanium
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP93108243A
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German (de)
English (en)
Other versions
EP0574727B1 (fr
Inventor
Peter Dr. Ernst
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.)
Alstom SA
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0574727A1 publication Critical patent/EP0574727A1/fr
Application granted granted Critical
Publication of EP0574727B1 publication Critical patent/EP0574727B1/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, in particular a turbine blade, according to the introductory part of patent claim 1.
  • Such a component and a method for producing such a component are described in DE 28 13 892 A1.
  • the component described is designed as a turbine impeller, which has been produced by hot pressing metal powders with different particle structures and different chemical compositions.
  • mechanically pretreated powder of a nickel-based superalloy, such as alloy IN 792, with particles in the form of flattened spheres was used as the starting material for the blades.
  • a mechanically non-pretreated powder of another nickel-based superalloy, such as alloy IN 100, with spherical particles was used as the starting material for the impeller disk.
  • the blades Due to the structure and chemical composition of the starting powder, the blades are characterized by good corrosion resistance at high temperatures and the impeller disc has high tensile strength and good fatigue resistance.
  • alloys are suitable as starting materials for the turbine impeller which, like the very related nickel-based superalloys, do not Changes in their structure and thus their properties can be exposed to the high temperatures during hot isostatic pressing. For this reason, no alloys can be used in the production of this turbine impeller, each of which has excellent properties for different tasks, but which can only be hot-compressed at significantly different temperatures.
  • the invention is based on the object of specifying a component, in particular a turbine blade, of the type mentioned at the outset, which can be used when used in a device operated at high temperatures, in particular a gas turbine is characterized by a long service life, and at the same time to point out a way that makes it possible to manufacture such a component in a simple manner and suitable for mass production.
  • the component according to the invention is distinguished from comparable components according to the prior art by a long service life. On the one hand, this is due to the fact that differently stressed parts of the component consist of differently specified alloys, which are adapted to the different stresses of the parts of the component. On the other hand, these alloys are selected so that they form a boundary layer of high strength when hot compressed to a bimetallic composite material.
  • the component according to the invention can therefore with great certainty absorb high thermal and mechanical loads such as occur, for example, when operating a gas turbine or a compressor of a turbocharger.
  • the method used to manufacture the components according to the invention is characterized in that hot compression is carried out at temperatures at which the structure of the alloys desired for the desired physical or chemical properties is present with great certainty even if the alloys forming the starting powder have chemical compositions which differ greatly from one another.
  • FIGS. 1 and 2 and each designed as a turbine blade 1 each contain an elongated blade 2 and a blade root 3 formed on one end of the blade 2
  • Reference numeral 4 denotes a press can.
  • this press can encloses the blade root 3 and has an opening 5 filled by the blade 2, which is preferably sealed gas-tight by welding or soldering the press can 4 to the blade 2.
  • the press can 4 encloses the entire turbine blade 1.
  • the turbine blade 1 shown in FIG. 1 is manufactured 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 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 which accommodates the blade root of the turbine blade 1, is filled with alloy powder.
  • the press can 4 is then evacuated and sealed gas-tight.
  • Doped gamma titanium aluminides are used as the material for the cast body and alloys based on titanium or nickel are used for the powder.
  • the alloy forming the cast body is advantageously a gamma titanium aluminide with a proportion of at least 0.5 and at most 8 atom 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.
  • a typical alloy is, for example, one that has 48 atomic percent Al, 2 to 4 atomic percent chromium and the remainder besides impurities that cannot be avoided, Ti.
  • the titanium base alloy used in the form of powder contains, in addition to titanium, aluminum and a proportion of up to 20 atomic percent of one or more additional elements, such as, in particular, V and / or Nb.
  • additional elements such as, in particular, V and / or Nb.
  • typical alloys contain either 6 atomic percent Al and 4 atomic percent V or 24 atomic percent Al and 11 atomic percent Nb.
  • the nickel-based alloy used in the form of powder can be, for example, the alloy IN 792 (composition in percent by weight Ni -0.12 C - 12.4 Cr - 9.0 Co - 1.9 Mo - 3.8 W - 3.9 Ta - 3.1 Al - 4.5 Ti - 0.2 B - 0.1 Zr).
  • the size of the powder particles is less than 500 ⁇ m for all powders used.
  • Such titanium and nickel-based alloys are characterized by good ductility (> 10%) at room temperature.
  • the mechanical resistance of the titanium base alloys at high temperatures is not as high as that of gamma titanium aluminides.
  • Nickel-based alloys on the other hand, have a much higher density than gamma titanium aluminides.
  • the sample completed by gas-tight sealing of the press can 4 was placed in a press device and hot-isostatically compressed using a titanium-based alloy at temperatures between 900 and 980 ° C.
  • a typical pressing process at approx. 950 ° C took approx. 3 hours at a pressure of approx. 200 MPa.
  • the two alloys were compacted to form a boundary layer 6 to form a bimetallic composite material.
  • This composite material which already has the shape of the turbine blade, was then typically heat-treated at temperatures of about 700 ° C. for about 4 hours after removal of the deformed press can 4. Subsequently, through slight material-removing processing, such as grinding, Polishing and / or electrochemical treatment, the turbine blade according to the invention completed.
  • a press can 4 which was extended in the longitudinal direction and accommodates the entire turbine blade 1 was used.
  • the cast body forming the airfoil 2 was first introduced into this press can 4 and the alloy powder was subsequently introduced in accordance with the exemplary embodiment described above.
  • the press can 4 was then evacuated and sealed gas-tight.
  • the test specimen produced in this way was treated in accordance with the exemplary embodiment described above.
  • the alloys used had the same composition as in the previously described embodiment.
  • FIG. 3 shows the structure and the structural structure of a part of the turbine blade according to the invention which is outlined in FIG. 2. It can be seen from this that the alloy forming the airfoil 2 has a coarse-grained and the alloy forming the airfoil 3 has a fine-grained microstructure, and that the boundary layer 6 connecting the two alloys to one another is almost unstructured and, according to chemical analysis, essentially of a binary TiAl alloy is formed with a proportion of about 25 atomic percent Al.
  • the alloy forming the airfoil 2 has a ductility of approximately 0.5 to 1% at room temperature, while the alloy forming the airfoil 3 has a ductility of 18 to 20%. At a temperature of approx. 700 ° C., the airfoil 2 has a creep resistance which is considerably higher than the creep resistance that is usually in it Temperature range used nickel-based super alloys.
  • the turbine blade 1 shows a ductility of 0.5 to 1% corresponding to the material of the blade leaf 2, which means that the ductility of the blade is not negatively influenced by the boundary layer 6.
  • the turbine blade 1 according to the invention is therefore characterized by a blade root 3 with high ductility and an airfoil 2 which is brittle at room temperature but has a high creep resistance at high temperatures.
  • the strength of the boundary layer 6 is sufficient to ensure safe operation of the turbine blade 1 at high temperatures.
  • An increased strength of the boundary layer 6 can be achieved in that the two alloys - as shown in FIG. 2 - are at least partially or completely interlocked in the region of the boundary layer 6. This can be effected in a simple manner before the casting body is introduced into the press can 4 by grinding or sandblasting the casting body at its end receiving the blade root 3 to a roughness depth of up to 0.1 mm.
  • a body made of a hot-isostatically compressed powder can also be introduced into the press can 4.
  • approx. 100 g of an alloy powder with 48 atom percent Al, 3 atom percent Cr, rest Ti and small amounts of impurities at temperatures between 1050 and 1300 ° C. and a pressure of approx. 250 MPa were used for approx. 3 Hours hot isostatically compressed.
  • the compacted powder was then heat-treated at temperatures between 1300 and 1400 ° C for a few hours.
  • the resulting body was then brought into the press can 4 shown in FIG. 2 and, under the conditions described there, was hot isostatically compressed together with the powder forming the blade root 3. That after appropriate heat treatment and post-processing
  • the resulting turbine blade had a ductility of the airfoil 2 at room temperature which was increased by approximately 50% compared to the turbine blade according to FIG.
  • a blade root 3 made of a nickel-based alloy was molded onto the blade made of gamma titanium aluminide.
  • 4 powders of the nickel-based alloy were filled into the press can already containing the airfoil or alternatively into the press can welded onto the airfoil.
  • the press can 4 was evacuated and sealed gas-tight.
  • a pore-free bimetallic composite material was produced by hot isostatic pressing for approx. 3 hours at approx. 1000 to 1250 ° C and a pressure of approx. 250 MPa, from which after removing the press jug 4, after heat treatment at approx. 700 ° to 800 ° C and material-removing post-processing a turbine blade was produced according to the invention.
  • the boundary layer 6 had particularly good strength.
  • the invention is not limited to turbine blades. It also relates to other components that are subjected to high mechanical loads at high temperatures, such as one-piece turbine wheels of turbochargers. LIST OF DESIGNATIONS 1 Turbine blade 4th press jug 2nd Airfoil 5 opening 3rd Blade root 6 Boundary layer

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  • 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)
EP93108243A 1992-06-13 1993-05-21 Méthode de production d'un élément réfractaire à partir de deux matériaux différents Expired - Lifetime EP0574727B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4219469 1992-06-13
DE4219469A DE4219469A1 (de) 1992-06-13 1992-06-13 Hohen Temperaturen aussetzbares Bauteil, insbesondere Turbinenschaufel, und Verfahren zur Herstellung dieses Bauteils

Publications (2)

Publication Number Publication Date
EP0574727A1 true EP0574727A1 (fr) 1993-12-22
EP0574727B1 EP0574727B1 (fr) 1998-08-26

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EP93108243A Expired - Lifetime EP0574727B1 (fr) 1992-06-13 1993-05-21 Méthode de production d'un élément réfractaire à partir de deux matériaux différents

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US (1) US5395699A (fr)
EP (1) EP0574727B1 (fr)
JP (1) JPH06172816A (fr)
DE (2) DE4219469A1 (fr)

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WO2011135451A1 (fr) 2010-04-29 2011-11-03 OÜ Skeleton Technologies Électrode en carbone composite pour condensateur électrique à double couche

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US6852273B2 (en) * 2003-01-29 2005-02-08 Adma Products, Inc. High-strength metal aluminide-containing matrix composites and methods of manufacture the same
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DE102010042889A1 (de) * 2010-10-25 2012-04-26 Manfred Renkel Turboladerbauteil
US8944762B2 (en) 2011-10-28 2015-02-03 United Technologies Corporation Spoked spacer for a gas turbine engine
US9938831B2 (en) 2011-10-28 2018-04-10 United Technologies Corporation Spoked rotor for a gas turbine engine
US10315279B2 (en) 2014-08-08 2019-06-11 Siemens Aktiengesellschaft Hot isostatic pressing system for the assembly of modular components usable in a turbine engine
CN105014068A (zh) * 2015-08-06 2015-11-04 潘桂枝 一种双金属复合材料的制备方法
US10422228B2 (en) 2016-04-12 2019-09-24 United Technologies Corporation Manufacturing a monolithic component with discrete portions formed of different metals
US20190040749A1 (en) * 2017-08-01 2019-02-07 United Technologies Corporation Method of fabricating a turbine blade
RU178967U1 (ru) * 2017-10-31 2018-04-24 федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" Лопатка турбомашины из алюминиевого сплава с упрочняющим слоем, содержащим углерод

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Publication number Priority date Publication date Assignee Title
US2431660A (en) * 1944-12-01 1947-11-25 Bbc Brown Boveri & Cie Turbine blade
FR1052893A (fr) * 1951-02-07 1954-01-28 Plansee Metallwerk Aube de turbine à grande résistance à la chaleur et à l'inflammation utilisable en particulier dans les turbines à gaz, et son procédé de fabrication
FR2317502A1 (fr) * 1975-06-27 1977-02-04 Special Metals Corp Roues composites a aubes, particulierement destinees aux turbines a gaz, et leur procede de fabrication
EP0073651A1 (fr) * 1981-08-27 1983-03-09 ASEA Stal Aktiebolag Procédé de fabrication d'éléments d'aubage pour turbomachines à fluide
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US5098484A (en) * 1991-01-30 1992-03-24 The United States Of America As Represented By The Secretary Of The Air Force Method for producing very fine microstructures in titanium aluminide alloy powder compacts
EP0513407A1 (fr) * 1991-05-13 1992-11-19 Asea Brown Boveri Ag Procédé de fabrication d' une aube de turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011135451A1 (fr) 2010-04-29 2011-11-03 OÜ Skeleton Technologies Électrode en carbone composite pour condensateur électrique à double couche

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EP0574727B1 (fr) 1998-08-26
JPH06172816A (ja) 1994-06-21
US5395699A (en) 1995-03-07
DE59308916D1 (de) 1998-10-01
DE4219469A1 (de) 1993-12-16

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