EP1849879A1 - Procédé de traitement thermique cyclique pour un superalliage - Google Patents

Procédé de traitement thermique cyclique pour un superalliage Download PDF

Info

Publication number
EP1849879A1
EP1849879A1 EP06008688A EP06008688A EP1849879A1 EP 1849879 A1 EP1849879 A1 EP 1849879A1 EP 06008688 A EP06008688 A EP 06008688A EP 06008688 A EP06008688 A EP 06008688A EP 1849879 A1 EP1849879 A1 EP 1849879A1
Authority
EP
European Patent Office
Prior art keywords
temperature
solv
pendulum
dissolution
solution annealing
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.)
Withdrawn
Application number
EP06008688A
Other languages
German (de)
English (en)
Inventor
Michael Ott
Rolf Dr. Wilkenhöner
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP06008688A priority Critical patent/EP1849879A1/fr
Priority to JP2009507010A priority patent/JP2009534539A/ja
Priority to EP07726949A priority patent/EP2010683A1/fr
Priority to US12/226,551 priority patent/US20100163142A1/en
Priority to KR1020087028833A priority patent/KR20090007767A/ko
Priority to PCT/EP2007/052461 priority patent/WO2007124979A1/fr
Publication of EP1849879A1 publication Critical patent/EP1849879A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/78—Combined heat-treatments not provided for above
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/78—Combined heat-treatments not provided for above
    • C21D1/785—Thermocycling
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/02—Alloys based on aluminium with silicon as the next major constituent
    • 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
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/043—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with silicon as the next major constituent
    • 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
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D11/00—Process control or regulation for heat treatments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/40—Heat treatment

Definitions

  • the invention relates to a heat treatment method of a material having an excretion.
  • Nickel-base superalloys which are used in particular for gas turbine components, such as turbine blades or combustion chamber inserts, have a .gamma. 'Phase, which undergoes a so-called .gamma.' Solution annealing during refurbishment, in order to restore the original material properties. This is not possible without difficulty for components with aligned solidified nickel base superalloys.
  • the ⁇ '-solution annealing leads to a mechanically deformed surface, such as in the region of the blade feet to a recrystallization of the ⁇ '-phase at the component surface.
  • Nickel-base superalloys unlike conventional nickel-base superalloys, have few or no grain boundary strengthening elements, and the re-nucleation of grain on the surface of the device is an intolerable material weakening.
  • the object is achieved by a heat treatment method according to claim 1, in which the mechanical stresses are relieved by dissolving the precipitate, precipitating the precipitate and again dissolving and precipitating, so that no recrystallization can occur.
  • the heat treatment according to the invention is carried out in particular for nickel-base super alloys.
  • Such DX or SX nickel base superalloys (FIG. 13) are used in particular for turbine blades 120, 130 (FIGS. 14, 15), combustor elements 155 (FIG. 16) for turbines, in particular for gas turbines 100 (FIG. 14).
  • the heat treatment can also be carried out with aircraft turbine components (in particular blades).
  • FIC Fluoride ion cleaning
  • the required FIC cleaning is preferably carried out at temperatures around 1000 ° C with HF / H 2 mixtures.
  • T LG 1299.315 + 3.987 W - 3.624 Ta + 2.424 Ru + 0.958 Re - 6.362 Cr - 4.943 Ti - 2.602 Al - 2.415 Co - 2.224 Mo.
  • the temperature profile T (t) is plotted over the time t, wherein the temperature T LG represents the Voll substancessglühtemperatur described above and the dissolution temperature T SOLV represents a material-specific temperature, from which the excretion can only dissolve, but a complete resolution of Excretions take too long.
  • the time period t1 is the time from the first time exceeding the temperature T SOLV until the time t3, from which the temperature T preferably remains constant at the full solution annealing temperature T LG .
  • the residence time at the full solution annealing temperature is preferably at least 1 hour (1 hour).
  • the temperature T SOLV can be exceeded (in Figure 1 not) by the pendulum-like motion.
  • the temperature T remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1 hour.
  • the temperature profile is similar to that in Figure 1, but the pendular motion begins only above the temperature T SOLV .
  • the temperature T SOLV is preferably not undershot by the pendulum-shaped movement.
  • the temperature T remains constant at the full solution annealing temperature T LG on which it preferably remains for at least 1 hour.
  • three local maxima can be seen, so that there are three oscillations here.
  • the temperature T rises above the temperature T SOLV (not in the form of a pendulum) and, for example, once again drops below the temperature T SOLV and then rises in a pendulum-shaped fashion up to the temperature T LG .
  • the temperature T remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1 hour.
  • three local maxima can be seen, so that there are three oscillations here.
  • the temperature may oscillate once or more than a temperature above T SOLV below the temperature T SOLV .
  • the pendulum-shaped temperature profile T (t) then preferably runs uniformly, recognizable by the horizontal dashed line.
  • the temperature T remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1 hour.
  • two oscillations are shown. However, three or more oscillations can be performed.
  • the temperature T also increases (not in the form of a pendulum) to the full solution annealing temperature T LG and then drops, but the temperature T SOLV is not reached (difference ⁇ T> 0).
  • the pendulum-shaped temperature profile T (t) then preferably runs uniformly, recognizable by the horizontal dashed line.
  • the temperature T remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1 hour.
  • three local maxima can be seen, so that there are three oscillations here.
  • the temperature T rises (not pendulum-shaped) beyond the temperature T SOLV up to a temperature below the temperature T LG and then oscillates between these two values.
  • the pendulum-shaped temperature profile T (t) then preferably runs uniformly, recognizable by the horizontal dashed line.
  • the temperature T remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1 hour.
  • two oscillations are shown. However, three or more oscillations can also be performed.
  • the temperature T rises above the temperature T SOLV (not in the form of a pendulum) up to a temperature below the temperature T LG and oscillates between this temperature below T LG and a temperature above T SOLV .
  • the pendulum-shaped temperature profile T (t) then preferably runs uniformly, recognizable by the horizontal dashed line.
  • the temperature T remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1 hour.
  • three local maxima can be seen, so that there are three oscillations here.
  • the temperature T in Figure 8, 9 also oscillates below the temperature T SOLV .
  • the temperature always reaches a maximum value of the full solution annealing temperature T LG
  • the maximum value of the temperature profile reaches a temperature above T SOLV but below the full solution annealing temperature T LG .
  • the temperature T in Figure 8, 9 remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1h.
  • two oscillations are shown. However, three or more oscillations can also be performed. In Figure 9, two oscillations are shown. However, three or more oscillations can also be performed.
  • the temperature T rises (not pendulum-shaped) above the temperature T SOLV and oscillates between this value and a lower value ( ⁇ T SOLV ).
  • the pendulum-shaped temperature profile T (t) then preferably runs uniformly, recognizable by the horizontal dashed line.
  • the temperature increases in particular pendulum-shaped to the full solution annealing temperature T LG .
  • the temperature T remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1 hour.
  • four local maxima are present, so that there are four pendulum-shaped movements. But it can also be carried out five or more oscillations.
  • FIG. 12 shows a further exemplary embodiment of the pendulum-shaped temperature profile T (t) according to the invention.
  • the mean value of the temperature T, by which the temperature fluctuates, is increased step by step until, starting from a time t3, the temperature is set to a constant temperature T LG .
  • the temperature T oscillates by the temperature T SOLV , then increases to a higher temperature, so that the temperature T SOLV preferably no longer falls below, oscillates and in turn increases in a third or in further steps, in which case the maximum temperature T LG is achieved or a distance to the temperature T LG is present.
  • the temperature T remains constant at the full solution annealing temperature T LG , on which it preferably remains for at least 1 hour.
  • the pendulum movements are only shown in a wave or sinusoidal manner, they can also be triangular (FIG. 11), rectangular (not illustrated) or designed differently.
  • the temperature T LG can be exceeded by the pendulum movement one or more times.
  • FIG. 13 shows a list of nickel-based DS or SX superalloys which can be treated by the method according to the invention.
  • the temperature T SOLV is 1100 ° C, the temperature T LG 1150 ° C.
  • the temperature T SOLV is 1140 ° C and the temperature T LG 1230 ° C.
  • the material PWA 1483 SX has a temperature T SOLV of 1150 ° C and a temperature T LG of 1250 ° C on.
  • FIG. 14 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • Each turbine stage 112 is formed, for example, from two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • the vanes 130 are attached to an inner housing 138 of a stator 143, whereas the blades 120 a row 125 are attached to the rotor 103, for example by means of a turbine disk 133. Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110. To withstand the prevailing temperatures, they can be cooled by means of a coolant.
  • substrates of the components can have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • SX structure monocrystalline
  • DS structure only longitudinal grains
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 15 shows a perspective view of a moving blade 120 or guide blade 130 of a turbomachine that extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjacent thereto and an airfoil 406 and a blade tip 415.
  • the blade 130 may have at its blade tip 415 another platform (not shown).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the airfoil 406.
  • blades 120, 130 for example, in all areas 400, 403, 406 of the blade 120, 130 massive metallic materials, in particular superalloys used.
  • superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 EP 1 319 729 A1 .
  • the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • Such alloys are known from the EP 0 486 489 B1 . EP 0 786 017 B1 . EP 0 412 397 B1 or EP 1 306 454 A1 which are to be part of this disclosure with regard to the chemical composition of the alloy.
  • the density is preferably 95% of the theoretical density.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • the thermal barrier coating covers the entire MCrAlX layer.
  • suitable coating processes such as electron beam evaporation (EB-PVD)
  • stalk-shaped grains are produced in the thermal barrier coating.
  • Other coating methods are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD.
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • the blade 120, 130 may be hollow or solid.
  • the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 16 shows a combustion chamber 110 of the gas turbine 100.
  • the combustion chamber 110 is configured, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged around a rotation axis 102 in the circumferential direction open into a common combustion chamber space 154, which generate flames 156.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M side with an inner lining formed from heat shield elements 155.
  • the heat shield elements 155 are then, for example, hollow and possibly still have cooling holes (not shown) which open into the combustion chamber space 154.
  • Each heat shield element 155 made of an alloy is equipped on the working medium side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • MCrAlX means: M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • Such alloys are known from the EP 0 486 489 B1 .
  • a ceramic thermal barrier coating may be present and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • suitable coating methods such as electron beam evaporation (EB-PVD)
  • stalk-shaped grains are produced in the thermal barrier coating.
  • APS atmospheric plasma spraying
  • LPPS LPPS
  • VPS vacuum plasma spraying
  • CVD chemical vaporation
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • Refurbishment means that turbine blades 120, 130, heat shield elements 155 may need to be deprotected (e.g., by sandblasting) after use. This is followed by removal of the corrosion and / or oxidation layers or products. In solution annealing, the inventive method is used. Optionally, cracks in the turbine blade 120, 130 or the heat shield element 155 are also repaired. This is followed by a re-coating of the turbine blades 120, 130, heat shield elements 155 and a renewed use of the turbine blades 120, 130 or the heat shield elements 155.

Landscapes

  • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat Treatment Of Articles (AREA)
EP06008688A 2006-04-26 2006-04-26 Procédé de traitement thermique cyclique pour un superalliage Withdrawn EP1849879A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP06008688A EP1849879A1 (fr) 2006-04-26 2006-04-26 Procédé de traitement thermique cyclique pour un superalliage
JP2009507010A JP2009534539A (ja) 2006-04-26 2007-03-15 超合金用揺動熱処理方法
EP07726949A EP2010683A1 (fr) 2006-04-26 2007-03-15 Procédé pendulaire de traitement thermique d'un superalliage
US12/226,551 US20100163142A1 (en) 2006-04-26 2007-03-15 Oscillating heat treatment method for a superalloy
KR1020087028833A KR20090007767A (ko) 2006-04-26 2007-03-15 초합금에 대한 진동성 열 처리 방법
PCT/EP2007/052461 WO2007124979A1 (fr) 2006-04-26 2007-03-15 Procédé pendulaire de traitement thermique d'un superalliage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06008688A EP1849879A1 (fr) 2006-04-26 2006-04-26 Procédé de traitement thermique cyclique pour un superalliage

Publications (1)

Publication Number Publication Date
EP1849879A1 true EP1849879A1 (fr) 2007-10-31

Family

ID=37003327

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06008688A Withdrawn EP1849879A1 (fr) 2006-04-26 2006-04-26 Procédé de traitement thermique cyclique pour un superalliage
EP07726949A Ceased EP2010683A1 (fr) 2006-04-26 2007-03-15 Procédé pendulaire de traitement thermique d'un superalliage

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP07726949A Ceased EP2010683A1 (fr) 2006-04-26 2007-03-15 Procédé pendulaire de traitement thermique d'un superalliage

Country Status (5)

Country Link
US (1) US20100163142A1 (fr)
EP (2) EP1849879A1 (fr)
JP (1) JP2009534539A (fr)
KR (1) KR20090007767A (fr)
WO (1) WO2007124979A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5408768B2 (ja) * 2008-12-04 2014-02-05 三菱マテリアル株式会社 高温強度および樹枝状晶組織を有するＮｉ基耐熱合金鋳塊およびこれからなるガスタービン翼鋳物
US20110076181A1 (en) * 2009-09-30 2011-03-31 General Electric Company Nickel-Based Superalloys and Articles
JP5427642B2 (ja) * 2010-02-24 2014-02-26 株式会社日立製作所 ニッケル基合金及びそれを用いたランド用ガスタービン部品
US9551053B2 (en) 2011-06-23 2017-01-24 United Technologies Corporation Method for limiting surface recrystallization
DE102011054718B4 (de) * 2011-10-21 2014-02-13 Hitachi Power Europe Gmbh Verfahren zur Erzeugung einer Spannungsverminderung in errichteten Rohrwänden eines Dampferzeugers
CN103451736B (zh) * 2012-06-01 2016-06-01 中国科学院金属研究所 一种减少单晶高温合金精铸件再结晶的方法
JP6849806B2 (ja) * 2016-12-29 2021-03-31 北京中科三環高技術股▲ふん▼有限公司Ｂｅｉｊｉｎｇ Ｚｈｏｎｇ Ｋｅ Ｓａｎ Ｈｕａｎ Ｈｉ−Ｔｅｃｈ Ｃｏ．，Ｌｔｄ． 微粒子希土類合金鋳片、その製造方法、および回転冷却ロール装置
CN109136806B (zh) * 2018-11-09 2020-12-25 中国石油大学(华东) 一种固态下NiTi单晶循环热处理制备方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5074925A (en) * 1990-06-25 1991-12-24 The United States Of America As Represented By The Secretary Of The Air Force Thermomechanical fabrication of net shape single crystal airfoils
US5302217A (en) * 1992-12-23 1994-04-12 United Technologies Corporation Cyclic heat treatment for controlling grain size of superalloy castings
US5551999A (en) * 1984-04-23 1996-09-03 United Technologies Corporation Cyclic recovery heat treatment
US20030136811A1 (en) * 2002-01-24 2003-07-24 Siemens Westinghouse Power Corporation Liquid phase diffusion bonding to a superalloy component

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4222794A (en) * 1979-07-02 1980-09-16 United Technologies Corporation Single crystal nickel superalloy
US5653828A (en) * 1995-10-26 1997-08-05 National Research Council Of Canada Method to procuce fine-grained lamellar microstructures in gamma titanium aluminides
US6968991B2 (en) * 2002-07-03 2005-11-29 Honeywell International, Inc. Diffusion bond mixture for healing single crystal alloys
JP4812301B2 (ja) * 2002-10-23 2011-11-09 シーメンス アクチエンゲゼルシヤフト 合金の熱処理方法

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5551999A (en) * 1984-04-23 1996-09-03 United Technologies Corporation Cyclic recovery heat treatment
US5074925A (en) * 1990-06-25 1991-12-24 The United States Of America As Represented By The Secretary Of The Air Force Thermomechanical fabrication of net shape single crystal airfoils
US5302217A (en) * 1992-12-23 1994-04-12 United Technologies Corporation Cyclic heat treatment for controlling grain size of superalloy castings
US20030136811A1 (en) * 2002-01-24 2003-07-24 Siemens Westinghouse Power Corporation Liquid phase diffusion bonding to a superalloy component

Also Published As

Publication number Publication date
KR20090007767A (ko) 2009-01-20
US20100163142A1 (en) 2010-07-01
WO2007124979A1 (fr) 2007-11-08
JP2009534539A (ja) 2009-09-24
EP2010683A1 (fr) 2009-01-07

Similar Documents

Publication Publication Date Title
EP1772228A1 (fr) Procédé pour la réparation d'une pièce à microstructure orientée.
EP2458025B1 (fr) Alliage, couche de protection et composant
WO2006061267A1 (fr) Systeme stratifie, utilisation et procede de realisation d'un systeme stratifie
EP1849879A1 (fr) Procédé de traitement thermique cyclique pour un superalliage
WO2009144077A1 (fr) Procédé pour souder en fonction d’une orientation préférentielle du substrat
EP1808508A1 (fr) Composant disposé dans le conduit d'écoulement d'une turbomachine et procédé de pulvérisation pour produire un revêtement.
EP1857218A1 (fr) Procédé de réparation d'élément et un élement
EP1716965A1 (fr) Brasure comprenant de la poudre d'apport métallique sous forme élémentaire
EP1722901B1 (fr) Procede de nettoyage au plasma d'un composant
EP1816222A1 (fr) Système de revêtements de couches métalliques protectrices à double couche
EP1816316B1 (fr) Procédé de réparation de composants
WO2007048696A1 (fr) Procede de nettoyage aux ions fluor de composants oxydes ou attaques par la corrosion
EP1798299B1 (fr) Alliage, couche de protection et élément de construction
EP1839801A1 (fr) Méthode de réparation pour la remise en état de pièces
EP2710167B1 (fr) Alliage, couche de protection et composant
EP1681374B1 (fr) Système de revêtement comprenant une couche barrière et procédé de fabrication
EP1841951A1 (fr) Composant presentant un meplat dans un alesage
WO2006069822A1 (fr) Procede de creation d'un trou
EP2661370B1 (fr) Alliage, couche protectrice et pièce
EP1658924A1 (fr) Pièce avec une rainure remplie
EP1812186A2 (fr) Procédé et pièce de coulée
EP1676938A1 (fr) Methode de fabrication d'un component d'une turbine et le component d'une turbine
EP1930115A1 (fr) Fil, son utilisation et procédé de soudage
EP1790746A1 (fr) Alliage, couche de protection et composant
EP2021530A2 (fr) Procédé de traitement électrolytique d'un composant

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20080502

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566