EP2597167A1 - Superalliage DS et composant - Google Patents

Superalliage DS et composant Download PDF

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Publication number
EP2597167A1
EP2597167A1 EP11190432.2A EP11190432A EP2597167A1 EP 2597167 A1 EP2597167 A1 EP 2597167A1 EP 11190432 A EP11190432 A EP 11190432A EP 2597167 A1 EP2597167 A1 EP 2597167A1
Authority
EP
European Patent Office
Prior art keywords
alloy according
alloy
blade
component
nickel
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
EP11190432.2A
Other languages
German (de)
English (en)
Other versions
EP2597167B1 (fr
Inventor
Sebastian Piegert
Winfried Esser
Uwe Paul
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 EP11190432.2A priority Critical patent/EP2597167B1/fr
Priority to US13/675,266 priority patent/US20130136649A1/en
Publication of EP2597167A1 publication Critical patent/EP2597167A1/fr
Application granted granted Critical
Publication of EP2597167B1 publication Critical patent/EP2597167B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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    • 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
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • 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
    • 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
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%

Definitions

  • the invention relates to an improved nickel-based superalloy for the production of components with columnar grains.
  • thermo-mechanical and oxidative stresses on the turbine blades in operation are getting higher.
  • these alloys are also susceptible to the formation of brittle phases at higher operating temperatures and long propagation delays.
  • these 2nd generation DS materials have a higher density than the 1st generation DS materials (Without Re) and usually have an insufficient heat treatment window (Solution annealing), which increases the risk of recrystallization and melting during the necessary solution annealing and thus leads to a higher scraping rate.
  • the object of the invention is therefore to solve the above-mentioned problems.
  • the object is achieved by an alloy according to claim 1 and a component according to claim 8.
  • the inventive step is a new DS alloy with an optimal adjustment of Re, Ta, Ti, Hf, C, B, Zr contents to achieve the above advantages:
  • Nickel-based alloy which has (in% by weight): Cobalt (Co) 9% - 11%, especially 10% Chrome (Cr) 4% - 6%, especially 5% Molybdenum (Mo) 1.7% - 2.1%, especially 1.9% Tungsten (W) 5.5% - 6.3%, especially 5.9% Tantalum (Ta) 6.8% - 7.6%, especially 7.2% Titanium (Ti) 0.8% - 1.2%, especially 1.0% Aluminum (Al) 5.4% - 5.9%, especially 5.6% Rhenium (Re) 1.8% - 2.2%, especially 2.0% Hafnium (Hf) 0.008% - 0.12%, especially 0.10% Boron (B) 0.006% to 0.01%, especially 0.008% Carbon (C) 0.13% to 0.15%, in particular 0.12% Zircon (Zr) 0.004% - 0.006%, especially 0.005%
  • the tantalum content (Ta) is kept as low as possible because it raises the ⁇ 'solution annealing temperature and lowers the melting temperature and stabilizes harmful TCP phases.
  • the molybdenum content (Mo) is also kept as low as possible because molybdenum increases the ⁇ 'solution annealing temperature and stabilizes the harmful TCP phases.
  • Titanium (Ti) is used as a substitute for tantalum (Ta). It contributes to ⁇ '-formation and reduces the ⁇ '-solution annealing temperature, which increases the solution annealing window.
  • Boron, carbon, hafnium and zirconium are added as grain boundary stabilizers in a balanced ratio as micro-alloying elements. This makes the grain boundaries at high temperatures more stable to hot cracking without bearing the deleterious effect of these elements at higher levels.
  • FIG. 1 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.
  • 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.
  • Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
  • Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, i.e., grains that run the full length of the workpiece and here, in common usage, are referred to as directionally solidified) or a monocrystalline structure, i. the whole workpiece consists of a single crystal.
  • a columnar grain structure columnar, i.e., grains that run the full length of the workpiece and here, in common usage, are referred to as directionally solidified
  • a monocrystalline structure i. the whole workpiece consists of a single crystal.
  • directionally solidified microstructures which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures.
  • 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 0 412 397 B1 or EP 1 306 454 A1 are known from the EP 0 486 489 B1 .
  • the density is preferably 95% of the theoretical density.
  • the layer composition comprises Co-30Ni-28Cr-8Al-0.6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10A1-0,4Y-1 are also preferably used , 5RE.
  • 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 methods e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.
  • 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.
  • Refurbishment means that components 120, 130 may have to be freed of protective layers after use (eg by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. Thereafter, a recoating occurs of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11190432.2A 2011-11-24 2011-11-24 Superalliage DS et composant Not-in-force EP2597167B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11190432.2A EP2597167B1 (fr) 2011-11-24 2011-11-24 Superalliage DS et composant
US13/675,266 US20130136649A1 (en) 2011-11-24 2012-11-13 Ds superalloy and component

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11190432.2A EP2597167B1 (fr) 2011-11-24 2011-11-24 Superalliage DS et composant

Publications (2)

Publication Number Publication Date
EP2597167A1 true EP2597167A1 (fr) 2013-05-29
EP2597167B1 EP2597167B1 (fr) 2014-04-23

Family

ID=45093457

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11190432.2A Not-in-force EP2597167B1 (fr) 2011-11-24 2011-11-24 Superalliage DS et composant

Country Status (2)

Country Link
US (1) US20130136649A1 (fr)
EP (1) EP2597167B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112853154A (zh) * 2021-01-04 2021-05-28 广东省科学院中乌焊接研究所 镍基中间层合金材料及其制备方法、焊件及焊接方法以及应用

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4169742A (en) * 1976-12-16 1979-10-02 General Electric Company Cast nickel-base alloy article
EP0240451A2 (fr) * 1986-04-03 1987-10-07 United Technologies Corporation Articles monocristallins à anisotropie réduite
EP0246082A1 (fr) * 1986-05-13 1987-11-19 AlliedSignal Inc. Matériaux en monocristal de superalliage
US4849030A (en) * 1986-06-09 1989-07-18 General Electric Company Dispersion strengthened single crystal alloys and method
GB2232685A (en) * 1986-06-09 1990-12-19 Gen Electric Dispersion strengthened single crystal alloys
EP0486489B1 (fr) 1989-08-10 1994-11-02 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0412397B1 (fr) 1989-08-10 1998-03-25 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium possédant une résistance plus grande à la corrosion et l'oxydation
EP0892090A1 (fr) 1997-02-24 1999-01-20 Sulzer Innotec Ag Procédé de fabrication de structure smonocristallines
EP0786017B1 (fr) 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
US6024792A (en) 1997-02-24 2000-02-15 Sulzer Innotec Ag Method for producing monocrystalline structures
EP1306454A1 (fr) 2001-10-24 2003-05-02 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0637476B1 (fr) * 1993-08-06 2000-02-23 Hitachi, Ltd. Aube de turbine à gaz, procédé de fabrication de celle-ci et turbine à gaz utilisant cette aube

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4169742A (en) * 1976-12-16 1979-10-02 General Electric Company Cast nickel-base alloy article
EP0240451A2 (fr) * 1986-04-03 1987-10-07 United Technologies Corporation Articles monocristallins à anisotropie réduite
EP0246082A1 (fr) * 1986-05-13 1987-11-19 AlliedSignal Inc. Matériaux en monocristal de superalliage
US4849030A (en) * 1986-06-09 1989-07-18 General Electric Company Dispersion strengthened single crystal alloys and method
GB2232685A (en) * 1986-06-09 1990-12-19 Gen Electric Dispersion strengthened single crystal alloys
EP0486489B1 (fr) 1989-08-10 1994-11-02 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0412397B1 (fr) 1989-08-10 1998-03-25 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium possédant une résistance plus grande à la corrosion et l'oxydation
EP0786017B1 (fr) 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
EP0892090A1 (fr) 1997-02-24 1999-01-20 Sulzer Innotec Ag Procédé de fabrication de structure smonocristallines
US6024792A (en) 1997-02-24 2000-02-15 Sulzer Innotec Ag Method for producing monocrystalline structures
EP1306454A1 (fr) 2001-10-24 2003-05-02 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112853154A (zh) * 2021-01-04 2021-05-28 广东省科学院中乌焊接研究所 镍基中间层合金材料及其制备方法、焊件及焊接方法以及应用

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Publication number Publication date
EP2597167B1 (fr) 2014-04-23
US20130136649A1 (en) 2013-05-30

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