WO2012038166A2 - Nickel-base superalloy - Google Patents
Nickel-base superalloy Download PDFInfo
- Publication number
- WO2012038166A2 WO2012038166A2 PCT/EP2011/064310 EP2011064310W WO2012038166A2 WO 2012038166 A2 WO2012038166 A2 WO 2012038166A2 EP 2011064310 W EP2011064310 W EP 2011064310W WO 2012038166 A2 WO2012038166 A2 WO 2012038166A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- nickel
- base superalloy
- vane
- turbine
- blade
- Prior art date
Links
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
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
-
- 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
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
Definitions
- Nickel-base superalloy The present invention relates to a nickel-base superalloy which may be used in turbine components, in particular in gas turbine components with a directionally solidified (DS) or a single crystal (SX) structure.
- Nickel-base superalloys are often used for components which are to operate in a hot and corrosive environment such as blades and vanes of gas turbines which are exposed to the hot and corrosive combustion gases driving the turbine. In such environments, a high strength and a strong resistance to chemical attacks at high temperatures is needed.
- thermal barrier coatings are applied onto the corrosion resistant coating in order to reduce the temperature experienced by this coating and the underlying nickel-base superalloy.
- the temperature of the combus ⁇ tion gases i.e. the inlet temperature at the turbine en ⁇ trance
- the thermal barrier coating need to be improved for allowing the components to operate at higher temperatures.
- the present invention deals with improvements of the nickel- base superalloy.
- An inventive nickel-base superalloy comprises (in wt%) : carbon (C) : ⁇ 0.1
- aluminium (Al) 4.0 to 5.5
- hafnium (Hf ) 0.9 to 1.3
- niobium (Nb) ⁇ 0.01
- tantalum (Ta) 4.8 to 5.2
- titanium (Ti) 0.8 to 2.0
- zirconium (Zr) ⁇ 0.01
- Ni nickel (Ni) : balance
- inventive nickel-base superalloy may comprise (in wt% ) :
- inventive nickel-base superalloy shows high cor rosion resistance and creep strength in all compositions giv en above the compositions according to the first and second variant show particularly good results in corrosion resistance and creep strength.
- An inventive turbine component which may in particular be a gas turbine blade or vane, is made of an inventive nickel- base superalloy. If the turbine component is a gas turbine component it is advantageous if it has a directionally so ⁇ lidified structure (DS structure) or a single crystal struc ⁇ ture (SX structure) .
- DS structure ⁇ lidified structure
- SX structure single crystal struc ⁇ ture
- Figure 1 schematically shows a gas turbine blade or vane.
- Figure 1 shows a perspective view of a rotor blade 120 or a guide vane 130 of a gas turbine, which may be a gas turbine of an aircraft or of a power plant for generating electric ⁇ ity.
- the blade or vane 120, 130 extends along a longitudinal axis 121 and has, in succession along its longitudinal axis 121, a fixing region (also called blade root), an adjoining platform 103 and an airfoil 406 extending from the platform 403 to a tip 415.
- the vane may have a further platform at its tip end and a further fixing section extending from the further platform.
- the fixing section has, in the shown embodiment a hammer head form.
- the blade or vane 120, 130 comprises a leading edge 409 which shows towards the incoming combustion gas and a trailing edge 412 which shows away from the incoming combustion gas.
- the airfoil extends from the leading to the trailing edge and forms an aerodynamic surface which allows for transferring momentum from the streaming combustion gas to the blade 120.
- the airfoil allows to guide the streaming com ⁇ bustion gases so as to optimize the momentum transfer to the turbine blades and, hence, so as to optimize the momentum transfer from the streaming combustion gas to the turbine.
- the whole blade or vane 120, 130 is made of a nickel-base su- peralloy and formed by an investment casting process.
- the airfoil section 406 and a least parts of the platform 403 are coated with a corrosion resistive coating, for example a MCrAlY-coating, and a thermal barrier coating overlying the corrosion resistive coating.
- the fixing section 400 is uncoated.
- a nickel-base superalloy is used as the base material of the turbine blade or vane 120, 130.
- the nickel-base superalloy comprises (in wt%) : C: ⁇ 0.1, preferably 0.03 to 0.07
- Hf 0.9 to 1.3, preferably 1 .0 to 1.2
- Ta 4.8 to 5.2, preferably 4 .9 to 5.1
- W 1.8 to 2.5, preferably 2 .0 to 2.4
- the mentioned nickel-base superalloy offers a high creep strength and, at the same time, a high corrosion resistance so that there is no need for coating the fixing section 400 of the blade or vane 120, 130.
- the investment casting is performed with a direc- tionally solidification of the component so as to form a di- rectionally solidified structure (DX-structure) or a single crystal structure ( SX-structure ) .
- DX-structure di- rectionally solidified structure
- SX-structure single crystal structure
- dendritic crystals are oriented along a directional heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the work piece and are referred to here, in accordance with the language customarily used, as directionally solidified (DX) ) , or a single crystal structure, i.e. the entire work piece consists of a single crystal.
- a nickel-base superalloy having the following composition forms the base material of the turbine blade or vane 120:
- the superalloy above can provide the same stress rupture life than IN-6203 but at a temperature about 20° Celsius higher than IN-6203.
- the alloy mentioned above has a low electron vacancy number Nv of 2.59.
- the electron vacancy number is a measure for the tendency to form brittle phases at high temperatures. The lower the elec ⁇ tron vacancy number Nv is the less is the tendency to form brittle phases. Less brittle phases, in turn, decrease the likelihood of mechanical integrity issues.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Architecture (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2013118013/02A RU2567759C2 (en) | 2010-09-20 | 2011-08-19 | Nickel-based superalloy |
CN201180045022.4A CN103119183B (en) | 2010-09-20 | 2011-08-19 | Nickel-base superalloy |
US13/825,140 US9593583B2 (en) | 2010-09-20 | 2011-08-19 | Nickel-base superalloy |
EP11758146.2A EP2563943B1 (en) | 2010-09-20 | 2011-08-19 | Nickel-base superalloy |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10177620.1 | 2010-09-20 | ||
EP10177620A EP2431489A1 (en) | 2010-09-20 | 2010-09-20 | Nickel-base superalloy |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2012038166A2 true WO2012038166A2 (en) | 2012-03-29 |
WO2012038166A3 WO2012038166A3 (en) | 2012-09-07 |
Family
ID=43063859
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2011/064310 WO2012038166A2 (en) | 2010-09-20 | 2011-08-19 | Nickel-base superalloy |
Country Status (5)
Country | Link |
---|---|
US (1) | US9593583B2 (en) |
EP (2) | EP2431489A1 (en) |
CN (1) | CN103119183B (en) |
RU (1) | RU2567759C2 (en) |
WO (1) | WO2012038166A2 (en) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8992699B2 (en) | 2009-05-29 | 2015-03-31 | General Electric Company | Nickel-base superalloys and components formed thereof |
CN105492639B (en) * | 2013-07-23 | 2018-05-22 | 通用电气公司 | The component of superalloy and its formation |
US9404388B2 (en) | 2014-02-28 | 2016-08-02 | General Electric Company | Article and method for forming an article |
CN104087786B (en) * | 2014-06-25 | 2016-06-15 | 盐城市鑫洋电热材料有限公司 | A kind of nickel chromium triangle composite electrothermal material and preparation method thereof |
CN104789817B (en) * | 2015-04-26 | 2016-09-07 | 北京金恒博远冶金技术发展有限公司 | Engine turbine ODS high-temperature alloy material and preparation method thereof |
CN104862533B (en) * | 2015-04-26 | 2016-08-17 | 北京金恒博远冶金技术发展有限公司 | engine turbine high-temperature alloy material and preparation method thereof |
CN105950917A (en) * | 2016-05-26 | 2016-09-21 | 张日龙 | Heat-resistant alloy and preparing method thereof |
CN106702217A (en) * | 2017-03-07 | 2017-05-24 | 四川六合锻造股份有限公司 | Ni-Cr-Co-Mo-Al-Ti high-temperature alloy material and preparation method thereof |
RU2636338C1 (en) * | 2017-03-14 | 2017-11-22 | Акционерное общество "Научно-производственное объединение "Центральный научно-исследовательский институт технологии машиностроения", АО "НПО "ЦНИИТМАШ" | Nickel-base heat resistant alloy for casting nozzle vanes of gas turbine plants |
JP6965364B2 (en) * | 2017-04-21 | 2021-11-10 | シーアールエス ホールディングス, インコーポレイテッドCrs Holdings, Incorporated | Precipitation hardening cobalt-nickel superalloys and articles manufactured from them |
IT201800003601A1 (en) * | 2018-03-15 | 2019-09-15 | Nuovo Pignone Tecnologie Srl | HIGH-PERFORMANCE METAL ALLOY FOR ADDITIVE MANUFACTURING OF MACHINE COMPONENTS |
EP3575424A1 (en) * | 2018-06-01 | 2019-12-04 | Siemens Aktiengesellschaft | Improvements relating to superalloy components |
CN110484777B (en) * | 2019-09-23 | 2020-12-15 | 烟台通用节能设备有限公司 | High-temperature wear-resistant corrosion-resistant alloy and production process thereof |
CN112342440A (en) * | 2020-10-11 | 2021-02-09 | 深圳市万泽中南研究院有限公司 | Directional solidification nickel-based high-temperature alloy |
CN113265566B (en) * | 2021-05-19 | 2022-01-28 | 山西太钢不锈钢股份有限公司 | Corrosion-resistant nickel-based alloy |
CN115652266A (en) * | 2022-10-21 | 2023-01-31 | 中国科学院金属研究所 | Machinable CoCrAlY target alloy and preparation method thereof |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0325760A1 (en) | 1988-01-18 | 1989-08-02 | Asea Brown Boveri Ag | Work piece made of a nickel base superalloy hardened by dispersion of oxides |
JPH10317080A (en) | 1997-05-22 | 1998-12-02 | Toshiba Corp | Ni(nickel)-base superalloy, production of ni-base superalloy, and ni-base superalloy parts |
US20030041930A1 (en) | 2001-08-30 | 2003-03-06 | Deluca Daniel P. | Modified advanced high strength single crystal superalloy composition |
US20050194068A1 (en) | 2000-11-30 | 2005-09-08 | Pierre Caron | Nickel-based superalloy having very high resistance to hot-corrosion for monocrystalline blades of industrial turbines |
EP1914327A1 (en) | 2006-10-17 | 2008-04-23 | Siemens Aktiengesellschaft | Nickel-base superalloy |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US362064A (en) * | 1887-05-03 | Lightning-rod | ||
US3333957A (en) * | 1966-05-18 | 1967-08-01 | Martin Marietta Corp | Cobalt-base alloys |
US3459545A (en) * | 1967-02-20 | 1969-08-05 | Int Nickel Co | Cast nickel-base alloy |
US3526499A (en) * | 1967-08-22 | 1970-09-01 | Trw Inc | Nickel base alloy having improved stress rupture properties |
US4039330A (en) | 1971-04-07 | 1977-08-02 | The International Nickel Company, Inc. | Nickel-chromium-cobalt alloys |
US3677747A (en) * | 1971-06-28 | 1972-07-18 | Martin Marietta Corp | High temperature castable alloys and castings |
US4152488A (en) * | 1977-05-03 | 1979-05-01 | United Technologies Corporation | Gas turbine blade tip alloy and composite |
JPS5576038A (en) * | 1978-12-04 | 1980-06-07 | Hitachi Ltd | High strength high toughness cobalt-base alloy |
US4526749A (en) * | 1984-07-02 | 1985-07-02 | Cabot Corporation | Tantalum-columbium-molybdenum-tungsten alloy |
US5141704A (en) * | 1988-12-27 | 1992-08-25 | Japan Atomic Energy Res. Institute | Nickel-chromium-tungsten base superalloy |
RU2016118C1 (en) | 1991-07-19 | 1994-07-15 | Малое многопрофильное предприятие "Техматус" | Nickel based alloy |
US6224673B1 (en) * | 1999-08-11 | 2001-05-01 | General Electric Company | Apparatus for masking turbine components during vapor phase diffusion coating |
US20030111138A1 (en) | 2001-12-18 | 2003-06-19 | Cetel Alan D. | High strength hot corrosion and oxidation resistant, directionally solidified nickel base superalloy and articles |
WO2006059784A1 (en) * | 2004-11-30 | 2006-06-08 | Nippon Steel Corporation | Steel and steel wire for high strength spring |
US8075839B2 (en) | 2006-09-15 | 2011-12-13 | Haynes International, Inc. | Cobalt-chromium-iron-nickel alloys amenable to nitride strengthening |
US7632075B2 (en) * | 2007-02-15 | 2009-12-15 | Siemens Energy, Inc. | External profile for turbine blade airfoil |
CN100543164C (en) * | 2007-04-25 | 2009-09-23 | 中国科学院金属研究所 | A kind of directional solidification heat corrosion resistant nickel base cast superalloy and preparation method thereof |
US8105043B2 (en) * | 2009-06-30 | 2012-01-31 | Pratt & Whitney Canada Corp. | HP turbine blade airfoil profile |
-
2010
- 2010-09-20 EP EP10177620A patent/EP2431489A1/en not_active Withdrawn
-
2011
- 2011-08-19 CN CN201180045022.4A patent/CN103119183B/en active Active
- 2011-08-19 RU RU2013118013/02A patent/RU2567759C2/en active
- 2011-08-19 US US13/825,140 patent/US9593583B2/en active Active
- 2011-08-19 WO PCT/EP2011/064310 patent/WO2012038166A2/en active Application Filing
- 2011-08-19 EP EP11758146.2A patent/EP2563943B1/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0325760A1 (en) | 1988-01-18 | 1989-08-02 | Asea Brown Boveri Ag | Work piece made of a nickel base superalloy hardened by dispersion of oxides |
JPH10317080A (en) | 1997-05-22 | 1998-12-02 | Toshiba Corp | Ni(nickel)-base superalloy, production of ni-base superalloy, and ni-base superalloy parts |
US20050194068A1 (en) | 2000-11-30 | 2005-09-08 | Pierre Caron | Nickel-based superalloy having very high resistance to hot-corrosion for monocrystalline blades of industrial turbines |
US20030041930A1 (en) | 2001-08-30 | 2003-03-06 | Deluca Daniel P. | Modified advanced high strength single crystal superalloy composition |
EP1914327A1 (en) | 2006-10-17 | 2008-04-23 | Siemens Aktiengesellschaft | Nickel-base superalloy |
Also Published As
Publication number | Publication date |
---|---|
US9593583B2 (en) | 2017-03-14 |
RU2567759C2 (en) | 2015-11-10 |
RU2013118013A (en) | 2014-10-27 |
WO2012038166A3 (en) | 2012-09-07 |
EP2563943B1 (en) | 2014-12-17 |
CN103119183B (en) | 2015-05-06 |
CN103119183A (en) | 2013-05-22 |
US20130177442A1 (en) | 2013-07-11 |
EP2431489A1 (en) | 2012-03-21 |
EP2563943A2 (en) | 2013-03-06 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US9593583B2 (en) | Nickel-base superalloy | |
RU2521924C2 (en) | Alloy, protective layer and part | |
US9556748B2 (en) | Layer system with double MCrAlX metallic layer | |
US20130136948A1 (en) | Alloy, protective layer and component | |
EP1997923B1 (en) | Method for producing an ni-base superalloy | |
JP2005298973A (en) | Nickel based superalloy, composition, article and gas turbine engine blade | |
US20070071607A1 (en) | High-temperature-resistant component | |
CN111172430A (en) | Nickel-based superalloy and article | |
US20130302638A1 (en) | Alloy, protective layer and component | |
EP2098606A1 (en) | A MCrAlY alloy, methods to produce a MCrAlY layer and a honeycomb seal | |
US11092034B2 (en) | Alloy, protective layer and component | |
JP5615970B2 (en) | Metal bond coats or alloys and parts with high gamma / gamma prime transition temperatures | |
JP6982172B2 (en) | Ni-based superalloy castings and Ni-based superalloy products using them | |
KR101597924B1 (en) | Layer system having a two-ply metal layer | |
US20130288072A1 (en) | Alloy, protective layer and component | |
US20130337286A1 (en) | Alloy, protective coating, and component | |
JPH07207391A (en) | Alloy material for turbine blade of gas turbine | |
US11092035B2 (en) | Alloy, protective layer and component | |
US11739398B2 (en) | Nickel-based superalloy | |
US20120288730A1 (en) | Alloy, protective layer, and component | |
US20120328900A1 (en) | Alloy, protective layer, and component | |
EP2622110B1 (en) | METALLIC BONDCOAT OR ALLOY WITH A HIGH y/y' TRANSITION TEMPERATURE AND A COMPONENT | |
JP2015034344A (en) | METALLIC BONDCOAT WITH HIGH γ/γ' TRANSITION TEMPERATURE AND COMPONENT |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 201180045022.4 Country of ref document: CN |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 11758146 Country of ref document: EP Kind code of ref document: A2 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2011758146 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 10531/DELNP/2012 Country of ref document: IN |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 13825140 Country of ref document: US |
|
ENP | Entry into the national phase |
Ref document number: 2013118013 Country of ref document: RU Kind code of ref document: A |