RU2000114253A - PRODUCT EXPOSED BY HOT AGGRESSIVE GAS, IN PARTICULAR, PART OF GAS TURBINE (OPTIONS) AND METHOD FOR PRODUCING A HEAT-INSULATING LAYER FOR THE PRODUCT - Google Patents

PRODUCT EXPOSED BY HOT AGGRESSIVE GAS, IN PARTICULAR, PART OF GAS TURBINE (OPTIONS) AND METHOD FOR PRODUCING A HEAT-INSULATING LAYER FOR THE PRODUCT

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Publication number
RU2000114253A
RU2000114253A RU2000114253/02A RU2000114253A RU2000114253A RU 2000114253 A RU2000114253 A RU 2000114253A RU 2000114253/02 A RU2000114253/02 A RU 2000114253/02A RU 2000114253 A RU2000114253 A RU 2000114253A RU 2000114253 A RU2000114253 A RU 2000114253A
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RU
Russia
Prior art keywords
product
preceding paragraphs
heat
mixture
insulating layer
Prior art date
Application number
RU2000114253/02A
Other languages
Russian (ru)
Other versions
RU2218447C2 (en
Inventor
Беате ХАЙМБЕРГ
Вольфрам БЭЛЕ
Карл КЭМПТЕР
Ульрих БАСТ
Томас ХАУБОЛЬД
Михаель ХОФФМАНН
Аксель ЭНДРИСС
Петер ГРАЙЛЬ
Чу-Ван ХОНГ
Фритц АЛЬДИНГЕР
Ханс-Й. ЗАЙФЕРТ
Original Assignee
Сименс Акциенгезелльшафт
Роллс-Ройс Дойчланд Гмбх
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Application filed by Сименс Акциенгезелльшафт, Роллс-Ройс Дойчланд Гмбх filed Critical Сименс Акциенгезелльшафт
Publication of RU2000114253A publication Critical patent/RU2000114253A/en
Application granted granted Critical
Publication of RU2218447C2 publication Critical patent/RU2218447C2/en

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Claims (14)

1. Изделие (3), подвергаемое воздействию горячего агрессивного газа, снабженное металлической основой (1) с нанесенным керамическим теплоизоляционным слоем (4), который содержит металлическую систему смеси оксидов, включая алюминат лантана.1. The product (3), exposed to hot aggressive gas, equipped with a metal base (1) coated with a ceramic heat-insulating layer (4), which contains a metal system of a mixture of oxides, including lanthanum aluminate. 2. Изделие (3) по п. 1, отличающееся тем, что лантан в алюминате лантана частично замещен по меньшей мере одним замещающим элементом. 2. The product (3) according to claim 1, characterized in that the lanthanum in lanthanum aluminate is partially substituted by at least one replacement element. 3. Изделие (3) по п. 2, отличающееся тем, что по меньшей мере один замещающий элемент происходит из группы лантанидов, в частности, является гадолинием (Gd). 3. The product (3) according to claim 2, characterized in that at least one replacement element comes from the group of lanthanides, in particular, gadolinium (Gd). 4. Изделие (3), подвергаемое воздействию горячего агрессивного газа, снабженное металлической основой (1), на которую нанесен керамический теплоизоляционный слой (4), который содержит металлическую систему смеси оксидов, включая цирконат кальция, в котором кальций частично замещен по меньшей мере одним элементом, в частности, стронцием (Sr). 4. The product (3), exposed to hot aggressive gas, equipped with a metal base (1), on which is applied a ceramic thermal insulation layer (4), which contains a metal system of a mixture of oxides, including calcium zirconate, in which calcium is partially substituted by at least one element, in particular, strontium (Sr). 5. Изделие (3) по любому из предыдущих пунктов, отличающееся тем, что замещающий элемент замещает до 0,8, предпочтительно, 0,5 лантана или, соответственно, кальция. 5. The product (3) according to any one of the preceding paragraphs, characterized in that the replacement element replaces up to 0.8, preferably 0.5 lanthanum or, respectively, calcium. 6. Изделие (3) по любому из предыдущих пунктов, отличающееся тем, что металлическая система смеси оксидов содержит дополнительный оксид. 6. The product (3) according to any one of the preceding paragraphs, characterized in that the metal oxide mixture system contains an additional oxide. 7. Изделие (3) по любому из предыдущих пунктов, отличающееся тем, что между основой (1) и теплоизоляционным слоем (4) расположен образующий связывающий оксид адгезионный слой (2). 7. The product (3) according to any one of the preceding paragraphs, characterized in that between the base (1) and the heat-insulating layer (4) there is an oxide bonding adhesive layer (2). 8. Изделие (3) по любому из предыдущих пунктов, отличающееся тем, что адгезионный слой (2) является сплавом, включающим один из элементов металлической системы смеси оксидов. 8. The product (3) according to any one of the preceding paragraphs, characterized in that the adhesive layer (2) is an alloy comprising one of the elements of the metal system of a mixture of oxides. 9. Изделие (3) по любому из предыдущих пунктов, отличающееся тем, что металлическая основа (1) содержит жаропрочный сплав на основе никеля, кобальта и/или хрома. 9. The product (3) according to any one of the preceding paragraphs, characterized in that the metal base (1) contains a heat-resistant alloy based on nickel, cobalt and / or chromium. 10. Изделие (3) по любому из предыдущих пунктов, отличающееся тем, что оно выполнено в виде детали тепловой машины, в частности, газовой турбины. 10. The product (3) according to any one of the preceding paragraphs, characterized in that it is made in the form of a part of a heat engine, in particular, a gas turbine. 11. Изделие (3) по пункту 10, отличающееся тем, что оно выполнено в виде рабочей лопатки турбины, направляющей лопатки турбины или теплозащитного экрана камеры сгорания. 11. The product (3) according to paragraph 10, characterized in that it is made in the form of a working turbine blade, a guide blade of the turbine or a heat shield of the combustion chamber. 12. Изделие (3) по любому из предыдущих пунктов, отличающееся тем, что коэффициент теплового расширения α тройного оксида составляет между 7•10-6/К и 17•10-6/К.12. The product (3) according to any one of the preceding paragraphs, characterized in that the coefficient of thermal expansion α of the ternary oxide is between 7 • 10 -6 / K and 17 • 10 -6 / K. 13. Изделие (3) по любому из предыдущих пунктов, отличающееся тем, что коэффициент теплопроводности тройного оксида составляет между 1,0 вт/м К и 4,0 вт/м К. 13. The product (3) according to any one of the preceding paragraphs, characterized in that the thermal conductivity of the ternary oxide is between 1.0 W / m K and 4.0 W / m K. 14. Способ изготовления теплоизоляционного слоя на изделии с металлической основой, причем посредством плазменного напыления или способа осаждения из газопаровой фазы наносят предварительно прореагировавшую металлическую систему смеси оксидов, включая алюминат лантана и/или цирконат кальция, в котором кальций частично замещен по меньшей мере одним элементом, в частности, стронцием (Sr). 14. A method of manufacturing a heat-insulating layer on an article with a metal base, wherein a pre-reacted metal system of a mixture of oxides, including lanthanum aluminate and / or calcium zirconate, in which calcium is partially replaced by at least one element, is applied by plasma spraying or by a vapor deposition method. in particular, strontium (Sr).
RU2000114253/02A 1997-11-03 1998-11-03 A gas turbine member (versions) and method to manufacture its heat-insulating coating RU2218447C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19748508 1997-11-03
DE19748508.1 1997-11-03

Publications (2)

Publication Number Publication Date
RU2000114253A true RU2000114253A (en) 2002-06-10
RU2218447C2 RU2218447C2 (en) 2003-12-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000114253/02A RU2218447C2 (en) 1997-11-03 1998-11-03 A gas turbine member (versions) and method to manufacture its heat-insulating coating

Country Status (6)

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US (2) US6440575B1 (en)
EP (1) EP1029101B1 (en)
JP (1) JP2001521988A (en)
DE (1) DE59801471D1 (en)
RU (1) RU2218447C2 (en)
WO (1) WO1999023271A1 (en)

Families Citing this family (54)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6365281B1 (en) * 1999-09-24 2002-04-02 Siemens Westinghouse Power Corporation Thermal barrier coatings for turbine components
EP1143030A1 (en) * 2000-04-03 2001-10-10 ABB Alstom Power N.V. Tip material for a turbine blade and method of manufacturing or repairing a tip of a turbine blade
JP3955724B2 (en) * 2000-10-12 2007-08-08 株式会社ルネサステクノロジ Manufacturing method of semiconductor integrated circuit device
US6812176B1 (en) 2001-01-22 2004-11-02 Ohio Aerospace Institute Low conductivity and sintering-resistant thermal barrier coatings
US7001859B2 (en) * 2001-01-22 2006-02-21 Ohio Aerospace Institute Low conductivity and sintering-resistant thermal barrier coatings
US6846574B2 (en) * 2001-05-16 2005-01-25 Siemens Westinghouse Power Corporation Honeycomb structure thermal barrier coating
JP2003073794A (en) * 2001-06-18 2003-03-12 Shin Etsu Chem Co Ltd Heat-resistant coated member
US6887588B2 (en) * 2001-09-21 2005-05-03 General Electric Company Article protected by thermal barrier coating having a sintering inhibitor, and its fabrication
US6821641B2 (en) * 2001-10-22 2004-11-23 General Electric Company Article protected by thermal barrier coating having a sintering inhibitor, and its fabrication
DE10200803A1 (en) * 2002-01-11 2003-07-31 Forschungszentrum Juelich Gmbh Production of a ceramic material for a thermal insulation layer and a thermal insulation layer containing the material
ES2256351T3 (en) * 2002-04-10 2006-07-16 Siemens Aktiengesellschaft THERMAL INSULATION LAYER SYSTEM.
DE10226295A1 (en) * 2002-06-13 2004-01-08 Forschungszentrum Jülich GmbH Thermal insulation layer made of a complex perovskite
JP4481027B2 (en) * 2003-02-17 2010-06-16 財団法人ファインセラミックスセンター Thermal barrier coating member and manufacturing method thereof
DE10334698A1 (en) * 2003-07-25 2005-02-10 Rolls-Royce Deutschland Ltd & Co Kg Shroud segment for a turbomachine
US20060177676A1 (en) * 2003-08-13 2006-08-10 Ulrich Bast Heat-insulation material and arrangement of a heat-insulation layer containing said heat-insulation material
EP1658480A1 (en) * 2003-08-13 2006-05-24 Siemens Aktiengesellschaft Arrangement of at least one heat-insulation layer on a carrier body
US6969555B2 (en) * 2003-10-06 2005-11-29 General Electric Company Aluminate coating for a silicon containing substrate
US20050129869A1 (en) * 2003-12-12 2005-06-16 General Electric Company Article protected by a thermal barrier coating having a group 2 or 3/group 5 stabilization-composition-enriched surface
DE102004025798A1 (en) * 2004-05-26 2005-12-22 Mtu Aero Engines Gmbh Thermal barrier coating system
EP1657536A1 (en) * 2004-11-05 2006-05-17 Siemens Aktiengesellschaft Device comprising at least one luminescent thermal barrier coating on a substrate
JP2007052100A (en) * 2005-08-16 2007-03-01 Konica Minolta Opto Inc Optical reflection member
US7504157B2 (en) * 2005-11-02 2009-03-17 H.C. Starck Gmbh Strontium titanium oxides and abradable coatings made therefrom
US7662489B2 (en) * 2006-01-20 2010-02-16 United Technologies Corporation Durable reactive thermal barrier coatings
FR2897748B1 (en) * 2006-02-20 2008-05-16 Snecma Services Sa THERMAL BARRIER DEPOSITION METHOD BY PLASMA TORCH
ES2527741T3 (en) 2006-06-08 2015-01-29 Siemens Aktiengesellschaft Coated turbine component and method of coating a turbine component
DE102006040360A1 (en) * 2006-08-29 2008-03-06 FNE Forschungsinstitut für Nichteisen-Metalle Freiberg GmbH Heat insulation used in gas turbine components comprises a covering layer containing zirconium oxide doped with barium zirconate and yttrium oxide
JP5100313B2 (en) * 2007-10-31 2012-12-19 株式会社東芝 Method for producing lanthanum oxide compound
EP2128299B1 (en) 2008-05-29 2016-12-28 General Electric Technology GmbH Multilayer thermal barrier coating
EP2196559A1 (en) 2008-12-15 2010-06-16 ALSTOM Technology Ltd Thermal barrier coating system, components coated therewith and method for applying a thermal barrier coating system to components
US20110110790A1 (en) * 2009-11-10 2011-05-12 General Electric Company Heat shield
US20150274981A1 (en) * 2010-09-22 2015-10-01 Skyworks Solutions, Inc. Dual function lanthanide coatings
US9347126B2 (en) 2012-01-20 2016-05-24 General Electric Company Process of fabricating thermal barrier coatings
DE102012101032A1 (en) * 2012-02-08 2013-08-08 Eads Deutschland Gmbh Rotary piston engine and method of manufacturing a rotary piston engine
WO2015053947A1 (en) * 2013-10-09 2015-04-16 United Technologies Corporation Thermal barrier coating with improved adhesion
US10676403B2 (en) 2014-01-16 2020-06-09 Honeywell International Inc. Protective coating systems for gas turbine engine applications and methods for fabricating the same
US9243511B2 (en) 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
WO2015130528A1 (en) 2014-02-25 2015-09-03 Siemens Aktiengesellschaft Turbine component thermal barrier coating with crack isolating engineered surface features
US9151175B2 (en) 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays
US8939706B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface
WO2016133987A2 (en) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Forming cooling passages in combustion turbine superalloy castings
RU2591024C2 (en) * 2014-05-05 2016-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" Method of processing working surfaces of parts of gas turbine plants
RU2588956C2 (en) * 2014-05-06 2016-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" Method of treating working surfaces of gas-turbine plants
RU2588973C2 (en) * 2014-05-06 2016-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" Method for treatment of working surfaces of parts of bladed machines
WO2015194861A1 (en) * 2014-06-17 2015-12-23 한국에너지기술연구원 Thin plate bonding method and thin plate assembly
WO2016133583A1 (en) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Turbine shroud with abradable layer having ridges with holes
DE102015205807A1 (en) * 2015-03-31 2016-10-06 Siemens Aktiengesellschaft Coating system for gas turbines
WO2016172144A1 (en) 2015-04-23 2016-10-27 University Of Florida Research Foundation, Inc. Method for the generation of power
CN107868924B (en) * 2016-09-23 2018-10-09 北京华石联合能源科技发展有限公司 A kind of thermal barrier coating and the superhigh temperature floating bed hydrogenation cold wall reactor comprising it
EP3470680A1 (en) * 2017-10-16 2019-04-17 OneSubsea IP UK Limited Erosion resistant blades for compressors
WO2020098967A1 (en) * 2018-11-13 2020-05-22 Oerlikon Surface Solutions Ag, Pfäffikon Coated article exhibiting high corrosion and erosion resistance including ain-layer
WO2021046548A1 (en) * 2019-09-06 2021-03-11 The University Of Connecticut Thermal barrier coatings for internal combustion engines
US11686208B2 (en) 2020-02-06 2023-06-27 Rolls-Royce Corporation Abrasive coating for high-temperature mechanical systems
US11415004B2 (en) 2020-12-09 2022-08-16 Honeywell International Inc. Corrosion and oxidation resistant coatings for gas turbine engines, and methods for producing the same
CN113214739A (en) * 2021-06-22 2021-08-06 哈尔滨工业大学 High-temperature-resistant organic silicon coating doped with divalent metal zirconium salt and preparation method thereof

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5393134A (en) 1977-01-27 1978-08-15 Mitsubishi Heavy Ind Ltd Heattproof acidification resistance metal portion material
US4339509A (en) 1979-05-29 1982-07-13 Howmet Turbine Components Corporation Superalloy coating composition with oxidation and/or sulfidation resistance
US4321310A (en) 1980-01-07 1982-03-23 United Technologies Corporation Columnar grain ceramic thermal barrier coatings on polished substrates
US4585481A (en) 1981-08-05 1986-04-29 United Technologies Corporation Overlays coating for superalloys
DE3539029A1 (en) * 1985-11-02 1987-05-07 Bbc Brown Boveri & Cie HIGH TEMPERATURE PROTECTIVE LAYER AND METHOD FOR THEIR PRODUCTION
DE3543802A1 (en) * 1985-12-12 1987-06-19 Bbc Brown Boveri & Cie HIGH TEMPERATURE PROTECTIVE LAYER AND METHOD FOR THEIR PRODUCTION
US4764341A (en) 1987-04-27 1988-08-16 International Business Machines Corporation Bonding of pure metal films to ceramics
DE3926479A1 (en) 1989-08-10 1991-02-14 Siemens Ag RHENIUM-PROTECTIVE COATING, WITH GREAT CORROSION AND / OR OXIDATION RESISTANCE
JP2773050B2 (en) 1989-08-10 1998-07-09 シーメンス アクチエンゲゼルシヤフト Heat-resistant and corrosion-resistant protective coating layer
JPH03226553A (en) * 1990-01-31 1991-10-07 Nippon Steel Corp A.c. plasma torch having high durability
US5077140A (en) 1990-04-17 1991-12-31 General Electric Company Coating systems for titanium oxidation protection
JP2747087B2 (en) * 1990-05-31 1998-05-06 新日本製鐵株式会社 Thermal spray coating material and thermal spray coating heat resistant member
US5032557A (en) * 1990-07-02 1991-07-16 Tocalo Co., Ltd. Thermal spray material and and thermal sprayed member using the same
US5082741A (en) * 1990-07-02 1992-01-21 Tocalo Co., Ltd. Thermal spray material and thermal sprayed member using the same
US5401307A (en) 1990-08-10 1995-03-28 Siemens Aktiengesellschaft High temperature-resistant corrosion protection coating on a component, in particular a gas turbine component
JPH04231451A (en) * 1990-12-28 1992-08-20 Nippon Steel Corp Thermal spray material and sprayed heat-resistant member
JPH04231452A (en) * 1990-12-28 1992-08-20 Nippon Steel Corp Thermal spray material and sprayed heat-resistant member
US5236787A (en) 1991-07-29 1993-08-17 Caterpillar Inc. Thermal barrier coating for metallic components
JP2697469B2 (en) * 1992-04-03 1998-01-14 株式会社日立製作所 Gas turbine blades, vanes and combustor liners and manufacturing method
GB2286977A (en) 1994-02-24 1995-09-06 Lee Chwen Chern Inorganic coating composition
US5512382A (en) 1995-05-08 1996-04-30 Alliedsignal Inc. Porous thermal barrier coating
US6258467B1 (en) * 2000-08-17 2001-07-10 Siemens Westinghouse Power Corporation Thermal barrier coating having high phase stability

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