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公开(公告)号：CA2274412C
公开(公告)日：2007-09-04
申请号：CA2274412
申请日：1999-06-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOSE SUDHANGSHU , GUPTA DINESH K , MARCIN JEANINE T , ULION NICHOLAS E
Abstract: A thermal barrier coating system for a superalloy substrate is disclosed. T he superalloy is preferably of the type that is capable of forming an adherent alumina layer. A bond coat is applied to a local area of the substrate, so that a portion of the substrate remains exposed. The localized area is defined to be the area(s) a t which a TBC typically fails first, e.g., the leading and trailing edges of an airfoi l, or other area. An alumina layer is formed on the remaining portion of the substrate, and al so on the bond coat. A ceramic layer is then applied on the alumina layer. Even if the ceramic material is removed, the localized bond coat remains, and reduces the rate a t which the underlying substrate oxidizes. A coated article is also disclosed, as is a system that utilizes a conventional superalloy and aluminide coating with the localized bond coat.
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公开(公告)号：AT301203T
公开(公告)日：2005-08-15
申请号：AT01309195
申请日：2001-10-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZELESKY MARK F , GUPTA DINESH K , CETEL ALAN D
Abstract: A low density superalloy and no bond coat thermal barrier coating system is described. The combination of alloy and TBC system can be used to fabricate light weight turbine blades with reduced blade pull. The present invention concerns nickel base superalloy articles which include additions of yttrium and hafnium that causes them to develop a durable, adherent aluminium oxide coating which will adhere to both the substrate and a ceramic thermal barrier coating thereby eliminating the need for an intermediate bond coat.
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公开(公告)号：FR2716237B1
公开(公告)日：1996-05-31
申请号：FR9501793
申请日：1995-02-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN , GUPTA DINESH K
Abstract: In a gas turbine engine, a method and apparatus for containing molten materials and ignited titanium and titanium alloys within the confines of the turbine engine environment. The method includes the step of first applying a bond coating to the inner surface of the outer compressor casing. The bond coating is then plasma oversprayed with a non-reactive, thermally insulative ceramic top coating. The apparatus includes a substrate having a bond coating and a ceramic top coating, surrounding at least a portion of the gas turbine engine, for containing turbine engine fires within the turbine engine environment. Preferably, the bond coating is a Ni-Co-Cr-Al-Y alloy, and the top coat is stabilized zirconia.
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公开(公告)号：AU601235B2
公开(公告)日：1990-09-06
申请号：AU8068787
申请日：1987-11-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MILANIAK MICHAEL S , GUPTA DINESH K , OLSON WALTER E
Abstract: Methods are described for forming an yttrium enriched aluminide coating on the surface of a nickel or cobalt base superalloy article. In one preferred embodiment, a pack mixture for forming the coating consists essentially of, by weight percent, 5-35 of an Al-Y-Si alloy, 1-20 CoI2, balance Y2O3.
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公开(公告)号：BR8906389A
公开(公告)日：1990-08-21
申请号：BR8906389
申请日：1989-12-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUPTA DINESH K , OLSON WALTER E
Abstract: A protective coating system for superalloys is described. The coating is an active element enriched aluminide, and can be formed by aluminizing an overlay coated superalloy, wherein during the aluminizing process, aluminum diffuses completely through the overlay coating and into the substrate. The coating system exhibits desirable oxidation resistance and resistance to thermal fatigue cracking, due to the presence of oxygen active elements in the overlay.
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Patent Agency Ranking26.发明公开
公开(公告)号：EP2971239A4
公开(公告)日：2017-03-29
申请号：EP14767987
申请日：2014-03-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TRUBELJA MLADEN F , GUPTA DINESH K , TRYON BRIAN S , UCASZ MARK T , ZIMMERMAN BENJAMIN J
CPC classification number: C23C14/08 , C23C14/16 , C23C14/24 , C23C14/325 , F01D5/288 , F05D2300/13 , F05D2300/175 , F05D2300/2118 , Y10T428/12618
Abstract: A coated article has: a metallic substrate (22); a bondcoat (30); and a thermal barrier coating (TBC) (28). The bondcoat has a first layer (32) and a second layer (34), the first layer having a lower Cr content than the second layer.
Abstract translation: 涂层制品具有：金属基材（22）; 一个bondcoat（30）; 和热障涂层（TBC）（28）。 该结合涂层具有第一层（32）和第二层（34），第一层具有比第二层更低的Cr含量。
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公开(公告)号：DE69826096D1
公开(公告)日：2004-10-14
申请号：DE69826096
申请日：1998-11-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN , GUPTA DINESH K , LAGUEUX KEN , DEMASI-MARCIN JEANINE T
Abstract: A gas turbine engine seal system includes a rotating member 12;30 having an abrasive tip 28 disposed in use in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat 44 having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface. The coat 44 comprises zirconium oxide and about 3% to 25% of a stabilizer selected from yttrium oxide, magnesium oxide, calcium oxide or mixtures thereof.
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公开(公告)号：ES2181365T3
公开(公告)日：2003-02-16
申请号：ES99304588
申请日：1999-06-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOSE SUDHANGSU , GUPTA DINESH K , MARCIN JEANINE T , ULION NICHOLAS E
Abstract: A thermal barrier coating system for a superalloy substrate is disclosed. The superalloy is preferably of the type that is capable of forming an adherent alumina layer. A bond coat is applied to a local area of the substrate (24), so that a portion of the substrate remains exposed. The localized area is defined to be the area(s) at which a TBC typically fails first, e.g., the leading (30) and trailing edges (32) of an airfoil (20), or other area. An alumina layer (26) is formed on the remaining portion of the substrate, and also on the bond coat. A ceramic layer (28) is then applied on the alumina layer. Even if the ceramic material is removed, the localized bond coat remains, and reduces the rate at which the underlying substrate oxidizes. A coated article is also disclosed, as is a system that utilizes a conventional superalloy and aluminide coating with the localized bond coat.
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公开(公告)号：SG71165A1
公开(公告)日：2000-03-21
申请号：SG1998004201
申请日：1998-10-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN , GUPTA DINESH K , LAGUEUX KEN , DEMASI-MARCIN JEANINE T
Abstract: A gas turbine engine seal system includes a rotating member 12;30 having an abrasive tip 28 disposed in use in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat 44 having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface. The coat 44 comprises zirconium oxide and about 3% to 25% of a stabilizer selected from yttrium oxide, magnesium oxide, calcium oxide or mixtures thereof.
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公开(公告)号：CA2274412A1
公开(公告)日：1999-12-12
申请号：CA2274412
申请日：1999-06-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOSE SUDHANGSHU , MARCIN JEANINE T , GUPTA DINESH K , ULION NICHOLAS E
Abstract: A thermal barrier coating system for a superalloy substrate is disclosed. The superalloy is preferably of the type that is capable of forming an adherent alumina layer. A bond coat is applied to a local area of the substrate, so that a portion of the substrate remains exposed. The localized area is defined to be the areas) at which a TBC typically fails first, e.g., the leading and trailing edges of an airfoil, or other area. An alumina layer is formed on the remaining portion of the substrate, and also on the bond coat. A ceramic layer is then applied on the alumina layer. Even if the ceramic material is removed, the localized bond coat remains, and reduces the rate at which the underlying substrate oxidizes. A coated article is also disclosed, as is a system that utilizes a conventional superalloy and aluminide coating with the localized bond coat.
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