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1.发明专利
公开(公告)号：JP2002167636A
公开(公告)日：2002-06-11
申请号：JP2001330211
申请日：2001-10-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZELESKY MARK F , GUPTA DINESH K , ALAN D SETEL
Abstract: PROBLEM TO BE SOLVED: To provide a low density superalloy and no bond coat thermal barrier system. SOLUTION: The combination of an alloy and a TBC system can be used to fabricate lightweight turbine blades with reduced blade pull. The alloy has a composition substantially consisting of, by weight, about 7 to about 13% Cr, about 4.5 to about 6.7% Al, about 0.5 to about 2% Ti, about 3 to about 12% W, about
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公开(公告)号：JP2000096261A
公开(公告)日：2000-04-04
申请号：JP16034699
申请日：1999-06-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOSE SUDHANGSU , GUPTA DINESH K , MARCIN JEANINE T , ULION NICHOLAS E
Abstract: PROBLEM TO BE SOLVED: To provide a heat insulating coating system having the advantage or reducing the weight and moreover limiting the oxidation even in the case ceramic is peeled. SOLUTION: In a heat insulating coating system 20 for a base material 22 made of a superalloy, a superalloy of a type capable of forming an adhesive alumina layer 26 is used. At first, a bonding coat 24 is applied to the local region of the base material 22 in such a manner that a part of the base material 22 is left exposed. The local region is ordinarily defined as the region in which heat insulating coating is first chipped such as the front edge and rear edge of airfoil or the like. Next, the alumina layer 26 is formed on the exposed part of the base material 22 and the bonding coat 24 by heat treatment. Successively, the alumina layer 26 is applied with a ceramic layer 28. In this way, even in the case the ceramic material 28 is peeled, the local bonding coat 24 is left, so that the oxidation of the base material can be limited.
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公开(公告)号：JPH11229810A
公开(公告)日：1999-08-24
申请号：JP33516798
申请日：1998-11-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN , GUPTA DINESH K , LAGUEUX KEN , DEMASI-MARCIN JEANINE T
Abstract: PROBLEM TO BE SOLVED: To achieve an abrasive end portion for a seal mechanism of a gas turbine engine that receives a high degree of wear which is more durable, and the production of which is less expensive. SOLUTION: An abrasive end portion 28 includes a zirconium oxide wear coating 44 which is harder than a abraded seal surface such that it is able to grind the abraded seal surface, and which directly covers the top which has substantially no macrogrit. The coating 44 has a pillar-like structure and contains a stabilizer of approximately 3 wt.% to approximately 25 wt.%. The stabilizer may be selected from yttrium oxide, magnesium oxide, calcium oxide, or a mixture of these materials.
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公开(公告)号：DE69826096T3
公开(公告)日：2012-01-12
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
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公开(公告)号：DE60112382T2
公开(公告)日：2006-06-01
申请号：DE60112382
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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Patent Agency Ranking
公开(公告)号：DE69826096T2
公开(公告)日：2005-09-29
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：DE60112382D1
公开(公告)日：2005-09-08
申请号：DE60112382
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：DE69903595D1
公开(公告)日：2002-11-28
申请号：DE69903595
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：FR2716237A1
公开(公告)日：1995-08-18
申请号：FR9501793
申请日：1995-02-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MELVIN FRELING , 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：AU626355B2
公开(公告)日：1992-07-30
申请号：AU4590389
申请日：1989-12-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUPTA DINESH K , OLSON WALTER E
IPC: C22C19/00 , C23C4/08 , C23C10/02 , C23C10/48 , C23C28/02 , C22C19/05 , C22C19/07 , C22C30/00 , C23C4/12 , C23C4/18 , C23C10/60
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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