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公开(公告)号：SG71166A1
公开(公告)日：2000-03-21
申请号：SG1998004211
申请日：1998-10-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZAJCHOWSKI PAUL H , DIAZ ALFONSO , FRELING MELVIN , LALLY JOHN F
Abstract: A process for controllably applying thermal spray coating onto substrates is described. The process includes positioning rotor blades (10) in a fixture (12) rotatable about an axis, forming a spray of particles of softened coating medium in an apparatus for propelling the coating medium towards the blade tips and coating the blade tips by passing the blades through the spray of particles of coating medium. Various process details, including process parameters, are developed.
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公开(公告)号：FR2649125B1
公开(公告)日：1992-08-21
申请号：FR9008410
申请日：1990-07-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ROUTSIS KOSTAS , PARKOS JOSEPH JOHN JR , FRELING MELVIN
Abstract: An abrasive layer is formed on the tip portion of a turbine engine blade made of Ti alloy by (a) electroplating a 12-18 microns thick first Ni layer onto the blade tip; (b) electroplating a max. 1 micron thick second Ni layer; (c) electroplating a third Ni layer, immersing the tip in a slurry of electrically non-conductive particles in an electroplating soln. present on a membrane which is permeable to electric current and the soln., and then contg. electroplating of the third Ni layer; (d) electroplating a fourth Ni layer such that the combined thickness of the third and fourth layers corresponds to 50-95% of the mean dimension of the embedded particles, and (e) heat treating the blade to cause diffusion between the first Ni layer and the blade tip.
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公开(公告)号：AU614315B2
公开(公告)日：1991-08-29
申请号：AU2651388
申请日：1988-12-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUPTA DINESH KUMER , FRELING MELVIN
Abstract: Coated gas turbine engine hardware is described. The hardware comprises a titanium alloy substrate having a coating thereon consisting essentially of titanium nitride wherein the ratio of nitrogen to titanium is greater than one. Such coatings have a residual compressive stress state which aids in minimizing the fatigue debit which would otherwise result from the use of a hard coating on a titanium substrate. Coatings are applied by the use of a vacuum arc deposition process.
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公开(公告)号：AU2651388A
公开(公告)日：1989-06-29
申请号：AU2651388
申请日：1988-12-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUPTA DINESH KUMER , FRELING MELVIN
Abstract: Coated gas turbine engine hardware is described. The hardware comprises a titanium alloy substrate having a coating thereon consisting essentially of titanium nitride wherein the ratio of nitrogen to titanium is greater than one. Such coatings have a residual compressive stress state which aids in minimizing the fatigue debit which would otherwise result from the use of a hard coating on a titanium substrate. Coatings are applied by the use of a vacuum arc deposition process.
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公开(公告)号：SG140539A1
公开(公告)日：2008-03-28
申请号：SG2007058100
申请日：2007-08-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHLICHTING KEVIN W , LITTON DAVID A , MALONEY MICHAEL J , FRELING MELVIN , SMEGGIL JOHN G , SNOW DAVID B
Abstract: SILICATE RESISTANT THERMAL BARRIER COATING WITH ALTERNATING LAYERS A thermal barrier coating system for use on a turbine engine component which reduces sand related distress is provided. The coating system comprises at least one first layer of a stabilized material selected from the group consisting of zirconia, hafnia, and titania and at least one second layer containing at least one of oxyapatite and garnet. Where the coating system comprises multiple first layers and multiple second layers, the layers are formed or deposited in an alternating manner.
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Patent Agency Ranking
公开(公告)号：SG134216A1
公开(公告)日：2007-08-29
申请号：SG2006086771
申请日：2006-12-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LITTON DAVID A , SCHLICHTING KEVIN W , FRELING MELVIN , SMEGGIL JOHN G , SNOW DAVID B , MALONEY MICHAEL J
Abstract: A turbine engine component is provided which has a substrate and a thermal barrier coating applied over the substrate. The thermal barrier coating comprises at least one layer of a first material selected from the group consisting of a zirconate, a hafnate, a titanate, and mixtures thereof, which first material has been mixed with, and contains, from about 25 to 99 wt% of at least one oxide. The at least one oxide comprises at least one oxide of a material selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, indium, and yttrium. If desired, a metallic bond coat may be present between the substrate and the thermal barrier coating system. A method for forming the thermal barrier coating system of the present invention is described.
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17.发明专利
公开(公告)号：SG134215A1
公开(公告)日：2007-08-29
申请号：SG2006086748
申请日：2006-12-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN , MALONEY MICHAEL J , LITTON DAVID A , SCHLICHTING KEVIN W , SMEGGIL JOHN G , SNOW DAVID B
Abstract: A process of coating an article includes the steps of (1) applying upon at least one surface of an article at least one graded layer of at least one ceramic based compound comprising at least one metal selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutelium, indium, scandium, yttrium, zirconium, hafnium, titanium, and mixtures thereof; (2) optionally drying the coated article; and (3) optionally repeating steps (1) and (2).
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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：DE3887975T2
公开(公告)日：1994-06-01
申请号：DE3887975
申请日：1988-12-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUPTA DINESH KUMER , FRELING MELVIN
Abstract: Coated gas turbine engine hardware is described. The hardware comprises a titanium alloy substrate having a coating thereon consisting essentially of titanium nitride wherein the ratio of nitrogen to titanium is greater than one. Such coatings have a residual compressive stress state which aids in minimizing the fatigue debit which would otherwise result from the use of a hard coating on a titanium substrate. Coatings are applied by the use of a vacuum arc deposition process.
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公开(公告)号：DE3887975D1
公开(公告)日：1994-03-31
申请号：DE3887975
申请日：1988-12-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUPTA DINESH KUMER , FRELING MELVIN
Abstract: Coated gas turbine engine hardware is described. The hardware comprises a titanium alloy substrate having a coating thereon consisting essentially of titanium nitride wherein the ratio of nitrogen to titanium is greater than one. Such coatings have a residual compressive stress state which aids in minimizing the fatigue debit which would otherwise result from the use of a hard coating on a titanium substrate. Coatings are applied by the use of a vacuum arc deposition process.
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