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公开(公告)号：FR2649125A1
公开(公告)日：1991-01-04
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：AT540135T
公开(公告)日：2012-01-15
申请号：AT07250918
申请日：2007-03-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN
Abstract: A coating (17) suitable for use as a wear-resistant coating for a gas turbine engine component comprises a lubricating material and a hard carbide material.
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公开(公告)号：AT441739T
公开(公告)日：2009-09-15
申请号：AT06251532
申请日：2006-03-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DEBICCARI ANDREW , FRELING MELVIN , HAYNES JEFFREY D
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公开(公告)号：SG136910A1
公开(公告)日：2007-11-29
申请号：SG2007028616
申请日：2007-04-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN , ZAJCHOWSKI PAUL HENRY
Abstract: A coating suitable for use as a wear-resistant coating for a gas turbine engine component comprises titanium chrome carbonitride and nickel cobalt.
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25.发明专利
公开(公告)号：SG134218A1
公开(公告)日：2007-08-29
申请号：SG2006086813
申请日：2006-12-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHLICHTING KEVIN W , LITTON DAVID A , MALONEY MICHAEL J , FRELING MELVIN , SMEGGIL JOHN G , SNOW DAVID B
Abstract: A process of coating an article includes the steps of (1) applying a ceramic based compound to at least one surface of an article to form a layer of ceramic based compound; (2) applying at least one inert compound upon the ceramic based compound layer to form a protective layer, wherein the at least one inert compound is composed of a first inert compound having a cubic crystalline structure of formula (I) A 3 B 2 X 3 O 12 , or a second inert compound comprising a hexagonal crystalline structure of formula (II) A 4 B 6 X 6 O 26 , or a mixture of the first inert compound and the second inert compound; and (3) heat treating the coated article.
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Patent Agency Ranking
公开(公告)号：CA2504449A1
公开(公告)日：2005-11-06
申请号：CA2504449
申请日：2005-04-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN , SCHLICHTING KEVIN WALTER , DIERBERGER JAMES A
IPC: F01D5/28 , B22C9/04 , B22D19/00 , B22F7/04 , B32B15/04 , C04B38/00 , C04B41/88 , C22C19/03 , C22C19/07 , C23C4/12 , C23C4/18 , C23C26/00 , C23C28/00 , F02C7/00 , F23R3/42 , C04B35/74 , C04B37/02
Abstract: Integrated ceramic/metallic components and methods of making same are described herein. Embodiments of these integrated ceramic/metallic components comprise a metallic non-foam region; and a ceramic foam region comprising a gradient porosity therein, wherein the ceramic foam region and the metallic non-foam region are integrally formed together to create the integrated ceramic/metallic component. Embodiments of these integrated ceramic/metallic components comprise a metallic region; and a single piece ceramic foam construction comprising a plurality of ceramic foam regions therein, each ceramic foam region comprising a predetermined pore size and a predetermined volume percent porosity, wherein the single piece ceramic foam construction is integrally joined to the metallic region to form the integrated ceramic/metallic component. These components may be utilized in gas turbine engines.
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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：DE69823150D1
公开(公告)日：2004-05-19
申请号：DE69823150
申请日：1998-12-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FRELING MELVIN , LAGUEUX KEN R , ZAJCHOWSKI PAUL H
Abstract: An abrasive coating is prepared by plasma spraying a top coating over a bond coating medium. The resultant structure has an improved resistance to corrosion, and a lower thermal conductivity. The coating provides substantially enhanced engine efficiency and improved durability. The coating consists of from eleven to fourteen weight percent (11 to 14 wt.%) yttria and the balance essentially zirconia.
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公开(公告)号：DE69703144T2
公开(公告)日：2001-05-17
申请号：DE69703144
申请日：1997-11-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZAJCHOWSKI PAUL H , FRELING MELVIN , MEIER SUSAN M
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公开(公告)号：DE69703144D1
公开(公告)日：2000-10-26
申请号：DE69703144
申请日：1997-11-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZAJCHOWSKI PAUL H , FRELING MELVIN , MEIER SUSAN M
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