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    41.
    发明专利
    未知

    公开(公告)号：DE69823150T2

    公开(公告)日：2005-03-24

    申请号：DE69823150

    申请日：1998-12-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FRELING MELVIN ,  LAGUEUX KEN R ,  ZAJCHOWSKI PAUL H

    IPC: F01D5/28 ,  C23C4/02 ,  C23C4/06 ,  C23C4/10 ,  F02C7/28

    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.

    42.
    发明专利
    未知

    公开(公告)号：DE4436186C2

    公开(公告)日：2001-10-25

    申请号：DE4436186

    申请日：1994-10-10

    Applicant: UNITED TECHNOLOGIES CORP PRATT

    Inventor： FRELING MELVIN ,  GRUVER GARY A ,  PARKOS JUN JOSEPH J ,  WELCH DOUGLAS A

    IPC: F01D5/14 ,  F01D5/20 ,  F01D5/28 ,  F04D29/02 ,  F04D29/08 ,  F04D29/32 ,  F04D29/38

    Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

    44.
    发明专利
    未知

    公开(公告)号：DE4436186A1

    公开(公告)日：1995-05-04

    申请号：DE4436186

    申请日：1994-10-10

    Applicant: UNITED TECHNOLOGIES CORP PRATT

    Inventor： FRELING MELVIN ,  GRUVER GARY A ,  PARKOS JUN JOSEPH J ,  WELCH DOUGLAS A

    IPC: F01D5/14 ,  F01D5/20 ,  F01D5/28 ,  F04D29/02 ,  F04D29/08 ,  F04D29/32 ,  F04D29/38 ,  F01D5/12 ,  C23C4/10 ,  B23P15/02 ,  B23P9/04 ,  B23P9/02

    Abstract: A method and apparatus for increasing blade fatigue strength in a turbine engine. The blades in the turbine engine are configured so as to reduce stress at the tip of the blades during operation of the turbine engine, thus increasing blade fatigue strength. This stress reduction helps to counteract the detrimental effect of abrasive tip coatings on blade fatigue strength. In one embodiment, the tip of the blade is chamfered in order to reduce the stress on the tip of the blade. An abrasive coating is then applied to the tip of the blade to assist the blade in seating into an abradable outer air seal. In another embodiment, an abrasive coating is applied to a center portion of the tip of the blade, with the periphery of the abrasive coating being set back from the opposing surfaces of the blade.

    Method for applying an abrasive layer to titanium alloy compressor airfoils
    45.
    发明专利
    Method for applying an abrasive layer to titanium alloy compressor airfoils 未知

    公开(公告)号：GB2234526B

    公开(公告)日：1993-11-10

    申请号：GB9014728

    申请日：1990-07-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ROUTSIS KOSTAS ,  PARKOS JR JOSEPH JOHN ,  FRELING MELVIN

    IPC: F01D5/28 ,  C25D5/14 ,  C25D15/02 ,  F01D5/20 ,  C25D15/00

    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.

    CHROMIUM BORON SURFACED NICKEL-IRON BASE ALLOYS
    46.
    发明专利
    CHROMIUM BORON SURFACED NICKEL-IRON BASE ALLOYS 未知

    公开(公告)号：CA1223780A

    公开(公告)日：1987-07-07

    申请号：CA457555

    申请日：1984-06-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： RASHID JAMES M ,  FRIEDRICH LEONARD A ,  FRELING MELVIN

    IPC: C23C12/02 ,  C23C12/00 ,  C23C10/54

    Abstract: Chromium Boron Surfaced Nickel-Iron Base Alloys Chromium boron diffusion coatings on nickel iron alloys uniquely provide them with improvement in high cycle fatigue strength (up to 30%) and erosion resistance (up to 15 times), compared to uncoated alloy. The diffused chromium layer extends in two essential concentration zones to a total depth of about 40 x 10-6 m, while the succeeding boron layer is limited to 50-90% of the depth of the richest Cr layer nearest the surface. Both coatings are applied using conventional pack diffusion processes.

    WEAR-RESISTANT COATING
    49.
    发明专利
    WEAR-RESISTANT COATING 未知

    公开(公告)号：SG136036A1

    公开(公告)日：2007-10-29

    申请号：SG2007010135

    申请日：2007-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FRELING MELVIN

    Abstract: A coating 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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