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    21.
    发明专利
    未知

    公开(公告)号：DE3788116T2

    公开(公告)日：1994-03-03

    申请号：DE3788116

    申请日：1987-12-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHAEFER ROBERT P ,  RUTZ DAVID A ,  LEE EDWARD ,  JOHNSON EDWARD L

    IPC: B24D3/00 ,  B22F3/10 ,  B24D3/06 ,  C22C1/10 ,  C22C32/00 ,  C23C24/10 ,  F01D5/20 ,  F01D11/00 ,  F16J15/10

    Abstract: An abrasive material (22) comprised of a metal matrix (26) and evenly distributed ceramic particulates (24), is made by mixing powder metal with the ceramic powder and heating to a temperature sufficient to melt most, but not all of the powder. In this way the ceramic does not float to the top of the material, yet a dense material is obtained. A nickel superalloy matrix will have at least some remnants of the original powder metal structure, typically some equiaxed grains, along with a fine dendritic structure, thereby imparting desirable high temperature strength when the abrasive material is applied to the tips of blades of gas turbine engines. Preferred matrices have a relatively wide liquidus-solidus temperature range, contain a melting point depressant, and a reactive metal to promote adhesion to the ceramic.

    22.
    发明专利
    未知

    公开(公告)号：DE3785166T2

    公开(公告)日：1993-07-15

    申请号：DE3785166

    申请日：1987-12-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHAEFER ROBERT P ,  RUTZ DAVID A ,  LEE EDWARD ,  JOHNSON EDWARD L

    IPC: F01D5/20

    Abstract: A gas turbine engine blade has an abrasive material tip with a fused superalloy matrix and evenly distributed ceramic particulate. The matrix will have a desirable metallurgical structure characterized by fine dendrites and remnants of the original powder metal structure from which it was made. Due to the fusion of the tip, the peripheral edge will tend to be curved. To lessen the effect of thermal strains on such an abrasive tip, a sheath of a superalloy, such as a portion of the turbine blade substrate, extends along the side of the abrasive. The sheath may be present only in the thicker leading edge part of the blade airfoil.

    PRE-COATING BURNISHING OF EROSION COATED PARTS
    25.
    发明专利
    PRE-COATING BURNISHING OF EROSION COATED PARTS 未知

    公开(公告)号：SG139615A1

    公开(公告)日：2008-02-29

    申请号：SG2007025562

    申请日：2007-04-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： RUTZ DAVID A ,  KINSTLER MONIKA D

    Abstract: PRE-COATING BURNISHING OF EROSION COATED PARTS A gas turbine engine blade has a platform. A root depends from the platform and an airfoil extends from the platform. The airfoil has leading and trailing edges and pressure and suction sides. The blade has a substrate having a surface. A compressive stress exists below a first region of the surface. The first region extends over a majority of a streamwise perimeter of the airfoil at a location at a spanwise distance from the tip or more than 50% of a tip-to-platform span. A coating is on the surface including at the location.

    Repair and reclassification of superalloy components
    26.
    发明专利
    Repair and reclassification of superalloy components 未知

    公开(公告)号：SG124400A1

    公开(公告)日：2006-08-30

    申请号：SG200600523

    申请日：2006-01-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PIETRUSKA NORMAN ,  OLSON WALTER E ,  ABRILES BETH K ,  RUTZ DAVID A

    Abstract: Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 weight percent of a low melting point alloy and about 81.1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.

    SELF CLEANING BRAZE MATERIAL
    27.
    发明专利
    SELF CLEANING BRAZE MATERIAL 未知

    公开(公告)号：CA2353374C

    公开(公告)日：2004-09-28

    申请号：CA2353374

    申请日：2001-07-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MANIS BRYAN W ,  KWIATKOWSKI ABRILES BETH ,  RUTZ DAVID A

    IPC: F02C7/00 ,  B23K35/00 ,  B23K35/02 ,  B23K35/14 ,  B23K35/30 ,  B23K35/36 ,  B23K35/22 ,  B23K1/00

    Abstract: The present invention relates to a self cleaning braze paste which is used in the repair of gas turbine engines. The braze paste comprises lithium fluoride in an amount sufficient to act as a flux which allows the braze material to flow into a crack or void in a part to be repaired up to an amount where there is no residual lithium or fluoride in the crack or void, preferably up to about 20% by volume, a gel binder in an amount up to about 15% by volume, and the balance comprising at least one of a nickel braze alloy and a cobalt braze alloy. In a preferred embodiment, the lithium fluoride is present in an amount from about loo to-about 15% by volume. The braze material of the present invention may be applied in a paste form or, alternatively, in a paint or tape form. A method for cleaning and repairing a braze joint is also disclosed. The method broadly comprises the steps of forming a braze material containing lithium fluoride in the above mentioned range, a gel binder in an amount up to about 15% by volume, and the balance comprising at least one of a nickel braze alloy or a cobalt braze alloy, applying the braze material to the braze joint, and heating the braze material to a temperature in the range of from about a temperature sufficient to cause the lithium fluoride to volatize up to about 2300ÀFfor a time period from about 1.0 minute to about 30.0 minutes.

    TURBINE BLADE HAVING A FUSED METAL-CERAMIC ABRASIVE TIP
    29.
    发明专利
    TURBINE BLADE HAVING A FUSED METAL-CERAMIC ABRASIVE TIP 未知

    公开(公告)号：CA1284770C

    公开(公告)日：1991-06-11

    申请号：CA555386

    申请日：1987-12-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： RUTZ DAVID A ,  LEE EDWARD ,  SCHAEFER ROBERT P ,  JOHNSON EDWARD L

    IPC: F01D5/20 ,  B63H1/26

    Abstract: A gas turbine engine blade has an abrasive material tip with a used superalloy matrix and evenly distributed ceramic particulate. The matrix will have a desirable metallurgical structure characterized by fine dendrites and remnants of the original powder metal structure from which it was made. Due to the fusion of the tip, the peripheral edge will tend to be curved. To lessen the effect of thermal strains on such an abrasive tip, a sheath of a superalloy, such as a portion of the the turbine blade substrate, extends along the side of the abrasive. The sheath may be present only in the thicker leading edge part of the blade airfoil.

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