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    11.
    发明专利
    未知

    公开(公告)号：NO875411A

    公开(公告)日：1988-06-30

    申请号：NO875411

    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 ,  C22C19/00 ,  F01D5/28

    CPC classification number: C22C32/00 ,  B22F1/0003 ,  B22F3/1035 ,  C22C1/1036 ,  F01D5/20

    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.

    TURBINE BLADE HAVING A FUSED METAL-CERAMIC ABRASIVE TIP
    12.
    发明专利
    TURBINE BLADE HAVING A FUSED METAL-CERAMIC ABRASIVE TIP 未知

    公开(公告)号：AU8303287A

    公开(公告)日：1988-06-30

    申请号：AU8303287

    申请日：1987-12-24

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: F01D5/20 ,  F01D11/08 ,  F01D5/28 ,  B23P15/04 ,  B23P15/02

    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.

    13.
    发明专利
    未知

    公开(公告)号：NO875411D0

    公开(公告)日：1987-12-23

    申请号：NO875411

    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 ,  C22C ,  F01D5/28

    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.

    15.
    发明专利
    未知

    公开(公告)号：DE3788116D1

    公开(公告)日：1993-12-16

    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.

    16.
    发明专利
    未知

    公开(公告)号：DE3785166D1

    公开(公告)日：1993-05-06

    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.

    19.
    发明专利
    未知

    公开(公告)号：PT86476A

    公开(公告)日：1989-01-17

    申请号：PT8647687

    申请日：1987-12-29

    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 ,  C04B35/71 ,  C09K3/14

    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.

    20.
    发明专利
    未知

    公开(公告)号：PT86474A

    公开(公告)日：1989-01-17

    申请号：PT8647487

    申请日：1987-12-28

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: F01D5/20 ,  F01D1/00

    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.

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