中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

45 records (took 0.026 seconds)

    APARATO Y METODOS DE DEPOSICION.
    4.
    发明专利
    APARATO Y METODOS DE DEPOSICION. 未知

    公开(公告)号：MXPA06003711A

    公开(公告)日：2007-01-15

    申请号：MXPA06003711

    申请日：2006-04-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： RUTZ DAVID A ,  BLANKENSHIP DONN R ,  PIETRUSKA NORMAN A ,  ZAJCHOWSKI PAUL H ,  SHUBERT GARY

    IPC: F22B20060101

    Abstract: La presente invencion describe un aparato y metodos de microaspersion que involucran inyectar material pulverizado en una corriente de gas de plasma. El material comprende primero y segundo componentes de polvo. El segundo polvo es una mayoria por peso de material pulverizado. El primer polvo actua como un depresor del punto de fusion. El primero y segundo polvos pueden tener composiciones similares pero el primer polvo incluye una mayor cantidad de un elemento depresor del punto de fusion.

    TURBINE BLADE HAVING A FUSED METAL-CERAMIC TIP
    5.
    发明专利
    TURBINE BLADE HAVING A FUSED METAL-CERAMIC TIP 未知

    公开(公告)号：AU596050B2

    公开(公告)日：1990-04-12

    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.

    6.
    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
    7.
    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.

    8.
    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.

    PRE-COATING BURNISHING OF EROSION COATED PARTS
    9.
    发明专利
    PRE-COATING BURNISHING OF EROSION COATED PARTS 未知

    公开(公告)号：CA2590496A1

    公开(公告)日：2008-02-03

    申请号：CA2590496

    申请日：2007-05-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： RUTZ DAVID A ,  KINSTLER MONIKA D

    IPC: F01D5/28 ,  C23C4/10

    Abstract: 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.

Patent Agency Ranking