中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

5 records (took 0.021 seconds)

    WELDING METHOD OF METALLIC MATERIAL
    2.
    发明专利
    WELDING METHOD OF METALLIC MATERIAL 失效

    公开(公告)号：JPS5666390A

    公开(公告)日：1981-06-04

    申请号：JP14079979

    申请日：1979-10-31

    Applicant: NAT AEROSPACE LAB

    Inventor： MATSUKI MASAKATSU ,  TAKAHARA KITAO ,  YOSHIDA TOYOAKI ,  SAKATA KIMIO

    IPC: B23K20/00 ,  B23K20/16

    Abstract: PURPOSE:To practice a pressure welding with superior strength, by applying fine- grained powders of specific particle size as an inserting material between contacting surfaces of metallic materials and heating up all these materials to a temperature lower than a solid phase line of metallic materials. CONSTITUTION:The particle size of fine-grained metallic powders is 1mum-1mm. and the surface area of grained powders is about 10-100cm /g. The sintering temperature of metallic powders is a little lower than that of the lump of same metal. Both contacting surfaces of metallic materials are finished by grinding and washed and a thin layer of the powdered mixture containing fine-grained metallic powders or fine-grained powders is applied on the contacting surfaces. Then, these materials are kept combined by pressure force so that both contacting surfaces be closely touched to each other. Sintering and diffusing actions will proceed when all materials are kept heated in a vacuum or an inert gas atmosphere at a temperature not higher than each solid phase line of the mother materials and inserting material, but higher than a sintering temperature of the fine-grained powder material. The proper grading of the inserting material is about 0.01-1.0mg/1cm . Thus, the welded zone between metals is excellent in its strength, oxidation resistance, corrosion resistance and heat impact resistance and a residual strain can be minimized.

    STRUCTURE OF COOLING TURBINE BLADE
    3.
    发明专利
    STRUCTURE OF COOLING TURBINE BLADE 失效

    公开(公告)号：JPS56148601A

    公开(公告)日：1981-11-18

    申请号：JP5202080

    申请日：1980-04-18

    Applicant: NAT AEROSPACE LAB

    Inventor： TAKAHARA KITAO ,  YOSHIDA TOYOAKI ,  SASAKI MAKOTO ,  SAKATA KIMIO

    IPC: F01D5/18

    Abstract: PURPOSE:To vary the cooling effect of a cooling turbine blade in a direction of span thereof by joining a plurality of gas turbine blade elements one upon another and to improve the cooling performance of the turbine blade by forming a film cooling passage in a curved form. CONSTITUTION:Cooling turbine blade elements 11, 12, 13 are combined to form impinge passages 2 and film cooling passages 4. The cooling effect can be varied in a direction of span of the cooling turbine blade by inserting those elements having no cooling passages 2, 4 in serveral locations in the direction of span or by changing dimensions of cooling passages of the cooling turbine blade elements 11, 12, 13. Each film cooling passage can be formed into a curved form by seaming the cooling turbine blade elements by diffusion, thereby improving the cooling performance.

Patent Agency Ranking