Composite X-ray target
    2.
    发明授权
    Composite X-ray target 失效
    复合X射线靶

    公开(公告)号:US6390876B2

    公开(公告)日:2002-05-21

    申请号:US84684801

    申请日:2001-05-01

    Applicant: GEN ELECTRIC

    Abstract: An X-ray tube anode comprises a graphite ring, a target substrate applied onto the graphite ring and a target focal track applied onto the target substrate. The target focal track comprises a first refractory metal and the target substrate comprises a second refractory metal and at least one layer of a material that is characterized by characterized by a coefficient of thermal expansion (CTE) that is the same as the CTE of the target focal track or is intermediate between the CTE of the target focal track and the CTE of the substrate.

    Abstract translation: X射线管阳极包括石墨环,施加到石墨环上的目标基底和施加到目标基底上的目标焦点轨迹。 目标焦点轨道包括第一耐火金属,并且目标基底包括第二难熔金属和至少一层材料,其特征在于热膨胀系数(CTE)与靶的CTE相同 焦点轨迹或者在目标焦点轨迹的CTE和基底的CTE之间的中间。

    PRODUCT SURFACE HAVING METAL WIRE AND ITS MANUFACTURING METHOD

    公开(公告)号:JP2001214702A

    公开(公告)日:2001-08-10

    申请号:JP2000384547

    申请日:2000-12-19

    Applicant: GEN ELECTRIC

    Abstract: PROBLEM TO BE SOLVED: To correctly control the surface area of a tabulator for transferring heat from a surface, and also correctly arrange and secure the tabulator to the surface. SOLUTION: Plural metal wires 14 are secured to a product surface 12 along the longitudinal direction of the wires 14 in the surface 12 of a product 10 (e.g. an external fluid flow surface). Such a product can be composed of the part of a device (e.g. the part of a gas turbine engine), and also the wires 14 are secured to the surface of the product 10 to change the surface characteristic of the product 10. The product 10 can be also composed of a joining layer including the wires 14 carried along the surface 12 of the layer (e.g. a brazed tape).

    THERMAL BARRIER COATING SYSTEM FOR TURBINE ENGINE COMPONENT

    公开(公告)号:JP2001164353A

    公开(公告)日:2001-06-19

    申请号:JP2000293211

    申请日:2000-09-27

    Applicant: GEN ELECTRIC

    Abstract: PROBLEM TO BE SOLVED: To provide a method for forming a thermal barrier coating system on turbine engine components, where a bond coat is formed on the turbine engine components and then the thermal barrier coating is deposited onto the bond coat. SOLUTION: The bond coat is formed by co-spraying a first and a second dissimilar alloy powder on the turbine engine components to form an oxidation- resistant region and then thermally spraying a third alloy powder on the oxidation-resistant region to form a bond region. The oxidation resistance of the oxidation-resistant region is higher than that of the bond region.

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