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    Abrasive surface coating process for superalloys
    5.
    发明授权
    Abrasive surface coating process for superalloys 失效
    超级合金的磨料表面涂层工艺

    公开(公告)号：US4610698A

    公开(公告)日：1986-09-09

    申请号：US624446

    申请日：1984-06-25

    申请人： Harry E. Eaton ,  Richard C. Novak ,  Alfred P. Matarese

    发明人： Harry E. Eaton ,  Richard C. Novak ,  Alfred P. Matarese

    IPC分类号： C23C4/18 ,  F01D5/20 ,  B24D11/02

    CPC分类号： F01D11/12 ,  C23C4/18

    摘要： A combination of sintering, plasma arc spraying, hot isostatic pressing and chemical milling is used to form an abrasive surface on an article. Alumina coated silicon carbide particulates are clad with nickel and sinter bonded to the surface of a superalloy turbine blade tip. An impermeable layer of plasma arc sprayed superalloy matrix is deposited over the particulates and then has its inherent voids eliminated by hot isostatic pressing. The abrasive material so formed on the surface is then machined to expose the particulates. Next, a portion of the matrix is removed so that the machined particulates project into space and are thus best enabled to interact with abradable ceramic air seals in a gas turbine engine. The ceramic particulates are sized so they are larger than the finished thickness of the abrasive and they have small aspect ratios. Thus, a high density spacing can be achieved while at the same time it is insured that matrix adequately surrounds the particles and holds them in place during use.

    摘要翻译： 使用烧结，等离子体电弧喷涂，热等静压和化学研磨的组合来在制品上形成研磨表面。 氧化铝涂覆的碳化硅颗粒用镍包覆并烧结结合到超级合金涡轮叶片尖端的表面。 将不透水层的等离子体电弧喷涂超合金基体沉积在颗粒上，然后通过热等静压将其固有的空隙消除。 然后在表面上形成的研磨材料被加工以暴露颗粒。 接下来，去除矩阵的一部分，使得机加工的微粒投射到空间中，因此最佳地能够与燃气涡轮发动机中的可磨损的陶瓷空气密封件相互作用。 陶瓷颗粒的尺寸使其大于研磨剂的成品厚度，并且它们具有小的纵横比。 因此，可以实现高密度间隔，同时确保基体充分地围绕颗粒并在使用期间将其保持在适当的位置。

    Engineered ceramic components for the leading edge of a helicopter rotor blade
    9.
    发明授权
    Engineered ceramic components for the leading edge of a helicopter rotor blade 失效
    用于直升机转子叶片前缘的工程陶瓷部件

    公开(公告)号：US5542820A

    公开(公告)日：1996-08-06

    申请号：US363498

    申请日：1994-12-23

    申请人： Harry E. Eaton ,  John E. Holowczak ,  William C. Reinfelder

    发明人： Harry E. Eaton ,  John E. Holowczak ,  William C. Reinfelder

    IPC分类号： B64C27/473 ,  F04D29/18

    CPC分类号： B64C27/473 ,  B64C2027/4736

    摘要： An engineered ceramic component for the leading edge of a rotor blade provides enhanced erosion protection therefor. In one embodiment, the engineered ceramic component includes a strain isolator member, an aerodynamic ceramic member, a first adhesive bond layer, and a second adhesive bond layer. The strain isolator member, which is operative to minimize strain transfer between the rotor blade infrastructure and the aerodynamic ceramic member, is configured so that inner mold line surface thereof is complementary to outer mold line surface of the rotor blade infrastructure. The aerodynamic ceramic member, which is operative to provide enhanced erosion protection for the respective leading edge of the rotor blade, is configured so that the outer mold line surface thereof defines the aerodynamic configuration of the respective leading edge and the inner mold line surface is complementary to the outer mold line surface of the strain isolator member. The aerodynamic ceramic member is fabricated from an engineered ceramic material, which are defined in the present context as ceramic materials having a hardness greater than 1200 kg/mm.sup.2 and an average flexural strength equal to or greater than 40 ksi. The first adhesive bond layer is operative to bond the strain isolator member to the rotor blade infrastructure and the second adhesive bond layer is operative to bond the aerodynamic ceramic member to the strain isolator member. In another embodiment, the engineered ceramic member includes the aerodynamic ceramic member described hereinabove and a thick adhesive layer. The thick adhesive layer is operative to minimize strain transfer between the rotor blade infrastructure and the aerodynamic ceramic member and to bond the aerodynamic ceramic member in combination with the rotor blade infrastructure.

    摘要翻译： 用于转子叶片前缘的工程陶瓷部件为其提供了增强的侵蚀保护。 在一个实施例中，工程陶瓷部件包括应变隔离构件，空气动力学陶瓷构件，第一粘合剂接合层和第二粘合剂接合层。 用于使转子叶片基础设施和空气动力陶瓷构件之间的应变传递最小化的应变隔离构件被构造成使得其内模线表面与转子叶片基础设施的外模线表面互补。 用于为转子叶片的相应前缘提供增强的侵蚀保护的空气动力陶瓷构件被构造成使得其外模具线表面限定相应前缘的空气动力学构造，并且内模线表面是互补的 到应变隔离构件的外模线表面。 空气动力陶瓷构件由工程陶瓷材料制成，其在本上下文中被定义为具有大于1200kg / mm2的硬度和等于或大于40ksi的平均弯曲强度的陶瓷材料。 第一粘合剂层可操作以将应变隔离器构件结合到转子叶片基础设施，并且第二粘合剂粘合层可操作以将空气动力学陶瓷构件结合到应变隔离构件。 在另一个实施例中，工程陶瓷构件包括上述空气动力陶瓷构件和厚粘合剂层。 厚粘合剂层可操作以最小化转子叶片基础设施和空气动力学陶瓷构件之间的应变传递并将空气动力学陶瓷构件与转子叶片基础结构结合。