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    Turbine blade cooling channel formation
    7.
    发明公开
    Turbine blade cooling channel formation 审中-公开

    公开(公告)号：EP2775100A3

    公开(公告)日：2018-06-06

    申请号：EP14157384.0

    申请日：2014-02-28

    申请人： General Electric Company

    发明人： Knorr, David Bruce ,  Morey, Kathleen Blanche

    IPC分类号： F01D5/18 ,  F01D5/28

    CPC分类号： F01D5/183 ,  F01D5/147 ,  F01D5/186 ,  F01D5/187 ,  F01D5/286 ,  F01D5/288 ,  F05D2230/11 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2260/204 ,  F05D2300/514

    摘要： Embodiments of the invention relate generally to turbine blades and, more particularly, to the formation of cooling channels on a surface of a turbine blade and turbine blades including such cooling channels. In one embodiment, the invention provides a method of forming a cooling channel along a surface (10) of a turbine blade, the method comprising: applying a first mask material (30) to a first portion (12) of a surface (10) of a turbine blade; forming a first barrier (40) layer atop the first mask material (30) and atop a second portion (14) of the surface (10) of the turbine blade; removing the first mask material (30) and the barrier layer (40) atop the first mask material (30) to expose the first portion (12) of the surface (10) of the turbine blade; and etching the first portion (12) of the surface (10) of the turbine blade to form a cooling channel (20) along the surface (10) of the turbine blade.

    PROCESS FOR FORMING DIFFUSION COATING ON SUBSTRATE
    9.
    发明公开
    PROCESS FOR FORMING DIFFUSION COATING ON SUBSTRATE 审中-公开
    在基材上形成扩散涂层的过程

    公开(公告)号：EP3293281A1

    公开(公告)日：2018-03-14

    申请号：EP17189764.8

    申请日：2017-09-07

    申请人： General Electric Company

    发明人： LIN, Dechao ,  BUCCI, David Vincent ,  LIU, Shan ,  SCHAEFFER, Jon ,  ADAMS, John ,  HENDRIX, Ron

    IPC分类号： C23C10/20 ,  C23C10/18 ,  C23C10/02 ,  C23C10/60

    CPC分类号： C23C10/18 ,  C23C10/02 ,  C23C10/20 ,  C23C10/60 ,  C23C28/321 ,  C23C30/00 ,  F01D5/288 ,  F01D9/041 ,  F01D11/08 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2300/611

    摘要： A process for forming a diffusion coating (500) on a substrate (100) is disclosed, including preparing a slurry (102) including a donor metal powder, an activator powder, and a binder, and applying the slurry (102) to the substrate (100). The slurry (102) is dried on the substrate (100), forming a slurry layer (200) on the substrate (100). A covering composition (300) is applied over the slurry layer (200), and the covering composition (300) is dried, forming at least one covering layer (400) enclosing the slurry layer (200) against the substrate (100). The slurry layer (200) and the at least one covering layer (400) are heated to form the diffusion coating (500) on the substrate (100), the diffusion coating (500) including an additive layer (502) and an interdiffusion zone (504) disposed between the substrate (100) and the additive layer (502). The at least one covering layer (400) is removed.

    摘要翻译： 公开了一种在基底（100）上形成扩散涂层（500）的方法，包括制备包含施主金属粉末，活化剂粉末和粘合剂的浆料（102），并将该浆料（102）施加到基底 （100）。 浆料（102）在衬底（100）上干燥，在衬底（100）上形成浆料层（200）。 将覆盖组合物（300）施加在浆料层（200）上，并且将覆盖组合物（300）干燥，形成至少一个将浆料层（200）封闭在基底（100）上的覆盖层（400）。 加热浆料层（200）和至少一个覆盖层（400）以在基底（100）上形成扩散涂层（500），扩散涂层（500）包括添加剂层（502）和相互扩散区 （504）设置在基底（100）和添加剂层（502）之间。 该至少一个覆盖层（400）被去除。

    Turbocharger with divided turbine housing and annular rotary bypass valve for the turbine
    10.
    发明公开
    Turbocharger with divided turbine housing and annular rotary bypass valve for the turbine 审中-公开
    涡轮增压器带有分体式涡轮机壳体和用于涡轮机的环形旋转旁通阀

    公开(公告)号：EP2463483A3

    公开(公告)日：2018-03-07

    申请号：EP11192700.0

    申请日：2011-12-08

    申请人： Honeywell International Inc.

    发明人： Lombar, Alain ,  Serres, Nicolas ,  Palaniyappan, Mani ,  Celaya, Aitor Herrera

    IPC分类号： F01D17/10 ,  F02B37/00 ,  F02B37/18 ,  F01D9/02 ,  F16K3/08

    CPC分类号： F01D17/105 ,  F01D9/026 ,  F01D25/24 ,  F02B37/183 ,  F05D2220/40 ,  F05D2230/90 ,  F05D2240/55 ,  F05D2250/411 ,  F05D2260/606 ,  F16K3/085 ,  Y02T10/144

    摘要： A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a divided volute (58a,58b) that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines a pair of concentric annular bypass passages (73a,73b) surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel as two separate bypass streams. An annular bypass valve (74) is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member (74) arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.

    摘要翻译： 涡轮增压器包括安装在涡轮机壳体内并通过轴连接到压缩机叶轮的涡轮机叶轮。 涡轮机壳体限定连接到围绕涡轮机叶轮的分开的蜗壳（58a，58b）的排气入口以及已经穿过涡轮机叶轮的排气从涡轮机壳体排出的轴向孔。 涡轮机壳体还限定围绕孔的一对同心环形旁路通道（73a，73b），并布置成允许排气作为两个单独的旁路流绕过涡轮机叶轮。 环形旁通阀（74）设置在旁路通道中。 旁通阀包括固定的环形阀座和与阀座同轴布置的旋转环形阀构件（74）。 阀构件设置成抵靠阀座并且可绕轴线旋转，用于选择性地改变阀座和阀构件中的相应孔口之间的对准程度。