| 发明名称 | Method for manufacturing a hot gas path component and hot gas path turbine component | ||
| 摘要 | According to one aspect of the invention, a method for manufacturing a hot gas path component of a turbine is provided, the method including forming cooling channels in a surface of a member. The method also includes disposing a layer on the surface of the member to enclose the cooling channels, the layer being disposed on a portion of the member to be cooled and bonding the layer to the surface, wherein bonding comprises heating the member and the layer. | ||
| 申请公布号 | US8870523(B2) | 申请公布日期 | 2014.10.28 |
| 申请号 | US201113042167 | 申请日期 | 2011.03.07 |
| 申请人 | General Electric Company | 发明人 | Kottilingam Srikanth Chandrudu;Bucci David Vincent;Lacy Benjamin Paul;Morey Kathleen Blanche;Tollison Brian Lee;Walsh Patrick Thomas |
| 分类号 | F01D5/14;B23P15/04;F02C7/00;F01D9/04;B23K31/02 | 主分类号 | F01D5/14 |
| 代理机构 | Cantor Colburn LLP | 代理人 | Cantor Colburn LLP |
| 主权项 | 1. A method for manufacturing a hot gas path component of a turbine, the method comprising: forming cooling channels in a surface of a member; disposing a layer on the surface of the member to enclose the cooling channels, the layer being disposed on a portion of the member to be cooled; and bonding the layer to the surface, wherein bonding comprises heating the member and the layer, wherein bonding the layer comprises disposing a braze filler metal between the layer and the surface and heating the layer, the member and the braze filler metal to a selected temperature. | ||
| 地址 | Schenectady NY US | ||