| 发明名称 | Turbomachine component having an airfoil core shape | ||
| 摘要 | A turbomachine component includes a turbine stator nozzle member having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil core shape. | ||
| 申请公布号 | US8814511(B2) | 申请公布日期 | 2014.08.26 |
| 申请号 | US201113206016 | 申请日期 | 2011.08.09 |
| 申请人 | General Electric Company | 发明人 | Check Benjamin Michael;Bielek Craig Allen;Pollard Hal Feaster;Vedhagiri Sivaraman |
| 分类号 | F01D9/02 | 主分类号 | F01D9/02 |
| 代理机构 | Cantor Colburn LLP | 代理人 | Cantor Colburn LLP |
| 主权项 | 1. A turbomachine component comprising: a turbine stator nozzle member having an airfoil core shape, the airfoil core shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil core shape. | ||
| 地址 | Schenectady NY US | ||