| 发明名称 | Rotor blade for a gas turbine | ||
| 摘要 | A rotor blade (10) for a gas turbine includes a blade airfoil (11), a blade tip (15), a blade root (14), and a platform (12) which is formed between the blade tip (15) and the blade root (14), and is assembled from a plurality of individual sections (16, 17, 18), the material of which is adapted in each case to the intended purpose of the individual section concerned. With such a rotor blade, a simplified production is achieved as a result of each of the individual sections (16, 17, 18) from the dimensions being significantly smaller than the assembled rotor blade (10). | ||
| 申请公布号 | US8911213(B2) | 申请公布日期 | 2014.12.16 |
| 申请号 | US200912637280 | 申请日期 | 2009.12.14 |
| 申请人 | Alstom Technology Ltd | 发明人 | Brandl Herbert;Schofer Sven;Gerdes Claus Paul;Bossmann Hans-Peter |
| 分类号 | F01D5/14 | 主分类号 | F01D5/14 |
| 代理机构 | Buchanan Ingersoll & Rooney PC | 代理人 | Buchanan Ingersoll & Rooney PC |
| 主权项 | 1. Rotor blade for a gas turbine, which rotor blade comprises: a blade airfoil, a blade tip, a blade root, and a platform which is formed between the blade tip and the blade root; a plurality of individual sections together forming the rotor blade, the plurality of individual sections comprising an upper blade section, a lower blade section, and a tie rod, a material of each of which sections is adapted to the intended purpose of said individual section; wherein the tie rod has an angled element on an upper end that is radially outward of and in engagement with an angled element on a lower end of the upper blade section; and wherein each of the plurality of individual sections in a longitudinal direction of the rotor blade is significantly smaller than an assembled rotor blade. | ||
| 地址 | Baden CH | ||