| 发明名称 |
GAS TURBINE ENGINE BLADE AND DISK |
| 摘要 |
In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface. |
| 申请公布号 |
US2014241890(A1) |
申请公布日期 |
2014.08.28 |
| 申请号 |
US201314133140 |
申请日期 |
2013.12.18 |
| 申请人 |
Rolls-Royce Corporation |
发明人 |
Fulayter Roy David;Rivers Jonathan Michael |
| 分类号 |
F01D5/30;B23P15/02 |
主分类号 |
F01D5/30 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An apparatus comprising:
a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform; and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface. |
| 地址 |
Indianapolis IN US |
