| 发明名称 |
GAS TURBINE ENGINE ROTOR DISK BALANCING |
| 摘要 |
A gas turbine engine rotor disk includes a web that extends inward in a radial direction from a rim to a bore that circumscribes an axis. An annular ridge extends axially from the side of the web. A balancing cut is in the annular ridge that includes a fillet that extends in the radial direction. |
| 申请公布号 |
US2016222784(A1) |
申请公布日期 |
2016.08.04 |
| 申请号 |
US201514613404 |
申请日期 |
2015.02.04 |
| 申请人 |
United Technologies Corporation |
发明人 |
Espinoza Michael |
| 分类号 |
F01D5/02;B23C3/00 |
主分类号 |
F01D5/02 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine rotor disk comprising:
a web that extends inward in a radial direction from a rim to a bore that circumscribes an axis; an annular ridge extends axially from side of the web; and a balancing cut in the annular ridge that includes a fillet extending in the radial direction. |
| 地址 |
Hartford CT US |
