| 发明名称 |
COMPOSITE COMPRESSOR BLADE AND METHOD OF ASSEMBLING |
| 摘要 |
Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein. |
| 申请公布号 |
US2016130955(A1) |
申请公布日期 |
2016.05.12 |
| 申请号 |
US201414893217 |
申请日期 |
2014.05.21 |
| 申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
KRAY Joseph Nicholas;GEMEINHARDT Gregory Carl;JADHAV Prakash Kashiram;KLEI Douglas Edward;NANDULA Phani;SUBRAMANIAN Suresh |
| 分类号 |
F01D5/28 |
主分类号 |
F01D5/28 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A compressor blade, comprising:
a composite blade panel comprising;
an airfoil having a span extending radially outward with respect to an axis of rotation, anda blade attachment feature radially inward from said airfoil with respect to said axis of rotation, said blade attachment feature being circumferentially oriented with respect to said axis of rotation. |
| 地址 |
Schenectady NY US |
