| 发明名称 |
ADDITIVELY MANUFACTURED BLADED DISK |
| 摘要 |
A bladed disk for a gas turbine engine is provided. The bladed disk includes a rotor disk, a plurality of rotor blades, and an interlocking transition zone. The rotor disk includes a plurality of fused layers of a first material formed via additive manufacturing and defines an outer rim. The plurality of rotor blades includes a plurality of fused layers of a second material formed via additive manufacturing. The interlocking transition zone includes a plurality of projections alternately extending from the outer rim of the rotor disk and the plurality of rotor blades, respectively, to undetachably couple the rotor disk and the plurality of rotor blades. |
| 申请公布号 |
US2017107832(A1) |
申请公布日期 |
2017.04.20 |
| 申请号 |
US201514887531 |
申请日期 |
2015.10.20 |
| 申请人 |
General Electric Company |
发明人 |
Roberts Herbert Chidsey;Albrecht, JR. Richard William;McCarren Michael John;Flynn Peter Andrew;Gigliotti, JR. Michael Francis Xavier;Estill Eric Alan |
| 分类号 |
F01D5/30 |
主分类号 |
F01D5/30 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A bladed disk for a gas turbine engine, comprising:
a rotor disk comprising from a plurality of fused layers of a first material formed via additive manufacturing, wherein the rotor disk defines an outer rim; a plurality of rotor blades comprising from a plurality of fused layers of a second material formed via additive manufacturing; and an interlocking transition zone comprising a plurality of projections alternately extending from the outer rim of the rotor disk and the plurality of rotor blades, respectively, to undetachably couple the rotor disk and the plurality of rotor blades. |
| 地址 |
Schenectady NY US |
