| 发明名称 |
MULTI-PIECE TURBINE AIRFOIL |
| 摘要 |
A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a flow path, and a turbine fluidly connected to the combustor via the flow path. At least one multi-piece structure is disposed within the flow path such that the multi-piece structure at least partially radially spans the flow path. The at least one multi-piece structure includes a fore portion defining a leading edge, a consumable aft portion defining a trailing edge, a pressure surface at least partially defined by a first surface of the fore portion and a first surface of the consumable aft portion, and a suction surface at least partially defined by a second surface of the fore portion and a second surface of the consumable aft portion. |
| 申请公布号 |
US2016115801(A1) |
申请公布日期 |
2016.04.28 |
| 申请号 |
US201514887847 |
申请日期 |
2015.10.20 |
| 申请人 |
United Technologies Corporation |
发明人 |
Carr Jesse M. |
| 分类号 |
F01D9/02;F02C3/04 |
主分类号 |
F01D9/02 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a compressor; a combustor fluidly connected to the compressor via a flow path; a turbine fluidly connected to the combustor via the flow path; at least one multi-piece structure disposed within said flow path such that the multi-piece structure at least partially radially spans the flow path, and wherein the at least one multi-piece structure includes:
a fore portion defining a leading edge;a consumable aft portion defining a trailing edge;a pressure surface at least partially defined by a first surface of said fore portion and a first surface of said consumable aft portion;a suction surface at least partially defined by a second surface of said fore portion and a second surface of said consumable aft portion. |
| 地址 |
Hartford CT US |
