| 发明名称 |
MICROCIRCUIT COOLING FOR GAS TURBINE ENGINE COMBUSTOR |
| 摘要 |
A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel. The microcircuit flow path includes an inlet and an outlet radially outward of the inlet. The microcircuit flow path at the bend is positioned radially between the inlet and the outlet, and the microcircuit flow path follows the bend. A method of cooling a combustor of a gas turbine engine is also disclosed. |
| 申请公布号 |
US2015184857(A1) |
申请公布日期 |
2015.07.02 |
| 申请号 |
US201514644227 |
申请日期 |
2015.03.11 |
| 申请人 |
United Technologies Corporation |
发明人 |
Cunha Frank J.;Snyder Timothy S. |
| 分类号 |
F23R3/26 |
主分类号 |
F23R3/26 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A combustor component of a gas turbine engine, comprising:
a heat shield panel defining a bend and a microcircuit flow path within a thickness of said heat shield panel; and wherein said microcircuit flow path includes an inlet and an outlet radially outward of the inlet, said microcircuit flow path at said bend being positioned radially between said inlet and said outlet, and said microcircuit flow path follows said bend. |
| 地址 |
Hartford CT US |
