| 发明名称 |
Cooling Flow for Leading Panel in a Gas Turbine Engine Combustor |
| 摘要 |
A heat resistant panel has a bulkhead and a swirler adjacent a combustion chamber. The heat resistant panel comprises an inner panel for facing the combustion chamber and defining a first exit port at an upstream end thereof configured to direct cooling air into the combustor chamber in a first direction adjacent the bulkhead. A second exit port at a downstream end thereof is configured to direct cooling air into the combustor chamber in a second direction with an axial direction defined between the upstream and downstream ends. The first and second directions have opposed axial components. A heat resistant structure and a combustor are also disclosed. |
| 申请公布号 |
US2016327273(A1) |
申请公布日期 |
2016.11.10 |
| 申请号 |
US201515108107 |
申请日期 |
2015.01.09 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Cunha Frank J.;Snyder Timothy S. |
| 分类号 |
F23R3/06;F02C3/14;F23R3/14;F23R3/58;F23M5/08 |
主分类号 |
F23R3/06 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A heat resistant panel for use in a combustor of a gas turbine engine having a bulkhead and a swirler adjacent a combustion chamber, the heat resistant panel comprising:
an inner panel for facing the combustion chamber and defining a first exit port at an upstream end thereof configured to direct cooling air into the combustor chamber in a first direction adjacent the bulkhead, and a second exit port at a downstream end thereof configured to direct cooling air into the combustor chamber in a second direction with an axial direction defined between the upstream and downstream ends, wherein the first and second directions have opposed axial components. |
| 地址 |
Hartford CT US |
