| 发明名称 |
CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR |
| 摘要 |
A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases. |
| 申请公布号 |
US2016281988(A1) |
申请公布日期 |
2016.09.29 |
| 申请号 |
US201415037484 |
申请日期 |
2014.12.03 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Tu, JR. John S.;Snyder Timothy S.;Hoke James B.;Bangerter James P.;Duhamel Dennis J.;Burns David A. |
| 分类号 |
F23R3/06;F23R3/00 |
主分类号 |
F23R3/06 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A liner panel for use in a combustor for a gas turbine engine, comprising:
a forward region including a multiple of effusion passages each directed at an orientation substantially aligned with a local swirl direction of combustion gases. |
| 地址 |
Hartford CT US |
