| 发明名称 |
COOLING ARCHITECTURE FOR TURBINE EXHAUST CASE |
| 摘要 |
Cooling a turbine exhaust case (TEC) employed in an industrial gas turbine engine includes supplying cooling airflow from an outer diameter (OD) to an inner diameter (ID) cavity, supplying a secondary airflow having a pressure greater than the pressure of the cooling airflow to the ID cavity for mixing with the cooling airflow to provide a mixed airflow, and directing the mixed airflow in a serpentine cooling path that includes first directing the mixed airflow radially outward via hollow struts to an OD cavity, then radially inward via hollow fairings that surround the hollow struts. |
| 申请公布号 |
US2015337682(A1) |
申请公布日期 |
2015.11.26 |
| 申请号 |
US201314443818 |
申请日期 |
2013.12.17 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Yeager William;Tu John S. |
| 分类号 |
F01D25/14;F01D25/30;F01D25/24 |
主分类号 |
F01D25/14 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A method of cooling a turbine exhaust case (TEC) employed in an industrial gas turbine engine, the method comprising:
supplying cooling airflow from an outer diameter (OD) to an inner diameter (ID) cavity; supplying a secondary airflow having a pressure greater than the pressure of the cooling airflow to the ID cavity for mixing with the cooling airflow to provide a mixed airflow; and directing the mixed airflow in a serpentine cooling path that includes first directing the mixed airflow radially outward via hollow struts to an OD cavity, then radially inward via hollow fairing struts that surround the hollow struts. |
| 地址 |
Hartford CT US |
