发明名称 |
Gas turbine engine providing simulated boundary layer thickness increase |
摘要 |
A nacelle assembly for a gas turbine engine includes a fan cowl disposed about an axis, a core cowl within the fan cowl and a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The bleed airflow is selectively introduced near a boundary layer of an inlet lip section of the fan cowl.
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申请公布号 |
US2008112799(A1) |
申请公布日期 |
2008.05.15 |
申请号 |
US20060595040 |
申请日期 |
2006.11.10 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
WINTER MICHAEL;JAIN ASHOK K. |
分类号 |
F01D17/00 |
主分类号 |
F01D17/00 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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