发明名称 |
Gas turbine engine having tri-body variable area fan nozzle and thrust reverser |
摘要 |
<p>A gas turbine engine system includes a fan (14), a housing (28) arranged about the fan, a gas turbine engine core having a compressor (16) at least partially within the housing, and a fan bypass passage (30) downstream of the fan for conveying a bypass airflow (D) between the housing and the gas turbine engine core. A nozzle (40) associated with the fan bypass passage includes a first nozzle section (54a) that is operative to move in a generally axial direction to influence the bypass airflow, and a second nozzle section that is operative to also move in a generally axial direction between a stowed position and a thrust reverse position that diverts the bypass airflow in a thrust reversing direction. An actuator (42) selectively moves the first nozzle section and the second nozzle section to influence the bypass airflow and provide thrust reversal.</p> |
申请公布号 |
EP2074304(B1) |
申请公布日期 |
2015.03.25 |
申请号 |
EP20060816749 |
申请日期 |
2006.10.12 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
MARSHALL, RICHARD M.;GUKEISEN, ROBERT L. |
分类号 |
F02K1/09;F02K1/72 |
主分类号 |
F02K1/09 |
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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