发明名称 |
COMBINED INLET LAMINAR AND THRUST REVERSER CASCADE EFFLUX FLOW CONTROL SYSTEM |
摘要 |
A nacelle assembly (16) for a gas turbine engine includes a fan nacelle (62) bounding a bypass flow path (B). The fan nacelle (62) includes a first nacelle section (68A) and a second nacelle section (68B). The second nacelle section (68B) includes a moveable portion (79) movable relative to a forward portion (81) to define a secondary flow passage (74). The first nacelle section (68A) includes an inlet lip (71). A thrust reverser (72) is configured to selectively communicate a portion of bypass airflow between the bypass flow path (B) and the secondary flow passage (74). A pump (88) is configured to selectively communicate airflow between the inlet lip (71) and the secondary flow passage (74). |
申请公布号 |
EP3081798(A1) |
申请公布日期 |
2016.10.19 |
申请号 |
EP20160164848 |
申请日期 |
2016.04.12 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SAWYERS-ABBOTT, NIGEL DAVID |
分类号 |
F02K1/72;B64D33/02;F02K1/70;F02K1/76;F02K3/06 |
主分类号 |
F02K1/72 |
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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