发明名称 Aircraft engine thrust reverser
摘要 A thrust reverser 30 comprising a flow redirecting structure 33 displaceable between an operative and inoperative position by a moveable cowl portion 35 includes a redirecting wall portion 41, and a cavity 40, where gaseous fluid is turned to produce reverse thrust. In the operative position an opening 37 is provided across which a cantilevered cascade assembly 34 extends, and a control slot being defined between the cascade and a leading edge of the portion 35. In the inoperative position, assembly 34 is mounted within the cavity 40 and flow into a box structure 51 urges structure 33 towards the inoperative position and sealed with seal 52. A leakage slot (48, fig 4) is defined between the redirecting wall portion 41 and an adjacent duct wall.
申请公布号 GB2395175(A) 申请公布日期 2004.05.19
申请号 GB20030025261 申请日期 2001.10.02
申请人 * SHORT BROTHERS PLC 发明人 MICHAEL JOHN * HATRICK;FINBARR * MCEVOY;WILLIAM EDWIN * BEATTIE;JOEL DAVID * BENNETT;HUGH KEITH * CAMPBELL
分类号 B64D33/04;F02K1/56;F02K1/72;F02K3/04;(IPC1-7):F02K1/72 主分类号 B64D33/04
代理机构 代理人
主权项
地址