发明名称 |
Cooled aerofoil for a gas turbine engine |
摘要 |
A hollow cooled aerofoil blade (10) is provided with a central, lengthways extending plenum (16) and has pressure and suction flanks (20,15). The suction flank (15) has lengthways extending passages (21) therein that direct cooling air from the root region (13) into the central plenum (16). From the central plenum, the cooling air flows through a first set of apertures (27) into lengthways extending passages (28) in the pressure flank (20). The cooling air then flows through a second set of apertures (30) in the pressure flank to provide film cooling of the pressure flank (20) external surface. <IMAGE> |
申请公布号 |
EP1022432(B1) |
申请公布日期 |
2005.03.23 |
申请号 |
EP20000300108 |
申请日期 |
2000.01.10 |
申请人 |
ROLLS-ROYCE PLC |
发明人 |
DAILEY, GEOFFREY MATTHEW;MCCALL, RICHARD ADRIAN BEVERLEY;EVANS, PETER ANTONY |
分类号 |
F01D5/18 |
主分类号 |
F01D5/18 |
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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