发明名称 |
GAS TURBINE ENGINE BOOSTER HAVING ROTATABLE RADIALLY INWARDLY EXTENDING BLADES AND NON-ROTATABLE VANES |
摘要 |
A gas turbine engine booster includes one or more rotatable booster stages having booster blades extending radially inwardly from a rotatable drum and one or more non-rotatable vane stages having booster vanes extending radially outwardly from a non-rotatable shell. The booster stages may be interdigitated with the vane stages. The booster may be co-rotatable or counter-rotatable with respect to a fan stage of an aircraft gas turbine engine. The booster may be driven by a single turbine or one of counter-rotatable turbines or though a gearbox by these turbines. The booster blades and the booster vanes extend across a core engine inlet duct having an entrance downstream of the first fan stage. A fan section with the booster may have counter-rotatable first and second fan stages with fan blades of the second fan stages connected to and mounted radially outwardly of the rotatable drum.
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申请公布号 |
US2010126141(A1) |
申请公布日期 |
2010.05.27 |
申请号 |
US20080275813 |
申请日期 |
2008.11.21 |
申请人 |
SCHILLING JAN CHRISTOPHER |
发明人 |
SCHILLING JAN CHRISTOPHER |
分类号 |
F02K3/072;F01D9/04;F02C3/067 |
主分类号 |
F02K3/072 |
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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