发明名称 |
ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE |
摘要 |
<p>A gas turbine engine comprises a first turbine rotor positioned upstream of a second intermediate turbine rotor and a third turbine rotor positioned downstream of the first and second turbine rotors. A fan rotor and three compressor rotors, with an upstream one of the compressor rotors are connected to rotate on a shaft with a fan drive turbine and a reduced speed fan rotor through a gear reduction. A second intermediate compressor rotor for being driven by the second intermediate turbine rotor, and a third compressor rotor downstream of the first and second compressor rotors and for being driven by the first turbine rotor.</p> |
申请公布号 |
WO2015119698(A2) |
申请公布日期 |
2015.08.13 |
申请号 |
WO2014US66094 |
申请日期 |
2014.11.18 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SCHWARZ, FREDERICK M.;SUCIU, GABRIEL L. |
分类号 |
F02K3/02 |
主分类号 |
F02K3/02 |
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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