发明名称 |
GEARED TURBOFAN WITH THREE TURBINE SECTIONS |
摘要 |
A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flow into a core engine where it reaches an upstream compressor rotor. The upstream compressor rotor is configured to be driven through a second shaft by an intermediate turbine rotor. A downstream compressor rotor is configured to be driven by an upstream turbine rotor through a third shaft. An overall pressure ratio across the upstream and downstream compressor rotors is greater than or equal to about 35.0 and less than or equal to about 75.0. |
申请公布号 |
EP3084173(A4) |
申请公布日期 |
2016.12.28 |
申请号 |
EP20140880333 |
申请日期 |
2014.11.07 |
申请人 |
United Technologies Corporation |
发明人 |
SCHWARZ, Frederick M.;STAUBACH, Joseph Brent |
分类号 |
F02K3/06;F02C7/36 |
主分类号 |
F02K3/06 |
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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