发明名称 |
GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION |
摘要 |
A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. The shaft includes a main shaft and a flex shaft having bellows. The flex shaft is secured to the main shaft at a first end and includes a second end opposite the first end. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supports the shaft relative to the inlet case. The second bearing is arranged radially outward from the flex shaft.
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申请公布号 |
US2013192199(A1) |
申请公布日期 |
2013.08.01 |
申请号 |
US201313762970 |
申请日期 |
2013.02.08 |
申请人 |
UNITED TECHNOLOGIES CORPORATION;UNITED TECHNOLOGIES CORPORATION |
发明人 |
MERRY BRIAN D.;SUCIU GABRIEL L. |
分类号 |
F02K3/04;F02C7/06;F02C7/36 |
主分类号 |
F02K3/04 |
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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