A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.
申请公布号
WO2015017041(A1)
申请公布日期
2015.02.05
申请号
WO2014US43175
申请日期
2014.06.19
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
MERRY, BRIAN D.;SUCIU, GABRIEL L.;DAVIS, TODD A.;REINHARDT, GREGORY E.;DIBENEDETTO, ENZO