发明名称 |
Gas turbine spindle bolt structure with reduced fretting motion |
摘要 |
A spindle bolt structure is provided in a gas turbine engine. The gas turbine engine includes a rotor including a plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk. The spindle bolt structure includes a plurality of spindle bolts extending through the turbine disks and disposed offset from a rotational axis of the turbine disks. The spindle bolts include a first terminal end located adjacent to the compressor side of the turbine disks, and a sleeve member is provided extending over a portion of the first terminal end of each spindle bolt and embedded within a compressor side of the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk.
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申请公布号 |
US8465259(B2) |
申请公布日期 |
2013.06.18 |
申请号 |
US20100769928 |
申请日期 |
2010.04.29 |
申请人 |
LIGHT KEVIN M.;GURAO MANISH S.;SHAEFER DAVID M.;SIEMENS ENERGY, INC. |
发明人 |
LIGHT KEVIN M.;GURAO MANISH S.;SHAEFER DAVID M. |
分类号 |
F04D29/18 |
主分类号 |
F04D29/18 |
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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