发明申请
- 专利标题: Turbine engine compressor
- 专利标题(中): 涡轮发动机压缩机
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申请号: US11455980申请日: 2006-06-19
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公开(公告)号: US20100218478A1公开(公告)日: 2010-09-02
- 发明人: Brian D. Merry , Gabriel L. Suciu , John P. Nikkanen
- 申请人: Brian D. Merry , Gabriel L. Suciu , John P. Nikkanen
- 专利权人: United Technologies Corporation
- 当前专利权人: United Technologies Corporation
- 主分类号: F02K3/00
- IPC分类号: F02K3/00 ; F16H1/28
摘要:
A counter-rotating blade stage in lieu of a stator stage may compensate for relatively low rotational speed of a gas turbine engine spool. A first spool may have at least one compressor blade stage and at least one turbine blade stage. A combustor is located between the at least one compressor blade stage and the at least one turbine blade stage along a core flowpath. The at least one counter-rotating compressor blade stage is interspersed with the first spool at least one compressor blade stage. A transmission couples the at least one additional compressor blade stage to the first spool for counter-rotation about the engine axis.
公开/授权文献
- US07950220B2 Turbine engine compressor 公开/授权日:2011-05-31