基本信息:
- 专利标题： 发动机
- 专利标题（英）：Engine
- 申请号：CN201480060282.2 申请日：2014-08-31
- 公开(公告)号：CN105705748A 公开(公告)日：2016-06-22
- 发明人： A·布兰德斯泰因 , A·蓬赫克
- 申请人： 以色列宇航工业有限公司
- 申请人地址： 以色列卢德镇
- 专利权人： 以色列宇航工业有限公司
- 当前专利权人： 以色列宇航工业有限公司
- 当前专利权人地址： 以色列卢德镇
- 代理机构： 北京派特恩知识产权代理有限公司
- 代理人： 姚开丽; 迟姗
- 优先权： 228274 2013.09.03 IL
- 国际申请： PCT/IL2014/050780 2014.08.31
- 国际公布： WO2015/033336 EN 2015.03.12
- 进入国家日期： 2016-05-03
- 主分类号： F02C6/00
- IPC分类号： F02C6/00 ; F01D15/00
There is provided a method for converting a turbofan engine, including the step of providing a turbofan engine and the step of converting the turbofan engine to provide a converted turbofan engine. The turbofan engine includes a core engine (including at least one high pressure spool assembly and a combustion chamber), and an unmodified fan configured for providing at least a bypass flow bypassing the core engine, the fan being mechanically coupled to a low pressure turbine that is in turn driven by the core engine. The conversion step includes modifying or replacing the unmodified fan to provide a modified fan, the modified fan being configured for generating a reduced bypass flow with respect to said fan bypass flow during operation of the converted turbofan engine corresponding to at least one set of engine conditions corresponding to step (a), thereby enabling said low pressure turbine to generate an excess shaft power above a baseline shaft power required for driving the modified fan during operation of the converted turbofan engine. Also provided is a corresponding converted turbofan engine.
公开/授权文献:
- CN105705748B 发动机 公开/授权日：2018-02-16