- 专利标题： EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES
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申请号： EP20175433.0申请日： 2012-06-29
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公开(公告)号： EP3734052A1公开(公告)日： 2020-11-04
- 发明人: GALLAGHER, Edward J. , JIANG, Jun , ROSE, Becky E. , ELLIOTT, Jason , BIFULCO, Anthony R.
- 申请人： Raytheon Technologies Corporation
- 申请人地址： 10 Farm Springs Road Farmington, CT 06032 US
- 专利权人： Raytheon Technologies Corporation
- 当前专利权人： Raytheon Technologies Corporation
- 当前专利权人地址： 10 Farm Springs Road Farmington, CT 06032 US
- 代理机构： Dehns
- 优先权： US201113176255 20110705
- 主分类号： F02K3/06
- IPC分类号： F02K3/06 ; F04D29/32 ; F02C7/36
摘要：
A gas turbine engine includes a spool (30), a turbine (46) coupled to drive the spool (30) and a propulsor (42) that is coupled to be driven by the turbine (46) through the spool (30). A gear assembly (48) is coupled between the propulsor (42) and the spool (30) such that rotation of the spool (30) drives the propulsor (42) at a different speed than the spool (30). The propulsor (42) includes a hub (76) and a row (72) of propulsor blades (74) that extends from the hub (76). The row (72) includes no more than 16 of the propulsor blades (74).
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