发明名称 |
Efficient, low pressure ratio propeller for gas turbine engines |
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 turbine (46) 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 20 of the propulsor blades (74). |
申请公布号 |
EP2543867(A3) |
申请公布日期 |
2016.10.19 |
申请号 |
EP20120174431 |
申请日期 |
2012.06.29 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
GALLAGHER, EDWARD J.;MONZON, BYRON R. |
分类号 |
F02K3/06 |
主分类号 |
F02K3/06 |
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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