公开(公告)号：EP4144962A1

公开(公告)日：2023-03-08

申请号：EP22203597.4

申请日：2012-06-29

申请人： Raytheon Technologies Corporation

发明人： GALLAGHER, Edward J. ,  ROSE, Becky E. ,  BRILLIANT, Lisa I

IPC分类号： F01D25/34 ,  F02K3/06 ,  F01D15/12 ,  F02C7/05 ,  F01D21/04 ,  F01D5/14 ,  F02C7/36

摘要： A gas turbine engine (20) includes a spool (30), a turbine (46) coupled to drive the spool (30), a propulsor (42) coupled to be rotated about an axis by the turbine (46) through the spool (30), and a gear assembly (48) coupled between the propulsor (74) 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 of propulsor blades (74) that extend from the hub (76). Each of the propulsor blades (74) has a span between a root (68) at the hub (76) and a tip (80), and a chord (30) between a leading edge (82) and a trailing edge (84). The chord forms a stagger angle α with the axis (A), and the stagger angle α is less than 15° at a position along the propulsor blade (74) that is within an inboard 20% of the span.