公开(公告)号：EP4306788A2

公开(公告)日：2024-01-17

申请号：EP23212765.4

申请日：2013-01-28

申请人： RTX Corporation

发明人： BRILLIANT, Lisa I. ,  ROSE, Becky E. ,  DONG, Yuan ,  BALAMUCKI, Stanley J.

IPC分类号： F02C7/36

摘要： A turbine engine (20) includes a fan exit stator (62) located between a fan section (22) and a compressor section (24). The fan exit stator (62) includes an airfoil (72) that defines an entrance angle (J°) with respect to a leading edge (74) of the airfoil (72) and a line parallel to the longitudinal axis (A), and defines an exit angle (K°) with respect to a trailing edge (76) of the airfoil (72) and a line parallel to the longitudinal axis (A). The difference between the entrance angle (J°) and the exit angle (K°) is between about 45° and about 65°. A portion of the compressor section (24) is driven by a portion of a turbine section (28).

公开(公告)号：EP4306788A3

公开(公告)日：2024-04-17

申请号：EP23212765.4

申请日：2013-01-28

申请人： RTX Corporation

发明人： BRILLIANT, Lisa I. ,  ROSE, Becky E. ,  DONG, Yuan ,  BALAMUCKI, Stanley J.

IPC分类号： F02K3/072 ,  F02C7/36

CPC分类号： F01D5/141 ,  F05D2220/3620130101 ,  F02K3/072 ,  F02C7/36 ,  Y02T50/60

摘要： A turbine engine (20) includes a fan exit stator (62) located between a fan section (22) and a compressor section (24). The fan exit stator (62) includes an airfoil (72) that defines an entrance angle (J°) with respect to a leading edge (74) of the airfoil (72) and a line parallel to the longitudinal axis (A), and defines an exit angle (K°) with respect to a trailing edge (76) of the airfoil (72) and a line parallel to the longitudinal axis (A). The difference between the entrance angle (J°) and the exit angle (K°) is between about 45° and about 65°. A portion of the compressor section (24) is driven by a portion of a turbine section (28).