公开(公告)号：EP4290050A1

公开(公告)日：2023-12-13

申请号：EP23173772.7

申请日：2023-05-16

申请人： PRATT & WHITNEY CANADA CORP.

发明人： AZMI, Ali ,  ANAND, Karan ,  CAPRON, Alexandre ,  YAM, Tammy ,  CLAUDE, Sylvain ,  BALIKE, Krishna Prasad ,  BRUNI, Anthony Robert ,  GONZALEZ, Juan Ignacio Ruiz-Gopegui ,  MERINO, Cesar Valbuena ,  JARNE, Ignacio Javier Ucin

IPC分类号： F01D9/04 ,  F01D5/14 ,  F01D21/04

摘要： An aircraft engine, has: an upstream stator (30) having upstream stator vanes (31) circumferentially distributed about a central axis; and a downstream stator (40) having downstream stator vanes (41; 42, 43) circumferentially distributed about the central axis, the downstream stator (40) located downstream of the upstream stator (30) relative to an airflow flowing within a core gaspath of the aircraft engine, a number of the upstream stator vanes (31) being different than a number of the downstream stator vanes (41; 42, 43), the downstream stator vanes (41; 42, 43) including: a first vane (42) made of a first material, a major portion of a leading edge (41A) of the first vane (42) circumferentially overlapped by one of the upstream stator vanes (31), and a second vane (43) made of a second material having a greater stiffness, strength, and/or ductility than that of the first material, a major portion of a leading edge of the second vane (43) exposed via a spacing (32) defined between two of the upstream stator vanes (31).

公开(公告)号：EP4286649A1

公开(公告)日：2023-12-06

申请号：EP23176107.3

申请日：2023-05-30

申请人： PRATT & WHITNEY CANADA CORP.

发明人： CAPRON, Alexandre ,  ANAND, Karan ,  YAM, Tammy ,  AZMI, Ali ,  CLAUDE, Sylvain ,  BALIKE, Krishna Prasad ,  MITTAL, Prakul

IPC分类号： F01D5/14

摘要： An aircraft engine (10), has: an upstream stator (30) having upstream stator vanes (31) distributed about a central axis (11); and a downstream stator (40) having downstream stator vanes (41) distributed about the central axis (11), the downstream stator (40) located downstream of the upstream stator (30), a number of the upstream stator vanes (31) different than a number of the downstream stator vanes (41), the downstream stator vanes (41) including: a first vane (42), a major portion of a leading edge (41A) of the first vane (42) circumferentially overlapped by one of the upstream stator vanes (31); and a second vane (43) differing from the first vane (42) by a geometric parameter, the geometric parameter causing the second vane (43) to have one or more of: a stiffness greater than that of the first vane (42), and a major portion of a leading edge (41A) of the second vane (43) circumferentially overlapped by another one of the upstream stator vanes (31).