公开(公告)号：EP4137674A1

公开(公告)日：2023-02-22

申请号：EP22191265.2

申请日：2022-08-19

申请人： PRATT & WHITNEY CANADA CORP.

发明人： CAULFEILD, Stephen

IPC分类号： F01D21/04 ,  F01D25/04

摘要： An assembly (20) is provided for a turbine engine. This turbine engine assembly includes a stationary structure (24), a rotating structure (22), a bearing (26). The rotating structure (22) rotatable about an axis (28) relative to the stationary structure (24). The bearing (26) supports the rotating structure (22). The stationary structure (24) includes a flexible bearing support (50) and a crushable bumper (54). The flexible bearing support (50) supports the bearing (26). The crushable bumper (54) is arranged radially outward of and axially overlaps the flexible bearing support (50). The stationary structure (24) is configured such that: the flexible bearing support (50) is disengaged from the crushable bumper (54) during a first mode of operation; and the flexible bearing support (50) contacts the crushable bumper (54) during a second mode of operation.

公开(公告)号：EP3865678A1

公开(公告)日：2021-08-18

申请号：EP21156632.8

申请日：2021-02-11

申请人： Pratt & Whitney Canada Corp.

发明人： CAULFEILD, Stephen

IPC分类号： F01D21/04

摘要： The fan case (23) can be used around a rotary fan (12) of a turbofan engine (10), the rotary fan (12) including a plurality of circumferentially interspaced blades (34) protruding radially from a rotor, the fan blade case (23) including a first annular wall (32) providing a radially outward delimitation to a gas path around the blades (34), the first annular wall (32) being configured to allow blade penetration therethrough while absorbing at least 30% of the kinetic energy in the event of detachment of one of said blades (34), and a second annular wall (36) surrounding the first annular wall (32), the second annular wall (36) configured to cooperate with the first annular wall (32) for containing the detachment of the fan blade (34).

公开(公告)号：EP2821621A1

公开(公告)日：2015-01-07

申请号：EP14173524.1

申请日：2014-06-23

申请人： Pratt & Whitney Canada Corp.

发明人： CAULFEILD, Stephen ,  OLVER, Bryan ,  CHEUNG, Kin-Leung

IPC分类号： F02C7/045 ,  F02C7/24 ,  F02C7/25 ,  F02K1/82 ,  G10K11/168 ,  B64C1/40

CPC分类号： F02C7/25 ,  F02C7/24 ,  F02K1/827 ,  F05D2220/327 ,  F05D2240/14 ,  F05D2240/15 ,  F05D2250/283 ,  F05D2260/96 ,  F05D2300/44 ,  F05D2300/502 ,  F23M20/005 ,  Y02T50/672

摘要： An acoustic structure (20) for a gas turbine engine comprises a noise reduction layer (20a) and a fire protector layer (20b) connected to the noise reduction layer (28). The noise reduction (24) includes a perforated inner wall (22) adapted to be in contact with a first fluidic environment (E1), and a noise reduction (24) adjacent to the inner wall (22). The fire protector layer (20b) includes a non-perforated outer wall (26) adapted to be in contact with a second fluidic environment (E1) having potentially a fire, a fire protector (28) adjacent to the outer wall (26), and a pressure resisting wall (30) disposed between the fire protector (28) and the noise reduction (24). The second fluidic environment (E2) is under a pressure lower than a pressure of the first fluidic environment (E1). The inner and outer walls (22, 26) are load-bearing walls of the acoustic structure (20).

摘要翻译： 用于燃气涡轮发动机的声学结构（20）包括连接到降噪层（28）的降噪层（20a）和防火器层（20b）。 降噪（24）包括适于与第一流体环境（E1）接触的穿孔内壁（22）和邻近内壁（22）的噪声降低（24）。 火保护层（20b）包括适于与潜在地发生火灾的第二流体环境（E1）接触的非穿孔外壁（26），邻近外壁（26）的防火器（28） 以及设置在所述防火器（28）和所述降噪（24）之间的耐压壁（30）。 第二流体环境（E2）的压力低于第一流体环境（E1）的压力。 内壁和外壁（22,26）是声学结构（20）的承载壁。