公开(公告)号：EP3002070B1

公开(公告)日：2019-02-20

申请号：EP15181028.0

申请日：2015-08-14

申请人： Rolls-Royce plc

发明人： Wilson, Paul ,  Neale, Christopher ,  Barr, Andrew S

IPC分类号： B22C9/10 ,  F01D5/28

公开(公告)号：EP3002070A1

公开(公告)日：2016-04-06

申请号：EP15181028.0

申请日：2015-08-14

申请人： Rolls-Royce plc

发明人： Wilson, Paul ,  Neale, Christopher ,  Barr, Andrew S

IPC分类号： B22C9/10 ,  F01D5/28

CPC分类号： B22C9/24 ,  B22C9/103 ,  F01D5/187 ,  F05D2230/21 ,  F05D2260/22141 ,  Y02T50/676

摘要： A process for investment casting of an engine part (100), e.g. a high-performance turbine blade for an aircraft engine, having at least one internal cast wall (120), the wall (120) being defined during the casting thereof by a pair of core members (110a, 110b) having respective ones of a pair of opposed faces, major portions of the said opposed faces being spaced from each other by a first distance (W) corresponding to a predetermined minimum thickness (W) of a major portion of the resulting cast wall (120),
a face of a first core member (110a) of the pair which faces a second core member (110b) of the pair being provided with one or more protrusions (130) thereon, and a face of the second core member (110b) of the pair which faces the first core member (110a) of the pair being provided with one or more respective open recesses (150) therein, the or each respective protrusion (130) on the first core member (110a) facing the or a respective one of the said open recesses (150) in the second core member(110b),
wherein during at least part of the casting procedure the first (110a) and second (110b) core members are maintained in a spatial position relative to each other such that:
the said major portions of the opposed faces of the first and second core members (110a, 110b) assume a mutual spacing which substantially equals the said first distance (W) corresponding to the predetermined minimum thickness (W) of the major portion of the resulting cast wall (120); and
at least a head portion of the or each protrusion (130) on the first core member (110a) is located within the or a respective open recess (150) in the second core member (110b), such that the or each respective protrusion (130) and the or each respective open recess (150) define therebetween a respective minor portion of the resulting cast wall (120) which is laterally displaced from the major portion of the resulting cast wall (120).

摘要翻译： 发动机部件（100）的熔模铸造工艺，例如 一种用于飞行器发动机的高性能涡轮机叶片，具有至少一个内部铸造壁（120），所述壁（120）在其通过一对具有一对相对的一对的芯构件（110a，110b）的铸造期间被限定 所述相对面的主要部分彼此间隔开相应于所得铸造壁（120）的主要部分的预定最小厚度（W）的第一距离（W），第一 一对中心部件（110a）面对一对的第二芯体（110b），其上设置有一个或多个突起（130），并且该对的第二芯体（110b）的面向第一 一对中心构件（110a）在其中设置有一个或多个相应的开口凹部（150），所述第一芯构件（110a）上的或每个相应的突起（130）面对或相应的一个所述开口凹部 150）在第二芯构件（110b）中，其中在铸造的至少一部分期间 第一（110a）和第二（110b）芯构件相对于彼此保持在空间位置，使得第一和第二芯构件（110a，110b）的相对面的所述主要部分呈现相互 间隔大体上等于所得到的铸造壁（120）的主要部分的预定最小厚度（W）的所述第一距离（W）; 并且所述第一芯体（110a）上的所述或每个突出部（130）的至少头部位于所述第二芯构件（110b）内的相应的开放凹部（150）内，使得所述或每个相应突起 （130）和所述或每个相应的开口凹部（150）在其间限定所得铸造壁（120）的相应的较小部分，其从所得浇铸壁（120）的主要部分横向移位。