公开(公告)号：EP4365408A1

公开(公告)日：2024-05-08

申请号：EP23201124.7

申请日：2023-10-02

申请人： Rolls-Royce plc

发明人： Neale, Christopher

IPC分类号： F01D5/14 ,  B22D31/00 ,  B22F7/00 ,  B23P15/02

CPC分类号： F01D5/141 ,  F05D2230/0020130101 ,  F05D2230/21120130101 ,  F05D2230/1020130101 ,  B23P15/02 ,  B22D31/00 ,  B22F7/00 ,  G05B19/4097 ,  G05B2219/4514720130101 ,  B22C9/04 ,  B22C7/02

摘要： The present disclosure provides a method of manufacturing a turbomachinery component for a gas turbine engine, comprising: receiving an ideal design of the turbomachinery component, the turbomachinery component comprising: an aerofoil portion comprising an aerofoil surface and having an ideal aerofoil wall thickness; and a platform portion comprising a platform surface coterminous with the aerofoil surface, the platform portion having an ideal radial platform thickness along a radial direction; determining an intermediate design of the turbomachinery component comprising an intermediate platform portion having an intermediate platform surface and an intermediate radial platform thickness which is greater than the ideal radial platform thickness; forming, by an investment casting process, an intermediate turbomachinery component based on the intermediate design, wherein the intermediate turbomachinery component comprises at least one detectable reference feature formed by an internal core element during the investment casting process; defining a datum system for machining the intermediate turbomachinery component comprising detecting the at least one reference feature and defining a radial datum based on the at least one reference feature; and machining the intermediate turbomachinery component using the datum system to remove material from at least the intermediate platform portion of the intermediate turbomachinery component to create a machined turbomachinery component.

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。

公开(公告)号：EP3132870A1

公开(公告)日：2017-02-22

申请号：EP16180562.7

申请日：2016-07-21

申请人： Rolls-Royce plc

发明人： Neale, Christopher

IPC分类号： B22C9/10 ,  F01D5/18

CPC分类号： B22C9/10 ,  B22C9/24 ,  B22D25/02 ,  B22D29/001 ,  F01D5/18 ,  F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/141 ,  F05D2250/75 ,  F05D2260/2212 ,  F05D2260/2214

摘要： A method for casting a turbine component body comprises; providing a mould defining the external geometry of the component body and providing a core defining an internal geometry of the component body. The core comprises a main body defining an internal chamber of the component body and an array of pedestals (43) extending between opposing walls of the internal chamber. A molten material is cast between the mould and the core and the core is then removed after the molten material has solidified. The core is provided using a core die which has an inlet (40) for receiving fluid core material. The core die is configured such as to provide a gradient of injection pressure which decreases from a first injection pressure at a first position (46) proximal to the inlet and a second injection pressure at a second position (47) distal to the inlet. The pedestal array is arranged such that the separation of the pedestals (43) increases between the first position (46) and the second position (47).

摘要翻译： 一种用于铸造涡轮机部件主体的方法包括： 提供限定组件主体的外部几何形状的模具，并提供限定组件主体的内部几何形状的芯。 芯部包括限定组件主体的内部室的主体和在内部室的相对壁之间延伸的基座阵列（43）。 熔融材料在模具和芯之间铸造，然后在熔融材料固化之后取出芯。 使用具有用于接收流体芯材料的入口（40）的芯模提供芯。 芯模具被配置成提供喷射压力的梯度，其从靠近入口的第一位置（46​​）处的第一喷射压力减小，并且在远离入口的第二位置（47）处的第二喷射压力降低。 基座阵列被布置成使得基座（43）的分离在第一位置（46​​）和第二位置（47）之间增加。

公开(公告)号：EP3132870B1

公开(公告)日：2019-05-15

申请号：EP16180562.7

申请日：2016-07-21

申请人： Rolls-Royce plc

发明人： Neale, Christopher

IPC分类号： B22C9/10 ,  F01D5/18 ,  B22C9/24 ,  F01D9/06

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：EP3098385A1

公开(公告)日：2016-11-30

申请号：EP16167125.0

申请日：2016-04-26

申请人： Rolls-Royce plc

发明人： Neale, Christopher ,  Villasante Llarena, Marta

IPC分类号： F01D5/18 ,  B22C9/10

CPC分类号： F01D5/187 ,  B22C9/10 ,  B22C9/101 ,  B22C9/24 ,  B22D25/02 ,  B22D29/001 ,  B22D30/00 ,  F01D5/186 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/211

摘要： A method for casting a turbine blade body comprises; providing a mould defining the external geometry of the blade body; providing a core defining an internal geometry of the blade body, the core comprising a main body defining an internal chamber of the blade body and having a root end and a tip end and a plurality of pedestals defining an array of cooling channels extending from the internal chamber; casting a molten material between the mould and the core; and removing the core after the molten material has solidified, wherein the pedestals are arranged in a single row (22) starting from the root end to a mid-portion of the main body (9) branching into multiple and divergent rows (23a,23b) towards the tip end of the body.

摘要翻译： 一种用于铸造涡轮叶片体的方法，包括： 提供限定所述叶片主体的外部几何形状的模具; 提供限定所述叶片本体的内部几何形状的芯部，所述芯部包括主体，所述主体限定所述叶片主体的内部腔室，并且具有根部端部和顶端端部，以及限定从所述内部部分延伸的冷却通道阵列的多个基座 室; 在模具和芯之间铸造熔融材料; 并且在所述熔融材料凝固之后移除所述芯，其中所述基座被布置成从所述主体（9）的根部到所述主体（9）的中间部分分成多个和发散的行（23a，23b）的单行（22） ）朝向身体的尖端。