公开(公告)号：EP2410129B1

公开(公告)日：2018-10-17

申请号：EP11167131.9

申请日：2011-05-23

申请人： Rolls-Royce plc

发明人： Strother, Oliver Michael

IPC分类号： F01D5/02 ,  F01D5/34

CPC分类号： F01D5/027 ,  F01D5/34 ,  Y02T50/671 ,  Y10T29/4932 ,  Y10T29/49321 ,  Y10T29/49325

摘要： A method is provided of rotationally balancing a rotating part. A rotor hub or ring and a plurality of rotor blades for assembly onto the hub or ring are provided, each blade having an unfilled internal cavity. The respective masses and moment weights of the blades with filled internal cavities are then predicted. Next, the rotor blades are assembled onto the hub or ring to form the rotating part. The relative positions of the assembled blades are determined on the basis of their predicted masses and moment weights with filled internal cavities. The internal cavities of the assembled rotor blades are then filled.

公开(公告)号：EP2233239A2

公开(公告)日：2010-09-29

申请号：EP10250319.0

申请日：2010-02-23

申请人： Rolls-Royce Plc

发明人： Strother, Oliver Michael

IPC分类号： B23K20/18 ,  F01D5/12 ,  B21D26/02

CPC分类号： B21D26/021 ,  B21D26/055 ,  B23K20/02 ,  B23K2201/001 ,  B23P15/04 ,  F01D5/147 ,  F01D5/28 ,  F04D29/324 ,  F04D29/668 ,  F05D2220/36 ,  F05D2260/96 ,  F05D2300/603 ,  F05D2300/615 ,  Y02T50/672 ,  Y02T50/673

摘要： A method of manufacturing a component (10) by superplastic forming and diffusion bonding a first layer (12), a second layer (14), a first membrane (16), and a second membrane (18), the first and second membranes (16, 18) being disposed between the first and second layers (12, 14) with the first membrane (16) adjacent the first layer (12) and the second membrane (18) adjacent the second layer (14), wherein the method comprises: applying a stop-off material in a first predetermined pattern between the first layer (12) and the first membrane (16) so as to prevent a diffusion bond from forming between the first layer (12) and the first membrane (16) across regions defined by said first predetermined pattern; applying the stop-off material in a second predetermined pattern between the second layer (14) and the second membrane (18) so as to prevent a diffusion bond from forming between the second layer (14) and the second membrane (18) across regions defined by said second predetermined pattern; and providing a damping material (40) between the first and second membranes.

摘要翻译： 一种通过超塑性成形和扩散接合第一层（12），第二层（14），第一膜（16）和第二膜（18）的方法来制造组分（10），所述第一和第二膜（ 所述第一和第二层（12,14）之间的所述第一膜（16）邻近所述第一层（12），所述第二膜（18）邻近所述第二层（14），所述方法包括 ：在第一层（12）和第一膜（16）之间以第一预定图案施加停止材料，以防止在第一层（12）和第一膜（16）之间形成扩散接合 由所述第一预定图案限定的区域; 在所述第二层（14）和所述第二膜（18）之间以第二预定图案施加所述停止材料，以便防止在所述第二层（14）和所述第二膜（18）之间形成扩散接合区域 由所述第二预定图案限定; 以及在所述第一和第二膜之间提供阻尼材料（40）。

公开(公告)号：EP2147731A1

公开(公告)日：2010-01-27

申请号：EP09251341.5

申请日：2009-05-18

申请人： Rolls-Royce plc

发明人： Goldfinch, Keith Christopher ,  Strother, Oliver Michael

IPC分类号： B21D53/78 ,  B21D26/02 ,  B23P15/00 ,  B23K20/02

CPC分类号： B21D53/78 ,  B21D26/055 ,  B21D47/00 ,  B23K20/023 ,  B23K20/22 ,  B23K2201/006

摘要： A method of making an aerofoil comprises the steps of providing first and second skin panels (12,14) and first and second web-forming membranes (16,18). The web-forming membranes each have a series of elongate slots formed longitudinally therein so as to define a series of alternating wide and narrow strips. The wide strips of one membrane are arranged against the narrow strips of the other membrane and the skin panels are arranged either side of the two web-forming membranes. Parts of the web-forming membranes and parts of the skin panels are treated with a release layer and the sub-assembly is compressed and heated so as to effect diffusion bonding between those parts of the membranes and skin panels which are not treated with the release layer. The sub-assembly is then heated and inflated so as to draw the first and second skin panels apart and that, in turn, causes the web-forming membranes to form webs internally.

摘要翻译： 一种制造机翼的方法包括以下步骤：提供第一和第二皮肤面板（12,14）和第一和第二网状物形成膜（16,18）。 幅材形成膜各自具有纵向形成的一系列细长槽，以便限定一系列交替的宽而窄的条。 一个膜的宽条布置成抵靠另一个膜的窄条，并且皮肤片布置在两个幅材形成膜的两侧。 将成网膜和部分皮肤面板的部分用剥离层处理，并且将子组件压缩和加热，以便在膜的那些部分和不经释放处理的皮肤面板之间实现扩散粘合 层。 然后将该子组件加热并充气以便将第一和第二表皮面板分开，并进而导致幅材形成膜在内部形成纤维网。

公开(公告)号：EP2233223B1

公开(公告)日：2016-03-02

申请号：EP10250408.1

申请日：2010-03-05

申请人： Rolls-Royce plc

发明人： Strother, Oliver Michael ,  Goldfinch, Keith Christopher

IPC分类号： B21D53/78 ,  F01D5/18

CPC分类号： B21D53/78 ,  B21D26/055 ,  F01D5/147 ,  Y02T50/672

公开(公告)号：EP2119871A2

公开(公告)日：2009-11-18

申请号：EP09251303.5

申请日：2009-05-13

申请人： Rolls-Royce plc

发明人： Strother, Oliver Michael

IPC分类号： F01D5/14 ,  F01D5/16 ,  F01D5/28

CPC分类号： F01D5/147 ,  F01D5/16 ,  F01D5/282 ,  F05D2250/20

摘要： Within hollow structures, such as blade structures (30) in a gas turbine engine, traditionally rigid girdered reinforcement has been utilised to define structure and shape. Such rigid definition can inhibit utilisation of damping fillers within the hollow structure. By providing a web former (31) comprising spaced bond areas (33,34) suspended upon angled interconnecting membranes (35) a hollow structure is achieved which is flexible and can be used in conjunction with a damping filler to achieve desired performance. The web former (31) supports skins (32) defining the shape and takes some load such that the damping filler does not separate within the hollow structure.

摘要翻译： 在中空结构中，例如燃气涡轮发动机中的叶片结构（30），传统的刚性桁架钢筋已被用于限定结构和形状。 这种刚性定义可以抑制中空结构内的阻尼填料的利用。 通过提供包括悬挂在成角度的互连膜（35）上的间隔开的结合区域（33,34）的网状物（31），其实现了柔性的中空结构并且可以与阻尼填料一起使用以实现期望的性能。 网状物（31）支撑限定形状并承载一些载荷的外皮（32），使得阻尼填料在中空结构内不分离。

公开(公告)号：EP2014386A8

公开(公告)日：2009-03-11

申请号：EP08011077.8

申请日：2008-06-18

申请人： Rolls-Royce plc

发明人： Goldfinch, Keith Christopher ,  Strother, Oliver Michael ,  Mackechnie-Jarvis, Julian

IPC分类号： B21D53/78 ,  B23P15/04 ,  F01D5/18

CPC分类号： B21D53/78 ,  B23P15/04 ,  F01D5/147 ,  F01D5/26 ,  F04D29/023 ,  F04D29/324 ,  F04D29/666 ,  F04D29/668 ,  F05D2220/36 ,  F05D2260/96 ,  F05D2300/133 ,  F05D2300/43 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49339

摘要： A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.

公开(公告)号：EP2014384B1

公开(公告)日：2012-03-21

申请号：EP08011080.2

申请日：2008-06-18

申请人： Rolls-Royce plc

发明人： Strother, Oliver Michael

IPC分类号： B21D26/02 ,  B21D53/78 ,  B23P15/04 ,  F01D5/16 ,  B21D47/00 ,  F04D29/66

CPC分类号： B21D53/78 ,  B21D26/055 ,  B21D47/00 ,  B23P15/04 ,  F01D5/147 ,  F01D5/16 ,  F02K3/06 ,  F04D29/023 ,  F04D29/388 ,  F04D29/668 ,  F05D2300/43 ,  F05D2300/501 ,  F05D2300/522 ,  Y10T29/49337

公开(公告)号：EP2233223A2

公开(公告)日：2010-09-29

申请号：EP10250408.1

申请日：2010-03-05

申请人： Rolls-Royce plc

发明人： Strother, Oliver Michael ,  Goldfinch, Keith Christopher

IPC分类号： B21D53/78 ,  B21D26/02

CPC分类号： B21D53/78 ,  B21D26/055 ,  F01D5/147 ,  Y02T50/672

摘要： A method of forming an internal structure in a hollow component, the method comprising: forming an assembly comprising first, second, and third plates (2, 4, 6), the first and second plates (2, 4) each comprising a substantially planar surface and a surface comprising at least one protrusion (10), the surfaces comprising said at least one protrusion (10) being on the exterior facing surfaces of the assembly, and the third plate (6) being sandwiched between the first and second plates (2, 4); selectively bonding portions of the third plate (6) to sections of the first and second plates (2, 4) substantially opposite the at least one protrusions (10) of the first and second plates (2, 4); forming the assembly against a die such that the at least one protrusions (10) of the first and second plates (2, 4) are transferred from the exterior facing surfaces to the interior facing surfaces of the first and second plates (2, 4).

摘要翻译： 一种在中空部件中形成内部结构的方法，所述方法包括：形成包括第一，第二和第三板（2,4,6）的组件，所述第一板和第二板（2,4）各自包括基本平坦的 表面和包括至少一个突起（10）的表面，所述表面包括所述至少一个突起（10）在所述组件的面向外表面上，并且所述第三板（6）夹在所述第一和第二板之间 2，4）; 选择性地将所述第三板（6）的部分接合到所述第一和第二板（2,4）的与所述第一和第二板（2,4）的所述至少一个突起（10）相对的部分; 将组件相对于模具形成，使得第一和第二板（2,4）的至少一个突起（10）从外表面转移到第一和第二板（2,4）的面向内表面， 。

公开(公告)号：EP2014386A1

公开(公告)日：2009-01-14

申请号：EP08011077.8

申请日：2008-06-18

申请人： Rolls-Royce plc

发明人： Goldfinch, Keith Christopher ,  Strother, Oliver Michael ,  Mackechnie-Jarvis, Julian

IPC分类号： B21D53/78 ,  B23P15/04 ,  F01D5/18

CPC分类号： B21D53/78 ,  B23P15/04 ,  F01D5/147 ,  F01D5/26 ,  F04D29/023 ,  F04D29/324 ,  F04D29/666 ,  F04D29/668 ,  F05D2220/36 ,  F05D2260/96 ,  F05D2300/133 ,  F05D2300/43 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49339

摘要： A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.

摘要翻译： 一种制造燃气涡轮发动机（10）的机翼的方法。 该方法包括以下步骤：提供第一和第二面板（16,18），在第一和第二面板之间提供卷筒纸（30），通过在面板之间施加内部压力来使面板变形，从而形成内部空腔。 该方法还包括在幅材上提供肋（60）的图案以便限定具有第一和第二面板的机翼，所述翼面具有至少一个肋（60），所述至少一个肋（60）形成从第一面板部分延伸穿过第二面板 第一和第二面板。

公开(公告)号：EP2014384A1

公开(公告)日：2009-01-14

申请号：EP08011080.2

申请日：2008-06-18

申请人： Rolls-Royce plc

发明人： Strother, Oliver Michael

IPC分类号： B21D26/02 ,  B21D53/78 ,  B23P15/04 ,  F01D5/16 ,  B21D47/00 ,  F04D29/66

CPC分类号： B21D53/78 ,  B21D26/055 ,  B21D47/00 ,  B23P15/04 ,  F01D5/147 ,  F01D5/16 ,  F02K3/06 ,  F04D29/023 ,  F04D29/388 ,  F04D29/668 ,  F05D2300/43 ,  F05D2300/501 ,  F05D2300/522 ,  Y10T29/49337

摘要： A method of manufacturing a component such as a gas turbine fan blade. The method comprises: disposing a plurality of webs between a plurality of panels; and deforming the panels and the webs by applying internal pressure between the panels, thereby forming a series of internal cavities (15) partitioned by the webs (20-22). Weakened regions (30a,30b,30c) are formed in the webs which open to form holes (30) in the webs (20-22) during the deformation step. A damping material (17) is introduced into at least one of the cavities (15) whereby it flows from the cavity into the other cavities via the holes in the webs.

摘要翻译： 如燃气涡轮风扇叶片：一种制造组件的方法。 该方法包括：设置面板之间的多个腹板的多元性; 并且通过施加在面板之间的内部压力，由此形成了一系列由腹板（20-22）之间分配内部空腔（15）的面板和腹板变形。 弱化区域（30A，30B，30C）的形成，其中打开以形成在变形步骤期间腹板（20-22）的孔（30）的纤维网。 阻尼材料（17）被引入到所述空腔中的至少一个（15），由此它从腔流入到经由在腹板上的孔的其他空腔。