公开(公告)号：EP2505790A2

公开(公告)日：2012-10-03

申请号：EP12159360.2

申请日：2012-03-14

申请人： Rolls-Royce plc

发明人： Dixon, Jeffrey ,  Udall, Kenneth ,  Nicholson, Richard

IPC分类号： F01D25/18 ,  F01D11/04

CPC分类号： F01D25/183 ,  F01D11/04 ,  F05D2240/55

摘要： An assembly, for example in a gas turbine engine, comprises a rotatable component 24, 26 supported by a bearing 30 in a support structure 16. A sealing arrangement 38 comprises a non-rotating sealing ring 56 which makes sealing contact with sealing features 60 on the rotatable component 24, 26. The non-rotating sealing ring 56 is radially displaceable with respect to the support structure 16 by means of ribs 62, 64 which engage axially facing support faces 66, 68 of the support structure 16. The non-rotating sealing ring 56 is radially located by an outer, non-rotating, race 44 of the bearing 30, by means of a locating surface 76 on a locating body 74 of the non-rotating sealing ring 56.
As a result of this arrangement, the running clearance at the sealing arrangement 38 can be maintained, despite radial displacement of the rotatable component 24, 26 with respect to the support structure 16, and despite thermal and mechanical deflections of the support structure 16.

摘要翻译： 例如在燃气涡轮发动机中的组件包括由支撑结构16中的轴承30支撑的可旋转部件24,26。密封装置38包括非旋转密封环56，其使密封接触与密封特征60 可旋转部件24,26。非旋转密封环56可通过肋62,64相对于支撑结构16径向移动，该肋62,64接合支撑结构16的轴向面对的支撑面66,68。不旋转 密封环56通过位于非旋转密封环56的定位体74上的定位表面76径向定位在轴承30的外部不旋转的座圈44上。作为这种结构的结果 尽管可旋转部件24,26相对于支撑结构16的径向位移，并且尽管支撑结构16的热和机械偏转也可以保持在密封装置38处的运行间隙。

公开(公告)号：EP2273076B1

公开(公告)日：2012-02-29

申请号：EP10161137.4

申请日：2010-04-27

申请人： Rolls-Royce plc

发明人： Pool, Clare ,  Udall, Kenneth ,  Stretton, Richard ,  Reed, Julian

IPC分类号： F01D21/04 ,  F01D25/06 ,  F01D5/16

CPC分类号： F01D21/045 ,  F01D5/16 ,  F01D25/06

公开(公告)号：EP2273076A1

公开(公告)日：2011-01-12

申请号：EP10161137.4

申请日：2010-04-27

申请人： Rolls-Royce plc

发明人： Pool, Clare ,  Udall, Kenneth ,  Stretton, Richard ,  Reed, Julian

IPC分类号： F01D21/04 ,  F01D25/06 ,  F01D5/16

CPC分类号： F01D21/045 ,  F01D5/16 ,  F01D25/06

摘要： A duct wall (2) of a fan casing of a gas turbine engine comprises an intake section (4) and a containment casing (6), provided respectively with flanges (20,22). An acoustic flutter damper (28) is secured between the flanges (20,22). The acoustic flutter damper (28) has a skin (34,36) which accommodates an internal structure which serves to provide damping of flutter arising in fan blades (18). In the event of detachment of a blade (18) or a blade fragment, the resulting deflection wave in the containment case (6) causes the internal structure to rupture, and the load path between the intake section (4) and the containment casing (6) passes along the skin (34,36), which consequently maintains the connection between the intake duct (4) and the containment casing (6), while permitting substantial radial deflection of the containment casing (6) relative to the intake section (4).

摘要翻译： 燃气涡轮发动机的风扇壳体的导管壁（2）包括分别设置有凸缘（20,22）的进气部分（4）和容纳壳体（6）。 声波阻尼器（28）固定在凸缘（20,22）之间。 声音颤动阻尼器（28）具有容纳内部结构的皮肤（34,36），其用于提供在风扇叶片（18）中产生的颤动的阻尼。 在叶片（18）或叶片碎片分离的情况下，容纳壳体（6）中产生的偏转波导致内部结构破裂，并且进气部分（4）和收容壳体 6）沿着皮肤（34,36）通过，从而保持进气管道（4）和容纳壳体（6）之间的连接，同时允许容纳壳体（6）相对于进气部分 4）。

公开(公告)号：EP2256302A1

公开(公告)日：2010-12-01

申请号：EP10161135.8

申请日：2010-04-27

申请人： Rolls-Royce plc

发明人： Brooks, Richard ,  Udall, Kenneth ,  Stretton, Richard

IPC分类号： F01D21/04 ,  F01D25/06 ,  F01D5/16

CPC分类号： F01D21/045 ,  F01D5/16 ,  F01D25/06

摘要： A duct wall 2 of a fan casing of a gas turbine engine comprises an intake section 4 and a containment casing 6, which are interconnected by bolts 50 at flanges 20, 22. An acoustic flutter damper 28 is provided between the flanges 20, 22 to reduce or eliminate flutter arising in blades 18 of the fan at certain important operating conditions. The damper 28 provides flexibility at the connection between the intake section 4 and the containment casing 6 so that, in the event of detachment of a blade 18 or a bladed fragment, the resulting deflection wave in the containment casing 6 can be accommodated by displacement and/or deformation of the acoustic flutter damper 28, reducing the risk that the bolts 50 will shear to allow the intake section 4 and the containment casing 6 to become detached from each other. The acoustic flutter damper 28 may comprise a circumferential array of separate segments 34 ( Figure 3 ).

摘要翻译： 燃气涡轮发动机的风扇壳体的管道壁2包括进气部分4和容纳壳体6，其通过螺栓50在凸缘20,22处相互连接。声波阻尼器28设置在凸缘20,22至22之间 在某些重要的操作条件下减少或消除风扇叶片18中产生的颤动。 阻尼器28在进气部分4和收容壳体6之间的连接处提供灵活性，使得在叶片18或叶片的分离的情况下，容纳壳体6中产生的偏转波可以通过位移和 /或声波阻尼器28的变形，降低螺栓50将被剪切以允许进气部分4和容纳壳体6彼此分离的风险。 声波阻尼器28可以包括分开的段34（图3）的圆周阵列。

公开(公告)号：EP2505790A3

公开(公告)日：2017-10-25

申请号：EP12159360.2

申请日：2012-03-14

申请人： Rolls-Royce plc

发明人： Dixon, Jeffrey ,  Udall, Kenneth ,  Nicholson, Richard

IPC分类号： F01D25/18 ,  F01D11/04

CPC分类号： F01D25/183 ,  F01D11/04 ,  F05D2240/55

摘要： An assembly, for example in a gas turbine engine, comprises a rotatable component 24, 26 supported by a bearing 30 in a support structure 16. A sealing arrangement 38 comprises a non-rotating sealing ring 56 which makes sealing contact with sealing features 60 on the rotatable component 24, 26. The non-rotating sealing ring 56 is radially displaceable with respect to the support structure 16 by means of ribs 62, 64 which engage axially facing support faces 66, 68 of the support structure 16. The non-rotating sealing ring 56 is radially located by an outer, non-rotating, race 44 of the bearing 30, by means of a locating surface 76 on a locating body 74 of the non-rotating sealing ring 56.
As a result of this arrangement, the running clearance at the sealing arrangement 38 can be maintained, despite radial displacement of the rotatable component 24, 26 with respect to the support structure 16, and despite thermal and mechanical deflections of the support structure 16.

摘要翻译： 例如在燃气涡轮发动机中的组件包括由支承结构16中的轴承30支承的可旋转部件24,26。密封装置38包括非旋转密封环56，该密封环56与密封部件60密封接触 可旋转部件24,26。非旋转密封环56通过与支撑结构16的轴向面对的支撑面66,68接合的肋62,64相对于支撑结构16可径向移位。不旋转 密封环56通过非旋转密封环56的定位主体74上的定位表面76由轴承30的外部非旋转座圈44径向地定位。作为这种布置的结果， 尽管可旋转部件24,26相对于支撑结构16径向移位，并且尽管支撑结构16发生热和机械偏转，但仍可保持密封装置38处的运行间隙。

公开(公告)号：EP2845805A1

公开(公告)日：2015-03-11

申请号：EP14183050.5

申请日：2014-09-01

申请人： Rolls-Royce plc

发明人： Stretton, Richard ,  Udall, Kenneth

IPC分类号： B64D27/26

CPC分类号： B64D27/26 ,  B64D2027/262 ,  B64D2027/266

摘要： An engine mount, for mounting the casing of an aircraft engine to the fuselage or wing of an aircraft, e.g. via a pylon, comprising first and second links (4, 5) having connector formations for connection to respective mounting formations (3A, 3B) and support formations (7, 8) on the engine casing and aircraft mounting structure. Each of the first and second links (4, 5) is typically connected by a pin between the mounting formations (3A, 3B) and support formations (7, 8). Each link has a further connector formation arranged such that the connector formation of the first link (4) is arranged to be offset from the connector formation of the second link (5). The connector formations are joined by an intermediate link (26). The mount allows lateral forces and torque to be resolved in such a way as to substantially avoid lateral displacement of the engine away from a central plane. The intermediate link (26) may also provide a failsafe catcher arrangement in the event that the first (4) or second (5) link fail.

公开(公告)号：EP2586701A2

公开(公告)日：2013-05-01

申请号：EP12188780.6

申请日：2012-10-17

申请人： Rolls-Royce plc

发明人： Udall, Kenneth ,  Mackie, Kenneth

IPC分类号： B64C11/06

CPC分类号： B64C11/06 ,  B64D2027/005 ,  F01D5/3023 ,  F05D2260/94 ,  Y02T50/66

摘要： A support ring for a rotary assembly such as a propeller assembly comprises support cups 20 for receiving blade roots 18 of propeller blades 16. The support cups 20 are interconnected by bridging structures 32. Each bridging structure 32 comprises bridging walls 36 which extend radially from a bridging web 38. The bridging structures 32 thus have a channel-shaped cross-section. The bridging walls 36 have a scalloped configuration at their radially outer edges 40. As a result of this configuration, the neutral axes of the bridging structures 36 are straight, so that the support ring 30 behaves, in structural terms, as a polygon.

摘要翻译： 用于诸如螺旋桨组件的旋转组件的支撑环包括用于接收螺旋桨叶片16的叶根18的支撑杯20.支撑杯20通过桥接结构32相互连接。每个桥接结构32包括桥接壁36，其从 桥接结构32因此具有通道形横截面。 桥接壁36在其径向外边缘40处具有扇形构造。作为该构造的结果，桥接结构36的中性轴线是直的，使得支撑环30在结构上表现为多边形。

公开(公告)号：EP2258926A2

公开(公告)日：2010-12-08

申请号：EP10159764.9

申请日：2010-04-13

申请人： Rolls-Royce plc

发明人： Hood, Ian ,  Udall, Kenneth

IPC分类号： F01D17/16 ,  F02C6/12 ,  F02C9/20 ,  F02K1/15 ,  F02C9/22

CPC分类号： F01D17/16 ,  F02C6/12 ,  F02C9/20 ,  F02C9/22 ,  F02K1/15 ,  F04D29/563

摘要： A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a moveable actuation rod. The control mechanism further comprises a first linkage arrangement which includes a first bell crank and which operatively connects the actuation rod to a first component of the gas turbine engine. Movement of the actuation rod produces an output motion of the first bell crank which in turn drives movement of the first component. The control mechanism further comprises a second linkage arrangement which includes a second bell crank and which operatively connects the actuation rod to a second component of the gas turbine engine. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component. The first linkage arrangement and the second linkage arrangement are configured so that over a predetermined range of movement of the actuation rod the first component is moved by the first bell crank while the second component is not moved by the second bell crank.

公开(公告)号：EP2796367B1

公开(公告)日：2017-09-06

申请号：EP14154449.4

申请日：2014-02-10

申请人： Rolls-Royce plc

发明人： Udall, Kenneth ,  Beaven, David ,  Houle, Mark

IPC分类号： B64C11/04 ,  F01D5/30

CPC分类号： B64C11/04 ,  B64C11/26

公开(公告)号：EP3184210A1

公开(公告)日：2017-06-28

申请号：EP16204326.9

申请日：2016-12-15

申请人： Rolls-Royce plc

发明人： Doorbar, Phillip ,  Friend, Gareth ,  Udall, Kenneth

IPC分类号： B22F3/15 ,  B22F7/06 ,  B22F5/10 ,  B23K20/02 ,  B21K1/76 ,  C22C32/00 ,  F16C7/02 ,  B23K101/06 ,  C22C47/20 ,  C22C49/11

CPC分类号： F01D25/005 ,  B21D11/203 ,  B21K1/762 ,  B22F3/15 ,  B22F5/008 ,  B22F5/106 ,  B22F7/06 ,  B22F7/062 ,  B22F2998/10 ,  B22F2999/00 ,  B23K20/023 ,  B23K20/22 ,  B23K2201/001 ,  B23K2203/166 ,  C22C32/00 ,  C22C32/0031 ,  C22C47/20 ,  C22C49/11 ,  F01D9/02 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/42 ,  F05D2300/6032 ,  F16C7/02

摘要： A method of manufacturing a metal matrix composite component comprises the steps of:
providing a first tubular member having a first end and an opposite second end, the first end of the first tubular member being formed as a first end block;
positioning a metal matrix composite tubular member concentrically over the first tubular member;
positioning a second tubular member concentrically over the metal matrix composite tubular member, the second tubular member having a first end and an opposite second end, the second end of the second tubular member being formed as a second end block;
welding the first end of the first tubular member to the first end of the second tubular member, and the second end of the first tubular member to the second end of the second tubular member, to join the first tubular member to the second tubular member and thereby to form a metal matrix composite preform; and
consolidating the metal matrix composite preform by a hot isostatic pressing process to form the metal matrix composite component.

摘要翻译： 一种制造金属基体复合部件的方法包括以下步骤：提供具有第一端和相对的第二端的第一管状部件，第一管状部件的第一端形成为第一端块; 将金属基质复合管状部件同心地定位在第一管状部件上; 将第二管状部件同心地定位在金属基质复合管状部件上，第二管状部件具有第一端和相对的第二端，第二管状部件的第二端形成为第二端块; 将第一管状构件的第一端焊接到第二管状构件的第一端，将第一管状构件的第二端焊接到第二管状构件的第二端，以将第一管状构件连接到第二管状构件，以及 从而形成金属基体复合材料预制件; 以及通过热等静压工艺来固化金属基体复合材料预制件以形成金属基体复合材料部件。