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1. 发明授权

EP2837773B1 Annulus filler and corresponding stage and gas turbine engine 有权转让
标题翻译：环形间隙填料和相关联的阶段和燃气涡轮发动机
公开(公告)号：EP2837773B1
公开(公告)日：2016-11-16
申请号：EP14180628.1
申请日：2014-08-12
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer , Lee, James , Mason, Paul , Thompson, Ewan
IPC分类号： F01D11/00
CPC分类号： F01D11/008 , F05D2220/36 , F05D2260/95 , F05D2300/434 , F05D2300/603

2. 发明公开

EP2290194A3 Aerofoil with erosion resistant leading edge 无效转让
标题翻译：永合抗侵蚀前缘
公开(公告)号：EP2290194A3
公开(公告)日：2013-07-10
申请号：EP10172258.5
申请日：2010-08-09
申请人： Rolls-Royce plc
发明人： Jevons, Matthew , Bottome, Kristofer
IPC分类号： F01D5/28 , B64C11/20 , B23P6/00
CPC分类号： F01D5/282 , F01D5/284 , F04D29/324 , F05D2240/303 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y02T50/673 , Y10T156/1153 , Y10T156/1158
摘要： The present invention relates to an aerofoil having an erosion resistant leading edge. The aerofoil comprises an aerofoil main body portion and a leading edge portion. The leading edge portion comprises a plurality of functionally distinct parts, including at least; a first part for resisting abrasion of the leading edge portion, and a second part for resisting a bending force applied to the leading edge portion, and located behind the first part.

3. 发明公开

EP2267273A2 Adjustable camber aerofoil 无效转让
标题翻译：可调弯翼
公开(公告)号：EP2267273A2
公开(公告)日：2010-12-29
申请号：EP10165054.7
申请日：2010-06-07
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer , Jevons, Matthew
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/148 , F01D9/041 , F04D29/324 , F04D29/644 , F05D2230/51 , F05D2230/80 , F05D2240/304 , F05D2250/90
摘要： The present invention relates to an aerofoil (20) comprising a leading edge portion (22) and a flexible thin-walled portion (26) that is rearwards of the leading edge portion, defining a cavity (28), and a shape-forming insert (30) for inserting into the cavity. The flexible thin-walled portion has an opening through which the shape-forming insert is inserted to at least partly define the profile of the aerofoil such that changing the shape of the insert changes the profile of the aerofoil.

4. 发明公开

EP2369155A3 A gas turbine engine nose cone 有权转让
标题翻译：燃气涡轮发动机鼻锥
公开(公告)号：EP2369155A3
公开(公告)日：2018-04-04
申请号：EP11157612.0
申请日：2011-03-10
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer
IPC分类号： F02C7/04 , B64C11/14
CPC分类号： H01M6/08 , B64C11/14 , F02C7/04 , F05D2250/232 , F05D2300/603 , H01M2/0235 , H01M2/30
摘要： A gas turbine engine nose cone assembly (40) comprises a tapering spinner (42). The tapering spinner (42) has a point (44) at a first end (46) and a circular base (48) at a second end (50). The tapering spinner (42) comprises a carbon fibre containing composite material layer (70), an electrically insulating layer (74) arranged on an inner surface (72) of the carbon fibre containing composite material layer (70), an electrically conducting layer (78) arranged on an inner surface (76) of the electrically insulating layer (74) and an electrically conducting member (80) extends through the first end of the tapering spinner (42) and is connected to the electrically conducting layer (78). This arrangement provides lightning protection for the gas turbine engine nose cone assembly (40).
摘要翻译：燃气涡轮发动机鼻锥组件（40）包括锥形旋转器（42）。锥形旋转器（42）在第一端（46）处具有点（44），在第二端（50）处具有圆形基部（48）。锥形旋转器（42）包括含碳纤维复合材料层（70），设置在含碳纤维复合材料层（70）的内表面（72）上的电绝缘层（74），导电层布置在电绝缘层（74）的内表面（76）上的导电构件（78）和导电构件（80）延伸穿过锥形旋转器（42）的第一端并连接到导电层（78）。该布置为燃气涡轮发动机鼻锥组件（40）提供防雷保护。

5. 发明公开

EP2290196A3 Adjustable fan case liner and mounting method 无效转让
标题翻译：可调风扇箱内胆和安装方法
公开(公告)号：EP2290196A3
公开(公告)日：2017-12-06
申请号：EP10169974.2
申请日：2010-07-19
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer
IPC分类号： F01D11/08 , F02K3/06
CPC分类号： F01D11/08 , F02K3/06 , F05D2240/11 , Y02T50/672
摘要： A liner for an interior surface of an engine casing (18), comprises a number of liner panels (32) disposed radially outwardly of a rotatable component (56) of the engine, such as a fan blade, and mounting means (46) arranged to mount the panels on the interior surface of the casing, wherein each panel is individually adjustable, such that the clearance between the panel and the rotatable component of the engine may be varied individually for each panel.
摘要翻译：用于发动机壳体（18）的内表面的衬套包括多个布置在发动机的可旋转部件（56）的径向外侧的衬板（32），例如风扇叶片和安装装置（46）以将面板安装在壳体的内表面上，其中每个面板是可单独调节的，使得面板和发动机的可旋转部件之间的间隙可以针对每个面板单独地改变。

6. 发明公开

EP2305985A2 Containment casing for an aero engine 有权转让
标题翻译： Sicherheitsgehäusefürein Flugtriebwerk
公开(公告)号：EP2305985A2
公开(公告)日：2011-04-06
申请号：EP10173514.0
申请日：2010-08-20
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer
IPC分类号： F02C7/05 , B64D33/02 , F01D21/04
CPC分类号： F02C7/05 , F01D21/045 , F01D25/26 , F05D2220/36 , F05D2240/14 , Y02T50/672
摘要： A containment assembly for a turbo fan engine, comprises a casing (30) arranged in use around a rotatable fan, to form a duct for the fan, the containment assembly comprising at least one liner element (32) disposed on an interior surface between the casing and blades (42) of a rotatable fan,
the liner element comprising a body portion (34) mounted in a recess in the casing and a wall portion arranged to form part of an inner wall of the duct,
the wall portion and the body portion being attached and defining a containment cavity (30a) therebetween for containment of a detached fan blade fragment in use,
wherein the wall portion comprises a moveable portion (36) which is movable between a first configuration in which it lies substantially flush with the inner wall of the duct, and a second configuration in which it provides an opening through which a fan blade fragment can enter the containment cavity.
摘要翻译：一种用于涡轮风扇发动机的容纳组件，包括围绕可旋转风扇布置的壳体（30），以形成用于风扇的管道，所述容纳组件包括至少一个衬套元件（32）套管和叶片（42），所述衬垫元件包括安装在所述壳体中的凹部中的主体部分（34）和布置成形成所述管道的内壁的一部分的壁部分，所述壁部分和所述主体部分被连接并且在其间限定一个容纳空腔（30a），用于容纳在使用中分离的风扇叶片碎片，其中所述壁部分包括可移动部分（36），所述可移动部分可在第一构型之间移动，管道的壁，以及第二构造，其中其提供了风扇叶片碎片可通过该开口进入容纳空腔的开口。

7. 发明公开

EP2837774A1 Annulus filler and corresponding stage and gas turbine engine 有权转让
标题翻译：环空填料和相应的阶段和燃气轮机发动机
公开(公告)号：EP2837774A1
公开(公告)日：2015-02-18
申请号：EP14180629.9
申请日：2014-08-12
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer , Lee, James , Mason, Paul , Thompson, Ewan
IPC分类号： F01D11/00
CPC分类号： F01D11/008 , F05D2250/712 , F05D2300/501 , F05D2300/603
摘要： An annulus filler (100) is provided for mounting to a rotor disc (34) of a gas turbine engine and bridging the gap between two adjacent blades (25) attached to the rotor disc. The annulus filler is substantially entirely formed from a polymer matrix composite material. It has an outer lid (30) which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and a support structure which is connectable to the rotor disc to support the rear of the lid on the rotor disc. The support structure has two support walls (32) extending from opposing lateral sides of the lid to an attachment strap (36) for receiving a hook (38) on the rotor disc, the attachment strap bridging the support walls. In use, under centrifugal loads, the opposing support walls resiliently deform to allow outward radial movement of the lid. Each support wall has a concave rear edge (57) which extends rearwardly and radially outwardly from the rear of the attachment strap towards a trailing edge of the lid. Each rear edge has a first curved section (61) proximal the attachment strap, a second curved section (63) proximal the trailing edge and a substantially straight section (65) therebetween.
摘要翻译：提供环形填充物（100）用于安装到燃气涡轮发动机的转子盘（34）并桥接连接到转子盘的两个相邻叶片（25）之间的间隙。环形填充物基本上完全由聚合物基质复合材料形成。它具有外部盖（30）和外部盖（30），外部盖（30）限定用于空气沿轴向气流方向通过发动机抽吸的空气流动表面，支撑结构可连接到转子盘以支撑转子盘上的盖的后部。该支撑结构具有两个支撑壁（32），该支撑壁从盖的相对横向侧延伸到用于接收转子盘上的钩（38）的连接带（36），连接带桥接支撑壁。在使用中，在离心负载下，相对的支撑壁弹性变形以允许盖的向外径向移动。每个支撑壁具有凹入的后边缘（57），该后边缘从附接带的后部朝向盖的后缘向后且径向向外延伸。每个后边缘具有靠近连接带的第一弯曲部分（61），靠近后边缘的第二弯曲部分（63）以及位于其间的基本直线部分（65）。

8. 发明公开

EP2267273A3 Adjustable camber aerofoil 无效转让
标题翻译： EinstellbaregewölbteTragfläche
公开(公告)号：EP2267273A3
公开(公告)日：2012-10-17
申请号：EP10165054.7
申请日：2010-06-07
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer , Jevons, Matthew
IPC分类号： F01D5/14 , F01D9/04 , F04D29/56
CPC分类号： F01D5/147 , F01D5/148 , F01D9/041 , F04D29/324 , F04D29/644 , F05D2230/51 , F05D2230/80 , F05D2240/304 , F05D2250/90
摘要： The present invention relates to an aerofoil (20) comprising a leading edge portion (22) and a flexible thin-walled portion (26) that is rearwards of the leading edge portion, defining a cavity (28), and a shape-forming insert (30) for inserting into the cavity. The flexible thin-walled portion has an opening through which the shape-forming insert is inserted to at least partly define the profile of the aerofoil such that changing the shape of the insert changes the profile of the aerofoil.
摘要翻译：本发明涉及一种机翼（20），其包括前缘部分（22）和柔性薄壁部分（26），该柔性薄壁部分（26）位于前缘部分的后方，形成空腔（28）（30），用于插入腔中。柔性薄壁部分具有开口，成形插入物通过该开口至少部分地限定翼型的轮廓，使得改变插入件的形状改变机翼的轮廓。

9. 发明公开

EP2458175A2 Nose cone assembly 无效转让
标题翻译： Nasenkonusanordnung
公开(公告)号：EP2458175A2
公开(公告)日：2012-05-30
申请号：EP11188017.5
申请日：2011-11-07
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer
IPC分类号： F02C7/04
CPC分类号： F02K3/06 , B64C11/14 , F02C7/04 , F03D1/0691 , F05B2280/5001 , F05D2300/501 , Y02E10/721
摘要： A nose cone assembly 102 is disclosed, comprising a one piece nose cone 104 and a support ring 106 on which the nose cone 104 is mounted. The support ring 106 comprises a plurality of circumferentially distributed resilient attachment tabs 114, via which the nose cone 104 is mounted on the support ring 106. The support ring 106 further comprises a load spreader 122, and each of the resilient attachment tabs 114 is operably connected to the load spreader 122, such that deflections and forces experienced by any one attachment tab 114 are distributed to other attachment tabs 114 via the load spreader 122.
摘要翻译：公开了一种鼻锥体组件102，其包括单件鼻锥体104和安装鼻锥体104的支撑环106。支撑环106包括多个周向分布的弹性附接突片114，鼻锥体104经由该支撑环106安装在支撑环106上。支撑环106还包括负载吊具122，并且每个弹性附接突片114可操作地连接到负载分散器122，使得任何一个附接翼片114经受的偏转和力经由负载扩展器122分配到其它附接翼片114。

10. 发明公开

EP2458146A1 Nose cone assembly 有权转让
标题翻译： Anordnung einer Eintrittskegel
公开(公告)号：EP2458146A1
公开(公告)日：2012-05-30
申请号：EP11188018.3
申请日：2011-11-07
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer , Ravey, Eric , Mason, Paul
IPC分类号： F01D5/06 , F02C7/04 , B64C11/14 , B64C11/00
CPC分类号： F02C7/04 , F01D5/066 , F05D2220/32 , F05D2260/31 , F05D2300/121 , F05D2300/133 , F05D2300/171 , F05D2300/2102 , F05D2300/44 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y02T50/673
摘要： A nose cone assembly is provided comprising a nose cone 104, a support ring 106 on which the nose cone 104 is mounted, and an insulating layer 110 disposed between the nose cone 104 and the support ring 106, the insulating layer 110 at least partially comprising glass fibres.
A composite nose cone is also provided comprising an attachment region A, in which composite fibres are oriented substantially perpendicular to an axis of rotation of the nose cone 104, and an impact region I, in which composite fibres are oriented substantially parallel to the axis of rotation of the nose cone 104.
Also provided is a support ring 106 for a nose cone assembly, the support ring 106 comprising an annular main body 140 and an annular projecting attachment flange 142, the attachment flange 142 terminating in a plurality of circumferentially spaced attachment tabs 144, wherein the attachment flange 142 forms with the main body 140 a cross section having at least two C curves 160, 162.
摘要翻译：提供了一种鼻锥体组件，其包括鼻锥体104，安装鼻锥体104的支撑环106以及设置在鼻锥体104和支撑环106之间的绝缘层110，绝缘层110至少部分地包括玻璃纤维。还提供复合鼻锥体，其包括附接区域A，其中复合纤维基本上垂直于鼻锥体104的旋转轴线定向，以及冲击区域I，其中复合纤维基本上平行于鼻锥体104的旋转。还提供了用于鼻锥组件的支撑环106，支撑环106包括环形主体140和环形突出的附接凸缘142，附接凸缘142终止于多个周向间隔开的附件凸片144，其中附接凸缘142与主体140形成具有至少两个C曲线160,162的横截面。

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