公开(公告)号：US20130266447A1

公开(公告)日：2013-10-10

申请号：US13666613

申请日：2012-11-01

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward EVANS ,  Ian Colin Deuchar CARE

IPC: F01D5/22

CPC classification number: F01D5/225 ,  F01D5/22 ,  F01D5/30 ,  F01D5/3007 ,  F01D11/008 ,  F02K3/06

Abstract: A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an annulus filler assembly. The annulus filler assembly includes at least two bodies and a brace, each of the bodies being arranged to abut respective adjacent blades and the brace is arranged to occupy a position centrally of the two bodies. The brace is mounted to the disc and each body and the brace are arranged to engage one another to form an airwash surface. The airwash surface improves aerodynamic flow of air entering the gas turbine engine.

Abstract translation: 一种用于燃气涡轮发动机的转子组件，转子组件具有支撑多个径向延伸叶片的盘。 叶片在其间限定通道，并且每个通道具有环形填料组件。 环形填料组件包括至少两个主体和支架，每个主体被布置成邻接相应的相邻的叶片，并且所述支架被布置成占据两个主体中心的位置。 支架安装到盘上，并且每个主体和支架被布置成彼此接合以形成空气清洗表面。 喷气表面改善了进入燃气涡轮发动机的空气的空气动力学流量。

公开(公告)号：US20140072426A1

公开(公告)日：2014-03-13

申请号：US13741728

申请日：2013-01-15

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward EVANS

IPC: F01D25/24

CPC classification number: F01D25/24 ,  F01D21/045 ,  F01D25/243 ,  F02K3/06 ,  F05D2250/283 ,  Y02T50/672

Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof.

Abstract translation: 涡轮机壳体组件包括可定位在涡轮机的一个或多个旋转机翼元件的径向外侧的第一壳体元件，位于径向远离第一壳体元件的第二壳体元件。 在第一壳体元件的第一端处，在第一壳体元件的径向近端面和第二壳体元件的径向近端面之间设置有空隙。 第一壳体元件的第一端通过能量吸收元件与第一壳体元件抵靠第二壳体元件的对应的第一端; 包括悬臂。 所述悬臂布置在从所述第一端沿着所述第一壳体元件延伸的区域中; 并且在其中部具有枢转轴线。

公开(公告)号：US20150330247A1

公开(公告)日：2015-11-19

申请号：US14700935

申请日：2015-04-30

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward EVANS ,  Ewan Fergus THOMPSON

IPC: F01D21/04 ,  F01D5/02 ,  F01D25/24

CPC classification number: F01D21/045 ,  F01D5/02 ,  F01D11/12 ,  F01D25/24 ,  F01D25/246 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/14

Abstract: A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element. A hook projects in a generally radially inward direction from the annular casing element and is positioned axially forward of an array of fan blades when the fan containment system is fitted around said fan blades. Tabs protrude from the hook in a generally rearward direction and are spaced circumferentially along the hook. Fasteners connect the fan track liner to the tabs. The fasteners are configured so as to permit movement of the fan track liner towards the annular casing element when the fan track liner is impacted by a released fan blade.

Abstract translation: 一种用于安装在轴向燃气涡轮发动机的轮毂上的径向延伸的风扇叶片阵列周围的风扇容纳系统。 风扇容纳系统包括用于环绕风扇叶片阵列的环形壳体元件。 环形风扇轨道衬套被定位成基本上与环形壳体元件同轴。 钩环从环形壳体元件沿大致径向向内的方向突出，并且当风扇容纳系统围绕所述风扇叶片安装时，其定位在风扇叶片阵列的轴向前方。 突片从钩沿大致向后的方向突出并且沿着钩沿周向间隔开。 紧固件将风扇轨道衬套连接到接头。 紧固件构造成当风扇履带衬板被释放的风扇叶片冲击时允许风扇履带衬板朝向环形壳体元件移动。

公开(公告)号：US20140286765A1

公开(公告)日：2014-09-25

申请号：US14185390

申请日：2014-02-20

Applicant: ROLLS-ROYCE PLC

Inventor： Matthew Ashley Charles HOYLAND ,  Dale Edward EVANS ,  Bijoysri KHAN

IPC: F01D5/28 ,  F01D9/02

CPC classification number: F01D5/282 ,  D03D25/005 ,  F01D9/02 ,  F01D9/041 ,  F01D25/005 ,  F04D29/023 ,  F04D29/542 ,  F05B2280/6003 ,  F05B2280/6013 ,  F05D2300/6034

Abstract: A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibres extending in a generally radial direction and a plurality of second reinforcing fibres extending in generally axial and circumferential directions. The second fibres are interlaced with the first fibres so as to form a more unified and integrated structure, and to prevent the first reinforcing fibres from moving relative to one another.

Abstract translation: 用于燃气涡轮发动机的复合翼型叶片在大致径向方向上跨越轴向和周向延伸的环形管道延伸。 叶片包括沿大致径向延伸的多个第一增强纤维和沿大致轴向和圆周方向延伸的多个第二增强纤维。 第二纤维与第一纤维交织以形成更统一且一体化的结构，并且防止第一增强纤维相对于彼此移动。

公开(公告)号：US20130136577A1

公开(公告)日：2013-05-30

申请号：US13658244

申请日：2012-10-23

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward EVANS

IPC: F01D25/26

CPC classification number: F01D21/045 ,  F04D27/0292 ,  F04D29/526 ,  Y02T50/672

Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine and a second casing element located radially distal to the first casing element, with a void being defined between the first and second casing elements. Each of the first and second casing elements includes, at a first end thereof, respective co-operating first and second interface portions. In the event that an aerofoil element becomes detached from the turbomachine and impacts the first casing element, the second interface portion; slides along the first interface portion and the first end of the first casing element enters the void.

Abstract translation: 涡轮机壳体组件包括可定位在涡轮机的一个或多个旋转机翼元件的径向外侧的第一壳体元件和位于第一壳体元件的径向远侧的第二壳体元件，在第一和第二壳体元件之间限定空隙。 第一和第二壳体元件中的每一个在其第一端处包括相应的协作的第一和第二接口部分。 在机翼元件从涡轮机分离并撞击第一壳体元件的情况下，第二接口部分; 沿着第一界面部分滑动并且第一壳体元件的第一端进入空隙。

公开(公告)号：US20160097300A1

公开(公告)日：2016-04-07

申请号：US14855723

申请日：2015-09-16

Applicant: ROLLS-ROYCE plc

Inventor： Dale Edward EVANS

IPC: F01D21/04 ,  F01D25/24

CPC classification number: F01D21/045 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/36

Abstract: A fan track liner assembly for ducted fan engine which provides for reduced strain and deformation of front of fan case in the event of a fan blade off event. Various assemblies are proposed. In one aspect, assembly includes fan track liner panel and plurality of fasteners which are arranged to secure panel to fan case of engine, wherein: a forward portion of panel includes hinged portion which operates as trapdoor to permit blade or blade fragment to pass through, and fasteners are arranged to fail in the event of blade or blade fragment passing through trapdoor causing panel to be displaced rearwards in fan case. Other aspects provide for reduced height of support on fan case for attaching fan track liner and for collapsible comb box.

Abstract translation: 用于管道风扇发动机的风扇轨道衬套组件，其在风扇叶片关闭事件的情况下提供风扇壳体前部的应变和变形。 提出了各种装配。 在一个方面，组件包括风扇轨道衬垫面板和多个紧固件，其被布置成将面板固定到发动机的风扇壳体上，其中：面板的前部部分包括铰接部分，其操作作为门板以允许叶片或叶片片段通过， 并且紧固件被布置成在叶片或叶片碎片通过引导门导致面板在风扇壳体中向后移位的情况下失效。 其他方面提供了用于附接风扇履带板和用于可折叠梳子箱的风扇壳体上的支撑架的高度减小。

公开(公告)号：US20160097299A1

公开(公告)日：2016-04-07

申请号：US14846323

申请日：2015-09-04

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward EVANS

IPC: F01D21/04 ,  F01D25/24

CPC classification number: F01D21/045 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/36 ,  F05D2230/60 ,  Y02T50/672

Abstract: A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa.

Abstract translation: 一种用于管道风扇发动机的风扇轨道衬套组件，其易于安装和更换。 组件包括多个面板; 以及多个紧固构件，其被布置成将所述面板固定到所述发动机的风扇壳体，其中：每个紧固构件具有基部和细长臂构件，并且其中：所述基部具有使用的附接部分 将紧固构件固定到风扇壳体上; 并且臂构件从基部延伸，并且每个面板在面板的一端处的相对边缘上具有开槽边缘部分，每个面板布置成当面板组装时与面板的任一侧上的紧固构件的相应臂构件接合 其中紧固构件通过将面板滑动到紧固构件上，反之亦然。

公开(公告)号：US20130216364A1

公开(公告)日：2013-08-22

申请号：US13765943

申请日：2013-02-13

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward EVANS

IPC: F04D29/40

CPC classification number: F04D29/40 ,  B64D29/00 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/04 ,  F04D29/526 ,  F05D2220/36 ,  F05D2230/53 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/171 ,  F05D2300/603 ,  Y02T50/672

Abstract: An aircraft propulsion system has an engine assembly having an axis of rotation, a fan assembly operatively connected to the engine assembly and comprising a plurality of fan blades arranged circumferentially around the axis of rotation and a monolithic nacelle assembly which circumferentially encloses the fan assembly. The propulsion system has a ratio of fan assembly outer diameter to nacelle assembly outer diameter of at least 0.87. As a result, the propulsion system provides for a significantly larger fan assembly outer diameter for a given nacelle assembly outer diameter than a conventional prior art turbofan engine, thereby increasing the specific power output or the bypass ratio of the propulsion system, which will result in improved propulsive efficiency without an increase in nacelle drag.

Abstract translation: 飞行器推进系统具有具有旋转轴线的发动机组件，可操作地连接到发动机组件的风扇组件，并且包括围绕旋转轴线周向布置的多个风扇叶片和沿周向包围风扇组件的整体式机舱组件。 推进系统的风扇组件外径与机舱组件外径之比至少为0.87。 因此，推进系统为传统的现有技术的涡扇发动机提供给定的机舱组件外径的显着更大的风扇组件外径，从而增加推进系统的比功率输出或旁路比，这将导致 提高推进效率，而不增加机舱阻力。

公开(公告)号：US20160003101A1

公开(公告)日：2016-01-07

申请号：US14729631

申请日：2015-06-03

Applicant: ROLLS-ROYCE PLC

Inventor： Ian Colin Deuchar CARE ,  Dale Edward EVANS

IPC: F01D25/24

CPC classification number: F01D25/24 ,  F01D25/28 ,  F02K9/34 ,  F05D2220/32 ,  F05D2240/14 ,  F05D2250/184 ,  F05D2300/603 ,  F05D2300/6034

Abstract: A composite casing comprising a barrel and a stiffening ring provided around the barrel. The stiffening ring includes a section having a waved profile in a circumferential direction.

Abstract translation: 一种复合壳体，包括围绕筒体设置的筒体和加强环。 加强环包括在圆周方向上具有波形轮廓的部分。

公开(公告)号：US20150275695A1

公开(公告)日：2015-10-01

申请号：US14657601

申请日：2015-03-13

Applicant: ROLLS-ROYCE PLC

Inventor： Dale Edward EVANS ,  David Laker CHRISTMAS

IPC: F01D25/26 ,  F01D25/28 ,  F01D25/24

CPC classification number: F01D25/26 ,  F01D21/045 ,  F01D25/243 ,  F01D25/28 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/51 ,  F05D2230/60 ,  F05D2260/311

Abstract: A turbomachine casing assembly including an inner casing element for arrangement radially outward of a turbomachine fan; an outer casing element for arrangement radially further outward of the turbomachine fan; a retaining lip arranged radially inward of a portion of the inner casing element; and a separator extending between the inner and outer casing elements and arranged to urge a portion of the inner casing element against the lip. The separator is arranged in compression between the inner and outer casing elements to urge the portion of the inner casing element against the lip. The separator is arranged to engage a frangible region of the inner casing element such that the frangible region is configured to break in response to an impact satisfying predetermined conditions, allowing the inner casing element to displace radially outwards exposing features to improve retention of a released fan blade.

Abstract translation: 一种涡轮机壳体组件，包括用于布置在涡轮机风扇的径向外侧的内壳体元件; 用于在所述涡轮机风扇的径向外侧配置的外壳元件; 保持唇缘，其设置在所述内壳体元件的一部分的径向内侧; 以及分隔件，其在所述内壳体元件和外壳体元件之间延伸并且被布置成将所述内壳元件的一部分推靠在所述唇缘上。 分离器被布置在内外壳元件之间的压缩中，以将内壳元件的一部分推靠在唇缘上。 分隔件布置成接合内壳体元件的易碎区域，使得易碎区域被构造成响应于满足预定条件的冲击而断裂，允许内壳体元件径向向外移动曝光特征以改善释放风扇的保持 刀。