公开(公告)号：US20130101434A1

公开(公告)日：2013-04-25

申请号：US13653780

申请日：2012-10-17

Applicant: ROLLS-ROYCE PLC

Inventor： Kenneth Franklin UDALL ,  Kenneth John MACKIE

IPC: F04D29/00

CPC classification number: B64C11/06 ,  B64D2027/005 ,  F01D5/3023 ,  F05D2260/94 ,  Y02T50/66

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

Abstract translation: 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的叶根的支撑杯。 支撑杯通过桥接结构相互连接。 每个桥接结构包括从桥接网径向延伸的桥接壁。 桥接结构因此具有通道形横截面。 桥接壁在其径向外边缘处具有扇形构造。 作为这种构造的结果，桥接结构的中性轴线是直的，使得支撑环在结构上表现为多边形。

公开(公告)号：US20160167797A1

公开(公告)日：2016-06-16

申请号：US14543402

申请日：2014-11-17

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Geoffrey STRETTON ,  Kenneth Franklin UDALL

IPC: B64D27/26 ,  B64D27/10 ,  F02C7/20

CPC classification number: B64D27/26 ,  B64D27/10 ,  B64D2027/262 ,  F02C7/20 ,  F05D2220/325 ,  F05D2250/11

Abstract: A mounting system is arranged in use for attaching a gas turbine engine to a pylon of an aircraft. The mounting system comprises a first frame of three elongate members arranged in a triangle. The first frame is arranged in use such that a core of the gas turbine engine is positioned extending through the area defined between the three elongate members. The first frame forms at least part of a load bearing connection between the pylon and gas turbine engine. The first frame consists of two portions, one corresponding to each side of the gas turbine engine when attached to the pylon. The triangle is symmetrical about a plane separating the two portions of the first frame.

Abstract translation: 安装系统被布置成用于将燃气涡轮发动机附接到飞机的塔架。 安装系统包括布置成三角形的三个细长构件的第一框架。 第一框架布置在使用中，使得燃气涡轮发动机的芯线定位成延伸穿过限定在三个细长构件之间的区域。 第一框架形成塔架和燃气涡轮发动机之间的承载连接的至少一部分。 第一框架由两部分组成，一部分与燃气涡轮发动机的每一侧对应，当连接到塔架上时。 三角形关于分开第一框架的两个部分的平面是对称的。

公开(公告)号：US20150069176A1

公开(公告)日：2015-03-12

申请号：US14474760

申请日：2014-09-02

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Geoffrey STRETTON ,  Kenneth Franklin UDALL

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/262 ,  B64D2027/266

Abstract: An engine mount, for mounting the casing of an aircraft engine to the fuselage or wing of an aircraft, e.g. via a pylon, including first and second links having connector formations for connection to respective mounting and support formations on the engine casing and aircraft mounting structure. Each of the first and second links is typically connected by a pin between the mounting and support formations. Each link has a further connector formation arranged such that the connector formation of the first link is offset from the connector formation of the second link. The connector formations are joined by an intermediate link. 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 may also provide a failsafe catcher arrangement in the event that the first or second link fail.

Abstract translation: 用于将飞机发动机的壳体安装到飞行器的机身或机翼上的发动机支架，例如 通过一个塔架，包括具有连接器结构的第一和第二连杆，用于连接到发动机壳体上的相应安装和支撑结构以及飞行器安装结构。 第一和第二连杆中的每一个通常通过销在安装和支撑结构之间连接。 每个连杆具有进一步的连接器形成，其布置成使得第一连杆的连接器形成从第二连杆的连接器形式偏移。 连接器结构通过中间链接连接。 该安装件允许以这样的方式解决横向力和扭矩，以便基本上避免发动机远离中心平面的横向位移。 在第一或第二链路故障的情况下，中间链路还可以提供故障保护捕获器装置。

公开(公告)号：US20140314577A1

公开(公告)日：2014-10-23

申请号：US14176646

申请日：2014-02-10

Applicant: ROLLS-ROYCE PLC

Inventor： Kenneth Franklin UDALL ,  David Michael BEAVEN ,  Mark John HOULE

IPC: B64C11/04

CPC classification number: B64C11/04 ,  B64C11/26

Abstract: A propeller blade retention arrangement having a propeller blade comprising in radial sequence an aerofoil portion, a shank portion and a root portion. The root portion having first cross-sectional area close to the shank portion and second cross-sectional area at the end distal to the aerofoil portion, wherein the second cross-sectional area is greater than the first cross-sectional area. At least two cheeks each having an inner surface arranged to abut the root portion, an outer surface that is threaded and edge surfaces that abut another of the at least two cheeks; wherein the at least two cheeks are arranged to surround the root portion in circumferential abutment. A collar having a threaded inner surface arranged to threadingly engage the outer surfaces of the at least two cheeks.

Abstract translation: 一种具有螺旋桨叶片的螺旋桨叶片保持装置，其具有径向顺序地包括机翼部分，柄部分和根部分。 所述根部具有接近所述柄部的第一横截面面积和在所述机翼部分远端的一端的第二横截面积，其中所述第二横截面面积大于所述第一横截面面积。 每个具有布置成邻接根部的内表面的至少两个脸颊，具有螺纹的外表面和与所述至少两个脸颊中的另一个相邻的边缘表面; 其中所述至少两个脸颊被布置成围绕所述根部部分周向邻接。 具有螺纹内表面的套环，布置成与所述至少两个脸颊的外表面螺纹接合。

公开(公告)号：US20130343896A1

公开(公告)日：2013-12-26

申请号：US13914961

申请日：2013-06-11

Applicant: ROLLS-ROYCE PLC

Inventor： Kenneth John MACKIE ,  Kenneth Franklin UDALL

IPC: B64C11/08

CPC classification number: B64C11/08 ,  B64C11/06 ,  B64D2027/005 ,  F01D5/3023 ,  Y02T50/66

Abstract: This invention relates to a blade assembly comprising: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device which comprises an annular catcher having a restriction through which the root portion cannot radially pass, the restriction being located radially outwardly and radially spaced from the root part during use.

Abstract translation: 本发明涉及一种叶片组件，其包括：可围绕轴线旋转的轮毂; 至少一个叶片具有机翼部分和根部，其中所述根部使用主保持装置联接到所述轮毂，所述主保持装置在正常使用中防止所述根部和轮毂的径向分离; 以及第二保持装置，其包括环形捕集器，所述环形捕集器具有根部不能径向通过的限制，所述限制件在使用期间径向向外定位并与根部部分径向间隔开。