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公开(公告)号：US09677570B2
公开(公告)日：2017-06-13
申请号：US14523336
申请日：2014-10-24
Applicant: ROLLS-ROYCE PLC
Inventor： Ian Colin Deuchar Care , Cedric Brett Harper
CPC classification number: F04D29/526 , F01D21/045 , F01D25/24 , F02C7/05 , F04D19/002 , F05D2220/36 , Y02T50/671
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 a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element. The fan containment system further includes an annular fan track liner comprising a plurality of adjacent arcuate fan track liner panels. Each of the plurality of fan track liner panels is connected to the fan case at the hook via one or more fasteners configured to permit movement of the fan track liner panel relative to the hook such that the fan track liner panel can pivot towards the annular casing element when a released fan blade impacts the fan track liner panel.
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公开(公告)号：US09850764B2
公开(公告)日：2017-12-26
申请号：US14613744
申请日：2015-02-04
Applicant: ROLLS-ROYCE PLC
Inventor： Ian Colin Deuchar Care , Stephane Baralon
CPC classification number: F01D5/20 , B23P15/04 , F01D5/147 , F01D5/282 , F04D29/023 , F04D29/324 , F05D2210/33 , F05D2220/36 , F05D2240/307 , F05D2300/603 , F05D2300/6032 , F05D2300/612 , F05D2300/614 , Y10T29/49337 , Y10T29/49339
Abstract: There is provided a blade tip for a rotary blade. The blade tip is formed of a metal foam and comprises at least one vortex generator. The vortex generator may comprise at least one passageway and/or cavity in the blade tip. In use, a vortex is created between the blade tip and a fan casing adjacent the blade tip.
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公开(公告)号：US09228444B2
公开(公告)日：2016-01-05
申请号：US13666613
申请日：2012-11-01
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans , Ian Colin Deuchar Care
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。
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公开(公告)号：US09222368B2
公开(公告)日：2015-12-29
申请号：US13741656
申请日：2013-01-15
Applicant: ROLLS-ROYCE PLC
Inventor： Cedric Brett Harper , Ian Colin Deuchar Care
CPC classification number: F01D25/24 , F01D21/045 , F01D25/243 , F02K3/06 , F05D2250/283 , Y02T50/672
Abstract: A turbomaehine casing assembly includes a first casing element, located radially outward of one or more rotating aerofoil elements of a turbomachine, and a second casing element, located radially distal to the first element. A void is provided at a first end of the first element, between radially proximal faces of the first and second elements. The first end of the first element is located against a corresponding first end of the second element by an energy absorbing element. The first element includes a cantilever, arranged in a region extending along the first element from the first end with a pivot axis at its mid-portion. Release of one of the rotating aerofoil elements, resulting in impact with the first element, further results in the cantilever bending into the void between the first and second elements, enabling the rotating aerofoil element to be trapped within the casing assembly.
Abstract translation: 涡轮机壳体组件包括位于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元件的径向远侧的第二壳体元件。 在第一元件的第一端处，在第一和第二元件的径向近端面之间设置有空隙。 第一元件的第一端通过能量吸收元件抵靠第二元件的对应的第一端。 第一元件包括悬臂，布置在沿着第一元件从第一端延伸的区域中，其中部具有枢转轴线。 旋转的机翼元件中的一个的释放导致与第一元件的冲击，进一步导致悬臂弯曲到第一和第二元件之间的空隙中，使得旋转的机翼元件被捕获在壳体组件内。
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公开(公告)号：US08821119B2
公开(公告)日：2014-09-02
申请号：US13799730
申请日：2013-03-13
Applicant: Rolls-Royce PLC
Inventor： Peter Rowland Beckford , Simon Read , Ian Colin Deuchar Care
CPC classification number: F01D5/147 , F01D5/14 , F01D21/045 , F05D2300/612
Abstract: A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former includes a zone of weakness, which reduces the ability of the root part to withstand an impact force. Thus, in an impact situation in which the fan blade has separated from the fan rotor and the fan blade has itself separated into fragments, the root part will fracture or buckle more easily than would be the case with conventional arrangements. This will lower the impact force of the root part upon the fan casing, thus permitting the fan casing to be designed to withstand lower impact forces. The fan casing can therefore be made lighter, and cheaper, than in conventional arrangements.
Abstract translation: 用于燃气涡轮发动机的风扇叶片具有机翼部分和根部部分。 根部包括根部; 根部部分包括一个弱点，这降低了根部抵抗冲击力的能力。 因此，在风扇叶片与风扇转子分离并且风扇叶片本身分离成碎片的冲击情况下，根部将比常规布置的情况更容易断裂或弯曲。 这将降低根部对风扇壳体的冲击力，从而允许风扇壳体设计成承受较低的冲击力。 因此，风扇壳体可以比常规布置更轻，更便宜。
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Patent Agency Ranking
公开(公告)号：US20140064949A1
公开(公告)日：2014-03-06
申请号：US13741842
申请日：2013-01-15
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans , Ian Colin Deuchar Care
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 and 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. Release of one of the rotating aerofoil elements results in the element, or part thereof, impacting the first casing element which results in the cantilever bending into the void provided between the first and second casing elements.
Abstract translation: 涡轮机壳体组件包括位于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径向远侧的第二壳体元件。 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。 旋转机翼元件之一的释放导致元件或其一部分冲击第一壳体元件，导致悬臂弯曲到设置在第一和第二壳体元件之间的空隙中。
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公开(公告)号：US09803648B2
公开(公告)日：2017-10-31
申请号：US14481107
申请日：2014-09-09
Applicant: ROLLS-ROYCE PLC
Inventor： Ian Colin Deuchar Care , Matthew Paul Jevons
CPC classification number: F04D29/34 , F01D5/3015 , F01D5/3092 , F01D5/323 , F04D19/002 , F05D2250/283 , F05D2260/80 , F05D2300/603 , F05D2300/612 , Y02T50/672
Abstract: A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is a unitary component and has a layered structure including a first layer at the first side of the plate, a second layer at the second side of the plate, and an intermediate layer between the first and the second layers.
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公开(公告)号：US09701584B2
公开(公告)日：2017-07-11
申请号：US14132754
申请日：2013-12-18
Applicant: ROLLS-ROYCE PLC
Inventor： Ian Colin Deuchar Care , Daniel Clark
CPC classification number: B22F3/15 , B22F1/0003 , B22F3/003 , B22F3/004 , B22F5/009 , B22F2003/153 , B22F2301/15 , B22F2301/205 , B22F2998/10 , B28B1/001 , C04B35/01 , C04B35/6455 , C04B2235/5472 , F01D25/24 , F05D2230/22 , F05D2230/31
Abstract: An apparatus for manufacturing an article from powder material includes a canister, a sorter, a plurality of hoppers and at least one valve. The canister has a predetermined internal shape to define the shape of the powder metal article. The sorter sorts the powder material by the size of the powder particles, the shape of the powder particles and/or the flow characteristics of the powder particles. The hoppers contain powder material with different sizes of powder particles, different shapes of powder particles and/or powder particles with different flow characteristics. The hoppers are arranged to supply the sorted powder material to the canister. The at least one valve controls the proportions of the different powder materials supplied from the one or more of the different hoppers into the canister to control the packing density of the powder material in the canister at all positions in the canister.
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公开(公告)号：US20130236320A1
公开(公告)日：2013-09-12
申请号：US13799730
申请日：2013-03-13
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Rowland Beckford , Simon Read , Ian Colin Deuchar Care
IPC: F01D5/14
CPC classification number: F01D5/147 , F01D5/14 , F01D21/045 , F05D2300/612
Abstract: A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former includes a zone of weakness, which reduces the ability of the root part to withstand an impact force. Thus, in an impact situation in which the fan blade has separated from the fan rotor and the fan blade has itself separated into fragments, the root part will fracture or buckle more easily than would be the case with conventional arrangements. This will lower the impact force of the root part upon the fan casing, thus permitting the fan casing to be designed to withstand lower impact forces. The fan casing can therefore be made lighter, and cheaper, than in conventional arrangements.
Abstract translation: 用于燃气涡轮发动机的风扇叶片具有机翼部分和根部部分。 根部包括根部; 根部部分包括一个弱点，这降低了根部抵抗冲击力的能力。 因此，在风扇叶片与风扇转子分离并且风扇叶片本身分离成碎片的冲击情况下，根部将比常规布置的情况更容易断裂或弯曲。 这将降低根部对风扇壳体的冲击力，从而允许风扇壳体设计成承受较低的冲击力。 因此，风扇壳体可以比常规布置更轻，更便宜。
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公开(公告)号：US09683490B2
公开(公告)日：2017-06-20
申请号：US14529810
申请日：2014-10-31
Applicant: ROLLS-ROYCE PLC
Inventor： Cedric Brett Harper , Ian Colin Deuchar Care , Julian Mark Reed
CPC classification number: F02C7/05 , F01D11/122 , F01D21/04 , F01D21/045 , F01D21/10 , F01D25/246 , F02K3/06 , F05D2220/36
Abstract: A fan containment system includes an annular casing element and a hook projecting in a generally radially inward direction from the annular casing element. A fan track liner is connected to the hook via a fastener. The fan track liner has a forward end proximal to the hook and a rearward end distal to the hook. A pivot member protrudes radially inward from the annular casing element and is arranged and positioned between the forward and rearward end of the fan track liner such that a forward portion of the fan track liner is pivotable about the pivot member, so that upon release of a fan blade the forward portion of the fan track liner pivots about the pivot member into a voidal region provided between the annular casing element and the forward portion of the fan track liner to encourage engagement of the hook with a released fan blade.
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