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公开(公告)号：US09822663B2
公开(公告)日：2017-11-21
申请号：US14596664
申请日：2015-01-14
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans
CPC classification number: F01D25/145 , F01D25/005 , F01D25/243 , F04D29/023 , F04D29/545 , F05D2300/174 , F05D2300/21 , F05D2300/43 , F05D2300/502 , F05D2300/603 , F05D2300/702
Abstract: The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad. The projection comprises at least one shell portion formed of a fiber/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.
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公开(公告)号：US09951645B2
公开(公告)日：2018-04-24
申请号：US14700935
申请日：2015-04-30
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans , Ewan Fergus Thompson
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.
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公开(公告)号：US09598978B2
公开(公告)日：2017-03-21
申请号：US14154671
申请日：2014-01-14
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew Ashley Charles Hoyland , Dale Edward Evans
CPC classification number: F01D21/045 , F02C7/04 , F05D2220/36 , F05D2250/25 , Y02T50/672
Abstract: A fan containment system having a generally cylindrical fan case including a hook projecting in a generally radially inward direction and positioned axially forward of a radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a panel which is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades and forms a substantially continuous air washed surface with the fan track liner. The panel is temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine, without compromising the structural integrity of the panel while being weak enough so that in the event that one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub.
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公开(公告)号：US09243647B2
公开(公告)日：2016-01-26
申请号：US13765943
申请日：2013-02-13
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans
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。
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公开(公告)号：US09206706B2
公开(公告)日：2015-12-08
申请号：US13741728
申请日：2013-01-15
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans
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。
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Patent Agency Ranking
公开(公告)号：US10125631B2
公开(公告)日：2018-11-13
申请号：US14855723
申请日：2015-09-16
Applicant: ROLLS-ROYCE plc
Inventor： Dale Edward Evans
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.
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公开(公告)号：US09957835B2
公开(公告)日：2018-05-01
申请号：US14846323
申请日：2015-09-04
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans
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.
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公开(公告)号：US09670788B2
公开(公告)日：2017-06-06
申请号：US14185390
申请日：2014-02-20
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew Ashley Charles Hoyland , Dale Edward Evans , Bijoysri Khan
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 fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are interlaced with the first fibers so as to form a more unified and integrated structure, and to prevent the first reinforcing fibers from moving relative to one another.
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公开(公告)号：US09085992B2
公开(公告)日：2015-07-21
申请号：US13658244
申请日：2012-10-23
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans
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。
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公开(公告)号：US09810096B2
公开(公告)日：2017-11-07
申请号：US14657601
申请日：2015-03-13
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans , David Laker Christmas
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.
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