公开(公告)号：EP1462642A1

公开(公告)日：2004-09-29

申请号：EP04251208.7

申请日：2004-03-02

申请人： ROLLS-ROYCE PLC ,  The Boeing Company

发明人： Beardsley, Peter ,  Parham, Dean

IPC分类号： F02K1/70 ,  F02K1/62

CPC分类号： F02K1/70 ,  F02K1/62

摘要： A thrust reverser having an engine cowl, a nacelle, a blocker door, a nacelle door and a cascade vane. The engine cowl has a hollow body that shrouds a jet engine and which includes a cowl opening. The nacelle surrounds the engine cowl and includes a nacelle opening that is positioned outwardly of the cowl opening. The blocker door is associated with the engine cowl and movable between a first position, wherein the blocker door closes the cowl opening, and a second position, wherein the blocker door is disposed in the propulsive air flow and substantially clears the cowl opening. The nacelle door is associated with the nacelle and movable between a forward position, which substantially closes the nacelle opening, and a rearward position, which substantially clears the nacelle opening. The cascade vane is disposed between the engine cowl and the nacelle and positioned between the cowl and nacelle openings.

摘要翻译： 推力反向器具有发动机罩，机舱，阻挡门，机舱门和级联叶片。 发动机罩具有中空体，其包围喷气发动机并且其包括罩盖开口。 机舱围绕发动机罩，并且包括位于罩盖开口外侧的机舱开口。 阻挡门与发动机整流罩相关联并且可在第一位置和第二位置之间移动，在第一位置和第二位置之间，其中阻挡门关闭整流罩开口，第二位置处于阻止门被设置在推进空气流中并基本上清除整流罩开口。 机舱门与机舱相关联，并且可在基本上关闭机舱开口的前部位置和基本上清除机舱开口的后方位置之间移动。 级联叶片设置在发动机罩和机舱之间并且位于前罩和机舱开口之间。

公开(公告)号：EP2551506A3

公开(公告)日：2017-04-05

申请号：EP12176501.0

申请日：2012-07-16

申请人： Rolls-Royce plc

发明人： Beardsley, Peter ,  Bolgar, Crispin

IPC分类号： F02K1/72 ,  F02K1/09 ,  F02K3/075

CPC分类号： F02K1/72 ,  F02K1/09 ,  F02K3/075 ,  Y02T50/671

摘要： A ducted fan gas turbine assembly has a thrust reverser assembly having a vane arrangement including a first set of turning vanes (37) for channelling airflow from the duct in a rearward direction and a second set of turning vanes (38) for channelling airflow from the bypass duct (30) in a forward direction. The thrust reverser assembly further has a plurality of blocker doors (41) which are deployable to block the bypass duct (30). The nacelle has a stationary cowl portion (32) and a movable cowl portion (33) which is translatable rearwardly relative to the stationary cowl portion (32) to open an annular gap (43) therebetween. The cowl portions (32, 33) cooperate with the thrust reverser assembly to provide three operational configurations. In the first operational configuration the gap (43) between the cowl portions (32, 33) is closed and the vane arrangement is stowed in the nacelle to prevent airflow from the duct (30) flowing therethrough. In the second operational configuration the first set of turning vanes (37) is positioned in the gap (43) opened between the cowl portions (32, 33) to form an annular secondary discharge nozzle from the bypass duct (30) for the duct airflow. In the third operational configuration the blocker doors (41) are deployed and the second set of turning vanes (38) is positioned in the gap (43) opened between the cowl portions (32, 33) to divert the duct airflow through the second set of turning vanes (38) and provide reverse thrust.

摘要翻译： 管道式风扇燃气轮机组件具有推力反向器组件，该推力反向器组件具有叶片装置，该叶片装置包括第一组转向叶片（37），用于沿向后方向引导来自管道的气流;以及第二组转向叶片（38），用于将来自 旁路管道（30）。 推力反向器组件还具有可展开以阻挡旁路管道（30）的多个阻挡门（41）。 机舱具有固定的前围部分（32）和可移动的整流罩部分（33），其可相对于静止的整流罩部分（32）向后平移以在其间打开环形间隙（43）。 整流罩部分（32,33）与推力反向器组件配合以提供三种操作构型。 在第一操作构造中，前围部分（32,33）之间的间隙（43）被关闭，并且叶片装置被收纳在机舱中，以防止流经管道30的气流。 在第二操作构造中，第一组转动叶片（37）定位在在前围部分（32,33）之间打开的间隙（43）中，以形成来自旁路管道（30）的环形二次排放喷嘴，用于管道气流 。 在第三操作构型中，阻挡门（41）展开，并且第二组转向叶片（38）位于在前围部分（32,33）之间打开的间隙（43）中，以将管道气流转过第二组 的转向叶片（38）并提供反向推力。

公开(公告)号：EP1479889B1

公开(公告)日：2006-05-17

申请号：EP04252567.5

申请日：2004-04-30

申请人： ROLLS-ROYCE PLC

发明人： Stretton, Richard, Geoffrey ,  Beardsley, Peter

IPC分类号： F02C7/047 ,  F02C7/12 ,  F02C7/32

CPC分类号： F02C7/12 ,  F02C7/047 ,  F02C7/32 ,  Y02T50/671 ,  Y02T50/675

公开(公告)号：EP3636906A1

公开(公告)日：2020-04-15

申请号：EP19197014.4

申请日：2019-09-12

申请人： Rolls-Royce plc

发明人： Whurr, John ,  Beardsley, Peter ,  Curnock, Philip ,  Mitzalis, Faidon

IPC分类号： F02K1/04 ,  F02K3/06 ,  F02K3/10

摘要： A turbofan engine, an afterburner system, and a method of operating a turbofan engine are provided. The turbofan engine has: an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor, and producing a core exhaust flow; a fan upstream of the engine core; a bypass duct surrounding the engine core and carrying a bypass air flow produced by the fan; an exhaust assembly comprising a first exhaust nozzle defining a downstream end of a first core flow duct which receives the core exhaust flow produced by the engine core. The turbofan engine further has an afterburner system comprising: a core plug defining a radially inner surface of the first core flow duct; a second core flow duct located in the core plug, and having one or more entrances from the first core flow duct for diversion into the second core flow duct of a portion of the core exhaust flow, and further having an exit therefrom for re-joining the diverted portion of the core exhaust flow to the undiverted portion of the core exhaust flow; one or more respective doors for the entrances to the second core flow duct, the doors being open during normal operation of the engine but being closable, during a reheat operation, to at least partially block the entrances to the second core flow duct; and one or more fuel injectors and one or more respective igniters operable, during the reheat operation, to respectively inject and ignite fuel within the second core flow duct, thereby providing a reheat flow into the core exhaust flow from the exit of the second core flow duct.

公开(公告)号：EP2562405A1

公开(公告)日：2013-02-27

申请号：EP12174096.3

申请日：2012-06-28

申请人： Rolls-Royce plc

发明人： Beardsley, Peter

IPC分类号： F02K1/72 ,  B64D29/06

CPC分类号： F02K1/72 ,  B64D29/06 ,  B64D33/04 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2260/02

摘要： A turbine engine comprising an engine core bounded by a bypass duct, a first portion of the bypass duct defined by a fan casing having a radially inner wall and a radially outer wall, a second portion of the bypass duct defined by a radially inner wall and a radially outer wall, a third portion of the bypass duct provided as at least one access door comprising a flow guide structure; and a thrust reverser mechanism coupled to the fan casing. The at least one access door being pivotable between an open position and a closed position relative to the thrust reverser mechanism. The flow guide structure having a first panel spaced apart from a second panel such that in a closed position the first panel forms a continuous flow surface with the second portion's radially outer wall and the second panel forms a continuous flow surface with the second portion's radially inner wall and covers a section of the engine core; and in an open position the access door provides access to the engine core.

摘要翻译： 一种涡轮发动机，包括由旁通管道限定的发动机芯，旁路管道的第一部分由具有径向内壁和径向外壁的风扇壳体限定，旁路管道的第二部分由径向内壁限定， 旁路管道的第三部分设置为包括流动引导结构的至少一个进入门; 以及联接到所述风扇壳体的推力反向器机构。 所述至少一个检修门可相对于所述推力反向器机构在打开位置和关闭位置之间枢转。 所述流动引导结构具有与第二面板间隔开的第一面板，使得在关闭位置，所述第一面板与所述第二部分的径向外壁形成连续的流动表面，并且所述第二面板形成具有所述第二部分的径向内部的连续流动表面 墙壁并覆盖发动机芯的一部分; 并且在打开位置，检修门提供对发动机芯的通路。

公开(公告)号：EP1479889A2

公开(公告)日：2004-11-24

申请号：EP04252567.5

申请日：2004-04-30

申请人： ROLLS-ROYCE plc

发明人： Stretton, Richard, Geoffrey ,  Beardsley, Peter

IPC分类号： F02C7/047 ,  F02C7/12 ,  F02C7/32

CPC分类号： F02C7/12 ,  F02C7/047 ,  F02C7/32 ,  Y02T50/671 ,  Y02T50/675

摘要： A gas turbine engine (10) comprising a nacelle (21) having an intake (12), the intake (12) defining a generally annular chamber (35), an engine accessory (33, 34) and a heat exchanger (36) for cooling a fluid of the accessory (33, 34) characterised in that the chamber (35) is closed and the heat exchanger (36) is disposed within the chamber (35) operable to provide heat to prevent ice forming on the intake (12) during engine (10) operation.

摘要翻译： 一种燃气涡轮发动机（10）包括机舱（21），其具有进气（12），进气（12）定义的基因的反弹环形腔室（35）固定到发动机附件（33，34）和用于热交换器（36） 冷却附件的DASS内室的流体（33，34）（35）关闭，在热交换器（36）的腔室（35），其可操作内设置成提供热量，以防止冰在进气形成（12） 发动机（10）运行期间。

公开(公告)号：EP2562405B1

公开(公告)日：2016-08-10

申请号：EP12174096.3

申请日：2012-06-28

申请人： Rolls-Royce plc

发明人： Beardsley, Peter

IPC分类号： F02K1/72 ,  B64D29/06

CPC分类号： F02K1/72 ,  B64D29/06 ,  B64D33/04 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2260/02

公开(公告)号：EP2886841A1

公开(公告)日：2015-06-24

申请号：EP14196868.5

申请日：2014-12-09

申请人： Rolls-Royce plc

发明人： Beardsley, Peter ,  Pons Perez, Marc

IPC分类号： F02K1/06 ,  B64D29/02 ,  F02K3/06

CPC分类号： B64D29/06 ,  B64D33/04 ,  F02K1/06 ,  F02K3/06 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2250/312 ,  F05D2250/90 ,  F05D2260/50

摘要： A gas turbine engine (30) comprising a rear cowl (38) defining an exhaust aperture (40) and a motive system. The rear cowl (38) comprises at least one panel (42) and the motive system is operable to selectively move the panel (42) between deployed and stowed configurations by rotation of the panel (42) about an axis substantially parallel to the main rotational axis of the engine (30). This alters the area of the exhaust aperture (40).

摘要翻译： 一种燃气涡轮发动机（30），包括限定排气孔（40）和动力系统的后罩（38）。 后罩（38）包括至少一个面板（42），并且所述动力系统可操作以通过所述面板（42）围绕基本上平行于所述主旋转的轴旋转来选择性地将所述面板（42）移动在展开和收起的构造之间 发动机（30）的轴线。 这改变了排气孔（40）的面积。

公开(公告)号：EP2551506A2

公开(公告)日：2013-01-30

申请号：EP12176501.0

申请日：2012-07-16

申请人： Rolls-Royce plc

发明人： Beardsley, Peter ,  Bolgar, Crispin

IPC分类号： F02K1/72

CPC分类号： F02K1/72 ,  F02K1/09 ,  F02K3/075 ,  Y02T50/671

摘要： A ducted fan gas turbine assembly has a thrust reverser assembly having a vane arrangement including a first set of turning vanes (37) for channelling airflow from the duct in a rearward direction and a second set of turning vanes (38) for channelling airflow from the bypass duct (30) in a forward direction. The thrust reverser assembly further has a plurality of blocker doors (41) which are deployable to block the bypass duct (30). The nacelle has a stationary cowl portion (32) and a movable cowl portion (33) which is translatable rearwardly relative to the stationary cowl portion (32) to open an annular gap (43) therebetween. The cowl portions (32, 33) cooperate with the thrust reverser assembly to provide three operational configurations. In the first operational configuration the gap (43) between the cowl portions (32, 33) is closed and the vane arrangement is stowed in the nacelle to prevent airflow from the duct (30) flowing therethrough. In the second operational configuration the first set of turning vanes (37) is positioned in the gap (43) opened between the cowl portions (32, 33) to form an annular secondary discharge nozzle from the bypass duct (30) for the duct airflow. In the third operational configuration the blocker doors (41) are deployed and the second set of turning vanes (38) is positioned in the gap (43) opened between the cowl portions (32, 33) to divert the duct airflow through the second set of turning vanes (38) and provide reverse thrust.

公开(公告)号：EP2537755A2

公开(公告)日：2012-12-26

申请号：EP12171446.3

申请日：2012-06-11

申请人： Rolls-Royce plc

发明人： Beardsley, Peter ,  Waldron, Dominic Adam

IPC分类号： B64D29/06

CPC分类号： B64D29/06 ,  B64D27/26 ,  B64D2027/262 ,  B64D2027/264 ,  B64D2027/266 ,  F02C7/20 ,  Y02T50/44

摘要： A mounting assembly for attaching a ducted fan gas turbine engine to an aircraft is provided. The engine has an intake (111), a propulsive fan, a fan case (125) surrounding the fan, and a core engine (126). The air intake (111) is attached to the front of the fan case such that loads acting on the air intake (111) are primarily transmitted to the fan case (125). The mounting assembly includes a support structure (133) extending in an axial direction of the engine and having a rearward region which is adapted to attach to the aircraft. The mounting assembly further includes load distribution ring (135) which is coaxial with and rearward of the fan case (125), the load distribution ring (135) being adapted to join to the fan case (125), and being joined to a forward region of the support structure (133). The support structure (133) and the load distribution ring (135) are adapted such that the primary load path for the loads transmitted to the fan case (125) by the air intake (111) is through the load distribution ring (135) and the support structure (133), and thence to the aircraft.

摘要翻译： 提供了用于将涵道风扇燃气涡轮发动机附接到飞机的安装组件。 发动机具有进气口111，推进风扇，围绕风扇的风扇壳体125和核心发动机126。 吸气口111安装在风扇壳体的前方，作用于吸气口111的负荷主要传递到风扇壳体125。 该安装组件包括支撑结构（133），该支撑结构在发动机的轴向方向上延伸并且具有适于附接到飞机的后部区域。 所述安装组件还包括负载分配环（135），所述负载分配环与所述风扇外壳（125）同轴并位于所述风扇外壳的后方，所述负载分配环（135）适于连接至所述风扇外壳（125），并且与所述风扇外壳 支撑结构（133）的区域。 支撑结构（133）和负载分配环（135）适于使得由进气口（111）传输到风扇壳体（125）的负载的主负载路径通过负载分配环（135），并且 支撑结构（133），然后到飞机。