公开(公告)号：EP2405115B1

公开(公告)日：2014-08-20

申请号：EP11169228.1

申请日：2011-06-09

申请人： Rolls-Royce plc

发明人： Morgan, Antony

IPC分类号： F02C7/228 ,  F02C7/232 ,  F16K11/20 ,  H03B5/28 ,  H03H11/18

CPC分类号： F02C7/228 ,  F02C7/232 ,  F05D2270/31 ,  H03B5/28 ,  H03H11/18 ,  Y10T137/87113 ,  Y10T137/87129 ,  Y10T137/87249 ,  Y10T137/87981

公开(公告)号：EP2340993A3

公开(公告)日：2013-12-25

申请号：EP10192587.3

申请日：2010-11-25

申请人： Rolls-Royce plc

发明人： Swift, Andrew ,  Morgan, Antony

IPC分类号： B64C11/32

CPC分类号： B64C11/32 ,  Y02T50/66

摘要： A pitch change apparatus is provided for a propeller assembly having a row of propeller blades which rotate around an axis of the assembly. The apparatus comprises a unison ring which is coaxial with the propeller assembly. The unison ring is movable to drive respective mechanisms for varying the pitch of the blades. The apparatus further comprises a plurality of pitch lock assemblies circumferentially distributed around the unison ring. Each pitch lock assembly has a free state which allows movement of the unison ring and a locked state which prevents or limits movement of the unison ring and thus prevents or limits variation of the pitch of the blades. The pitch lock assembly moves from the free to the locked state when the assembly receives a signal to lock the blades.

公开(公告)号：EP2192307A3

公开(公告)日：2013-08-07

申请号：EP09252496.6

申请日：2009-10-28

申请人： Rolls-Royce plc

发明人： Morgan, Antony

IPC分类号： F04D27/02 ,  F04D29/36 ,  B64C11/30 ,  B64C11/38

CPC分类号： F04D27/0246 ,  B64C11/385 ,  B64C11/40 ,  B64D2027/026 ,  F05B2270/1095 ,  F05B2270/301 ,  F05B2270/604 ,  Y02T50/66

摘要： A method of operating a blade pitch change system (59) of a gas turbine engine and its arrangement, the system comprising a blade (23, 24), an actuator (70), a pressurised fluid system (72) and a control system (60) that regulates pressurised fluid to the actuator (70) to control its position and thereby the blade's pitch; the blade pitch change system (59) operates in a forward thrust mode and a reverse thrust mode, the control system (60) comprises a main pitch control valve (64) and a first reverse blade control valve (66) through which the pressurised fluid passes. The method comprises the steps of a) continuously varying the main control valve (64) to change the blade's pitch within the forward thrust mode at a first rotational rate, b) switching the first reverse blade control valve (66) on to change the blades' pitch between the forward thrust mode and the reverse thrust mode at a second rotational rate that is greater than the first rotational rate.

公开(公告)号：EP2384965A2

公开(公告)日：2011-11-09

申请号：EP11162477.1

申请日：2011-04-14

申请人： Rolls-Royce plc

发明人： Morgan, Antony

IPC分类号： B64C11/32

CPC分类号： B64C11/325 ,  B64D2027/026 ,  Y02T50/66

摘要： A back-up featherer is provided for an engine arrangement. The engine arrangement has a main hydraulic actuator (63b) which operates a pitch change mechanism to angularly displace propellers (62a) of a propeller assembly of the engine arrangement, the pitch change mechanism and main hydraulic actuator (63b) rotating with the propeller assembly. The back-up featherer has one or more brakes (80) located on a static structure of the engine arrangement. The back-up featherer further has one or more input gears (82) rotatable about respective axes, which axes rotate with the propeller assembly. The input gears (82) are operatively connected to the brakes (80) such that, when the brakes (80) are activated, the input gears (82) rotate about their axes. The back-up featherer further has one or more load application members (81) which rotate with the propeller assembly and which are operatively connected to the input gears (82) such that, when the input gears (82) rotate about their axes, the load application members (81) bear against respective engagement portions of the pitch change mechanism. This applies a load to the pitch change mechanism which results in angular displacement of the propellers.

摘要翻译： 为发动机装置提供备用功能。 发动机装置具有主液压致动器（63b），该主液压致动器操作变桨机构以使发动机装置的螺旋桨组件的螺旋桨（62a），螺距改变机构和主液压致动器（63b）与螺旋桨组件一起旋转。 备用飞行器具有位于发动机装置的静态结构上的一个或多个制动器（80）。 备用飞行器还具有一个或多个输入齿轮（82），所述输入齿轮可围绕相应的轴线旋转，所述轴线与螺旋桨组件一起旋转。 输入齿轮（82）可操作地连接到制动器（80），使得当制动器（80）被激活时，输入齿轮（82）围绕它们的轴线旋转。 备用飞行器还具有一个或多个与螺旋桨组件一起旋转的负载施加构件（81），其可操作地连接到输入齿轮（82），使得当输入齿轮（82）围绕它们的轴线旋转时， 载荷施加构件（81）抵靠在间距改变机构的相应接合部分上。 这将负载施加到导致螺旋桨的角位移的变桨机构上。

公开(公告)号：EP2384966A3

公开(公告)日：2017-01-11

申请号：EP11162479.7

申请日：2011-04-14

申请人： Rolls-Royce plc

发明人： Morgan, Antony

IPC分类号： B64C11/32

CPC分类号： B64C11/32 ,  B64D2027/026

摘要： A pitch control mechanism is provided for angular displacement of propellers of a propeller assembly of an engine arrangement. The pitch control mechanism has an epicyclic gear system rotating with the propeller assembly. The epicyclic gear system comprises a sun gear (18), one or more planet gears (19) engaging the sun gear (18), a ring gear (20) engaging the planet gears, and a planet carrier carrying the planet gears. One of the sun gear (18), the ring gear (20) and the planet carrier is a first input to the epicyclic gear system. Another of the sun gear (18), the ring gear (19) and the planet carrier is a second input to the epicyclic gear system. The last of the sun gear (18), the ring gear (19) and the planet carrier is an output from the epicyclic gear system. The pitch control mechanism further has a drive gear located on a static structure of the engine arrangement, and controlling the rotational speed of the first epicyclic input in the rotating frame of reference of the propeller assembly. The pitch control mechanism further has a control gear (32) located on a static structure of the engine arrangement, and controlling the rotational speed of the second epicyclic input in the rotating frame of reference of the propeller assembly. The pitch control mechanism further has a drive mechanism (31) rotating with the propeller assembly. The drive mechanism (31) accepts rotary motion from the epicyclic output to deliver an output motion which angularly displaces the propellers (22a,22b) of the propeller assembly. Varying a rotation of at least one of the drive gear (31) and the control gear (32) varies the direction of rotation of the epicyclic output. This changes the output motion delivered by the drive mechanism to control the angular displacement of the propellers of the propeller assembly.

摘要翻译： 提供了一种俯仰控制机构，用于发动机装置的螺旋桨组件的螺旋桨的角位移。 桨距控制机构具有与螺旋桨组件一起旋转的行星齿轮系。 行星齿轮系统包括太阳齿轮（18），与太阳轮（18）接合的一个或多个行星齿轮（19），接合行星齿轮的环形齿轮（20）和承载行星齿轮的行星架。 太阳齿轮（18），齿圈（20）和行星架中的一个是行星齿轮系的第一输入。 太阳齿轮（18），齿圈（19）和行星架中的另一个是行星齿轮系统的第二输入。 太阳齿轮（18）中的最后一个，环形齿轮（19）和行星架是行星齿轮系统的输出。 俯仰控制机构还具有位于发动机装置的静态结构上的驱动齿轮，并且控制螺旋桨组件的旋转参考系中的第一行星输入的旋转速度。 俯仰控制机构还具有位于发动机装置的静态结构上的控制齿轮（32），并控制螺旋桨组件旋转参考系的第二行星输入的旋转速度。 俯仰控制机构还具有与螺旋桨组件一起旋转的驱动机构（31）。 驱动机构（31）接受来自行星式输出的旋转运动，以输送对螺旋桨组件的螺旋桨（22a，22b）进行角度位移的输出运动。 改变驱动齿轮（31）和控制齿轮（32）中的至少一个的旋转改变了周波输出的旋转方向。 这改变了由驱动机构传递的输出运动，以控制螺旋桨组件的螺旋桨的角位移。

公开(公告)号：EP2384967B1

公开(公告)日：2016-08-31

申请号：EP11162472.2

申请日：2011-04-14

申请人： Rolls-Royce plc

发明人： Swift, Andrew ,  Morgan, Antony ,  Simms, Paul

IPC分类号： B64C11/38 ,  B64D27/20

CPC分类号： B64C11/385 ,  B64D2027/026 ,  Y02T50/66

公开(公告)号：EP2384965A3

公开(公告)日：2016-06-22

申请号：EP11162477.1

申请日：2011-04-14

申请人： Rolls-Royce plc

发明人： Morgan, Antony

IPC分类号： B64C11/32

CPC分类号： B64C11/325 ,  B64D2027/026 ,  Y02T50/66

摘要： A back-up featherer is provided for an engine arrangement. The engine arrangement has a main hydraulic actuator (63b) which operates a pitch change mechanism to angularly displace propellers (62a) of a propeller assembly of the engine arrangement, the pitch change mechanism and main hydraulic actuator (63b) rotating with the propeller assembly. The back-up featherer has one or more brakes (80) located on a static structure of the engine arrangement. The back-up featherer further has one or more input gears (82) rotatable about respective axes, which axes rotate with the propeller assembly. The input gears (82) are operatively connected to the brakes (80) such that, when the brakes (80) are activated, the input gears (82) rotate about their axes. The back-up featherer further has one or more load application members (81) which rotate with the propeller assembly and which are operatively connected to the input gears (82) such that, when the input gears (82) rotate about their axes, the load application members (81) bear against respective engagement portions of the pitch change mechanism. This applies a load to the pitch change mechanism which results in angular displacement of the propellers.

公开(公告)号：EP2384968A3

公开(公告)日：2015-12-16

申请号：EP11162473.0

申请日：2011-04-14

申请人： Rolls-Royce plc

发明人： Swift, Andrew ,  Morgan, Antony

IPC分类号： B64C11/38

CPC分类号： B64C11/385 ,  B64D2027/026 ,  Y02T50/66

摘要： A pitch control mechanism for controlling the pitch of propellers of a propeller assembly is provided. The pitch control mechanism has a hydraulic actuator (63a) which has first and second hydraulic cylinders (80,81). Each hydraulic cylinder is operable to angularly displace the propellers (62a) of the propeller assembly between fine and coarse positions. The pitch control mechanism further has one or more main hydraulic fluid supply lines (68a) which are connected to the first and second hydraulic cylinders (80,81) such that fluid supplied by the main hydraulic fluid supply lines (68a) operates the hydraulic cylinders (80,81). The pitch control mechanism further has one or more first back-up hydraulic fluid supply lines which are connected to the first hydraulic cylinder such that fluid supplied by the first back-up hydraulic fluid supply lines (83) to the first hydraulic cylinder displaces the propellers to a coarser position. The pitch control mechanism further has one or more second back-up hydraulic fluid supply lines (84) which are connected to the second hydraulic cylinder (81) such that fluid supplied by the second back-up hydraulic fluid supply lines (84) to the second hydraulic cylinder displaces the propellers to a coarser position. In the event of inadequate supply of fluid by the main hydraulic fluid supply lines, the first and/or the second back-up hydraulic fluid supply lines (83,84) can supply fluid to the respective hydraulic cylinders to displace the propellers to a coarser position.

公开(公告)号：EP2351925A3

公开(公告)日：2015-07-08

申请号：EP10192552.7

申请日：2010-11-25

申请人： Rolls-Royce plc

发明人： Swift, Andrew ,  Morgan, Antony

IPC分类号： F02K3/062 ,  F02K3/072 ,  B64C11/30 ,  B64C11/38 ,  B64C11/40 ,  B64D27/00

CPC分类号： F02K3/062 ,  B64C11/308 ,  B64C11/385 ,  B64C11/40 ,  B64D2027/005 ,  F02K3/072 ,  F05D2220/324 ,  F05D2260/76 ,  F05D2260/79 ,  F05D2270/094 ,  Y02T50/66 ,  Y02T50/671

摘要： A back-up featherer is provided for an engine arrangement having a main hydraulic actuator which angularly displaces propellers of a propeller assembly of the engine arrangement. The back-up featherer has a back-up hydraulic actuator (80) for angular displacement of the propellers, the back-up hydraulic actuator rotating with the propeller assembly. The back-up featherer further has one or more back-up fluid supply lines (81) for transferring hydraulic fluid between a hydraulic pressure power source located on a static structure of the engine arrangement and the back-up hydraulic actuator (80). The back-up featherer further has a back-up hydraulic rotating coupling (83), the back-up fluid supply lines fluidly communicating with the back-up hydraulic actuator via the back-up rotating coupling. A static side of the back-up hydraulic rotating coupling is mounted to the static structure of the engine arrangement, and a rotating side of the back-up hydraulic rotating coupling rotates with the propeller assembly.

摘要翻译： 为具有主液压致动器的发动机装置提供备用功能，该主液压致动器使发动机装置的螺旋桨组件的螺旋桨成角度地移位。 备用飞行器具有用于推进器的角位移的备用液压致动器（80），备用液压致动器与螺旋桨组件一起旋转。 备用功能器还具有用于在位于发动机装置的静态结构上的液压动力源与备用液压致动器（80）之间传送液压流体的一个或多个备用流体供应管线（81）。 备用飞行器还具有备用液压旋转联轴器（83），备用流体供应管线通过备用旋转联轴器与备用液压致动器流体连通。 备用液压旋转联轴器的静止侧安装在发动机装置的静态结构上，并且备用液压旋转联轴器的旋转侧随着螺旋桨组件旋转。

公开(公告)号：EP2378081A3

公开(公告)日：2014-06-04

申请号：EP10192595.6

申请日：2010-11-25

申请人： Rolls-Royce plc

发明人： Swift, Andrew ,  Morgan, Antony

IPC分类号： F01D7/00 ,  F01D21/18 ,  F02C9/58 ,  F01D1/26

CPC分类号： F01D7/00 ,  B64C11/308 ,  B64D2027/005 ,  F01D1/26 ,  F01D21/18 ,  F02C7/36 ,  F02C9/58 ,  F02K3/072 ,  F05D2220/324 ,  F05D2250/44 ,  Y02T50/66 ,  Y02T50/673

摘要： A back-up featherer is provided for an engine arrangement having a main hydraulic actuator which angularly displaces propellers of a propeller assembly of the engine arrangement. The engine arrangement further has one or more fluid supply lines for transferring hydraulic fluid between a hydraulic pressure power source located on a static structure of the engine arrangement and the main hydraulic actuator. The back-up featherer has a back-up actuator assembly for angular displacement of the propellers, the back-up actuator assembly rotating with the propeller assembly. The back-up featherer further has a signal detector that is operatively connected to the back-up actuator assembly and rotates with the propeller assembly. The back-up featherer further has a back-up rotating coupling. A static side of the back-up rotating coupling is mounted to the static structure of the engine arrangement and communicates with a regulator located on a static structure of the engine arrangement. A rotating side of the back-up hydraulic rotating coupling rotates with the propeller assembly and communicates with the signal detector. The back-up actuator assembly angularly displaces the propellers when the signal detector detects a signal from the regulator to displace the propellers.