公开(公告)号：US08444084B2

公开(公告)日：2013-05-21

申请号：US11785826

申请日：2007-04-20

申请人： Kenneth F Udall ,  Peter K Beardsley

发明人： Kenneth F Udall ,  Peter K Beardsley

IPC分类号： B64D27/26

CPC分类号： B64D27/26 ,  B64D27/20 ,  B64D2027/266

摘要： A mounting arrangement of a gas turbine engine comprising a core engine, surrounded by a nacelle having a bypass duct, the mounting arrangement comprising a front mount, a rear mount and characterized by the mounting arrangement further comprising a fail-safe mount axially spaced from the front and rear mounts. The fail-safe mount comprises a number of A-frames connecting the core engine and the bypass duct. In normal operation the fail-safe mount does not transmit loads between the engine and a pylon, except in the event of damage to either the front or rear mounts.

摘要翻译： 一种燃气涡轮发动机的安装装置，包括一个由具有旁通管道的机舱包围的核心发动机，该安装装置包括前部安装件，后部安装件，其特征在于，所述安装装置还包括一个故障安全装置， 前后座。 故障安全座架包括连接核心发动机和旁路管道的多个A型框架。 在正常操作中，故障安全装置不会在发动机和吊架之间传递负载，除非在前部或后部安装座损坏的情况下。

公开(公告)号：US07523604B2

公开(公告)日：2009-04-28

申请号：US11363040

申请日：2006-02-28

申请人： Alan R Maguire ,  Kenneth F Udall ,  Richard G Stretton

发明人： Alan R Maguire ,  Kenneth F Udall ,  Richard G Stretton

IPC分类号： F02K1/54

CPC分类号： F02C7/20 ,  F02K1/70 ,  F05D2240/55

摘要： A gas turbine engine comprising a core engine surrounded by a core casing, at least one C-duct having radially inner and outer walls and a thrust reverser unit; the engine is mounted to an aircraft pylon via at least one thrust member attached to the core engine; the thrust reverser unit is mounted within the outer wall of the C-duct; the C-duct is secured to the core casing via a vee-groove attachment comprising vee-groove and vee-blade parts, the attachment is arranged to transfer loads between the thrust reverser unit and the pylon; wherein one cooperating part of the attachment is mounted to a torsion box mounted on the inner wall of the C-duct.

摘要翻译： 一种燃气涡轮发动机，包括由芯壳体围绕的核心发动机，至少一个具有径向内壁和外壁的C形管道和推力反向器单元; 发动机通过至少一个连接到核心发动机的推力构件安装到飞机塔架上; 推力反向器单元安装在C导管的外壁内; C导管通过包括vee-groove和vee-blade部件的vee-groove附件固定到芯壳体，该附件被布置成在推力反向器单元和塔架之间传递载荷; 其中所述附件的一个配合部分安装在安装在所述C导管的内壁上的扭转盒上。

公开(公告)号：US06827548B2

公开(公告)日：2004-12-07

申请号：US10309282

申请日：2002-12-04

申请人： Todd M Coxhead ,  James M Townsend ,  Kenneth F Udall

发明人： Todd M Coxhead ,  James M Townsend ,  Kenneth F Udall

IPC分类号： F01B3136

CPC分类号： F02C7/36 ,  F01D21/02 ,  F05D2270/091

摘要： A gas turbine engine 10 includes an intermediate pressure compressor 14 connected to an intermediate pressure turbine 22 by a driveshaft 28. The driveshaft 28 comprises a downstream turbine shaft 34 attached to the intermediate pressure turbine 22 and an upstream compressor shaft 32 attached to the intermediate pressure compressor 14. The compressor shaft 32 and turbine shaft 34 are connected together by a splined connection 36 which allows the turbine shaft 34 to drive the compressor shaft 32. If the splined connected 36 should fail, so that it no longer transmits torque, a further splined connection 41 comes into operation to transmit torque between the turbine shaft 34 and compressor shaft 32. When this happens, torque is transmitted via a torsionally weakened, shear section 48 of the turbine shaft 34 which tends to break under certain engine conditions. The turbine shaft 34 is then released axially and turbine overspeed is restrained.

摘要翻译： 燃气涡轮发动机10包括通过驱动轴28连接到中压涡轮机22的中压压缩机14.驱动轴28包括连接到中压涡轮22的下游涡轮轴34和附接到中压的上游压缩机轴32 压缩机轴32和涡轮轴34通过花键连接件36连接在一起，花键连接件36允许涡轮机轴34驱动压缩机轴32.如果花键连接的36应该失效，使得它不再传递扭矩 花键连接41运行以在涡轮机轴34和压缩机轴32之间传递扭矩。当这种情况发生时，扭矩通过涡轮机轴34的扭转减弱的剪切部分48传递，其在某些发动机条件下倾向于断裂。 涡轮轴34然后被轴向释放并且涡轮超速被限制。

公开(公告)号：US06971855B2

公开(公告)日：2005-12-06

申请号：US10724629

申请日：2003-12-02

申请人： Martyn Richards ,  Kenneth F Udall ,  Andrew Swift

发明人： Martyn Richards ,  Kenneth F Udall ,  Andrew Swift

IPC分类号： F01D5/30 ,  F04D29/34 ,  F01D5/32

CPC分类号： F04D29/34 ,  F01D5/3015

摘要： A blade arrangement for a gas turbine engine includes a plurality of blades mounted for rotation on a disc so as to extend radially therefrom and a retention member, the retention member including an attachment portion which is attached to the disc and an abutment portion for resisting forward axial movement of at least one of the blades relative to the disc. The blade arrangement further comprises restraint means spaced from the attachment portion of the retention member, for substantially preventing radially outward movement of the abutment portion of the retention member when a forward axial force is applied by the blade to the abutment portion.

摘要翻译： 用于燃气涡轮发动机的叶片装置包括多个叶片，其安装成用于在盘上旋转以从其径向延伸并且具有保持构件，所述保持构件包括附接到盘的附接部分和用于抵抗向前的邻接部分 至少一个叶片相对于盘的轴向运动。 叶片装置还包括与保持构件的附接部分间隔开的约束装置，用于当刀片向邻接部分施加向前的轴向力时，基本上防止保持构件的邻接部分的径向向外移动。

公开(公告)号：US06494032B2

公开(公告)日：2002-12-17

申请号：US09784163

申请日：2001-02-16

申请人： Kenneth F Udall ,  John W Allen ,  Stephen H Watson

发明人： Kenneth F Udall ,  John W Allen ,  Stephen H Watson

IPC分类号： F01D502

CPC分类号： F01D21/045 ,  F01D25/162 ,  F05B2260/3011 ,  F16C19/522 ,  F16C2360/23

摘要： A ducted fan gas turbine engine comprises a fan 12 mounted on a first shaft 16 and a compressor mounted on a second shaft 43. The shafts are coaxial both with each other and with said engine longitudinal axis 15. The shafts are mounted in roller bearings 21, 40. The first bearing 21 carrying the upstream part of the first shaft and the second bearing 40 carrying the upstream part of the second shaft. Both bearings are attached to a structure 26 which comprises an axial sleeve and a front frustoconical portion and a rear radially stiff but axially flexible frustoconical portion and is attached to the engine casing 36. The front frustoconical portion is frangibly attached to the front part of the axial sleeve 28. In the event of damage to the fan the frangible connection breaks and the first shaft is allowed to orbit about the engine longitudinal axis 15. The rear member 32 is swashingly non-linear flexible and accommodates the out of balance radial loads transferred to it as couples during such an incident.

摘要翻译： 管式风机燃气涡轮发动机包括安装在第一轴16上的风扇12和安装在第二轴43上的压缩机。轴彼此同轴并与所述发动机纵向轴线15同轴。该轴安装在滚子轴承21 40.承载第一轴的上游部分的第一轴承21和承载第二轴的上游部分的第二轴承40。 两个轴承都连接到一个结构26上，该结构26包括一个轴向套管和一个前截头圆锥形部分和一个后向径向刚性但是轴向柔性的截头圆锥形部分，并连接在发动机壳体36上。前截面圆锥体部分是易碎地连接到 在风扇损坏的情况下，易碎连接断裂，并且第一轴被允许围绕发动机纵向轴线15轨道运动。后部构件32是非线性的，并且适应不平衡的径向载荷转移 在这样的事件中，夫妇是这样做的。

公开(公告)号：US06098399A

公开(公告)日：2000-08-08

申请号：US20964

申请日：1998-02-10

申请人： Martyn Richards ,  John W Allen ,  Kenneth F Udall ,  David M Beaven

发明人： Martyn Richards ,  John W Allen ,  Kenneth F Udall ,  David M Beaven

IPC分类号： F01D21/04 ,  F01D25/16 ,  F16C19/52 ,  F16C35/077 ,  F02C7/06 ,  F02K3/04

CPC分类号： F16C19/52 ,  F01D21/045 ,  F01D25/16 ,  F16C35/077 ,  F05B2260/3011 ,  F16C19/26

摘要： A ducted fan gas turbine has a fan shaft which is supported at its upstream end by a bearing. In the event of damage to the engine's fan, frangible bolts fracture to permit radial movement of the shaft. That movement is limited by the sequential engagement of the outer race of the bearing with first and second movement limiting portions on fixed structure of the engine. This alters the natural frequency of vibration of the fan, so permitting the fan to windmill without excessive vibration.

摘要翻译： 风扇式燃气涡轮机具有风扇轴，其在其上游端由轴承支撑。 在发动机风扇损坏的情况下，易碎的螺栓破裂以允许轴的径向移动。 该运动受到轴承的外圈与发动机的固定结构上的第一和第二运动限制部分的顺序啮合的限制。 这改变了风扇的固有振动频率，从而允许风扇无风扇的振动。

公开(公告)号：US08506234B2

公开(公告)日：2013-08-13

申请号：US12768041

申请日：2010-04-27

申请人： Richard V Brooks ,  Kenneth F Udall ,  Richard G Stretton

发明人： Richard V Brooks ,  Kenneth F Udall ,  Richard G Stretton

IPC分类号： F01D21/00

CPC分类号： F01D21/045 ,  F01D5/16 ,  F01D25/06

摘要： A duct wall of a fan casing of a gas turbine engine comprises an intake section and a containment casing, which are interconnected by bolts at flanges. An acoustic flutter damper is provided between the flanges to reduce or eliminate flutter arising in blades of the fan at certain important operating conditions. The damper provides flexibility at the connection between the intake section and the containment casing so that, in the event of detachment of a blade or a bladed fragment, the resulting deflection wave in the containment casing can be accommodated by displacement and/or deformation of the acoustic flutter damper, reducing the risk that the bolts will shear to allow the intake section and the containment casing to become detached from each other. The acoustic flutter damper may comprise a circumferential array of separate segments.

摘要翻译： 燃气涡轮发动机的风扇壳体的导管壁包括通过螺栓在凸缘处互连的进气部分和容纳壳体。 在凸缘之间提供声波阻尼器以减少或消除在某些重要操作条件下风扇叶片中产生的颤动。 阻尼器在进气部分和收容壳体之间的连接处提供了灵活性，使得在叶片或叶片碎片脱离的情况下，容纳壳体中产生的偏转波可以通过位移和/或变形 声波阻尼器，减少了螺栓剪切的风险，使进气段和密封套彼此脱离。 声波阻尼器可以包括分开的段的圆周阵列。

公开(公告)号：US07806364B1

公开(公告)日：2010-10-05

申请号：US11651553

申请日：2007-01-10

申请人： Kenneth F Udall

发明人： Kenneth F Udall

IPC分类号： B64D27/00

CPC分类号： F01D21/045 ,  F05D2250/61 ,  F05D2300/433 ,  F05D2300/603

摘要： A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine.

摘要翻译： 用于燃气涡轮发动机的容纳系统包括用于吸收由发动机的故障部件的喷射部分施加在其上的力的力吸收装置。 力吸收装置周向地围绕发动机轴向长度的主要部分。

公开(公告)号：US07229252B2

公开(公告)日：2007-06-12

申请号：US10999978

申请日：2004-12-01

申请人： Brian Hermiston ,  Andrew MacNamara ,  Kenneth F Udall ,  Ian C D Care

发明人： Brian Hermiston ,  Andrew MacNamara ,  Kenneth F Udall ,  Ian C D Care

IPC分类号： F01D5/32 ,  F03B3/12

CPC分类号： F01D5/326 ,  F01D5/3015 ,  F05D2250/61 ,  F05D2260/33

摘要： A rotor stage (13, 14, 15, 17, 18, 19) of a gas turbine engine (10) comprises an annular retaining plate (38) capable of preventing axial movement of blades (30). The retaining plate (38) is secured to the disc (32) via a bayonet arrangement (49). A locking assembly (48) is provided to prevent relative rotation between the disc (32) and the retaining plate (38). The locking assembly (48) comprises a locking plug (50) configured in a generally Y-shaped cross section having a channel portion defined by arms (56), which engage upstream and downstream of the retaining plate (38) and a leg part (58) configured to span between bayonet parts (40 and 42), thereby preventing relative rotation between the disc (32) and the retaining plate (38). The assembly (48) further comprises a securing plate (52) configured to span between circumferentially adjacent castellations (40) thereby preventing the locking plug (50) disengaging the disc (32) and retaining plate (38).

摘要翻译： 燃气涡轮发动机（10）的转子级（13,14,15,17,18,19）包括能够防止叶片（30）的轴向移动的环形保持板（38）。 保持板（38）经由卡口装置（49）固定到盘（32）。 提供锁定组件（48）以防止盘（32）和保持板（38）之间的相对旋转。 锁定组件（48）包括构造成大致Y形横截面的锁定塞（50），其具有由臂（56）限定的通道部分，该通道部分与保持板（38）的上游和下游接合， 58）构造成跨越卡口部件（40和42），从而防止盘（32）和保持板（38）之间的相对旋转。 组件（48）进一步包括固定板（52），该固定板构造成在周向相邻的榫眼（40）之间跨接，从而防止锁定塞（50）脱离盘（32）和保持板（38）。

公开(公告)号：US07143975B2

公开(公告)日：2006-12-05

申请号：US11028535

申请日：2005-01-05

申请人： Kenneth F Udall

发明人： Kenneth F Udall

IPC分类号： B64C25/10

CPC分类号： B64C25/001 ,  B64C2025/008

摘要： A landing arrangement for an aircraft comprises an aircraft support assembly (22) to support the aircraft (10) when the aircraft is on the ground. The aircraft support assembly (2) is movable between a first ground engaging condition (22b) in which the aircraft nose (24) is spaced above the ground by a first distance (X) and a second ground engaging condition (22C) in which the aircraft nose (24) is spaced above the ground by a second distance (Y). The second distance (Y) is less than the first distance (X).

摘要翻译： 飞机的着陆装置包括当飞行器在地面上时支撑飞行器（10）的飞行器支撑组件（22）。 飞行器支撑组件（2）可在第一地面接合状态（22b）之间移动，其中飞行器鼻部（24）在地面上间隔第一距离（X）和第二地面接合条件（22℃） 飞行器鼻部（24）在地面上间隔第二距离（Y）。 第二距离（Y）小于第一距离（X）。