公开(公告)号：US07121758B2

公开(公告)日：2006-10-17

申请号：US10919409

申请日：2004-08-17

申请人： Alison J McMillan ,  Kevin A White

发明人： Alison J McMillan ,  Kevin A White

IPC分类号： F16D1/00

CPC分类号： F01D21/045 ,  F16B2200/50 ,  F16B2200/503 ,  F16B2200/506 ,  Y02T50/671 ,  Y10T403/11 ,  Y10T403/49 ,  Y10T403/75

摘要： A joint assembly 80 is provided for limiting an extension of the joint 80 in the direction of a load path derived from an impact comprising. In its simplest form, the joint 80 comprises a first member 40 having a portion 82 and a second member 50 having a portion 84, the portions 82, 84 overlapping one another and arranged generally parallel to one another and secured together via securing means 78. The securing means 78 is disposed through corresponding holes 92, 94 defined by portions 82 and 84. At least one of the overlapping portions 82 or 84 further defines, sequentially in the direction of extension a pocket 102. The securing means 78 comprises a deformable member 152, 178 and at least one of the overlapping portions 82, 84 comprises a wedge-shaped portion 74. In the event of a worst-case impact load the securing means 78 is forced through the pocket 106 while the wedge-shaped portion 74 causes the deformable member 152 to deform and thereby increase the clamping force, in a progressive manner, to limit the extension of the joint assembly 80 and retain an integral joint assembly 80.

摘要翻译： 提供了一种接头组件80，用于限制接头80沿着由冲击构成的载荷路径的方向延伸。 在其最简单的形式中，接头80包括具有部分82的第一构件40和具有部分84的第二构件50，部分82,84彼此重叠并且大体上彼此平行地布置并且通过固定装置78固定在一起。 固定装置78通过由部分82和84限定的对应孔92,94设置。 重叠部分82或84中的至少一个还在口袋102的延伸方向上依次限定。 固定装置78包括可变形构件152,178，并且重叠部分82,84中的至少一个包括楔形部分74。 在最坏情况的冲击载荷的情况下，固定装置78被迫通过袋106，而楔形部分74使可变形构件152变形，从而以渐进的方式增加夹紧力，以限制延伸 并且保持一体的接头组件80。

公开(公告)号：US08033789B2

公开(公告)日：2011-10-11

申请号：US11798552

申请日：2007-05-15

申请人： Simon Read ,  Alison J McMillan ,  Eric Ravey

发明人： Simon Read ,  Alison J McMillan ,  Eric Ravey

IPC分类号： F01D5/16 ,  F01D5/18

CPC分类号： F01D25/02 ,  F01D5/26 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/90 ,  F05D2300/43 ,  F05D2300/505 ,  F05D2300/507 ,  F05D2300/611 ,  Y02T50/672 ,  Y02T50/673

摘要： Aerofoils (22) of a gas turbine engine are provided with a coating (34) or filler (44) of viscoelastic material. As ice accretes on the aerofoils (22) during operation, the resulting aerodynamic stability imbalance induces vibration in the aerofoils (22). The viscoelastic material (34, 44) damps this vibration, and in so doing generates heat, which melts the ice away from the aerofoils (22). Heat-conducting members conduct the heat to regions of the component in which ice accretion is to be prevented. Alternative embodiments are described in which the pseudoelastic behaviour of a shape memory alloy (56), or eddy currents arising from the rotor blades' rotation in an axisymmetric magnetic field, are used as sources of heat.

摘要翻译： 燃气涡轮发动机的机翼（22）设置有粘弹性材料的涂层（34）或填料（44）。 由于在运行过程中机翼（22）上积冰，所产生的空气动力学稳定性失衡会引起机翼中的振动（22）。 粘弹性材料（34,44）阻止该振动，并且在这样做时产生热量，其将冰从机翼（22）熔化。 导热构件将热量传导到要防止积冰的部件的区域。 描述了替代实施例，其中形状记忆合金（56）的伪弹性行为或由轴对称磁场中的转子叶片旋转产生的涡流被用作热源。

公开(公告)号：US07783116B2

公开(公告)日：2010-08-24

申请号：US10720344

申请日：2003-11-25

申请人： Alison J McMillan ,  Graham Watson

发明人： Alison J McMillan ,  Graham Watson

IPC分类号： G06K9/36

CPC分类号： G06F17/5018 ,  H04N19/17 ,  H04N19/63

摘要： A computer system programmed to process a large data set includes means for analysing the data set. The means for analysing the data set typically comprises a means for finite element analysis. The computer system also includes means for applying a data compression technique to the analysed data set such that the compressed analysed data set has high fidelity in regions of interest and has lower fidelity in regions of lesser interest. The data compression technique comprises the use of a wavelet compression technique. The computer system comprises a high specification server and a local workstation. This compressed analysed data set is easily managed by the local workstation to produce different cross-sectional displays without reusing the high capability server. The analysed data set for example comprises a 4D data set of a fan blade containment analysis of a casing.

摘要翻译： 被编程为处理大数据集的计算机系统包括用于分析数据集的装置。 用于分析数据集的装置通常包括用于有限元分析的装置。 计算机系统还包括用于将数据压缩技术应用于所分析的数据集的装置，使得压缩的分析数据集在感兴趣的区域中具有高保真度，并且在较不感兴趣的区域中具有较低的保真度。 数据压缩技术包括使用小波压缩技术。 计算机系统包括高规格服务器和本地工作站。 该压缩的分析数据集由本地工作站轻松管理，以生成不同的横截面显示，而不需要重新使用高性能服务器。 所分析的数据集例如包括壳体的风扇叶片容纳分析的4D数据集。

公开(公告)号：US07744093B2

公开(公告)日：2010-06-29

申请号：US11519817

申请日：2006-09-13

申请人： Alison J McMillan

发明人： Alison J McMillan

IPC分类号： F16J15/44 ,  F16J15/447

CPC分类号： F16J15/445 ,  F01D11/003 ,  F05D2240/56 ,  F16J15/3228 ,  F16J15/3292 ,  F16J15/4472

摘要： A seal and method of making seals utilizes folds in order to form creases in a length of material such that the creases reinforce individual seal elements or surfaces while perforations or slots in a seal edge allow air leakage from one side of the seal element or surface to the other. Thus, air pressurization can take place between spaced seal elements or surfaces and this allows air flotation or riding of a rotating component relative to a static housing component. The perforations are typically graduated from the seal edge in order to provide the best pressurization and air-riding effect for proximity or gap control between the sealing edge and the rotating component surface. The slots effectively provide flexibility to the sealing edge such that the seal component emulates a brush seal.

摘要翻译： 密封件和密封件的制造方法利用折叠，以便在一定长度的材料中形成褶皱，使得折痕加强各个密封元件或表面，而密封边缘中的穿孔或狭缝允许空气从密封元件或表面的一侧泄漏到 另一个。 因此，空气加压可以在间隔的密封元件或表面之间发生，并且这允许相对于静态外壳部件的空气浮动或旋转部件的骑行。 穿孔通常从密封边缘刻度，以便为密封边缘和旋转部件表面之间的接近或间隙控制提供最佳的加压和乘坐效果。 插槽有效地为密封边缘提供了灵活性，使得密封部件模拟刷子密封。

公开(公告)号：US09140131B2

公开(公告)日：2015-09-22

申请号：US13445278

申请日：2012-04-12

申请人： Alison J McMillan

发明人： Alison J McMillan

IPC分类号： F01D5/30 ,  B23P9/00 ,  B24B19/14 ,  B24B15/08 ,  B24B19/06

CPC分类号： F01D5/3007 ,  B23P9/00 ,  B24B15/08 ,  B24B19/06 ,  B24B19/14 ,  F05D2230/90 ,  F05D2250/621 ,  F05D2260/941 ,  F05D2300/702 ,  Y10T29/49316 ,  Y10T29/49336

摘要： A method of conditioning a first, heterogeneous contact surface for operational engagement with a second contact surface, the method comprising: performing a smoothing operation on part or all of the first contact surface while subjecting said part or all of the first contact surface respectively to a contact pre-stress corresponding to a nominal operational contact stress between the first and second contact surfaces.

摘要翻译： 一种调节第一非均匀接触表面以与第二接触表面操作接合的方法，所述方法包括：对所述第一接触表面的部分或全部进行平滑处理，同时将所述部分或全部所述第一接触表面分别 接触对应于第一和第二接触表面之间的标称操作接触应力的预应力。

公开(公告)号：US08459955B2

公开(公告)日：2013-06-11

申请号：US12458768

申请日：2009-07-22

申请人： Alison J McMillan ,  Ian C D Care

发明人： Alison J McMillan ,  Ian C D Care

IPC分类号： F01D5/14

CPC分类号： F01D5/282 ,  F04D29/324 ,  F05D2230/60 ,  F05D2240/121 ,  F05D2240/303 ,  Y10T29/49336

摘要： Composite aerofoils for gas turbine engines are commonly provided with a metal protection strip along the leading edge, to prevent erosion of the leading edge in use and to protect against impacts from foreign bodies. A problem with such strips is that they can cause serious damage to other parts of the engine if they become detached from the aerofoil. The invention provides an aerofoil having such a protection strip, characterized in that the protection strip includes one or more weakening features to reduce the ability of the protection member to withstand a compressive force applied along its length. The weakening features encourage the protection member to break up under impact, or if it becomes detached from the aerofoil, so that damage to other parts of the engine is minimized.

摘要翻译： 用于燃气涡轮发动机的复合机翼通常沿着前缘设有金属保护带，以防止使用中的前缘侵蚀并防止异物的冲击。 这种条带的问题是，如果它们与机翼分离，它们可能对发动机的其它部件造成严重损坏。 本发明提供了一种具有这种保护条的机翼，其特征在于，保护带包括一个或多个弱化特征，以降低保护构件承受沿其长度施加的压缩力的能力。 弱化特征使得保护构件在冲击下分裂，或者如果它与机翼分离，则使发动机其他部件的损坏最小化。

公开(公告)号：US07399158B2

公开(公告)日：2008-07-15

申请号：US11104485

申请日：2005-04-13

申请人： Ian C D Care ,  Alison J McMillan ,  Seamus Garvey

发明人： Ian C D Care ,  Alison J McMillan ,  Seamus Garvey

IPC分类号： F01D25/06

CPC分类号： F04D29/668 ,  F01D5/26 ,  F04D25/066 ,  F05D2270/096 ,  F05D2270/11 ,  F05D2300/507 ,  Y02T50/671 ,  Y02T50/673 ,  Y10S416/50

摘要： A blade arrangement 31 includes an array of radially extending blades 20, which may for example comprise a fan of a gas turbine engine for an aircraft. The blades 20 are mounted for rotation about a central axis X-X. The blade arrangement 31 further includes a damping arrangement 32 comprising means 34 for inducing an axi-symmetric magnetic field whose axis of symmetry coincides with the central axis X-X of rotation of the blades 20. The damping arrangement 32 is configured such that when the magnetic field is induced, any movement of the blade 20 other than pure rotation about the central axis results in the magnetic field causing a force to be exerted on the blade 20, the force resisting such movement. The damping arrangement may be provided with means for inducing the magnetic field only when there is an increased likelihood of vibration of the blades, for example when a foreign body has entered the air intake of the engine.

摘要翻译： 叶片装置31包括径向延伸的叶片20的阵列，其可以例如包括用于飞行器的燃气涡轮发动机的风扇。 叶片20安装成围绕中心轴线X-X转动。 叶片装置31还包括阻尼装置32，其包括用于引导轴对称磁场的装置34，其对称轴与叶片20的旋转中心轴线X-X重合。 阻尼装置32被构造成使得当磁场被感应时，除了围绕中心轴线的纯旋转之外，叶片20的任何运动导致磁场引起力施加在叶片20上，抵抗这种运动的力 。 阻尼装置可以设置有仅当叶片振动的可能性增加时引起磁场的装置，例如当异物进入发动机的进气口时。

公开(公告)号：US07827685B2

公开(公告)日：2010-11-09

申请号：US11141406

申请日：2005-06-01

申请人： Alison J McMillan

发明人： Alison J McMillan

IPC分类号： B21D53/84 ,  F01D11/02 ,  F16J15/34

CPC分类号： F16J15/3292 ,  F01D11/001 ,  F05D2230/13 ,  Y10T29/49297

摘要： A seal and method of making seals utilises folds in order to form creases in a length of material such that the creases reinforce individual seal elements or surfaces whilst perforations or slots in a seal edge allow air leakage from one side of the seal element or surface to the other. Thus, air pressurisation can take place between spaced seal elements or surfaces and this allows air flotation or riding of a rotating component relative to a static housing component. The perforations are typically graduated from the seal edge in order to provide the best pressurisation and air-riding effect for proximity or gap control between the sealing edge and the rotating component surface. The slots effectively provide flexibility to the sealing edge such that the seal component emulates a brush seal.

摘要翻译： 密封件和密封件的制造方法利用折叠，以便在一定长度的材料中形成褶皱，使得折痕加强各个密封元件或表面，而密封边缘中的穿孔或狭槽允许空气从密封元件或表面的一侧泄漏到 另一个。 因此，空气加压可以在间隔的密封元件或表面之间发生，并且这允许相对于静态外壳部件的空气浮选或旋转部件的骑行。 穿孔通常从密封边缘分级，以便为密封边缘和旋转部件表面之间的接近或间隙控制提供最佳的加压和乘坐效果。 插槽有效地为密封边缘提供了灵活性，使得密封部件模拟刷子密封。

公开(公告)号：US06913436B2

公开(公告)日：2005-07-05

申请号：US10732344

申请日：2003-12-11

申请人： Alison J McMillan ,  Ian C D Care

发明人： Alison J McMillan ,  Ian C D Care

IPC分类号： F01D21/04 ,  F01D21/00

CPC分类号： F01D21/045 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2250/283 ,  F05D2300/43 ,  F05D2300/431 ,  F05D2300/433 ,  F05D2300/612 ,  F05D2300/702 ,  Y02T50/672

摘要： A gas turbine engine rotor blade containment assembly comprises a generally cylindrical, or frustoconical, stiff containment casing (54), a generally cylindrical, or frustoconical, flexible structure (62) arranged within and spaced radially from the stiff containment casing (54) by crushable structures (64, 66) at axially spaced positions on the flexible structure (62). A viscoelastic material (68) is arranged to fill the space (70) between the stiff containment casing (54), the flexible structure (62) and the crushable structures (64, 66). The viscoelastic material (68) provides local stiffening of the blade containment assembly in the region of a fan blade (34) impact and provides energy dissipation by viscoelastic damping of the flexing of the flexible structure (62) and plastic deformation in the crushing of the crushable structures (64, 66).

摘要翻译： 燃气涡轮发动机转子叶片容纳组件包括大致圆柱形或截头圆锥形的容纳壳体（54），大体上圆柱形或截头圆锥形的柔性结构（62），其布置在刚性容纳壳体（54）的径向内并且可通过可挤压 结构（64,66）在所述柔性结构（62）上的轴向间隔开的位置。 粘弹性材料（68）布置成填充刚性容纳壳体（54），柔性结构（62）和可压溃结构（64,66）之间的空间（70）。 粘弹性材料（68）在风扇叶片（34）的冲击区域中提供叶片容纳组件的局部加强，并且通过柔性结构（62）的挠曲的粘弹性阻尼和在破碎过程中的塑性变形来提供能量耗散 可压碎结构（64,66）。

公开(公告)号：US06893478B2

公开(公告)日：2005-05-17

申请号：US10379675

申请日：2003-03-06

申请人： Ian C Care ,  Colin A Foord ,  Alison J McMillan ,  Michael J Mountney

发明人： Ian C Care ,  Colin A Foord ,  Alison J McMillan ,  Michael J Mountney

IPC分类号： B01D45/14 ,  B01D46/26 ,  B01D50/00 ,  F01M13/04

CPC分类号： F01M13/04 ,  B01D45/14 ,  B01D46/003 ,  B01D46/0056 ,  B01D2275/307 ,  F01M2013/0422 ,  F05B2220/302 ,  F05B2220/704

摘要： An air/oil separator (40) comprises a rotor (60) and a casing (62) surrounding the rotor (60). The casing (60) has an inlet (64) at a first axial position (A) for the supply of an air and oil mixture into the air/oil separator (40). The rotor (60) has an outlet (66) for discharging cleaned air from the air/oil separator (40). The rotor (60) carries a plurality of porous members (68, 70, 72). The porous members (68, 70, 72) have an inlet (74) at a second axial position (B) and an outlet (76) at a third axial position (C). The third axial position (C) is arranged axially between the first axial position (A) and the second axial position (B). A first passage (88) supplies the air and oil mixture from the inlet (64) in the casing (62) to the inlet (74) to the porous members (68, 70, 72). A second passage (94) supplies cleaned air from the porous members (68, 70, 72) to the outlet (66) in the rotor (60). In use the air and oil mixture flows through the porous members (68, 70, 72) in the opposite direction to the air and oil mixture flowing through the first passage (88).

摘要翻译： 空气/油分离器（40）包括转子（60）和围绕转子（60）的壳体（62）。 壳体（60）在第一轴向位置（A）处具有用于将空气和油混合物供应到空气/油分离器（40）中的入口（64）。 转子（60）具有用于从空气/油分离器（40）排出净化空气的出口（66）。 转子（60）承载多个多孔构件（68,70,72）。 多孔构件（68,70,72）在第二轴向位置（B）处具有入口（74）和在第三轴向位置（C）处具有出口（76）。 第三轴向位置（C）轴向地布置在第一轴向位置（A）和第二轴向位置（B）之间。 第一通道（88）将空气和油混合物从壳体（62）中的入口（64）供给到多孔构件（68,70,72）的入口（74）。 第二通道（94）将清洁的空气从多孔构件（68,70,72）提供到转子（60）中的出口（66）。 在使用中，空气和油混合物沿着与流过第一通道（88）的空气和油混合物相反的方向流过多孔构件（68,70,72）。