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1. 发明申请

US20090016894A1 Component with internal damping 审中-公开
标题翻译：内部阻尼元件
公开(公告)号：US20090016894A1
公开(公告)日：2009-01-15
申请号：US12216505
申请日：2008-07-07
申请人： Oliver M. Strother
发明人： Oliver M. Strother
IPC分类号： F01D5/14 , B21K3/04
CPC分类号： B21D53/78 , B21D26/055 , B21D47/00 , B23P15/04 , F01D5/147 , F01D5/16 , F02K3/06 , F04D29/023 , F04D29/388 , F04D29/668 , F05D2300/43 , F05D2300/501 , F05D2300/522 , Y10T29/49337
摘要： A method of manufacturing a component such as a gas turbine fan blade. The method comprises: disposing a plurality of webs between a plurality of panels; and deforming the panels and the webs by applying internal pressure between the panels, thereby forming a series of internal cavities (15) partitioned by the webs (20-22). Weakened regions (30a,30b,30c) are formed in the webs which open to form holes (30) in the webs (20-22) during the deformation step. A damping material (17) is introduced into at least one of the cavities (15) whereby it flows from the cavity into the other cavities via the holes in the webs.
摘要翻译：一种制造诸如燃气轮机风扇叶片的部件的方法。该方法包括：在多个面板之间布置多个腹板; 以及通过在所述面板之间施加内部压力来使所述面板和所述腹板变形，从而形成由所述腹板（20-22）分隔的一系列内部空腔（15）。弱化区域（30a，30b，30c）形成在所述腹板中，所述腹板在变形步骤期间打开以在腹板（20-22）中形成孔（30）。阻尼材料（17）被引入到空腔（15）中的至少一个中，由此其通过腹板中的孔从空腔流入其它空腔。

2. 发明授权

US08529720B2 Aerofoil sub-assembly, an aerofoil and a method of making an aerofoil 有权
标题翻译： Aerofoil子组件，机翼和制作机翼的方法
公开(公告)号：US08529720B2
公开(公告)日：2013-09-10
申请号：US12453762
申请日：2009-05-21
申请人： Keith C. Goldfinch , Oliver M. Strother
发明人： Keith C. Goldfinch , Oliver M. Strother
IPC分类号： B32B3/00 , B32B37/00
CPC分类号： B21D53/78 , B21D26/055 , B21D47/00 , B23K20/023 , B23K20/22 , B23K2101/006 , Y10T29/49337 , Y10T29/49805 , Y10T156/10 , Y10T428/24612
摘要： A method of making an aerofoil comprises the steps of providing first and second skin panels and first and second web-forming membranes. The web-forming membranes each have a series of elongate slots formed longitudinally therein so as to define a series of alternating wide and narrow strips. The wide strips of one membrane are arranged against the narrow strips of the other membrane and the skin panels are arranged either side of the two web-forming membranes. Parts of the web-forming membranes and parts of the skin panels are treated with a release layer and the sub-assembly is compressed and heated so as to effect diffusion bonding between those parts of the membranes and skin panels which are not treated with the release layer. The sub-assembly is then heated and inflated so as to draw the first and second skin panels apart and that, in turn, causes the web-forming membranes to form webs internally.
摘要翻译：制备机翼的方法包括提供第一和第二皮肤面板以及第一和第二网状物形成膜的步骤。幅材形成膜各自具有纵向形成的一系列细长狭缝，以便限定一系列交替的宽而窄的条带。一个膜的宽条布置在另一个膜的窄条上，并且皮肤片布置在两个幅材形成膜的两侧。将成网膜和部分皮肤面板的部分用剥离层处理，并且将子组件压缩和加热，以便在膜的那些部分和未被释放的处理的皮肤面板之间实现扩散粘合层。然后将该子组件加热并充气以便将第一和第二表皮板分开，并且进而导致幅材形成膜在内部形成纤维网。

3. 发明授权

US08381398B2 Component with a damping filler and method 失效
标题翻译：具有阻尼填料和方法的组件
公开(公告)号：US08381398B2
公开(公告)日：2013-02-26
申请号：US12216502
申请日：2008-07-07
申请人： Keith C. Goldfinch , Oliver M. Strother , Julian Mackechnie-Jarvis
发明人： Keith C. Goldfinch , Oliver M. Strother , Julian Mackechnie-Jarvis
IPC分类号： B21D53/78 , B21D31/04 , B21K3/04
CPC分类号： B21D53/78 , B23P15/04 , F01D5/147 , F01D5/26 , F04D29/023 , F04D29/324 , F04D29/666 , F04D29/668 , F05D2220/36 , F05D2260/96 , F05D2300/133 , F05D2300/43 , Y10T29/49336 , Y10T29/49337 , Y10T29/49339
摘要： A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.
摘要翻译：一种制造燃气涡轮发动机（10）的机翼的方法。该方法包括以下步骤：提供第一和第二面板（16,18），在第一和第二面板之间提供腹板（30），通过在面板之间施加内部压力来使面板和腹板变形，从而形成一系列由腹板分隔的内腔。该方法还包括在整个宽度上切割卷筒纸（30）或使纸幅在其整个宽度上失效的步骤，以便限定具有第一和第二面板的机翼，其中至少一个突出部分从第一面板部分延伸横跨第一和第二面板之间的空间。

4. 发明授权

US08286349B2 Component with a damping filler and method 有权
公开(公告)号：US08286349B2
公开(公告)日：2012-10-16
申请号：US12216502
申请日：2008-07-07
申请人： Keith C. Goldfinch , Oliver M. Strother , Julian Mackechnie-Jarvis
发明人： Keith C. Goldfinch , Oliver M. Strother , Julian Mackechnie-Jarvis
IPC分类号： B21D53/78 , B21D31/04 , B21K3/04
摘要： A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.

5. 发明申请

US20100189933A1 Article with an internal structure 有权
标题翻译：文章内部结构
公开(公告)号：US20100189933A1
公开(公告)日：2010-07-29
申请号：US12654211
申请日：2009-12-14
申请人： Oliver M. Strother
发明人： Oliver M. Strother
IPC分类号： B32B1/06 , B32B37/00 , B23P11/00
CPC分类号： F01D5/16 , B21D26/055 , B21D53/78 , B23P15/04 , F04D29/023 , F04D29/324 , F04D29/668 , F05D2260/96 , F05D2300/43 , Y10S416/50 , Y10T29/49826 , Y10T156/10 , Y10T428/12 , Y10T428/12493 , Y10T428/13 , Y10T428/1352 , Y10T428/1355
摘要： An aerofoil has first and second panels spaced apart from each other to provide a cavity, the cavity containing a damping material, the first panel has at least one protrusion extending therefrom within the cavity towards the second panel, the protrusion having a proximal end and a distal end, wherein the proximal end is secured to the first panel and the distal end is slidably mounted to the second panel.
摘要翻译：机翼具有彼此间隔开的第一和第二面板，以提供空腔，空腔包含阻尼材料，第一面板具有至少一个突出部，该突出部在空腔内朝着第二面板延伸，突出部具有近端和远端，其中所述近端固定到所述第一面板，并且所述远端可滑动地安装到所述第二面板。

6. 发明申请

US20090057489A1 Component with a damping filler 失效
标题翻译：带阻尼填料的零件
公开(公告)号：US20090057489A1
公开(公告)日：2009-03-05
申请号：US12216502
申请日：2008-07-07
申请人： Keith C. Goldfinch , Oliver M. Strother , Julian Mackechnie-Jarvis
发明人： Keith C. Goldfinch , Oliver M. Strother , Julian Mackechnie-Jarvis
IPC分类号： B64C11/24
CPC分类号： B21D53/78 , B23P15/04 , F01D5/147 , F01D5/26 , F04D29/023 , F04D29/324 , F04D29/666 , F04D29/668 , F05D2220/36 , F05D2260/96 , F05D2300/133 , F05D2300/43 , Y10T29/49336 , Y10T29/49337 , Y10T29/49339
摘要： A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.
摘要翻译：一种制造燃气涡轮发动机（10）的机翼的方法。该方法包括以下步骤：提供第一和第二面板（16,18），在第一和第二面板之间提供腹板（30），通过在面板之间施加内部压力来使面板和腹板变形，从而形成一系列由腹板分隔的内腔。该方法还包括在整个宽度上切割卷筒纸（30）或使纸幅在其整个宽度上失效的步骤，以便限定具有第一和第二面板的机翼，其中至少一个突出部分从第一面板部分延伸横跨第一和第二面板之间的空间。

7. 发明申请

US20090057488A1 Component with a damping filler 有权
标题翻译：带阻尼填料的零件
公开(公告)号：US20090057488A1
公开(公告)日：2009-03-05
申请号：US12216497
申请日：2008-07-07
申请人： Keith C. Goldfinch , Oliver M. Strother , Julian MacKechnie-Jarvis
发明人： Keith C. Goldfinch , Oliver M. Strother , Julian MacKechnie-Jarvis
IPC分类号： B64C11/24
CPC分类号： B21D53/78 , B23P15/04 , F01D5/147 , F01D5/26 , F04D29/023 , F04D29/324 , F04D29/666 , F04D29/668 , F05D2220/36 , F05D2260/96 , F05D2300/133 , F05D2300/43 , Y10T29/49336 , Y10T29/49337 , Y10T29/49339
摘要： A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.
摘要翻译：一种制造燃气涡轮发动机（10）的机翼的方法。该方法包括以下步骤：提供第一和第二面板（16,18），在第一和第二面板之间提供腹板（30），通过在面板之间施加内部压力来使面板变形，从而形成内腔。该方法还包括以下步骤：在幅材上提供肋（60）的图案，以便限定具有第一和第二面板的翼面，所述翼面具有至少一个肋（60），所述至少一个肋（60）形成从第一面板部分穿过第一面板第一和第二面板。

8. 发明授权

US08182233B2 Component with a damping filler 有权
标题翻译：带阻尼填料的零件
公开(公告)号：US08182233B2
公开(公告)日：2012-05-22
申请号：US12216503
申请日：2008-07-07
申请人： Keith C. Goldfinch , Oliver M. Strother , Julian Mackechnie-Jarvis
发明人： Keith C. Goldfinch , Oliver M. Strother , Julian Mackechnie-Jarvis
IPC分类号： F04D29/38 , F03D11/02 , B63H1/26 , B63H7/02 , B64C11/16 , B64C27/46 , F01D5/14 , F01D5/08 , F01D5/20 , F03B7/00
CPC分类号： B21D53/78 , B23P15/04 , F01D5/147 , F01D5/26 , F04D29/023 , F04D29/324 , F04D29/666 , F04D29/668 , F05D2220/36 , F05D2260/96 , F05D2300/133 , F05D2300/43 , Y10T29/49336 , Y10T29/49337 , Y10T29/49339
摘要： A component (10) and method for manufacturing a component. The component comprises first and second panels (16, 18) spaced apart from each other, the first panel (16) having at least one protrusion (20) extending therefrom towards the second panel (18). The protrusion (20) extends partially across the space (19) between the first and second panels so as to define a free end of the protrusion. The free end is surrounded by damping material (24).
摘要翻译：一种部件（10）及其制造方法。该组件包括彼此间隔开的第一和第二面板（16,18），第一面板（16）具有从其向第二面板（18）延伸的至少一个突起（20）。突起（20）部分地延伸穿过第一和第二面板之间的空间（19），以便限定突起的自由端。自由端由阻尼材料（24）包围。

9. 发明申请

US20090060718A1 Component with a damping filler 有权
标题翻译：带阻尼填料的零件
公开(公告)号：US20090060718A1
公开(公告)日：2009-03-05
申请号：US12216503
申请日：2008-07-07
申请人： Keith C. Goldfinch , Oliver M. Strother , Julian MacKechnie-Jarvis
发明人： Keith C. Goldfinch , Oliver M. Strother , Julian MacKechnie-Jarvis
IPC分类号： F01D25/06 , B23P15/04
CPC分类号： B21D53/78 , B23P15/04 , F01D5/147 , F01D5/26 , F04D29/023 , F04D29/324 , F04D29/666 , F04D29/668 , F05D2220/36 , F05D2260/96 , F05D2300/133 , F05D2300/43 , Y10T29/49336 , Y10T29/49337 , Y10T29/49339
摘要： A component (10) and method for manufacturing a component. The component comprises first and second panels (16, 18) spaced apart from each other, the first panel (16) having at least one protrusion (20) extending therefrom towards the second panel (18). The protrusion (20) extends partially across the space (19) between the first and second panels so as to define a free end of the protrusion. The free end is surrounded by damping material (24).
摘要翻译：一种部件（10）及其制造方法。该组件包括彼此间隔开的第一和第二面板（16,18），第一面板（16）具有从其向第二面板（18）延伸的至少一个突起（20）。突起（20）部分地延伸穿过第一和第二面板之间的空间（19），以便限定突起的自由端。自由端由阻尼材料（24）包围。

10. 发明授权

US08701286B2 Rotationally balancing a rotating part 有权
标题翻译：旋转平衡旋转部件
公开(公告)号：US08701286B2
公开(公告)日：2014-04-22
申请号：US13114382
申请日：2011-05-24
申请人： Oliver M. Strother
发明人： Oliver M. Strother
IPC分类号： B21K25/00 , B23K15/04 , B63H1/26
CPC分类号： F01D5/027 , F01D5/34 , Y02T50/671 , Y10T29/4932 , Y10T29/49321 , Y10T29/49325
摘要： A method is provided of rotationally balancing a rotating part. A rotor hub or ring and a plurality of rotor blades for assembly onto the hub or ring are provided, each blade having an unfilled internal cavity. The respective masses and moment weights of the blades with filled internal cavities are then predicted. Next, the rotor blades are assembled onto the hub or ring to form the rotating part. The relative positions of the assembled blades are determined on the basis of their predicted masses and moment weights with filled internal cavities. The internal cavities of the assembled rotor blades are then filled.
摘要翻译：提供旋转平衡旋转部件的方法。提供了用于组装到轮毂或环上的转子轮毂或环和多个转子叶片，每个叶片具有未填充的内部空腔。然后预测具有填充的内部空腔的叶片的相应质量和力矩重量。接下来，将转子叶片组装到轮毂或环上以形成旋转部件。组合叶片的相对位置是根据它们预测的质量和填充内腔的力矩来确定的。然后填充组装的转子叶片的内部空腔。

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