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公开(公告)号：US06416280B1
公开(公告)日：2002-07-09
申请号：US09723113
申请日：2000-11-27
申请人： James Michael Forrester , Joseph Timothy Stevenson , Jeffrey Clayton Potter , Sean Joel Corrigan
发明人： James Michael Forrester , Joseph Timothy Stevenson , Jeffrey Clayton Potter , Sean Joel Corrigan
IPC分类号： B64C1114
CPC分类号： F01D5/3007 , B64C11/14 , F02C7/04 , Y02T50/671 , Y02T50/673
摘要： An exemplary embodiment of the invention is a spinner for a front end of a fan assembly of a gas turbine engine. The spinner includes a single piece substantially conically shaped hollow body circumscribed about a centerline extending aftwardly from a tip to an axially aft spinner end. A plurality of bolt holes extend axially parallel to the centerline through the hollow body at an axial location between the tip and the aft spinner end. The hollow body may include a forward conical section extending aftwardly from the tip to a transition section, an aft conical section extending aftwardly from the transition section to the aft spinner end, and the bolt holes are axially located in the transition section. An aft spinner flange attached to the axially aft spinner end includes a plurality of flange lightening holes axially disposed through the aft spinner flange and the flange lightening holes.
摘要翻译： 本发明的示例性实施例是用于燃气涡轮发动机的风扇组件的前端的旋转器。 旋转器包括一个基本上圆锥形的中空体的单件，其围绕从顶端向后轴向延伸端延伸的中心线环绕。 多个螺栓孔在尖端和后端旋转器端之间的轴向位置处通过中空体轴向平行于中心线延伸。 中空体可以包括从尖端向过渡部分向后延伸的前锥形部分，从过渡部分向后延伸到后旋转端部的后圆锥部分，并且螺栓孔轴向地位于过渡部分中。 附接到轴向后端旋转端的后旋转凸缘包括多个凸缘加亮孔，其沿轴向设置穿过后旋转凸缘和凸缘减光孔。
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公开(公告)号：US06634863B1
公开(公告)日：2003-10-21
申请号：US09723111
申请日：2000-11-27
申请人： James Michael Forrester , Joseph Timothy Stevenson , Jeffrey Clayton Potter , Sean Joel Corrigan
发明人： James Michael Forrester , Joseph Timothy Stevenson , Jeffrey Clayton Potter , Sean Joel Corrigan
IPC分类号： F01D532
CPC分类号： F01D5/323 , F01D5/06 , F01D11/008 , F01D21/045 , Y02T50/671
摘要： A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to a forward extension of the disk at a location between a tip and an axially aft spinner end of the spinner. Non-integral platforms circumferentially disposed between the fan blades. A booster spool is connected to the rotor disk by a mounting plate therebetween and the platforms are radially retained to the disk and mounting plates by pins through holes in mounting lugs depending radially inwardly from the platforms. Pairs of circumferentially oppositely facing retaining slots have retainers disposed therein which extend across the dovetail slots to axially retain the dovetail roots in the dovetail slots.
摘要翻译： 燃气涡轮发动机转子盘具有围绕中心线限定的多个环形毂，并且每个轮毂通过腹板连接到盘形边缘。 多个周向间隔开的圆弧燕尾槽穿过边缘设置。 周向延伸的环形裂缝槽径向延伸穿过边缘进入每个相邻的一对腹板之间的燕尾槽。 风扇叶片具有设置在周向间隔开的圆弧燕尾槽内的圆弧形燕尾根。 在旋转器的尖端和轴向后旋转器端之间的位置附接到盘的前延伸部的单件旋转器。 周向设置在风扇叶片之间的非整体平台。 辅助卷轴通过其间的安装板连接到转子盘，并且平台通过销穿过安装凸耳的孔径向保持到盘和安装板，安装凸耳从平台径向向内。 成对的周向相对的保持狭槽具有设置在其中的保持器，其延伸穿过燕尾槽，以将燕尾根轴向保持在燕尾槽中。
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公开(公告)号：US06447250B1
公开(公告)日：2002-09-10
申请号：US09723108
申请日：2000-11-27
申请人： Sean Joel Corrigan , Jeffrey Clayton Potter , Joseph Timothy Stevenson , Jay L. Cornell , James Michael Forrester , Rolf Robert Hetico
发明人： Sean Joel Corrigan , Jeffrey Clayton Potter , Joseph Timothy Stevenson , Jay L. Cornell , James Michael Forrester , Rolf Robert Hetico
IPC分类号： F01D522
CPC分类号： F01D5/3007 , F01D5/323 , F01D11/008 , F01D21/045 , F04D29/321 , F05D2240/80 , F05D2250/292 , F05D2250/70 , Y02T50/671
摘要： A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to a forward extension of the disk at a location between a tip and an axially aft spinner end of the spinner. Non-integral platforms circumferentially disposed between the fan blades. A booster spool is connected to the rotor disk by a mounting plate therebetween and the platforms are radially retained to the disk and mounting plates by pins through holes in mounting lugs depending radially inwardly from the platforms. Pairs of circumferentially oppositely facing retaining slots have retainers disposed therein which extend across the dovetail slots to axially retain the dovetail roots in the dovetail slots.
摘要翻译： 燃气涡轮发动机转子盘具有围绕中心线限定的多个环形毂，并且每个轮毂通过腹板连接到盘形边缘。 多个周向间隔开的圆弧燕尾槽穿过边缘设置。 周向延伸的环形裂缝槽径向延伸穿过边缘进入每个相邻的一对腹板之间的燕尾槽。 风扇叶片具有设置在周向间隔开的圆弧燕尾槽内的圆弧形燕尾根。 在旋转器的尖端和轴向后旋转器端之间的位置附接到盘的前延伸部的单件旋转器。 周向设置在风扇叶片之间的非整体平台。 辅助卷轴通过其间的安装板连接到转子盘，并且平台通过销穿过安装凸耳的孔径向保持到盘和安装板，安装凸耳从平台径向向内。 成对的周向相对的保持狭槽具有设置在其中的保持器，其延伸穿过燕尾槽，以将燕尾根轴向保持在燕尾槽中。
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公开(公告)号：US06520742B1
公开(公告)日：2003-02-18
申请号：US09723109
申请日：2000-11-27
IPC分类号： F01D532
CPC分类号： F01D5/326 , F01D5/06 , F01D11/008 , F01D21/045 , F05D2250/141 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart dovetail slots are disposed through the rim, extending circumferentially between disk posts, extending axially from a forward end to an aft end of the rim, and extending radially inwardly from a disk outer surface of the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. In the exemplary embodiment of the disk illustrated herein, the dovetail slots are circular arc dovetail slots. An axially forwardly extending overhang is located radially outwardly on each of the disk posts and a chamfer is on a radially outer corner of the each of the disk posts on a portion of the overhangs. A plurality of post holes extending axially aftwardly into the rim wherein each of the post hole extends axially aftwardly into a corresponding one of the disk posts.
摘要翻译： 燃气涡轮发动机转子盘具有围绕中心线限定的多个环形毂，并且每个轮毂通过腹板连接到盘形边缘。 多个周向间隔开的燕尾槽设置成穿过轮缘，沿圆周方向延伸，在圆柱之间，从轮缘的前端轴向延伸到后端，并从轮缘的盘外表面径向向内延伸。 周向延伸的环形裂缝槽径向延伸穿过边缘进入每个相邻的一对腹板之间的燕尾槽。 在本文所示的盘的示例性实施例中，燕尾槽是圆弧燕尾槽。 轴向向前延伸的突出部沿径向向外位于每个盘柱上，并且倒角位于突出部分上的每个盘柱的径向外角上。 多个柱孔轴向向后延伸到边缘中，其中每个柱孔轴向向后延伸到相应的一个盘柱中。
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公开(公告)号：US06884507B2
公开(公告)日：2005-04-26
申请号：US10366257
申请日：2003-02-13
申请人： Wendy Wen-Ling Lin , Scott Roger Finn , Kevin Warner Flanagan , Joseph Timothy Stevenson , James Claude Carnahan
发明人： Wendy Wen-Ling Lin , Scott Roger Finn , Kevin Warner Flanagan , Joseph Timothy Stevenson , James Claude Carnahan
CPC分类号： F01D5/147 , C08G18/10 , C08G2101/00 , C08J9/32 , C08J2203/22 , C08J2375/04 , F01D5/28 , Y02T50/672 , Y02T50/673 , Y10T428/2985 , C08G18/3814
摘要： The present invention provides tough, high modulus, low density thermoset polyurethane compositions which are useful in general as, for example, cast structural materials and in a preferred embodiment can be cured directly onto an aircraft engine fan blade, thereby providing a lighter blade, without concomitant loss in structural integrity or blade performance due to, for example, resistance to foreign object impacts and fuel efficiency. In a preferred embodiment, the composition is comprised of bis-amine compounds reacted with isocyanate-functional polyether polymers in the presence of hollow polymeric microspheres. The thermoset polymer compositions are formed by casting into a mold which is formed by a cavity within the metallic or composite fan blade or guide vane in the form of a pocket and a removable caul sheet. After the elastomeric polyurethane foam is injected through at least one injector port into the mold, the foam is cured.
摘要翻译： 本发明提供了韧性，高模量，低密度的热固性聚氨酯组合物，其通常可用于例如铸造结构材料，并且在优选实施方案中可直接固化到飞机发动机风扇叶片上，从而提供较轻的叶片，而不需要 结构完整性或叶片性能的伴随损失，例如由于抵抗异物影响和燃油效率。 在优选的实施方案中，组合物由在中空聚合物微球存在下与异氰酸酯官能的聚醚聚合物反应的双 - 胺化合物组成。 热固性聚合物组合物通过浇铸到由金属或复合风扇叶片或导向叶片内的空腔形成的模具形成，其形式为口袋和可移除的盖板。 在通过至少一个注射器端口将弹性体聚氨酯泡沫注入到模具中之后，泡沫体被固化。
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公开(公告)号：US06364616B1
公开(公告)日：2002-04-02
申请号：US09567553
申请日：2000-05-05
IPC分类号： B64C1116
CPC分类号： F01D5/16 , B64C11/00 , F01D5/147 , F05D2250/292 , F05D2250/711 , Y02T50/672 , Y02T50/673
摘要： A fan blade includes a metal airfoil having a pocket disposed in a first side thereof, with the pocket including a filler bonded thereto. The pocket includes a plurality of cells separated by corresponding ribs which are submerged in the filler.
摘要翻译： 风扇叶片包括具有设置在其第一侧中的袋的金属翼型件，其中袋包括与其结合的填料。 口袋包括多个细胞，这些细胞被浸没在填料中的相应的肋分开。
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