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公开(公告)号：US07018168B2
公开(公告)日：2006-03-28
申请号：US10820491
申请日：2004-04-08
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , F05D2250/312 , F05D2250/314 , F05D2300/6034 , F05D2300/614
摘要： A method facilitates fabricating a gas turbine engine. The method comprises coupling an engine casing circumferentially around a gas turbine engine. The method also comprises coupling an engine containment wrap to the gas turbine engine, such that the containment wrap circumscribes at least a portion of the gas turbine engine casing, wherein the containment wrap includes a plurality of layers coupled together such that a first layer is formed from at least three sheets coupled together such that the first sheet fibers are oriented substantially in a first direction, such that the second sheet fibers are oriented in a second direction that is offset approximately forty-five degrees from the first sheet, and such that the third sheet fibers are oriented substantially parallel to the first direction, and wherein the plurality of first sheet fibers are aligned substantially axially with the respect to the turbine engine.
摘要翻译： 一种方法有助于制造燃气涡轮发动机。 该方法包括将发动机壳体围绕燃气涡轮发动机周向连接。 该方法还包括将发动机容纳包装件连接到燃气涡轮发动机，使得容纳包装限定燃气涡轮发动机壳体的至少一部分，其中，所述安全壳包括耦合在一起的多个层，从而形成第一层 从至少三个片材联接在一起，使得第一片材纤维基本上沿第一方向取向，使得第二片纤维在与第一片材偏离大约四十五度的第二方向上取向，并且使得 第三片纤维基本上平行于第一方向定向，并且其中多个第一片纤维相对于涡轮发动机基本轴向对准。
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公开(公告)号：US08727721B2
公开(公告)日：2014-05-20
申请号：US12982411
申请日：2010-12-30
IPC分类号： F01D9/04
CPC分类号： F01D5/282 , F01D5/147 , F01D9/041 , F02C7/04 , F02K3/06 , F05D2260/30 , F05D2300/603 , Y02T50/672
摘要： A vane includes a composite airfoil having one or more pockets and one or more spars received therein respectively. The spars extending radially away from a bridge of a vane mount supporting airfoil. The spars may be integrally formed with the bridge. The spars may be adhesively bonded to the composite airfoil within the pockets. A passage may extend between an airfoil base and an airfoil tip. A gas turbine engine annular fan frame includes an annular row of the composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.
摘要翻译： 叶片包括分别容纳有一个或多个凹穴和一个或多个翼梁的复合翼型件。 翼梁从叶片安装支撑翼型的桥梁径向延伸。 翼梁可以与桥一体形成。 翼片可以在袋内粘合到复合翼型件上。 通道可以在翼型基座和翼型端头之间延伸。 燃气涡轮发动机环形风扇框架包括在风扇框架的径向内部和外部环之间径向延伸的复合出口导向叶片的环形排。
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公开(公告)号：US20120171025A1
公开(公告)日：2012-07-05
申请号：US12982448
申请日：2010-12-30
CPC分类号： F01D5/147 , F01D5/141 , F01D5/282 , F02C7/04 , F02K3/06 , F05D2260/30 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars may be integrally formed with the bridge and adhesively bonded to the composite airfoil within the pockets with a passage extending between an airfoil base and an airfoil tip. A metallic leading edge tip may be disposed along the leading edge of the composite airfoil. A gas turbine engine annular fan frame incorporates the vanes in an annular row of composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.
摘要翻译： 叶片包括具有一个或多个外袋和分别容纳在其中的一个或多个外梁的复合翼型件。 从外部叶片的外部桥梁径向向内延伸的外部翼梁安装向外支撑翼型件。 翼梁可以与桥一体地形成，并且在袋内具有通过在翼型基部和翼型端之间延伸的通道粘合地粘合到复合翼型件上。 金属前缘尖端可以沿着复合翼型件的前缘设置。 燃气涡轮发动机环形风扇框架将叶片结合在环形排的复合出口导向叶片中，该导管叶片径向延伸并连接到风扇框架的径向内外环之间。
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4.发明授权Methods and apparatus for fabricating a fan assembly for use with turbine engines 有权用于制造与涡轮发动机一起使用的风扇组件的方法和装置公开(公告)号：US07972109B2
公开(公告)日：2011-07-05
申请号：US11646826
申请日：2006-12-28
申请人： David William Crall , Frank Worthoff , Daniel Edward Mollmann , Nicholas Joseph Kray , Max Farson
发明人： David William Crall , Frank Worthoff , Daniel Edward Mollmann , Nicholas Joseph Kray , Max Farson
IPC分类号： F01D11/12
CPC分类号： F01D21/045 , F01D5/20 , F01D11/122 , F02K3/06 , F04D29/522 , F05D2220/36 , F05D2300/603 , F05D2300/615 , Y02T50/672 , Y10T29/49316
摘要： A method for fabricating a fan assembly is provided, wherein the method includes providing a rotor having a plurality of rotor blades. At least one rotor blade is fabricated from a frangible material. The method also includes coupling a casing substantially circumferentially about the rotor, and positioning the casing a distance from the plurality of rotor blades. The distance is selected to facilitate increasing an amount of initial resistance created between the casing and the plurality of rotor blades after a bladeout.
摘要翻译： 提供了一种用于制造风扇组件的方法，其中所述方法包括提供具有多个转子叶片的转子。 至少一个转子叶片由易碎材料制成。 该方法还包括基本上围绕转子周向地联接壳体，以及将壳体定位成距离多个转子叶片的距离。 选择该距离以便于在刮除之后增加壳体与多个转子叶片之间产生的初始阻力的量。
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公开(公告)号：US20120171028A1
公开(公告)日：2012-07-05
申请号：US12982411
申请日：2010-12-30
IPC分类号： F01D9/04
CPC分类号： F01D5/282 , F01D5/147 , F01D9/041 , F02C7/04 , F02K3/06 , F05D2260/30 , F05D2300/603 , Y02T50/672
摘要： A vane includes a composite airfoil having one or more pockets and one or more spars received therein respectively. The spars extending radially away from a bridge of a vane mount supporting airfoil. The spars may be integrally formed with the bridge. The spars may be adhesively bonded to the composite airfoil within the pockets. A passage may extend between an airfoil base and an airfoil tip. A gas turbine engine annular fan frame includes an annular row of the composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.
摘要翻译： 叶片包括分别容纳有一个或多个凹穴和一个或多个翼梁的复合翼型件。 翼梁从叶片安装支撑翼型的桥梁径向延伸。 翼梁可以与桥一体形成。 翼片可以在袋内粘合到复合翼型件上。 通道可以在翼型基座和翼型端头之间延伸。 燃气涡轮发动机环形风扇框架包括在风扇框架的径向内部和外部环之间径向延伸的复合出口导向叶片的环形排。
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公开(公告)号：US08690531B2
公开(公告)日：2014-04-08
申请号：US12982448
申请日：2010-12-30
IPC分类号： F01D9/04
CPC分类号： F01D5/147 , F01D5/141 , F01D5/282 , F02C7/04 , F02K3/06 , F05D2260/30 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars may be integrally formed with the bridge and adhesively bonded to the composite airfoil within the pockets with a passage extending between an airfoil base and an airfoil tip. A metallic leading edge tip may be disposed along the leading edge of the composite airfoil. A gas turbine engine annular fan frame incorporates the vanes in an annular row of composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.
摘要翻译： 叶片包括具有一个或多个外袋和分别容纳在其中的一个或多个外梁的复合翼型件。 从外部叶片的外部桥梁径向向内延伸的外部翼梁安装向外支撑翼型件。 翼梁可以与桥一体地形成，并且在袋内具有通过在翼型基部和翼型端之间延伸的通道粘合地粘合到复合翼型件上。 金属前缘尖端可以沿着复合翼型件的前缘设置。 燃气涡轮发动机环形风扇框架将叶片结合在环形排的复合出口导向叶片中，该导管叶片径向延伸并连接到风扇框架的径向内外环之间。
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7.发明申请Methods and apparatus for fabricating a fan assembly for use with turbine engines 有权用于制造与涡轮发动机一起使用的风扇组件的方法和装置公开(公告)号：US20080159854A1
公开(公告)日：2008-07-03
申请号：US11646826
申请日：2006-12-28
申请人： David William Crall , Frank Worthoff , Daniel Edward Mollmann , Nicholas Joseph Kray , Max Farson
发明人： David William Crall , Frank Worthoff , Daniel Edward Mollmann , Nicholas Joseph Kray , Max Farson
IPC分类号： F01D1/00
CPC分类号： F01D21/045 , F01D5/20 , F01D11/122 , F02K3/06 , F04D29/522 , F05D2220/36 , F05D2300/603 , F05D2300/615 , Y02T50/672 , Y10T29/49316
摘要： A method for fabricating a fan assembly is provided, wherein the method includes providing a rotor having a plurality of rotor blades. At least one rotor blade is fabricated from a frangible material. The method also includes coupling a casing substantially circumferentially about the rotor, and positioning the casing a distance from the plurality of rotor blades. The distance is selected to facilitate increasing an amount of initial resistance created between the casing and the plurality of rotor blades after a bladeout.
摘要翻译： 提供了一种用于制造风扇组件的方法，其中所述方法包括提供具有多个转子叶片的转子。 至少一个转子叶片由易碎材料制成。 该方法还包括基本上围绕转子周向地联接壳体，以及将壳体定位成距离多个转子叶片的距离。 选择该距离以便于在刮除之后增加壳体与多个转子叶片之间产生的初始阻力的量。
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公开(公告)号：US08550776B2
公开(公告)日：2013-10-08
申请号：US12845261
申请日：2010-07-28
申请人： Seth Alexander McDonald , William James Strock , Courtney James Tudor , William Howard Hasting , Frank Worthoff
发明人： Seth Alexander McDonald , William James Strock , Courtney James Tudor , William Howard Hasting , Frank Worthoff
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D5/282 , F04D29/023 , F04D29/542 , F04D29/644 , F05D2220/36 , F05D2250/23 , F05D2250/294 , F05D2260/31 , F05D2260/38 , F05D2300/603 , Y02T50/672
摘要： A vane includes a composite airfoil having chordwise spaced apart forward and aft dovetail feet at or near leading and trailing edges of the airfoil. Each foot includes a shank connecting a dovetail root to an airfoil base and each root is slidably received in a dovetail slot in an inner vane mount. The dovetail slot has a triangular slot cross section and a flat slot bottom and flat slot pressure and suction side crush faces corresponding to pressure and suction sides of the airfoil. The dovetail root having a triangular root cross section and a flat root bottom and flat dovetail root pressure and suction side crush faces. A biasing means urges the root bottom of the dovetail roots away from the slot bottom and presses and preloads the dovetail root pressure and suction side crush faces against the slot pressure and suction side slot crush faces.
摘要翻译： 叶片包括在翼型件的前缘和后缘处或其附近具有弦向间隔开的前后燕尾脚的复合翼型件。 每个脚包括将燕尾根连接到翼型基部的柄，并且每个根部可滑动地容纳在内叶片安装件中的燕尾槽中。 燕尾槽具有三角形槽横截面和平坦的槽底部以及对应于翼型的压力和吸力侧的平坦的槽压力和吸力侧的挤压面。 燕尾根具有三角形根部横截面和平底根部，扁平的燕尾根压力和吸力侧面。 偏压装置促使燕尾根的根部底部远离槽底，并将燕尾根压力和吸力侧挤压面按压并预加载在槽压力和吸力侧槽挤压面上。
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公开(公告)号：US06561760B2
公开(公告)日：2003-05-13
申请号：US09932595
申请日：2001-08-17
申请人： Aspi Rustom Wadia , Kenneth Edward Seitzer , Harjit Singh Hura , Frank Worthoff , Raymond Gust Holm , Eric Pierre Masse , Jason Corey Slagle
发明人： Aspi Rustom Wadia , Kenneth Edward Seitzer , Harjit Singh Hura , Frank Worthoff , Raymond Gust Holm , Eric Pierre Masse , Jason Corey Slagle
IPC分类号： F01D2510
CPC分类号： F02C7/047 , F01D25/02 , F04D29/584 , Y02T50/672
摘要： A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.
摘要翻译： 增压压缩机包括从护罩支撑的入口导向叶片。 壳体围绕护罩并且限定歧管。 分流器鼻部包括容纳护罩的前柄柄的凹槽，其间具有限定用于歧管的出口的间隙。 热空气被引导通过歧管，并从分流器鼻部引导以进行除冰。
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公开(公告)号：US08826957B2
公开(公告)日：2014-09-09
申请号：US13600780
申请日：2012-08-31
申请人： Sultan Shair , Julian Thomas O'Flynn , Mathias Messmer , Frank Worthoff , Mile Ostojic , Mark E. Vermilyea
发明人： Sultan Shair , Julian Thomas O'Flynn , Mathias Messmer , Frank Worthoff , Mile Ostojic , Mark E. Vermilyea
IPC分类号： B29C65/40 , B29C63/48 , B32B37/26 , B32B41/00 , B29C65/78 , B29C65/00 , B29C65/20 , B29C65/18 , B32B38/18 , B65H41/00
CPC分类号： B32B37/0007 , B29C33/68 , B29C65/18 , B29C65/20 , B29C65/78 , B29C66/004 , B29C66/80 , B29C66/83413 , B29C70/38 , B32B37/0053 , B32B37/02 , B32B37/144 , B32B37/146 , B32B37/26 , B32B38/0036 , B32B38/1858 , B32B2037/262 , B32B2305/022 , B32B2305/024 , B32B2305/77 , B32B2309/12 , B65H41/00 , Y10T156/16 , Y10T156/17 , Y10T156/1994
摘要： A method for applying at least one ply onto a tool or an uncured composite layup disposed on the tool includes automatically controlling slidably removing at least one nonstick separator relative to the at least one ply positioned on the at least one nonstick separator to inhibit at least a portion of the at least one ply from adhering to the tool or uncured composite layup while applying a moving compressive force to an outer surface of the at least one ply relative to a moving trailing edge of the at least one nonstick separator to adhere at least a portion of the at least one ply to the tool or to the uncured composite layup.
摘要翻译： 用于将至少一层施加到设置在工具上的工具或未固化的复合叠层上的方法包括自动控制相对于位于至少一个不粘分离器上的至少一层的至少一个不粘分离器滑动地移除，以至少抑制 所述至少一个帘布层的一部分粘附到所述工具或未固化的复合材料叠层上，同时相对于所述至少一个不粘分离器的移动后缘施加移动的压缩力至所述至少一个帘布层的外表面，以将至少一个 所述至少一层的所述部分至所述工具或所述未固化复合材料叠层。
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