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公开(公告)号：US6039542A
公开(公告)日：2000-03-21
申请号：US997832
申请日：1997-12-24
CPC分类号： F01D5/16 , F05D2220/36 , Y02T50/672 , Y02T50/673 , Y10S416/50
摘要： A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and a tip, and axially between a leading edge and a trailing edge. The airfoil further includes a pocket disposed in the first side having an elastomeric filler bonded therein. A panel is bonded to the filler along the pocket for allowing differential movement therebetween for damping vibratory response of the airfoil.
摘要翻译： 风扇叶片包括具有在根部和尖端之间径向延伸的第一和第二相对侧以及在前缘和后缘之间的轴向的金属翼型件。 机翼还包括设置在第一侧中的口袋，其中粘合有弹性体填料。 面板沿着口袋粘合到填料上，以允许它们之间的差动运动来阻止翼型的振动响应。
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公开(公告)号：US08172518B2
公开(公告)日：2012-05-08
申请号：US11617911
申请日：2006-12-29
CPC分类号： F01D5/20 , F01D5/147 , F05D2250/314 , Y10T29/49318 , Y10T29/49321 , Y10T29/49325 , Y10T29/49336
摘要： A method for assembling a rotor assembly and a rotor assembly are provided. The method comprises providing a rotor blade including a first sidewall, a second sidewall, where the first and second sidewalls are connected at a leading edge and a trailing edge and extend in span from a root portion to a tip portion, removing blade material from the tip portion to form a tip portion rake angle that enables the tip portion to extend obliquely between the first and second sidewalls, and coupling the rotor blade to a shaft such that during tip rubs the tip portion rake angle facilitates reducing radial loading induced to the blade during tip rubs.
摘要翻译： 提供了组装转子组件和转子组件的方法。 该方法包括提供包括第一侧壁和第二侧壁的转子叶片，其中第一和第二侧壁在前缘和后缘处连接，并且从根部到顶端部分的跨度延伸， 尖端部分以形成尖端部前角，其能够使尖端部分在第一和第二侧壁之间倾斜地延伸，并且将转子叶片联接到轴上，使得在末端摩擦期间尖端部分前角有助于减小引起叶片的径向负载 在尖端磨擦。
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公开(公告)号：US6033186A
公开(公告)日：2000-03-07
申请号：US293383
申请日：1999-04-16
CPC分类号： F01D5/16 , B63H1/26 , B64C11/00 , F01D5/34 , F05D2250/25 , F05D2300/431 , Y02T50/672 , Y02T50/673
摘要： A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.
摘要翻译： 风扇叶片包括具有在根部和尖端之间径向延伸的第一和第二相对侧以及在前缘和后缘之间轴向延伸的金属翼型件。 翼型件还包括设置在第一侧中并由相应的肋分开的多个袋。 填料结合在口袋中，与翼型件第一面共同延伸。 径向和对角肋分别彼此相交，以选择性地增加扭转和弯曲刚度，以增加相邻扭转和弯曲共振振动模式之间的频率裕度。
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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：US07445427B2
公开(公告)日：2008-11-04
申请号：US11294150
申请日：2005-12-05
申请人： James Edward Gutknecht , Robert William Bruce , Jay L. Cornell , Donald Charles Slavik , Wayne Ray Bowen , William Terence Dingwell
发明人： James Edward Gutknecht , Robert William Bruce , Jay L. Cornell , Donald Charles Slavik , Wayne Ray Bowen , William Terence Dingwell
IPC分类号： F01D17/16
CPC分类号： F01D17/162 , F04D29/563 , F05D2230/90 , F05D2300/133 , F05D2300/224 , F05D2300/2263 , F05D2300/50211 , F05D2300/611
摘要： A variable stator vane assembly and a bushing thereof. The bushing includes a metal bushing body and a wear-resistant coating. The assembly includes a rotatable trunnion and a first metal bushing. The trunnion is capable of being located in a through hole extending between outer and inner surfaces of a compressor casing of a gas turbine engine. The first metal bushing is capable of being located in the through hole proximate the outer surface to surround a first portion of the trunnion when the trunnion is located in the through hole. The first metal bushing and the first portion have wear-resistant coatings which are in mutual contact, apart from any intervening lubricant, when the trunnion and the first metal bushing are located in the through hole and the trunnion is rotating with respect to the first metal bushing.
摘要翻译： 可变定子叶片组件及其衬套。 衬套包括金属衬套主体和耐磨涂层。 组件包括可旋转的耳轴和第一金属衬套。 耳轴能够位于在燃气涡轮发动机的压缩机壳体的外表面和内表面之间延伸的通孔中。 当耳轴位于通孔中时，第一金属衬套能够位于邻近外表面的通孔中以围绕耳轴的第一部分。 当耳轴和第一金属衬套位于通孔中并且耳轴相对于第一金属旋转时，第一金属衬套和第一部分具有与任何中间润滑剂相互接触的耐磨涂层 衬套。
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公开(公告)号：US20080159869A1
公开(公告)日：2008-07-03
申请号：US11617911
申请日：2006-12-29
IPC分类号： F01D5/14
CPC分类号： F01D5/20 , F01D5/147 , F05D2250/314 , Y10T29/49318 , Y10T29/49321 , Y10T29/49325 , Y10T29/49336
摘要： In one aspect, a method for assembling a rotor assembly is provided. The method comprises providing a rotor blade including a first sidewall, a second sidewall, where the first and second sidewalls are connected at a leading edge and a trailing edge and extend in span from a root portion to a tip portion, removing blade material from the tip portion to form a tip portion rake angle that enables the tip portion to extend obliquely between the first and second sidewalls, and coupling the rotor blade to a shaft such that during tip rubs the tip portion rake angle facilitates reducing radial loading induced to the blade during tip rubs.
摘要翻译： 一方面，提供了组装转子组件的方法。 该方法包括提供包括第一侧壁和第二侧壁的转子叶片，其中第一和第二侧壁在前缘和后缘处连接，并且从根部到顶端部分的跨度延伸， 尖端部分以形成尖端部前角，其能够使尖端部分在第一和第二侧壁之间倾斜地延伸，并且将转子叶片联接到轴上，使得在末端摩擦期间尖端部分前角有助于减小引起叶片的径向负载 在尖端磨擦。
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7.发明授权公开(公告)号：US06579065B2
公开(公告)日：2003-06-17
申请号：US09951912
申请日：2001-09-13
IPC分类号： F01D522
CPC分类号： F01D11/006 , Y10T29/49321
摘要： A rotor assembly for a gas turbine engine includes a plurality of radially extending and circumferentially spaced rotor blades and a seal. Each of the blades includes a platform including a radially outer surface and a radially inner surface. The platform radially outer surface defines a surface for fluid flowing thereover. The seal includes at least one hollow member coupled to each rotor blade platform radially inner surface that is configured to reduce fluid flow through a gap defined between adjacent rotor blades.
摘要翻译： 用于燃气涡轮发动机的转子组件包括多个径向延伸且周向间隔开的转子叶片和密封件。 每个叶片包括包括径向外表面和径向内表面的平台。 平台径向外表面限定了用于在其上流动的流体的表面。 密封件包括联接到每个转子叶片平台径向内表面的至少一个中空构件，其构造成减少通过相邻转子叶片之间限定的间隙的流体流动。
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公开(公告)号：US5947688A
公开(公告)日：1999-09-07
申请号：US995975
申请日：1997-12-22
CPC分类号： F01D5/147 , F01D5/16 , F05D2240/80 , Y02T50/672 , Y02T50/673
摘要： A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.
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公开(公告)号：US5439354A
公开(公告)日：1995-08-08
申请号：US76668
申请日：1993-06-15
申请人： Kurt L. Hansen , Jay L. Cornell , Jan C. Schilling
发明人： Kurt L. Hansen , Jay L. Cornell , Jan C. Schilling
CPC分类号： F01D5/147
摘要： Hollow airfoils, such as fan blades, nozzles and struts used in axial flow gas turbine engines, that have improved resistance to impact from foreign objects are disclosed. Relocation of airfoil material is used to preferentially strengthen the airfoil to respond to the stress from the impact of a foreign object. Internal spacers are redistributed toward the leading edge and the material from the skin of the concave side and the convex side is shifted from one side to the other and toward the leading edge of the airfoil where impact stress is greatest.
摘要翻译： 公开了具有改进的抵抗异物冲击的空心翼型件，例如用于轴流式燃气涡轮发动机中的风扇叶片，喷嘴和支柱。 翼型材料的重新定位用于优先加强翼型件以应对异物冲击的应力。 内部间隔件朝向前缘重新分配，并且来自凹面侧和外侧的皮肤的材料从冲击应力最大的翼面的一侧向另一侧移动并朝向翼型的前缘移动。
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公开(公告)号：US4483661A
公开(公告)日：1984-11-20
申请号：US490820
申请日：1983-05-02
申请人： Gary B. Manharth , Jay L. Cornell
发明人： Gary B. Manharth , Jay L. Cornell
摘要： Gas turbine engines are used as powerplants for aircraft. When the aircraft are parked on the ground, the wind can blow through the engines and set fans and rotors into motion, i.e., windmill them. Given that the blades of the fans and rotors are loosely fastened to their rotors, the low speed rotation caused by windmilling causes the blades to clatter or clank, thus causing wear. The present invention provides means for clamping blades into position during this low speed rotation for reducing clanking.
摘要翻译： 燃气涡轮发动机用作飞机的动力装置。 当飞机停在地面上时，风可以吹过发动机，并使风扇和转子运动，即风车。 假设风扇和转子的叶片松动地固定在转子上，则由风车造成的低速旋转会导致叶片发生咔嗒声或咔嗒声，从而导致磨损。 本发明提供了用于在该低速旋转期间将叶片夹紧到适当位置以减少cl铐的装置。
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