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1.发明授权Turbine support assembly including turbine heat shield and bolt retainer assembly 失效涡轮支架组件，包括涡轮隔热罩和螺栓保持架组件
公开(公告)号：US5211541A
公开(公告)日：1993-05-18
申请号：US841154
申请日：1992-02-25
申请人： Steve R. Fledderjohn , James C. Przytulski , Sidney B. Elston, III , Alan R. Gilchrist , Ambrose A. Hauser
发明人： Steve R. Fledderjohn , James C. Przytulski , Sidney B. Elston, III , Alan R. Gilchrist , Ambrose A. Hauser
CPC分类号： F01D25/243 , F01D5/066 , F05B2260/301 , Y02T50/671 , Y02T50/673
摘要： A turbine support assembly includes a turbine rotor joined to a fan shaft through a support shaft. The support shaft is joined to the fan shaft in a V-configuration having first and second legs joined together at an apex and inclined axially apart, with at least the first leg forming an integral part of the fan shaft. The second leg is rotatably supportable to a frame. The V-configuration increases the stiffness of the turbine support to reduce blade tip clearances. The present invention also provides an annular integral bolt heat shield and axial retention apparatus to axially retain bolts used for holding together two rotor elements during assembly when the bolts are otherwise subject to sliding into a closed cavity of the assembled engine or one of its modules. The integral retainer and heat shield engage the bolts disposed through bolt holes in a gas turbine engine rotor shaft so that the bolts remain straight during assembly when a second rotor element such as a second shaft is being attached to the first shaft, and bolt holes in the second shaft have to engage and fit over the bolts of the first shaft. One particular embodiment of the present invention provides a low pressure turbine rotor shaft assembly of a low pressure turbine module wherein forward and aft shafts are attached by bolts which have bolt heads in a closed cavity of the module and are slidably disposed through corresponding bolt holes of each shaft such that the bolt heads are disposed aft of the aft shaft. An integral heat shield and axial bolt retainer is mounted to the aft shaft aft of the bolt heads so as to trap and retain the bolt heads between the shield and the aft shaft.
摘要翻译： 涡轮机支撑组件包括通过支撑轴连接到风扇轴的涡轮转子。 支撑轴以V形结合到风扇轴上，该V形构造具有在顶点处以第一和第二腿连接在一起并且轴向间隔开的倾斜，至少第一腿形成风扇轴的一体部分。 第二支腿可旋转地支撑在框架上。 V形构造增加了涡轮机支架的刚度以减小叶片尖端间隙。 本发明还提供了一种环形一体式螺栓隔热罩和轴向保持装置，用于当螺栓另外滑入组装的发动机或其模块之一的封闭空腔内时，轴向保持用于在组装期间将两个转子元件保持在一起的螺栓。 一体式保持器和隔热罩与通过燃气涡轮发动机转子轴中的螺栓孔布置的螺栓接合，使得当第二转子元件（例如第二轴）附接到第一轴时，螺栓在组装期间保持直立，并且螺栓孔 第二轴必须接合并装配在第一轴的螺栓上。 本发明的一个具体实施例提供了一种低压涡轮模块的低压涡轮转子轴组件，其中前轴和后轴通过螺栓附接，所述螺栓在模块的封闭空腔中具有螺栓头，并且可滑动地设置穿过相应的螺栓孔 每个轴使得螺栓头设置在后轴的后方。 一体式的热屏蔽和轴向螺栓保持器安装在螺栓头后部的后轴上，以便将螺栓头锁住并保持在护罩和后轴之间。
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公开(公告)号：US5123813A
公开(公告)日：1992-06-23
申请号：US662693
申请日：1991-03-01
CPC分类号： F01D5/323 , F01D5/26 , F01D5/3007 , Y10S416/50 , Y10T403/7061
摘要： Apparatus for preloading an airfoil blade attached to a rotor disk in a gas turbine engine. The dovetail root of a composite fan blade is preloaded to prevent rubbing and wear against the dovetail slot of a metal rotor disk during fan windmilling, with the aircraft engine off, due to wind and breezes at the airport. A resilient material is inserted into the lower portion of the slot below the engaged blade root. The disk has a radius which intersects the slot. The material is acted upon by a device which adjustably compresses the inserted material perpendicular to the radius of the disk. This causes the compressed material to exert a radially outward force against the bottom of the engaged root of the blade.
摘要翻译： 用于预装载在燃气涡轮发动机中的转子盘上的翼型叶片的装置。 复合风扇叶片的燕尾根预先加载，以防止在风扇风车期间摩擦和磨损金属转子盘的燕尾槽，飞机发动机由于机场的风和微风而关闭。 将弹性材料插入在所接合的叶片根部下方的狭槽的下部。 磁盘具有与槽相交的半径。 该材料被可调节地压缩垂直于盘半径的插入材料的装置作用。 这使得压缩的材料向刀片的接合根部的底部施加径向向外的力。
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公开(公告)号：US5213475A
公开(公告)日：1993-05-25
申请号：US802684
申请日：1991-12-05
CPC分类号： F04D29/321 , F01D5/02 , F01D5/3007
摘要： A rotor assembly for supporting rotor blades includes a plurality of axially adjoining discrete disks each having a rim. The rims include axial dovetail posts defining therebetween dovetail grooves for collectively supporting a respective blade dovetail therein. The disks are fixedly joined together by integral beams so that upon a crack failure of one of the disks, centrifugal load from the failed disk is transferred to an adjacent disk and crack propagation thereto is inhibited.
摘要翻译： 用于支撑转子叶片的转子组件包括多个具有边缘的轴向邻接的离散盘。 轮辋包括在其间限定燕尾槽的轴向鸠尾柱，用于在其中共同地支撑相应的叶片燕尾榫。 这些盘通过一体的梁固定地连接在一起，使得当其中一个盘的裂纹发生故障时，来自故障盘的离心负载被转移到相邻的盘并且阻止其裂纹传播。
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公开(公告)号：US5131814A
公开(公告)日：1992-07-21
申请号：US505121
申请日：1990-04-03
申请人： James C. Przytulski , Richard L. Horvath , Philip H. Stoughton , Christopher C. Glynn , Richard A. Wesling , Robert J. Corsmeier
发明人： James C. Przytulski , Richard L. Horvath , Philip H. Stoughton , Christopher C. Glynn , Richard A. Wesling , Robert J. Corsmeier
CPC分类号： F01D5/3007 , Y02T50/671
摘要： A gas turbine engine having an outer annular turbine rotor, which is counterrotatable relative to an inner annular turbine rotor, includes attachment structure for attaching turbine blades in circumferential rows to the inner rotor. The attachment structure includes first and second male members of hook-like configurations spaced axially along and circumferentially extending about the rotor, and first and second grooves defined by flanges attached to the rotor and axially spaced along and circumferentially extending about the rotor. The grooves open in a common axial direction for receiving in mated relation respectively and concurrently the hook-like configured first and second male members. The attachment structure also includes several different locking arrangements for locking the male members in mated relation with the grooves to thereby restrain the turbine blade against radial and axial movements relative to the rotor. Some locking arrangements are adapted for locking all of the blades but a last or final one thereof in a circumferential row around the rotor. Other locking arrangements are adapted for locking all of the blades in the circumferential row. Still other locking arrangements are adapted for locking only the last or final blade to complete the circumferential row of blades.
摘要翻译： 具有外环形涡轮机转子的燃气涡轮发动机，其相对于内环形涡轮机转子可逆地旋转，包括用于将周向行中的涡轮叶片附接到内转子的附接结构。 附接结构包括钩状构造的第一和第二阳构件，所述第一和第二阳构件沿轴向并沿着转子周向延伸，以及由附接到转子并由轴向间隔开并围绕转子周向延伸的凸缘限定的第一和第二槽。 所述凹槽在共同的轴向方向上打开以分别接合并且同时形成钩状配置的第一和第二阳构件。 附接结构还包括几个不同的锁定装置，用于将阳构件与凹槽配合关系锁定，从而约束涡轮叶片抵抗相对于转子的径向和轴向运动。 一些锁定装置适用于锁定所有叶片，但是围绕转子的圆周排锁定其最后的或最后的叶片。 其他锁定装置适于锁定圆周排中的所有叶片。 还有其它锁定装置适于仅锁定最后的刀片或最终刀片以完成圆周排的刀片。
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公开(公告)号：US5131813A
公开(公告)日：1992-07-21
申请号：US505118
申请日：1990-04-03
CPC分类号： F01D5/3038 , F01D5/03 , F01D9/042 , Y02T50/673
摘要： A gas turbine engine having an outer annular turbine rotor, which is counterrotatable relative to an inner annular turbine rotor, includes attachment structure for attaching turbine blades in circumferential rows to the outer rotor. The attachment structure includes first and second male members spaced axially along and circumferentially extending about the rotor, and first and second grooves spaced axially along and extending circumferentially about the rotor being defined by flanges attached to the rotor. Each male member has a first portion attached to an end of a turbine blade and extending therefrom in a radial direction. The first male member has a second portion attached to its first portion and extending therefrom in an axial direction to define the first male member with an overall hook-like cross-sectional configuration. The first groove is cross-sectionally shaped for receiving in mated relation the second portion of the first male member. The second groove is cross-sectionally shaped for receiving in mated relation in the second groove a lock segment of the locking assembly and the first portion of the second male member to lock the male members in the respective grooves and thereby lock the turbine blade against radial and axial movements relative to the rotor.
摘要翻译： 具有外环形涡轮机转子的燃气涡轮发动机，其相对于内部环形涡轮机转子可反转，包括用于将涡轮机叶片以周向排附接到外转子的附接结构。 附接结构包括沿着转子轴向间隔开并在周向上延伸的第一和第二阳构件，并且围绕转子沿轴向间隔开并且围绕转子周向延伸的第一和第二槽由连接到转子的凸缘限定。 每个阳构件具有附接到涡轮叶片的端部并且沿径向方向从其延伸的第一部分。 第一阳构件具有附接到其第一部分的第二部分并且在轴向方向上从第二部分延伸以限定具有整体钩状横截面构造的第一阳构件。 第一槽是横截面形状的，用于以配合的关系接收第一阳构件的第二部分。 第二凹槽是横截面形状的，用于在第二凹槽中以配合关系接收锁定组件的锁定段和第二阳构件的第一部分，以将阳构件锁定在相应的凹槽中，从而将涡轮叶片锁定在径向 和相对于转子的轴向移动。
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公开(公告)号：US06551057B1
公开(公告)日：2003-04-22
申请号：US09444623
申请日：1999-11-22
申请人： Frederic G. Haaser , Wayne R. Bowen , William T. Dingwell , Michael Even-Nur , James C. Przytulski
发明人： Frederic G. Haaser , Wayne R. Bowen , William T. Dingwell , Michael Even-Nur , James C. Przytulski
IPC分类号： F01D2504
CPC分类号： F04D29/563 , F01D17/162 , F01D25/04 , F04D29/668 , F16C3/12 , F16C3/22 , F16C2360/23
摘要： A torque shaft assembly includes a hollow tube with a central axis disposed between and fixedly connected to first and second crankshafts at first and second distal ends, respectively, of the tube for movement of an array of connecting members such as push rods. A hollow interior of tube between the first and second crankshafts is filled with a sufficient quantity of flowable inertia material or damping media to absorb vibratory energy by friction during operation of the engine. The hollow interior is preferably filled with a quantity of damping media to a level by volume of about 98% and a preferred flowable inertia material is round steel shot. A plurality of spaced-apart clevises are fixedly attached to a tube wall on an outer surface of the tube wall surrounding the hollow interior. Each clevis includes connection means disposed away from the wall outer surface for connection with an actuator for movement of the array of adjustable devices such as variable stator vanes.
摘要翻译： 扭矩轴组件包括中空管，其中心轴分别设置在第一和第二曲轴的第一和第二远端处并分别固定地连接到第一和第二远端，并且固定地连接到用于使诸如推杆的连接构件的阵列的运动的管中。 在第一和第二曲轴之间的管的中空内部填充有足够量的可流动的惯性材料或阻尼介质，以通过在发动机运行期间的摩擦吸收振动能。 中空内部优选地填充有一定量的阻尼介质，体积达到约98％，优选的可流动的惯性材料是圆钢。 多个间隔开的夹头固定地附接到围绕中空内部的管壁的外表面上的管壁。 每个U形夹包括远离壁外表面设置的连接装置，用于与致动器连接，用于可调节装置阵列如可变定子叶片的移动。
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公开(公告)号：US5281096A
公开(公告)日：1994-01-25
申请号：US943167
申请日：1992-09-10
CPC分类号： F01D11/008 , F05D2260/30 , F05D2300/603 , Y02T50/672
摘要： A fan assembly includes a plurality of discrete platforms disposed between adjacent rotor blades extending radially outwardly from a rotor disk. Each platform includes forward and aft axially spaced apart ends, and radially upper and lower spaced apart surfaces extending between the ends. Forward and aft retainer rings capture the platform to the disk with a predetermined clearance therebetween for allowing the platform to move radially upwardly under centrifugal force for retention by the retainer rings, while also allowing the platform to move radially inwardly under a radially inwardly directed impact load on the platform, which impact load is channeled through the platform lower surface at both the forward and aft ends into the rotor disk.
摘要翻译： 风扇组件包括设置在从转子盘径向向外延伸的相邻转子叶片之间的多个离散平台。 每个平台包括前部和后部轴向间隔开的端部，以及在端部之间延伸的径向上部和下部间隔开的表面。 前后保持环将平台以其间具有预定的间隙将平台捕获到盘上，以允许平台在离心力下径向向上移动以保持保持环，同时还允许平台在径向向内定向的冲击载荷 在平台上，冲击负载通过前端和后端的平台下表面引导到转子盘中。
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8.发明授权Interstage seal arrangement for airfoil stages of turbine engine counterrotating rotors 失效涡轮发动机调速转子的飞行器间隔密封安装
公开(公告)号：US5197281A
公开(公告)日：1993-03-30
申请号：US505120
申请日：1990-04-03
CPC分类号： F01D11/001 , B64C11/48 , F01D11/12 , F01D5/225 , F02K3/072 , Y10T29/49321
摘要： A gas turbine engine has outer and inner counterrotatable annular turbine rotors and pluralities of turbine blades disposed in alternating rows and mounted on and extending between the respective rotors. An interstage seal arrangement for the engine is composed of a sequence of alternating inner and outer seals. Each outer seal is disposed between an interior side of the outer rotor and outer ends of the blades in one plurality thereof being spaced radially inward at their outer ends from the outer rotor and being mounted at their inner ends to the exterior side of the inner rotor. Each inner seal is disposed between the exterior side of the inner rotor and inner ends of the blades in another plurality thereof being spaced radially outward at their inner ends from the inner rotor and being mounted at their outer ends to the interior side of the outer rotor. Each inner seal is composed of an annular honeycomb component attached to the blade inner ends and a plurality of annular seal elements or teeth mounted on the exterior side of the inner rotor and projecting radially outwardly therefrom for sealably interfacing with the honeycomb component concurrently as the outer and inner rotors counterrotate relative to one another.
摘要翻译： 燃气涡轮发动机具有外部和内部可反向旋转的环形涡轮转子和多个涡轮叶片，其以交替的排布置并安装在各个转子之间并在相应的转子之间延伸。 用于发动机的级间密封装置由一系列交替的内密封件和外密封件组成。 每个外部密封件设置在外部转子的内侧和多个叶片的外端之间，在其外端处与外转子径向向内间隔开，并且其内端安装在内转子的外侧 。 每个内密封件设置在内转子的外侧和另一多个叶片的内端之间，在其内端处与内转子径向向外间隔开，并且其外端安装在外转子的内侧 。 每个内密封件由附接到叶片内端的环形蜂窝构件和安装在内转子的外侧上并从其径向向外突出的多个环形密封元件或齿组成，以与蜂窝构件同时作为外部密封连接 并且内转子相对于彼此逆转。
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