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公开(公告)号：US07419360B2
公开(公告)日：2008-09-02
申请号：US11187852
申请日：2005-07-25
IPC分类号： F01D5/32
CPC分类号： F01D5/3038 , F05D2260/30 , F05D2300/501
摘要： A rotor disk for a turbomachine, the disk carrying blades whose roots are retained in a peripheral groove of the disk, the groove including a window for inserting blade roots and a locking member that is a single elastically deformable piece and dimensioned to be received and retained in a notch of the groove while in its free state, and to be capable of being displaced to slide inside the groove while in a stressed and elastically deformed state.
摘要翻译： 一种用于涡轮机的转子盘，盘片承载叶片，其根部保持在盘的周边槽中，该槽包括用于插入叶片根部的窗口和作为单个可弹性变形的块的锁定构件，并且其尺寸设计成被容纳和保持 在凹槽的凹口中处于其自由状态，并且能够在处于应力和弹性变形状态下移动以在凹槽内滑动。
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2.发明授权Balancing flyweight, rotor disk equipped therewith, rotor and aircraft engine comprising them 有权平衡飞重，与其配备的转子盘，包括它们的转子和飞机发动机公开(公告)号：US07753651B2
公开(公告)日：2010-07-13
申请号：US11622667
申请日：2007-01-12
IPC分类号： F01D5/10
CPC分类号： F01D5/027 , F01D5/10 , F16F15/32 , Y02T50/671 , Y10S416/50
摘要： The balancing flyweight of a turbomachine rotor includes two pyramid shaped end parts each one having a base and an apex, and an intermediate part which connects the two bases of the end parts together. The two apexes are aligned on a longitudinal axis. The two end parts and the intermediate part exhibit, in cross section through a plane perpendicular to said the longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis.
摘要翻译： 涡轮机转子的平衡轻重量包括两个金字塔形的端部，每个端部具有一个底部和一个顶点，以及一个中间部分，其将两个底部的两个底部连接在一起。 两个顶点在纵向轴线上对准。 两个端部和中间部分在垂直于所述纵向轴线的平面的横截面中表现出具有以所述纵向轴线为中心的多边形形状的横截面。
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3.发明申请BALANCING FLYWEIGHT, ROTOR DISK EQUIPPED THEREWITH, ROTOR AND AIRCRAFT ENGINE COMPRISING THEM 有权平衡飞轮，装有转子盘，转子和包括它们的飞机发动机公开(公告)号：US20100135774A1
公开(公告)日：2010-06-03
申请号：US11622667
申请日：2007-01-12
IPC分类号： F04D29/66
CPC分类号： F01D5/027 , F01D5/10 , F16F15/32 , Y02T50/671 , Y10S416/50
摘要： The balancing flyweight of a turbomachine rotor includes two pyramid shaped end parts each one having a base and an apex, and an intermediate part which connects the two bases of the end parts together. The two apexes are aligned on a longitudinal axis. The two end parts and the intermediate part exhibit, in cross section through a plane perpendicular to the longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis.
摘要翻译： 涡轮机转子的平衡轻重量包括两个金字塔形的端部，每个端部具有一个底部和一个顶点，以及一个中间部分，其将两个底部的两个底部连接在一起。 两个顶点在纵向轴线上对准。 两个端部和中间部分在横截面上通过垂直于纵向轴线的平面显示具有以所述纵向轴线为中心的多边形形状的横截面。
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公开(公告)号：US09879549B2
公开(公告)日：2018-01-30
申请号：US14112071
申请日：2012-05-03
CPC分类号： F01D5/225 , F01D9/042 , F01D25/246 , F04D29/542 , F04D29/644 , F05D2240/40 , Y10T29/4932
摘要： An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.
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公开(公告)号：US08794908B2
公开(公告)日：2014-08-05
申请号：US13074705
申请日：2011-03-29
IPC分类号： F01D25/06
CPC分类号： F01D9/042 , F01D11/008 , F04D29/542 , F04D29/644 , F05D2230/232 , F05D2260/96 , F05D2300/222 , F05D2300/43 , F05D2300/501
摘要： A turbomachine stator stage including two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the vanes being welded to the outer shroud and the radially inner ends of the vanes passing through orifices in an outer ring of the inner shroud, the inner ends being held by elastomer spacers in an annular cavity formed between the outer ring and an inner ring that is fastened to the outer ring.
摘要翻译： 涡轮机定子台包括两个同轴护罩，分别为内护罩和外护罩，其中具有在其间延伸的基本上径向的叶片，叶片的径向外端焊接到外护罩，并且叶片的径向内端通过孔口 所述内护罩的外环，所述内端由弹性体间隔件保持在形成在所述外环和固定到所述外环的内环之间的环形空腔中。
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公开(公告)号：US20110243742A1
公开(公告)日：2011-10-06
申请号：US13074705
申请日：2011-03-29
CPC分类号： F01D9/042 , F01D11/008 , F04D29/542 , F04D29/644 , F05D2230/232 , F05D2260/96 , F05D2300/222 , F05D2300/43 , F05D2300/501
摘要： A turbomachine stator stage comprising two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the vanes being welded to the outer shroud and the radially inner ends of the vanes passing through orifices in an outer ring of the inner shroud, the inner ends being held by elastomer spacers in an annular cavity formed between the outer ring and an inner ring that is fastened to the outer ring.
摘要翻译： 涡轮机定子台包括两个同轴护罩，分别是内护罩和外护罩，其中具有在其间延伸的基本上径向的叶片，叶片的径向外端焊接到外护罩，并且叶片的径向内端通过孔口 所述内护罩的外环，所述内端由弹性体间隔件保持在形成在所述外环和固定到所述外环的内环之间的环形空腔中。
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7.发明授权Device for blocking a ring for axially retaining a blade, associated rotor disk and retaining ring, and rotor and aircraft engine comprising them 有权用于阻挡用于轴向保持叶片，相关联的转子盘和保持环的环以及包括它们的转子和飞机发动机的装置公开(公告)号：US07540714B1
公开(公告)日：2009-06-02
申请号：US11466994
申请日：2006-08-24
IPC分类号： F01D5/32
CPC分类号： F01D5/3015
摘要： A device for rotationally blocking a retaining ring on a rotor disk three successive blocking hooks of the disk (10), two cleats of the retaining ring, arranged on either side of a split in the retaining ring. The position of the cleats on the retaining ring is such that, when the retaining ring is in place in a groove situated in the rotor disk, the two cleats are in respective abutment against the first and third blocking hooks, and the split is covered by the second blocking hook.
摘要翻译： 一种用于将转子盘上的保持环旋转地阻挡在盘（10）上的三个连续的阻塞钩，设置在保持环中的裂缝的任一侧的保持环的两个楔子。 夹板在保持环上的位置使得当保持环位于转子盘中的凹槽中时，两个防滑板分别抵靠第一和第三阻挡钩，并且该分割被 第二个阻塞钩。
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8.发明申请AIRCRAFT ENGINE ANNULAR SHROUD COMPRISING AN OPENING FOR THE INSERTION OF BLADES 有权包括开放刀片的飞机发动机安全防护罩公开(公告)号：US20140056711A1
公开(公告)日：2014-02-27
申请号：US14112071
申请日：2012-05-03
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F01D9/042 , F01D25/246 , F04D29/542 , F04D29/644 , F05D2240/40 , Y10T29/4932
摘要： An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.
摘要翻译： 飞机发动机环形护罩在其内表面上包括能够接纳多个叶片根部的周边环形槽; 用于将叶片根部插入到环形槽中的插入开口; 以及用于封闭插入开口的闭合装置。
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9.发明申请OUTER SHELL SECTOR FOR A BLADED RING FOR AN AIRCRAFT TURBOMACHINE STATOR, INCLUDING VIBRATION DAMPING SHIMS 审中-公开用于飞机涡轮机定子的叶片的外壳部分，包括振动阻尼系统公开(公告)号：US20120128482A1
公开(公告)日：2012-05-24
申请号：US13386496
申请日：2010-07-29
IPC分类号： F01D9/04
CPC分类号： F04D29/542 , F01D9/042 , F01D11/001 , F01D25/06 , F01D25/246 , F04D29/644 , F04D29/668
摘要： An assembly forming an outer shell sector, for a bladed ring sector configured to be used on a compressor or turbine stator in an aircraft turbomachine, including a plurality of elementary sectors and vibration damping shims each of them being inserted between two elementary sectors associated with it. A profile of each vibration damping shim is approximately the same as a profile of the elementary sectors.
摘要翻译： 一种形成外壳扇区的组件，用于叶片环形部分，其构造成用于飞机涡轮机中的压缩机或涡轮机定子，包括多个基本扇区和减振垫片，每个基本扇区和振动阻尼垫片插入在与其相关联的两个基本扇区之间 。 每个振动阻尼垫片的轮廓与基本扇区的轮廓大致相同。
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10.发明授权Sector of a compressor guide vanes assembly or a sector of a turbomachine nozzle assembly 有权压缩机导向叶片组件或涡轮机喷嘴组件的扇形部分公开(公告)号：US07887286B2
公开(公告)日：2011-02-15
申请号：US11763694
申请日：2007-06-15
申请人： Olivier Abgrall , Laurent Gilles Dezouche , Francois Maurice Garcin , Jean-Pierre Francois Lombard
发明人： Olivier Abgrall , Laurent Gilles Dezouche , Francois Maurice Garcin , Jean-Pierre Francois Lombard
CPC分类号： F04D29/542 , F01D5/225 , F01D9/041 , F01D11/005 , Y02T50/673
摘要： A sector of a compressor guide vanes assembly or a sector of a turbomachine nozzle assembly. It comprises an inner ring sector (4), an outer ring sector (6) and a multitude of blades (8) connecting the inner ring sector (4) to the outer ring sector (6). The outer ring sector (6) or the inner ring sector (4) comprises radial cuts (10) situated between two consecutive blades (8) in such a way as to split them into the same number of elementary sectors as there are blades. Housings (14) are provided, secant to the radial cuts (10), damping inserts (16) being positioned in said housings.
摘要翻译： 压缩机导向叶片组件的扇形部分或涡轮机喷嘴组件的扇形部分。 它包括内环扇区（4），外环扇区（6）和将内环扇区（4）连接到外环扇区（6）的多个叶片（8）。 外圈扇区（6）或内环扇区（4）包括位于两个连续叶片（8）之间的径向切口（10），以便将它们分成与叶片相同数量的基本扇区。 壳体（14）被设置成切割到径向切口（10），阻尼插入件（16）定位在所述壳体中。
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