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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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3.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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公开(公告)号：US09644640B2
公开(公告)日：2017-05-09
申请号：US13362464
申请日：2012-01-31
CPC分类号： F04D29/542 , F01D9/041 , F01D11/001 , F04D29/083 , F04D29/644 , F05D2230/232 , F05D2230/237 , F05D2260/96 , Y02T50/673
摘要： A single-piece compressor nozzle stage for a turbine engine, the stage including two coaxial rings, connected together by radial vanes, the inner ring including an annular cavity for housing a damper for damping vibration by friction, which damper is secured to an annular abradable-material support.
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