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21.发明申请LOW PRESSURE TURBINE FOR AN AIRCRAFT TURBOMACHINE, COMPRISING A SEGMENTED NOZZLE WITH AN IMPROVED DESIGN 有权用于飞机涡轮机的低压涡轮机，包括具有改进设计的分段喷嘴公开(公告)号：US20120134788A1
公开(公告)日：2012-05-31
申请号：US13300981
申请日：2011-11-21
IPC分类号： F04D29/58
CPC分类号： F01D9/042 , F01D11/005 , F01D25/12 , Y02T50/675
摘要： The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).
摘要翻译： 本发明涉及一种涡轮机的低压涡轮（1），其包括属于上游级（20B）的喷嘴（62）和属于下游级（20C）的喷嘴（162），所述喷嘴（62）形成段 （62a），其具有外部结构（66），所述外部结构（66）包括：径向地支撑在固定到所述壳体上的钩（79）上的突片（76），在所述壳体中的径向（87） 限定环形上游冷却空气循环空腔（91）;接触表面（84），其从所述突片（85）向下游方向延伸并且在内侧衬有可磨损元件（86），所述接触表面包括 位于所述喷嘴（162）上并且径向地支承在所述壳体的止动件（93）上的下游端（92），所述接触表面（84）限定与腔（91）连通的环形下游冷却空气循环腔（94） 。
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22.发明授权Control of clearance at blade tips in a high-pressure turbine of a turbine engine 有权控制涡轮发动机的高压涡轮机叶片尖端处的间隙公开(公告)号：US08100635B2
公开(公告)日：2012-01-24
申请号：US12254518
申请日：2008-10-20
CPC分类号： F01D11/005 , F01D11/24 , F05D2240/11 , Y02T50/671
摘要： A turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring held by a casing of the turbine, and an annular thermal protection sheet mounted between the casing and the sealing ring is disclosed. The annular thermal protection sheet is formed by a plurality of curved plates mounted end-to-end and attached by pins to the casing.
摘要翻译： 公开了一种涡轮发动机中的涡轮级，包括在由涡轮机的壳体保持的密封环内旋转的叶片的叶片，以及安装在壳体和密封环之间的环形热保护片。 环形热保护片由端对端安装的多个弯曲板形成，并通过销附接到壳体。
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公开(公告)号：US20080206047A1
公开(公告)日：2008-08-28
申请号：US12038422
申请日：2008-02-27
CPC分类号： F01D11/12 , F01D9/04 , F01D25/246 , F05D2240/11
摘要： A turbine stage in a turbomachine comprising ring sectors (20) arranged about a turbine impeller (18), and an annular support (50) supporting the ring sectors and attached to a turbine casing (22), this annular support being able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.
摘要翻译： 涡轮机中的涡轮机级包括围绕涡轮机叶轮（18）布置的环形部分（20），以及环形支撑件（50），其支撑所述环形部分并附接到涡轮机壳体（22），所述环形支撑件能够变形 在径向方向上弹性地运动，以缓冲涡轮机壳体的至少一部分变形。
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公开(公告)号：US06666645B1
公开(公告)日：2003-12-23
申请号：US09926122
申请日：2001-09-06
IPC分类号： F01D1124
CPC分类号： F01D11/24 , F01D25/246 , F05D2240/11
摘要： An arrangement for adjusting the diameter of a gas turbine stator includes a casing having a main portion and rings bordering a vein of a gas flow and located in front of respective levels of mobile blades of a rotor, and communication passages of a gas flow under pressure. The rings are surrounded by the casing and fixed thereto by circular groups of spacers. The rings include a wall extending from the casing to one of the rings and separating two chambers. The wall includes an outside edge curved into a spacer hook and engaged between the main portion of the casing and a respective appendage curved into a casing hook associated with the spacer hook. The communication passages of the gas flow under pressure exist between the chambers. At least one of the communication passages is realized by cavities through a junction of hooks.
摘要翻译： 用于调节燃气轮机定子的直径的装置包括壳体，壳体具有与气流的静脉接合的主要部分和环，并且位于转子的相应水平的可动叶片的前方，以及压力下的气体流动的连通通道 。 环被壳体包围并通过圆形的间隔件组固定。 环包括从壳体延伸到其中一个环并分离两个室的壁。 壁包括弯曲成间隔钩的外边缘，并且接合在壳体的主要部分和弯曲成与间隔钩相关联的壳体钩的相应附件中。 在室之间存在压力气流的连通通道。 连通通道中的至少一个通过空穴通过钩的连接件实现。
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