-
1.发明授权CMC turbine nozzle adapted to support a metallic turbine internal casing by a radial contact 有权CMC涡轮喷嘴适于通过径向接触来支撑金属涡轮内部壳体公开(公告)号：US09194241B2
公开(公告)日：2015-11-24
申请号：US13435910
申请日：2012-03-30
CPC分类号： F01D5/282 , F01D9/065 , F01D25/246 , F05D2300/603 , Y02T50/672
摘要： A composite material turbine nozzle blade including an airfoil adapted to have a cooling fluid flow through it and extending between a shroud and a root is provided. The shroud is shaped to be attached to one or more turbine casings of a turbomachine and the root is shaped to provide a junction with a turbine internal casing. The root is produced with a loosened texture and includes an external upstream side loosened texture lug and an external downstream side loosened texture lug. The ends of the two external side lugs extend radially relative to the rotation axis of the turbomachine to form a device for supporting and centering the internal casing.
摘要翻译： 提供一种复合材料涡轮喷嘴刀片，其包括适于使冷却流体流过其并在护罩和根部之间延伸的翼型件。 护罩被成形为附接到涡轮机的一个或多个涡轮机壳体，并且根部成形为提供与涡轮机内部壳体的连接。 根部产生松散的纹理，并且包括外部上游侧松动纹理凸起和外部下游侧松动纹理凸耳。 两个外侧凸耳的端部相对于涡轮机的旋转轴线径向延伸，以形成用于支撑和对中内部壳体的装置。
-
公开(公告)号：US09638042B2
公开(公告)日：2017-05-02
申请号：US14113584
申请日：2012-04-27
CPC分类号： F01D5/147 , F01D5/282 , F01D5/3084 , F01D5/3092 , F01D9/042 , Y02T50/672
摘要： A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface.
-
3.发明申请CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY A RADIAL CONTACT 有权CMC涡轮喷嘴适用于通过径向接触支撑金属涡轮机内壳公开(公告)号：US20120251314A1
公开(公告)日：2012-10-04
申请号：US13435910
申请日：2012-03-30
IPC分类号： F01D9/04
CPC分类号： F01D5/282 , F01D9/065 , F01D25/246 , F05D2300/603 , Y02T50/672
摘要： Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending radially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.
摘要翻译： 复合材料涡轮喷嘴刀片包括适于使冷却流体流过其并在护罩（11）和根部（12）之间延伸的翼型件（10），所述护罩成形为连接到一个或多个涡轮机壳体（6） ，7），并且所述根部被成形为提供与涡轮机内部壳体（5）的连接处，其中其根部（12）以松散的质地产生并且包括外部上游侧松动纹理凸耳（122）和 外部下游侧松动的纹理凸耳（124），两个外侧凸耳的端部相对于涡轮机的旋转轴线径向延伸，以形成用于支撑和定心所述内部壳体的装置。
-
4.发明申请CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY AN AXIAL CONTACT 有权CMC涡轮喷嘴适用于通过轴向接触支持金属涡轮内部壳体公开(公告)号：US20120251309A1
公开(公告)日：2012-10-04
申请号：US13435754
申请日：2012-03-30
CPC分类号： F01D5/282 , F01D9/065 , F01D25/246 , F05D2300/603 , Y02T50/672
摘要： Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending axially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.
摘要翻译： 复合材料涡轮喷嘴刀片包括适于使冷却流体流过其并在护罩（11）和根部（12）之间延伸的翼型件（10），所述护罩成形为连接到一个或多个涡轮机壳体（6） ，7），并且所述根部被成形为提供与涡轮机内部壳体（5）的连接处，其中其根部（12）以松散的质地产生并且包括外部上游侧松动纹理凸耳（122）和 外部下游侧松动的纹理凸耳（124），两个外侧凸耳的端部相对于涡轮机的旋转轴线轴向延伸，以形成用于支撑和对中所述内部壳体的装置。
-
5.发明授权CMC turbine nozzle adapted to support a metallic turbine internal casing by an axial contact 有权CMC涡轮喷嘴适于通过轴向接触来支撑金属涡轮机内部壳体公开(公告)号：US09103219B2
公开(公告)日：2015-08-11
申请号：US13435754
申请日：2012-03-30
CPC分类号： F01D5/282 , F01D9/065 , F01D25/246 , F05D2300/603 , Y02T50/672
摘要： A composite material turbine nozzle blade including an airfoil adapted to have a cooling fluid flow through it and extending between a shroud and a root is provided. The shroud is shaped to be attached to one or more turbine casings of a turbomachine and the root is shaped to provide a junction with a turbine internal casing. The root is produced with a loosened texture and includes an external upstream side loosened texture lug and an external downstream side loosened texture lug, the ends of the two external side lugs extending axially relative to the rotation axis of the turbomachine to form a device for supporting and centering the internal casing.
摘要翻译： 提供一种复合材料涡轮喷嘴刀片，其包括适于使冷却流体流过其并在护罩和根部之间延伸的翼型件。 护罩被成形为附接到涡轮机的一个或多个涡轮机壳体，并且根部成形为提供与涡轮机内部壳体的连接。 根部产生松散的纹理，并且包括外部上游侧松动纹理凸起和外部下游侧松动纹理凸耳，两个外侧凸耳的端部相对于涡轮机的旋转轴线轴向延伸以形成用于支撑 并将内壳定心。
-
公开(公告)号：US20140234118A1
公开(公告)日：2014-08-21
申请号：US14113584
申请日：2012-04-27
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/282 , F01D5/3084 , F01D5/3092 , F01D9/042 , Y02T50/672
摘要： A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface.
摘要翻译： 一种燃气涡轮发动机，其至少包括构造成用于安装在所述发动机的第二金属部分中的第一复合部件，所述第一复合部件包括被配置为与所述第二金属部件表面接触的界面，所述发动机可拆卸地包括金属保护件 安装在第一复合部件上并构造成覆盖界面表面。
-
7.发明申请SEGMENTED TURBINE RING FOR A TURBOMACHINE, AND TURBOMACHINE FITTED WITH SUCH A RING 审中-公开用于涡轮机的SEGMENTED涡轮环和用这种环的TURBOMACHINE公开(公告)号：US20120141257A1
公开(公告)日：2012-06-07
申请号：US13311094
申请日：2011-12-05
IPC分类号： F04D29/58
CPC分类号： F01D11/005 , F05D2240/11 , F05D2240/57
摘要： The segmented ring has the gaseous hot flow of the turbomachine passing through it and comprises: a plurality of segments assembled by means of sealed connection involving sealing strips, provided in the mutually-facing radial faces of said segments the internal lateral faces of which delimit the flow path along which the hot gaseous flow travels; and through-orifices, formed in said segments, to carry external fresh air towards their radial and internal faces. Advantageously, one, the lower one, of the sealing strips of the means of connection is designed to lie close to the lateral internal faces of said segments and to run parallel to them, passing through a cooling chamber formed in the radial faces of the segments and into which said orifices open.
摘要翻译： 分段环具有通过其的涡轮机的气态热流，并且包括：多个段，其通过密封连接组装，所述密封连接包括密封条，设置在所述段的相互面对的径向面中，其内侧面限定 热气流沿其流动的流路; 以及形成在所述段中的通孔，以将外部新鲜空气向其径向和内表面携带。 有利地，连接装置的密封条中的一个密封条的一个被设计成靠近所述段的侧向内表面并平行于它们延伸，通过形成在段的径向面中的冷却室 并且所述孔打开。
-
-
-
-
-
-
搜索结果
7 条记录 (耗时 0.023 秒)
