-
1.发明申请Rotation-locking of sectors of rectifier blades by bars in the parting planes of the housing 有权在壳体的分型平面中通过杆旋转锁定整流器叶片公开(公告)号：US20050079047A1
公开(公告)日：2005-04-14
申请号：US10925996
申请日：2004-08-26
申请人： Jean-Louis Bertrand , Jean-Francois Chabot , Leopold De-Verduzan , Francis Dome , Julien Girardot , Stephanie Pariset
发明人： Jean-Louis Bertrand , Jean-Francois Chabot , Leopold De-Verduzan , Francis Dome , Julien Girardot , Stephanie Pariset
CPC分类号： F01D9/042 , F01D25/246
摘要： The invention relates to a rotation-locking device of a sector of rectifier blades (5) mounted in a sector of the turbojet housing. A sector of blades comprises a support base (3). A housing sector comprises two recesses perpendicular to the axis of the housing, each receiving an edge (34-1, 34-2) of the support base. At one and the same axial end of the housing sector, each recess opens out into a seat (30-1, 30-2) defining an axial face (32-1). The device comprises an axial stop (26) adapting itself on each side in the seats (30-1; 30-1) of the two recesses, and once the complementary sector of the housing is installed and during operation of the turbojet, bearing on the axial faces (32-1) under the thrust of the complementary sector of rectifier blades in order to provide rotation locking.
摘要翻译： 本发明涉及一种安装在涡轮喷气发动机壳体的扇形区中的整流叶片（5）的扇形旋转锁定装置。 刀片扇区包括支撑基座（3）。 壳体扇区包括垂直于壳体的轴线的两个凹槽，每个凹部接收支撑基座的边缘（34-1,34-2）。 在壳体扇形体的同一轴向端部处，每个凹部开口形成限定轴向面（32-1）的座（30-1,30-2）。 该装置包括在两个凹部的座（30-1,30-1）中的每一侧自适应的轴向止动件（26），并且一旦壳体的互补部分被安装并且在涡轮喷气发动机运行期间 在整流叶片的互补扇区的推力下的轴向面（32-1）以提供旋转锁定。
-
2.发明授权Rotation-locking of sectors of rectifier blades by bars in the parting planes of the housing 有权在壳体的分型平面中通过杆旋转锁定整流器叶片公开(公告)号：US07059832B2
公开(公告)日：2006-06-13
申请号：US10925996
申请日：2004-08-26
申请人： Jean-Louis Bertrand , Jean-Francois Laurent Chabot , Leopold Jean-Marie De-Verduzan , Francis Dome , Julien Girardot , Stephanie Pariset
发明人： Jean-Louis Bertrand , Jean-Francois Laurent Chabot , Leopold Jean-Marie De-Verduzan , Francis Dome , Julien Girardot , Stephanie Pariset
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D25/246
摘要： The invention relates to a rotation-locking device of a sector of rectifier blades (5) mounted in a sector of the turbojet housing. A sector of blades comprises a support base (3). A housing sector comprises two recesses perpendicular to the axis of the housing, each receiving an edge (34-1, 34-2) of the support base. At one and the same axial end of the housing sector, each recess opens out into a seat (30-1, 30-2) defining an axial face (32-1). The device comprises an axial stop (26) adapting itself on each side in the seats (30-1; 30-1) of the two recesses, and once the complementary sector of the housing is installed and during operation of the turbojet, bearing on the axial faces (32-1) under the thrust of the complementary sector of rectifier blades in order to provide rotation locking.
摘要翻译： 本发明涉及一种安装在涡轮喷气发动机壳体的扇形区中的整流叶片（5）的扇形旋转锁定装置。 刀片扇区包括支撑基座（3）。 壳体扇区包括垂直于壳体的轴线的两个凹槽，每个凹部接收支撑基座的边缘（34-1,34-2）。 在壳体扇形体的同一个轴向端处，每个凹部开口形成限定轴向面（32-1）的座（30-1,30-2）。 该装置包括在两个凹部的座（30-1,30-1）中的每一侧自适应的轴向止动件（26），并且一旦外壳的互补部分被安装并且在涡轮喷气发动机运行期间 在整流叶片的互补扇区的推力下面的轴向面（32-1）以提供旋转锁定。
-
搜索结果
2 条记录 (耗时 0.023 秒)
