| Patent application number | Description | Published |
|---|
| 20090104026 | CONTROL OF CLEARANCE AT BLADE TIPS IN A HIGH-PRESSURE TURBINE OF A TURBINE ENGINE - Turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring ( | 04-23-2009 |
| 20110056055 | MEMBER FOR LOCKING RING SECTORS ON A TURBINE ENGINE CASING, INCLUDING RADIAL PASSAGES FOR GRIPPING SAME - A locking member for a device used to fasten ring sectors on a casing of an aircraft turbine engine, wherein the member includes two clamping arms connected together at the rear end thereof by a connection arm extending substantially parallel to the general spacing direction between the two clamping arms. The member includes, on either side of a virtual median plane orthogonal to the circumferential direction, a passage for gripping the member, each passage being formed through the connection arm, emerging in an inter-arm space. | 03-10-2011 |
| 20110076135 | HIGH PRESSURE TURBINE OF A TURBOMACHINE WITH IMPROVED ASSEMBLY OF THE MOBILE BLADE RADIAL CLEARANCE CONTROL BOX - A high pressure turbine of a turbomachine such as a turbojet, in which a control box of radial clearances of rotating blades are provided. An annular element including a determined flexibility has one end fixed to an annular support and the other end supported by a simple axial bearing with a given pressure on the upstream side of the control box. Thus, disturbing vibration loads are prevented at the attachment points of the control box with the external casing of turbines, thereby also eliminating the risk of cracks occurring. | 03-31-2011 |
| 20110121150 | UNIT FOR LOCKING RING SECTORS ON A TURBOMACHINE CASING, COMPRISING RADIAL PASSAGES FOR GRIPPING IT - A unit locking a ring sector attachment device onto an aircraft turbomachine casing, the unit including two clamping arms connected to each other at their aft ends by a connecting arm extending approximately parallel to the general direction between the two clamping arms. The unit also includes a passage enabling gripping of the unit on each side of a fictitious median plane orthogonal to the circumferential direction, each passage being formed in the connecting arm, extending along a direction line approximately parallel to the direction between the arms. | 05-26-2011 |
| 20110229314 | HIGH-PRESSURE TURBINE FOR TURBOMACHINE, ASSOCIATED GUIDE VANE SECTOR AND AIRCRAFT ENGINE - An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane. | 09-22-2011 |
