Patent application number | Description | Published |
20080206058 | METHOD FOR REDUCING VIBRATION LEVELS OF A BLADED WHEEL IN A TURBOMACHINE - The present invention concerns a method for reducing vibration levels likely to occur in a turbomachine comprising at least a first and a second bladed wheel, where the two wheels are moving relative to one another about an axis of rotation and a gaseous fluid is passing over them, due to perturbations of an aerodynamic origin that are produced by the second bladed wheel or an obstacle on the first bladed wheel. The method includes the following steps in the design of said two bladed wheels: an initial configuration of the blades is defined; the synchronous forced response on the first bladed wheel is calculated as a function of the harmonic excitation force produced by the second bladed wheel expressed in the form of a linear function of the generalized aerodynamic force for the mode considered; a geometric tangential shift value θ is determined for the stacked cross sections of one of the two wheels so as to reduce the corresponding term to the generalized aerodynamic force. The set of cross sections with the tangential shifts thus defines a new configuration of the blades of said one of the two wheels which is applied to the blades of said one of the two wheels. | 08-28-2008 |
20090004000 | DAMPING DEVICE FOR TURBOMACHINE STATOR - The present invention relates to a turbomachine stator forming a stator vane ring or upstream guide vane element comprising a plurality of vanes placed radially between a first inner ring and a second outer ring, the two rings being concentric, the second ring having a cylindrical outer surface portion. The stator is characterized in that, on said outer surface portion, at least one vibration-damping laminate is attached, the laminate comprising at least one layer of viscoelastic material in contact with said surface portion and one counterlayer of rigid material. | 01-01-2009 |
20090004021 | MOVABLE IMPELLER FOR A TURBOJET AND TURBOJET COMPRISING SAME - The impeller comprises a blade and a support of said blade which extend substantially radially. It also comprises at least one intermediate part extending, in a substantially axial direction, between said blade and said support of the blade, and at least one damping means placed on at least one face of said intermediate part. The damping means is segmented in an axial and/or circumferential direction into at least two elementary damping means. | 01-01-2009 |
20090005183 | DAMPING DEVICE FOR A SHAFT OF A TURBOMACHINE - The present invention relates to a hollow shaft of a turbomachine comprising a cylindrical wall with an inner surface portion and at one end a member for attachment to a rotor disk of the turbomachine. The shaft also comprises a damping device wherein at least one vibration-damping laminate is attached to said inner surface portion, the laminate comprising at least one layer of viscoelastic material in contact with said surface portion and a counterlayer of rigid material. | 01-01-2009 |
20090016890 | TURBOMACHINE ROTOR ASSEMBLY - A turbomachine rotor assembly comprising: a rotor disk ( | 01-15-2009 |
20090060745 | SHIM FOR A TURBOMACHINE BLADE | 03-05-2009 |
20090074569 | LEVER FOR ROTATING A TURBOMACHINE VARIABLE-PITCH STATOR VANE ABOUT ITS PIVOT - The present invention relates to a lever for rotating about its pivot a turbomachine variable-pitch stator vane comprising three zones: a first zone for attachment to a lever drive member, a second zone for attachment to said variable-pitch stator vane, and a third zone of elongate shape between the first zone and the second zone, wherein a vibration-damping laminate is applied to at least one surface portion of at least one of said zones of the lever, the laminate comprising at least one layer of viscoelastic material in contact with said surface portion and a backing layer of rigid material. | 03-19-2009 |
20090074586 | DAMPING DEVICE FOR COMPOSITE BLADE - The present invention relates to a blade made of composite, comprising a vane formed of woven filaments impregnated with a thermosetting resin with a protective element in the region of the leading edge of the vane comprising a part in the form of a rigid strip, said strip being secured to the vane. The blade is characterized in that at least one layer of a viscoelastic material is at least partially interposed between said rigid strip and the vane so as to form, with the protective element, a means of damping the vibrations of the vane. | 03-19-2009 |
20090297331 | TURBOMACHINE CASING INCLUDING A DEVICE FOR PREVENTING INSTABILITY DURING CONTACT BETWEEN THE CASING AND THE ROTOR - The invention relates to a cylindrical casing for a turbomachine that is suitable for receiving a rotor fitted with at least one bladed wheel, the casing including a device for preventing instability during contact between the casing and the bladed wheel. In characteristic manner, said device comprises a succession of elements disposed around the circumference of the casing, and presenting between two adjacent elements, different stiffnesses, the number of elements having the same stiffness not being equal to a multiple of the wave number of the vibratory mode of the bladed wheel that is to be inhibited. The invention is applicable to a compressor, a turbine, or a fan. | 12-03-2009 |
20100050594 | METHOD FOR REDUCING THE VIBRATION LEVELS OF A PROPFAN OF CONTRAROTATING BLADED DISKS OF A TURBINE ENGINE - The present invention relates to a method for reducing the vibration levels likely to occur, in a turbine engine comprising a first and a second bladed disk forming a propfan of contrarotating disks, when the two disks are traversed by a gaseous fluid, because of the turbulence of aerodynamic origin generated by the second bladed disk on the first bladed disk. The method comprises the following steps during the design of said two bladed disks: an initial configuration of the blades is defined, the synchronous forced response is calculated on the first bladed disk as a function of the harmonic excitation force generated by the second bladed disk expressed in the form of a linear function of the generalized aerodynamic force for the mode in question; for stacked sections of one of the two disks, a tangential geometric offset value θ of the individual aerodynamic profile is determined so as to reduce the term corresponding to the generalized aerodynamic force. The combination of the individual profiles on the sections with the tangential offsets therefore defines a new configuration of the blades of said one of the two disks which is applied to the blades of said one of the two disks. | 03-04-2010 |
20100054918 | METHOD FOR REDUCING THE VIBRATION LEVELS OF A PROPELLER OF A TURBINE ENGINE - The present invention relates to a method for reducing the vibration levels capable of occurring, in a turbine engine comprising at least one propeller and one coupling structure of the turbine engine, because of the turbulence of aerodynamic origin generated by the coupling structure on the propeller. The method comprises the following steps during the design of the aerodynamic profiles of the propeller and of the coupling structure: an initial configuration of the aerodynamic profiles is defined, the synchronous forced response on the propeller is calculated as a function of the force of harmonic excitation generated by the coupling structure expressed in the form of a linear function of the generalized aerodynamic force for the mode in question; for stacked sections of one of the propeller or of the coupling structure, a tangential geometric offset value θ of the individual aerodynamic profiles is determined in order to reduce the term corresponding to the generalized aerodynamic force. The combination of the sections with the tangential offsets therefore defines a new configuration of the aerodynamic profiles that is applied to the aerodynamic profiles of the propeller or of the coupling structure. | 03-04-2010 |
20100232974 | BLADE MADE OF COMPOSITE MATERIAL COMPRISING A DAMPING DEVICE - The present invention relates to a blade made of composite material ( | 09-16-2010 |
20110091310 | THERMOMECHANICAL PART CONSTITUTING A BODY OF REVOLUTION ABOUT A LONGITUDINAL AXIS AND INCLUDING AT LEAST ONE ABRADABLE RING FOR A SEALING LABYRINTH - The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that present different stiffnesses between adjacent pairs of sectors. The invention is applicable to a compressor, a turbine, or to a rotor and stator assembly. | 04-21-2011 |
20120018543 | DIFFUSER/RECTIFIER ASSEMBLY FOR A TURBINE ENGINE - A diffuser-nozzle assembly for mounting at an outlet from a compressor in a turbomachine, the assembly including a nozzle including two substantially cylindrical walls, a radially inner wall and a radially outer wall that are connected together by radial vanes. The walls of the nozzle are extended downstream beyond the radial vanes and the radial spacing therebetween varies downstream from the vanes to be at a minimum substantially in register with the vanes and at a maximum between the vanes. | 01-26-2012 |
20130202449 | AXISYMMETRIC PART FOR AN AVIATION TURBINE ENGINE ROTOR - A link part for a turbine engine, in particular such as a turbojet, the link part being mounted between a fan cone and a fan disk supporting fan blades, the link part having an annular wall pierced by a plurality of orifices, each for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform, the annular wall being made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform. | 08-08-2013 |