Patent application number | Description | Published |
20090124571 | METHOD FOR THE SYNTHESIS OF OLIGONUCLEOTIDE DERIVATIVES - Method for the synthesis of nucleotide derivatives wherein molecules of interest are grafted on the oligonucleotide with the help of a “click chemistry” reaction between an azide function on the molecule of interest and an alkyne function on the oligonucleotide, or between an alkyne function on the molecule of interest and an azide function on the oligonucleotide. | 05-14-2009 |
20090170729 | Method and a machine for ex situ fabrication of low and medium integration biochip arrays - A method of ex situ fabrication of at least one biochip, the method being of the type consisting in projecting onto a substrate a microvolume of reagent comprising at least one probe diluted in a suitable solvent so as to form, after the solvent has been eliminated, a spot comprising said probe, the method consisting in using a microprojection device comprising at least one tank in which the reagent is stored, and at least one source of gas under pressure put into communication with the tank, and in projecting the microvolume of reagent through an ejection nozzle under drive from the pressure exerted by the gas on the reagent. | 07-02-2009 |
20110245478 | Method for the Synthesis of Oligonucleotide Derivatives - Method for the synthesis of nucleotide derivatives wherein molecules of interest are grafted on the oligonucleotide with the help of a “click chemistry” reaction between an azide function on the molecule of interest and an alkyne function on the oligonucleotide, or between an alkyne function on the molecule of interest and an azide function on the oligonucleotide. | 10-06-2011 |
Patent application number | Description | Published |
20100050873 | FILTRATION SYSTEM FOR GAS TURBINES - A system for use with an inlet of a gas turbine through which airflow toward the gas turbine proceeds is provided and includes a first stage to remove primary aerosol droplets from the airflow by coalescing the primary aerosol droplets into secondary aerosol droplets, which are larger than the primary aerosol droplets, and to remove solid particulates from the airflow, a second water tight stage, disposed downstream from the first stage, to prevent the secondary aerosol droplets and aqueous solutions of deliquesced particulates, which are not removed by the first stage and which are re-released into the airflow from the first stage, from proceeding along the airflow and to remove solid particulates not removed by the first stage from the airflow, and a third water removal stage, disposed downstream from the second stage, to remove from the airflow the remaining secondary aerosol droplets leaking from the first and second stages. | 03-04-2010 |
20100054919 | FILTRATION SYSTEM FOR GAS TURBINES - A system for use with an inlet of a gas turbine through which an airflow toward the gas turbine proceeds is provided and includes a first self-cleaning stage to remove dust, snow and ice from the airflow, a second water tight stage, disposed downstream from the first stage, to prevent aerosol droplets and aqueous solutions of deliquesced particulates, which include at least portions of the dust not removed by the first stage and which are re-released into the airflow from the first stage, from proceeding along the airflow and to remove solid particulates not removed by the first stage from the airflow, and a third water removal stage, disposed downstream from the second stage, to remove from the airflow aerosol droplets leaking from the second stage. | 03-04-2010 |
Patent application number | Description | Published |
20090060722 | VARIABLE-PITCH VANE OF A TURBOMACHINE - A stator stage of a compressor of a turbomachine, comprising an annular row of variable-pitch vanes, each vane comprising an external cylindrical pivot defining the axis of rotation of the vane, and an internal cylindrical pivot mounted in a housing of an internal ring, the internal pivot of each vane extending along an axis substantially parallel to the axis of rotation of the vane and at a distance from this axis, and being mounted in the housing of the ring by a swiveling or a tilting system. | 03-05-2009 |
20090214347 | SPLIT RING FOR A ROTARY PART OF A TURBOMACHINE - A split ring for mounting with elastic prestress in an annular groove of a rotary part of a turbomachine and having, in the free state, a diameter that is greater than the diameter of the groove, is remarkable in that, in the free state and without stress, the end portions of the ring are circular arcs having a radius of curvature that is substantially equal to the radius of curvature of the annular groove. | 08-27-2009 |
20100266389 | TURBOMACHINE VARIABLE-PITCH STATOR BLADE - The present invention relates to a turbomachine variable-pitch stator blade comprising an aerofoil ( | 10-21-2010 |
20110123341 | DEVICE FOR AXIAL RETENTION OF MOBILE VANES MOUNTED ON A ROTOR DISC - A device for axial retention of mobile vanes mounted on a rotor disc includes two open rings, superimposed. At least one of the rings includes a rotating stop mechanism configured to cooperate with at least one hook of the disc. The two open rings are mounted in a discontinuous groove formed in the hooks, at the end of teeth situated on the periphery of the rotor disc, such that the rotating stop mechanism of the first ring is placed in the opening of the second ring. The significance of contact surfaces between the two rings allows a damping of vibrations during operation. | 05-26-2011 |
20120063907 | CIRCUMFERENTIAL BLOCKING DEVICE OF CLAMP VANES FOR TURBINE ENGINE, WITH IMPROVED RADIAL DEPLOYMENT - The invention relates to a device ( | 03-15-2012 |
20130202423 | ANGULAR SECTOR OF A STATOR FOR A TURBINE ENGINE COMPRESSOR, A TURBINE ENGINE STATOR, AND A TURBINE ENGINE INCLUDING SUCH A SECTOR - A stator angular sector for a turbine engine compressor and including: an outer shroud and an inner shroud; and at least one vane extending radially between the shrouds and connected thereto at its radial ends. At one of its axial ends the outer shroud includes a cavity opening out to the axial end and extending between a radially-inner tongue of the outer shroud to which the radially-outer end of the vane is connected, and a radially-outer tongue of the outer shroud carrying a mounting mechanism for mounting the stator angular sector to a casing of the engine. An abutment-forming insert is housed at least in part in the cavity, the abutment-forming insert configured to limit radial movements of the radially-inner tongue by contact and thus to modify vibratory behavior of the radially-inner tongue. | 08-08-2013 |
20130223990 | ANGULAR SECTOR OF A STATOR FOR A TURBINE ENGINE COMPRESSOR, A TURBINE ENGINE STATOR, AND A TURBINE ENGINE INCLUDING SUCH A SECTOR - A stator angular sector for a turbine engine compressor including: an outer shroud and an inner shroud, and at least one vane extending radially between the shrouds. The outer shroud includes first and second mounting mechanisms for mounting the stator angular sector on a casing of the engine, which mechanisms are oriented parallel to the axis in opposite directions and connected together by an intermediate portion. The outer shroud includes at least one axial end portion extending from the intermediate portion with which at least one damper-forming insert is configured to come into contact, such that beyond a given value for amplitude of vibration of the end portion, the damper insert and the end portion are configured to move relative to each other to vary total moving mass moving with the end portion, thereby modifying vibratory behavior of the end portion. | 08-29-2013 |
20140341728 | ANGULAR DIFFUSER SECTOR FOR A TURBINE ENGINE COMPRESSOR, WITH A VIBRATION DAMPER WEDGE - The invention provides an angular diffuser sector ( | 11-20-2014 |