Botrel
Erwan Botrel, Alfortville FR
Patent application number | Description | Published |
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20100040475 | OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE - When cold and in the uncoated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance from the point in question to a reference plane P | 02-18-2010 |
20110135496 | COOLING OF THE TIP OF A BLADE - A turbine blade including an open cavity at its distal tip, the cavity being defined by a bottom wall and a side wall extending along the perimeter of the distal tip in an extension of the upper and lower walls of the blade, the side wall of the cavity including an opening in a vicinity of the leading edge of the blade opening into the cavity. A deflector extends at least in the middle portion of the cavity between the leading edge and the trailing edge. | 06-09-2011 |
Erwan Daniel Botrel, Alfortville FR
Patent application number | Description | Published |
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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 |
20120282110 | INNER VENTILATION BLADE - A blade, for example of a high-pressure turbine, is designed with an internal partition ( | 11-08-2012 |
20140322028 | GAS TURBINE BLADE WITH TIP SECTIONS OFFSET TOWARDS THE PRESSURE SIDE AND WITH COOLING CHANNELS - A hollow blade including an airfoil extending along a longitudinal direction, a root, a tip, an internal cooling passage, and an open cavity defined by an end wall and a rim, together with cooling channels connecting the internal cooling passage to a pressure side. The cooling channels slope relative to the pressure side. A stack of airfoil sections of the blade at a level of the rim of the tip of the blade are offset towards the pressure side. The pressure side wall of the airfoil includes a projecting portion and cooling channels arranged in the projecting portion to open out into a terminal face of the projecting portion. | 10-30-2014 |
Erwan Daniel Botrel, Moissy Cramayel Cedex FR
Patent application number | Description | Published |
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20150240649 | COOLED VANE OF A HIGH-PRESSURE TURBINE - The invention relates to a movable vane of a turbomachine comprising a blade ( | 08-27-2015 |
Ronan Botrel, Marey Sur Tille FR
Patent application number | Description | Published |
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20090014321 | Surface Treatment Electrode - The invention concerns a surface treatment electrode ( | 01-15-2009 |
20150014172 | METHOD OF SYNTHESIZING A METAL FOAM, METAL FOAM, USES THEREOF AND DEVICE COMPRISING SUCH A METAL FOAM - A method of synthesizing a metal foam of at least one metal M having a porous micrometric structure, the method including a step of contact glow discharge electrolysis in an electrolytic plasma reduction conducted in an electrolytic solution in which are immersed an anode and a cathode connected to a continuous electrical power supply, the electrolytic solution including at least one first electrolyte in a solvent, the first electrolyte being the at least one metal M in cationic form, the electrolytic solution further including a gelatine, as well as a metal foam obtained by this method, and a device comprising such a foam. | 01-15-2015 |