Lamine
Lamine Benaissa, Gieres FR
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20150191847 | METHOD FOR PRODUCING A SINGLE-CRYSTALLINE LAYER - Process for fabricating a thin single-crystalline layer n, including steps of: a) providing a support substrate n, b) placing a seed sample n, c) depositing a thin layer n so as to form an initial interface region n including a proportion of seed sample n and a proportion of thin layer n, the proportion of seed sample n decreasing from the first peripheral part n towards the second peripheral part n, e) providing an energy input to the initial interface region n contiguous to the first peripheral part n so as to liquefy a portion n of the thin layer and form a solid/liquid interface region n, and f) gradually moving the energy input away from the seed sample n so as to solidify the portion n so as to gradually move the solid/liquid interface region n. | 07-09-2015 |
Lamine Benaissa, Massy FR
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20150364442 | METHOD FOR OBTAINING A BONDING SURFACE FOR DIRECT BONDING - A process for obtaining a bonding surface for direct bonding includes: a) providing a substrate based on a sintered metal having a base surface with an RMS roughness lower than 6 nanometres and a PV roughness lower than 100 nanometres; b) bombarding the base surface with ionic species; c) depositing a metal layer on the base surface; and d) carrying out a mechanical and/or chemical polish of an exposed surface of the metal layer. A structure including a substrate based on a sintered metal the base surface of which is at least partially formed from a metal including ionic species implanted by bombardment of the base surface, and a metal layer of identical chemical composition to that of the metal base substrate and including a bonding surface with an RMS roughness lower than 0.6 nanometres and a PV roughness lower than 10 nanometres is also provided. | 12-17-2015 |
Lamine M'Bengue, Vert Saint Denis FR
Patent application number | Description | Published |
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20140105737 | GAS TURBINE ENGINE COMPRISING THREE ROTARY BODIES - A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing through the engine from upstream to downstream. The at least one intermediate turbine rotor blade is followed directly downstream by a low pressure turbine rotor blade so as to straighten air flow deflected by the intermediate turbine rotor blade. | 04-17-2014 |