SNECMA MOTEURS Patent applications |
Patent application number | Title | Published |
20110048583 | HARDENED MARTENSITIC STEEL, METHOD FOR PRODUCING A COMPONENT FROM THIS STEEL AND COMPONENT OBTAINED IN THIS MANNER - The invention relates to steel which is characterized by the following composition as expressed in percentages by weight: —C=0.18 0.30%, —Co=5-7%, —Cr=2-5%, —Al=1-2%, —Mo+W/2=1-4%, —V=trace 0.3%, —Nb=trace 0.1%, —B=trace−50 ppm, —Ni=10.5-15% with Ni≧7+3.5 Al, —Si=trace 0.4%, —Mn=trace 0.4%, —Ca=trace−500 ppm, —Rare earths=trace−500 ppm, —Ti=trace−500 ppm, −O=trace−200 ppm if the steel is obtained by means of powder metallurgy or trace−50 ppm if the steel is produced in air or under a vacuum from molten metal, —N=trace−100 ppm, —S=trace−50 ppm, —Cu=trace−1%, and —P=trace−200 ppm, the remainder including iron and the inevitable impurities resulting from production. The invention also relates to a method of producing a part from said steel and to the part thus obtained. | 03-03-2011 |
20110041961 | HARDENED MARTENSITIC STEEL, METHOD FOR PRODUCING A COMPONENT FROM THIS STEEL AND COMPONENT OBTAINED IN THIS MANNER - The invention relates to steel which is characterized by the following composition as expressed in percentages by weight: —C=0.18 0.30%, —Co=5-7%, —Cr=2-5%, —Al=1-2%, —Mo+W/2=1-4%, —V=trace 0.3%, —Nb=trace 0.1%, —B=trace-50 ppm, —Ni=10.5-15% with Ni≧7+3.5 Al, —Si=trace 0.4%, —Mn=trace 0.4%, —Ca=trace-500 ppm, —Rare earths=trace-500 ppm, —Ti=trace-500 ppm, —O=trace-200 ppm if the steel is obtained by means of powder metallurgy or trace-50 ppm if the steel is produced in air or under a vacuum from molten metal, —N=trace-100 ppm, —S=trace-50 ppm, —Cu=trace-1%, and —P=trace-200 ppm, the remainder including iron and the inevitable impurities resulting from production. The invention also relates to a method of producing a part from said steel and to the part thus obtained. | 02-24-2011 |
20100254823 | HOLLOW ROTOR BLADE FOR THE TURBINE OF A GAS TURBINE ENGINE - A hollow blade includes an internal cooling passage, an open cavity located at the tip of the blade and bounded by an end wall and a rim and cooling channels that connect the internal cooling passage to the outer face of the pressure wall. The cooling channels are inclined to the pressure wall in such a way that they emerge on the outer face of the pressure wall near the top of the rim. A reinforcement of material is present between the rim and the end wall of the cavity along at least one portion of the pressure wall, whereby the rim is widened at its base adjacent to the end wall in such a way that the cooling channels emerge near the top of the rim without reducing the mechanical strength of the tip of the blade. | 10-07-2010 |
20100247755 | METHOD OF MANUFACTURING OR REPAIRING A COATING ON A METALLIC SUBSTRATE - The invention provides a method of manufacturing or repairing a coating on a metallic substrate. Production of said coating comprises forming a pre-layer on the substrate or on a sub-layer of the coating placed on the substrate by applying one or more layers of a paint containing at least one metal selected from the group constituted by platinum class metals (platinoids) and chromium. Application to the formation or localized repair of a thermal barrier on a superalloy turbo engine part. | 09-30-2010 |
20090148283 | NOZZLE RING ADHESIVE BONDED BLADING FOR AIRCRAFT ENGINE COMPRESSOR - A compressor nozzle ring for an aircraft includes an inner shroud, an outer shroud and a multiplicity of blades extending from the inner shroud to the outer shroud. Each blade passes through the inner shroud and is attached to it with sealing cement containing an organic polymer adhesive. The adhesive is polyimide based. | 06-11-2009 |
20090087572 | A METHOD OF FORMING A THERMAL PROTECTIVE COATING ON A SUPER ALLOY METAL SUBSTRATE - A method of forming a gas turbine part includes forming a bonding underlayer on a superalloy metal substrate, the underlayer including an intermetallic compound of aluminum, nickel, and platinum, and forming a ceramic outer layer on the alumina film formed on the bonding underlayer. The bonding underlayer essentially comprises an Ni—Pt—Al ternary system constituted by an aluminum-enriched α-NiPt type structure, in particular an Ni—Pt—Al ternary system having a composition Ni | 04-02-2009 |
20090074579 | TURBINE RING - A turbine ring made up of an assembly of a plurality of sectors forming the outer shroud of the rotor of said turbine. The sectors are united end to end with interposed sealing systems comprising tongues housed in slots, said tongues being rectilinear and engaged in respective rectilinear slots in the radial faces of said sectors. | 03-19-2009 |
20090071119 | METHOD AND SYSTEM FOR PROTECTING GAS TURBINE FUEL INJECTORS - The invention relates to a method and a device for protecting fuel injectors in a turboshaft engine. The protection is carried out by injecting compressed air directly into the injectors. The air thus directly purges the injectors and evacuates the fuel present in them into the combustion chamber. | 03-19-2009 |