REPARACION DE SUPERALEACION USANDO ASPERSION EN FRIO.

    公开(公告)号:MXPA05013002A

    公开(公告)日:2006-06-07

    申请号:MXPA05013002

    申请日:2005-12-01

    Inventor: HAYNES JEFFREY D

    Abstract: La presente invencion describe un metodo para reparar componentes formados de un material de superaleacion que comprende las etapas de proporcionar un componente formado de un material de superaleacion que tiene un defecto que se va a reparar y depositar un material de reparacion sobre una superficie del componente usando un gas portador no oxidante de modo que el material de reparacion se deforma plasticamente y se une a la superficie con el impacto con la superficie y por medio de esto cubre el defecto.

    Cold Spray Process for Coating Substrates

    公开(公告)号:GB2394479A

    公开(公告)日:2004-04-28

    申请号:GB0324367

    申请日:2003-10-17

    Abstract: A process for applying a coating to a substrate 10 comprising the steps of providing metal particles having a size up to 50 microns and passing the metal particles through a spray nozzle 20 at a speed sufficient to plastically deform them on the substrate. The metal particles preferably have a size of between 5-50 microns, and may be chosen from copper alloy, aluminium alloy or nickel alloy particles. The particles are preferably fed to the nozzle using a carrier gas of helium, nitrogen or a mixture of both. The substrate is preferably a stainless steel manifold for a rocket engine, and the coating is applied to at least one of its outer surface 26 or its inner surface 24. The nozzle may deposit a layer 28 between 0.025 - 0.076 mm thick per pass, and the total thickness of the layer may be greater than 1.27mm.

    COLD SPRAYED COPPER FOR ROCKET ENGINE APPLICATIONS

    公开(公告)号:CA2444917A1

    公开(公告)日:2004-04-18

    申请号:CA2444917

    申请日:2003-10-15

    Abstract: A process is provided for forming a deposit layer on a substrate, in particular forming a copper or copper alloy deposit layer on at least one of an inner surface and/or an outer surface of a metal alloy manifold used in a rocket engine. The process comprises the steps of providing metal powder particles having a size in the range of from a size sufficient to avoid getting swept away from the substrate due to a bow shock layer to up to 50 microns and forming a deposit layer on at least one surface of the substrate by passing the metal powder particles through a spray nozzle at a speed sufficient to plastically deform the metal powder particles on the at least one surface.

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