• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Method for compacting an anti-corrosion paint covering a part (1), in particular a turbomachine, comprising a step of spraying particles, preferably abrasive, onto the part (1), characterized in that said particles have a hardness less than or equal to 5 MOHS, preferably less than or equal to 4 MOHS, and more preferably between 3 and 4 MOHS.
    公开号:FR3040013A1
    申请号:FR1557725
    申请日:2015-08-13
    公开日:2017-02-17
    发明作者:Anthony Grunenwald
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Method for compacting anti-corrosion paint of a turbomachine part
    TECHNICAL AREA
    The present invention relates to a method of compacting an anti-corrosion paint covering a part, in particular a turbomachine.
    STATE OF THE ART
    Document FR-A1-2 991 216 describes a compacting process of this type.
    Some turbomachine parts have very high mechanical loads and only specific materials can meet the mechanical strength requirements imposed on them. These materials have, in general, the disadvantage of being very sensitive to corrosion; it is therefore imperative to protect them by a product that is likely to withstand the environment in which these parts evolve (high temperature, presence of engine oil, kerosene, etc.).
    The corrosion protection currently used consists of a covering of the part with a paint resistant to the high temperatures and the various fluids mentioned above. But this painting being classified CMR, acronym for Carcinogenic, Mutagenic, Reprotoxic, is struck by the REACH regulation on the registration, evaluation, authorization and restrictions of chemical substances. It has therefore been necessary to look for a new method of protection to overcome the constraints related to this regulation.
    A first solution consisted in basing the protection system no longer on the sole principle of a covering by a paint but on a physicochemical process, called anodic painting. This process involves spraying a liquid paint loaded with metal particles, such as aluminum or zinc, onto the surface of the workpiece, and then heating the workpiece in an oven to cure the projected paint. This results in a hard protective layer that protects against oxidation as long as it is not scuffed but has the property of not being conductive. As soon as the part is scratched or scratched, the protection ceases, the part becoming sensitive to electrochemical corrosion.
    To mitigate this risk, it is necessary to make conductive the surface layer to make a sacrificial layer that will corrode preferentially instead of the metal of the part to be protected. We then speak of anodic paint to designate the surface layer, thus made conductive. To do this, it is necessary to contact the aluminum pigments that are incorporated in the formulation of the paint after polymerization, by mechanical action, without degrading the cosmetic appearance and the integrity of the film. The contacting of the metallic pigments is generally carried out by compacting the paint. Compaction consists of sandblasting or blasting the painted parts after polymerization. This action makes it possible to achieve electrical continuity of the metallic pigments with the metal parts to be treated.
    In the present technique, compaction is carried out by spraying particles of white corundum, which is a very hard mineral element (9-9.5 on the MOHS scale). This compacting makes it possible to densify the paint and to give it sacrificial properties responsible for its effective anticorrosion properties.
    However, corundum is not suitable for compaction of all paints. The inventors have notably found that the compaction of certain paints by means of particles of white corundum induces large incrustations of fragments of white corundum in the paint.
    These inlays have a major disadvantage in the aeronautical industry. In operation, a release of these fragments of white corundum can occur. Due to the hardness of this element, these fragments could degrade rolling bearings of turbomachines and thus reduce their duration of use.
    The present invention provides a simple, effective and economical solution to this problem.
    DESCRIPTION OF THE INVENTION The invention proposes a method for compacting an anticorrosive paint covering a part, in particular a turbomachine, comprising a step of projecting particles, preferably abrasive particles, onto the part, characterized in that said particles have a hardness less than or equal to 5 MOHS, preferably less than or equal to 4 MOHS, and more preferably between 3 and 4 MOHS.
    The inventors have found that plastic particles, because of their hardness less than that of white corundum, become less encrusted in the paint, which therefore limits the risk of said release.
    The particles can be projected by sanding or blasting. They can for example be projected by sandblasting or shot blasting machines equipped with a circulation system adapted to light plastic particles.
    The projection can be carried out at a suitable air pressure and a mass flow rate of the air flow.
    For example, the particles have an apparent density of less than or equal to 800 kg / m 3, and preferably between 720 and 770 kg / m 3.
    For example, the particles have a specific gravity less than or equal to 2 g / cm 3, preferably less than or equal to 1.6 g / cm 3, and for example between 1.3 and 1.6 g / cm 3.
    For example, the particles have an average diameter less than or equal to 2 mm, preferably less than 1 mm, and for example of the order of 0.6 mm.
    The particles are advantageously made of plastic.
    The particles may be polyester resin, acrylic, or urea-formaldehyde or melamine.
    The part is for example a turbomachine shaft.
    The method preferably comprises a subsequent step of cooking the room under air. This baking step preferably takes place at 300 ° C. and for about 6 hours.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: Figure 1 is a schematic front view of a sanding device of a workpiece; FIG. 2 is a diagrammatic view, from above, of a sanding device of FIG. 1; FIG. 3 is a SEM image of a paint which has been compacted by particles of white corundum; FIG. 4 is a SEM image of a paint which has been compacted by plastic particles, and FIG. an SEM image of a paint that has been compacted by plastic particles, and annealing to remove them by combustion.
    DETAILED DESCRIPTION
    With reference to FIGS. 1 and 2, the sanding of a workpiece 1 as commonly practiced for the surface finishing of a turbomachine part, as seen from the front and in plan view, is seen respectively. than a tree.
    Sandblasting is carried out for example with two nozzles 2, which are oriented at 90 ° to each other and which each send a bundle of sand 3 perpendicular to the surface of the part 1, the two jets propagating in the same plane.
    The distance "d" from the straight line connecting the two nozzles 2 to the piece 1 is such that the two bundles 3 meet at a focusing point 4 which is located on the piece 1, that is to say they both reach the same point to sandblast.
    To sandblast the two nozzles 2 are moved simultaneously along the piece 1, its height and its circumference, maintaining at all times the same geometry for the relative position of the nozzles 2 and the surface of the workpiece 1.
    Given the solid angle characterizing the divergence of the beams 3 the surface swept at each instant by sanding in the shape of a circle of diameter "f". The invention is not limited to the use of this sanding machine which is described only by way of example. The sanding machine could for example comprise a single nozzle oriented at 85 ° to the surface to be compacted part. The sanding machine may be one of those marketed by the companies Rosier and Wheelabrator.
    In a particular embodiment of the invention, the turbomachine shaft is a turbine shaft which is covered with a Maberbind CF® metallic paint marketed by Soficor Mâder.
    Plastic particles are used, for example those marketed by Flugzeug-Union Süd GmbH under the name Dry Strip® Type 2. These particles can be sprayed using the aforementioned sanding machine or using a sucking shot blasting machine, with a suitable air pressure, for example 0.8 bar, and a mass flow rate adapted adapted flow, for example 20%. The machine is for example equipped with one or two round nozzles of 10 to 14mm.
    In this specific example, the invention makes it possible to obtain, after measurement with an ohmmeter, the necessary conductivity (conductivity which makes it possible to translate if the compacting has been sufficiently efficient - sacrificial property) and equivalent to the white corundum (180 μm) to ensure the Anticorrosion protection sought (resistance <5Ω).
    Salt spray tests (according to the ISO 9227 standard) have shown that the paint acts as a corrosion inhibitor of the substrate after 168 hours of aging. The advantage of the plastic material is a low hardness, for example between 3 and 4 MOHS, much lower than the materials of the turbine bearings sensitive to friction in case of encrustation and release of these particles. In addition, the rate of incrustation is much lower compared to the SEM images of FIGS. 3 and 4.
    FIG. 3 is a SEM image of the surface of a specimen compacted by projection of white corundum particles of 180 μιτι. It is found that this surface has many inlays, the density of incrustations being of the order of 2900 inlays / cm2.
    Figure 4 is an SEM image of the surface of a test specimen compacted by projection of plastic particles. It is found that this surface has fewer inlays, the density of incrustations being of the order of 600 inlays / cm2.
    Compaction with plastic particles therefore has a double advantage: - the risk of release is less, or in other words, the amount of particles that is désincruste is lower (due to the density of encrustations about five times lower), and the hardness of the salted elements is markedly reduced (corundum between 9 and 9.5 MOHS against 3.5 MOHS for the aforementioned plastic medium). The risk of bearing deterioration is thus reduced, and becomes more acceptable. To this is added the possibility of eliminating encrustations of plastic particles by cooking or burning, for example at 300 ° C. under air for 6 hours.
    FIG. 5 is an SEM image of the surface of a specimen compacted by projection of plastic particles after annealing at a temperature of 300 ° C. for 6 hours.
    Some fine traces of carbon residues are visible, but most of the encrusted plastic particles have been calcined. The risk of release and degradation of the bearings is thus significantly reduced.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A method of compacting an anti-corrosion paint covering a part (1), in particular a turbomachine, comprising a step of spraying particles, preferably abrasive particles, onto the part (1), characterized in that said particles have a hardness less than or equal to 5 MOHS, preferably less than or equal to 4 MOHS, and more preferably between 3 and 4 MOHS.
    [2" id="c-fr-0002]
    2. The method of claim 1, wherein said particles are projected by sanding or shot blasting.
    [3" id="c-fr-0003]
    3. Method according to claim 1 or 2, wherein said particles have a specific gravity less than or equal to 2g / cm3, preferably less than or equal to 1.6g / cm3, and for example between 1.3 and 1.6g / cm3.
    [4" id="c-fr-0004]
    4. Method according to one of the preceding claims, wherein said particles have a bulk density of less than or equal to 800kg / m3, for example between 720 and 770kg / m3.
    [5" id="c-fr-0005]
    5. Method according to one of the preceding claims, wherein said particles have an average diameter less than or equal to 2mm, preferably less than 1 mm, and for example of the order of 0.6mm.
    [6" id="c-fr-0006]
    6. Method according to one of the preceding claims, wherein said particles are plastic.
    [7" id="c-fr-0007]
    7. Method according to the preceding claim, wherein said particles are urea-formaldehyde-based resin.
    [8" id="c-fr-0008]
    8. Method according to one of the preceding claims, wherein the part (1) is a turbomachine shaft.
    [9" id="c-fr-0009]
    9. Method according to one of the preceding claims, wherein it comprises a subsequent step of cooking the part (1) in air.
    [10" id="c-fr-0010]
    10. Method according to the preceding claim, wherein the firing step takes place at 300 ° C and for about 6 hours.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3040013A1|2017-02-17|METHOD FOR COMPACTING AN ANTI-CORROSION PAINT OF A TURBOMACHINE PIECE
    EP2855083B1|2016-06-15|Method for compacting anodic paints, including the collision of sandblasting jets
    Chen et al.2012|High-power fibre laser cleaning for green shipbuilding.
    JPWO2017047722A1|2018-07-26|Composition, threaded joint for pipes provided with a solid lubricating film formed from the composition, and method for producing the threaded joint for pipes
    CH631091A5|1982-07-30|PROCESS FOR APPLYING A COATING CONSISTING OF A POLYMER CONTAINING A LOAD ON THE INSIDE OF A CYLINDRICAL BODY.
    US20030078170A1|2003-04-24|Ballistics conditioning
    Vicenzi et al.2006|HVOF-coatings against high temperature erosion | by coal fly ash in thermoelectric power plant
    JP2009293128A|2009-12-17|Surface treatment method for high-strength steel machine part and sealing system obtained by implementing the method
    JP2011137231A|2011-07-14|Method for inhibiting corrosion of high strength steel turbine component
    WO2007095490A3|2008-05-08|Methods of using halogen-containing organic compounds to remove deposits from internal surfaces of turbine engine components
    EP3653337A1|2020-05-20|Method for compacting anti-corrosion paint of a part of a turbine engine
    RU2553742C1|2015-06-20|Method of protective corrosion resistant coating application on external and internal surface of metal pipe
    EP0647505A1|1995-04-12|Method and apparatus for the treatment of metallic workpieces, either coated or not
    Antunes et al.2013|Characterization of FeCr and FeCoCr alloy coatings of carbon steels for marine environment applications
    FR2669397A1|1992-05-22|METALLIC TANK, IN PARTICULAR BOTTLE OR TANK FOR GAS.
    Luo et al.2001|Slurry erosion resistance of fusion-bonded epoxy powder coating
    Vite-Torres et al.2014|Study of solid particle erosion on AISI D2 using angular silicon carbide and steel round grit particles
    Hajji et al.2018|High pressure cryogenic nitrogen jet for clean coating removal: experimental study of polyamide ablation
    Relue et al.2021|Corrosion performance of different aluminum alloy deposits fabricated by lateral friction surfacing
    CN110539125A|2019-12-06|method for repairing slurry circulating pump
    KR20090048009A|2009-05-13|Process for surface treatment of break disk
    FR3096916A1|2020-12-11|Sandblasting medium and method of surface treatment using such a sandblasting medium
    Bilz et al.2012|ice clean
    WO2021084205A1|2021-05-06|Method for compacting an anti-corrosion coating
    Zaroog et al.2018|Improving Astm A516 Grade 70 Mechanical Properties by Sandblasting Process
    同族专利:
    公开号 | 公开日
    FR3040013B1|2018-02-23|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5512006A|1993-10-29|1996-04-30|Ultra Blast Partners|Method for enhancing the rust resistance and the surface finish of a non-ferrous workpiece|
    US20120294756A1|2009-10-30|2012-11-22|Eiji Yamaguchi|Shots made from zinc-based alloy|
    FR2991216A1|2012-05-29|2013-12-06|Snecma|METHOD FOR COMPACTING ANODIC PAINTS WITH COLLISION OF SANDBLASTING JETS|EP3653337A1|2018-11-16|2020-05-20|Safran Aircraft Engines|Method for compacting anti-corrosion paint of a part of a turbine engine|
    WO2021084205A1|2019-10-30|2021-05-06|Safran Aircraft Engines|Method for compacting an anti-corrosion coating|
    WO2021084202A1|2019-10-31|2021-05-06|Safran Aircraft Engines|Method for compacting an anti-corrosive paint of a turbine engine part|
    法律状态:
    2016-08-25| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-17| PLSC| Publication of the preliminary search report|Effective date: 20170217 |
    2017-05-17| PLFP| Fee payment|Year of fee payment: 3 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 5 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1557725A|FR3040013B1|2015-08-13|2015-08-13|METHOD FOR COMPACTING AN ANTI-CORROSION PAINT OF A TURBOMACHINE PIECE|
    FR1557725|2015-08-13|FR1557725A| FR3040013B1|2015-08-13|2015-08-13|METHOD FOR COMPACTING AN ANTI-CORROSION PAINT OF A TURBOMACHINE PIECE|
    [返回顶部]