EP2855083B1 - Verfahren zum verdichten anodischer farben einschliesslich einer sandstrahlenkollision - Google Patents

Verfahren zum verdichten anodischer farben einschliesslich einer sandstrahlenkollision Download PDF

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Publication number
EP2855083B1
EP2855083B1 EP13729999.6A EP13729999A EP2855083B1 EP 2855083 B1 EP2855083 B1 EP 2855083B1 EP 13729999 A EP13729999 A EP 13729999A EP 2855083 B1 EP2855083 B1 EP 2855083B1
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EP
European Patent Office
Prior art keywords
jets
sand
sandblasting
compacting
anodic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13729999.6A
Other languages
English (en)
French (fr)
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EP2855083A1 (de
Inventor
Jacques BOULOGNE
Alain Potel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Services SA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
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Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP2855083A1 publication Critical patent/EP2855083A1/de
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
    • B05D3/12—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by mechanical means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C3/00—Abrasive blasting machines or devices; Plants
    • B24C3/02—Abrasive blasting machines or devices; Plants characterised by the arrangement of the component assemblies with respect to each other
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/10—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening

Definitions

  • the field of the present invention is that of the surface treatment of mechanical parts and, in particular, that of compaction of anodic paints for the protection of turbine engine parts.
  • Some aircraft engine 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 with 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 to the various fluids mentioned above. But this painting being classified CMR (for Carcinogenic, Mutagenic, Reprotoxic), it is struck by the REACH regulation on the registration, the evaluation, the authorization and the restrictions of the 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 consists in projecting onto the surface of the part a liquid loaded with metal pigments, such as aluminum or zinc, and then heating the part in an oven to polymerize the projected product.
  • metal pigments such as aluminum or zinc
  • the protection ceases, the part becoming sensitive to electrochemical corrosion.
  • it is advisable to make the surface layer conductive so as to make it a sacrificial layer which will corrode preferentially, in place of the metal of the part to be protected.
  • the subject of the invention is a process for compacting sand-blasting anodic paints comprising sending at least two jets of an abrasive material towards a part covered by said paint, said jets being oriented from convergent manner and meeting at a point of focus, characterized in that said point of focus is positioned upstream of the piece.
  • the arrangement of the jets of abrasive material has a symmetry with respect to the direction perpendicular to the surface to be treated.
  • the jets of abrasive material are two in number and form an angle of 90 ° between them.
  • the distance of the focusing point from the surface of the workpiece is between 200 and 300 mm.
  • the sanding pressure is greater than 2 bars. It is therefore possible to use the existing sandblasting facilities, by simply making a drop in the sand spray nozzles.
  • FIG. 1 and 2 it is seen, respectively in front view and in top view, sanding a workpiece 1 as it is commonly practiced for the surface finish of a turbomachine part.
  • the conventional sanding is carried out 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 plan.
  • the distance "d" from the straight line connecting the two nozzles 2 to the piece 1 is such that the two beams 3 meet at a focusing point 4 which is located on the piece 1, that is to say they reach both have the same point to sand.
  • FIG. 3 and 4 it is seen, respectively in front view and in top view, the compaction, according to the invention, of the paint which covers the workpiece.
  • the two nozzles 2 are positioned as before with jets 3 oriented in the same plane at 90 ° to each other and with the same solid angle of divergence.
  • the sweeping along the piece is done, again, in the same way as for a conventional sandblasting.
  • the distance at which the nozzles are placed from the surface of the part is increased compared to the previous case, so that the straight line connecting them is now at a distance greater than the focusing distance d.
  • the adjustment of the nozzle / workpiece distance is made so that the focal point 4 of the jet is on the surface of the workpiece 1, that is to say where the kinetic energy of sand is the strongest.
  • the sanding pressures used are commonly of the order of 3 bars.
  • the focusing length d is invariable, irrespective of the sanding pressures used.
  • the invention consists in increasing the nozzle / piece distance without changing the angle of incidence of 90 ° of the sand bundles between them. The focal point 4 of these beams is then no longer at the level of the room itself, but at a point of convergence where the sand jets intertwine.
  • the collision of the particles then generates a beam diffraction, which has the effect of reducing the speed of the sand particles on the part 1 thus reducing its kinetic energy and making the diffracted beam 5 lose its power.
  • the consequence is a conservation of the cosmetic integrity of the paint while making it electrically conductive.
  • this solution has the advantage, because of the greater divergence of the diffracted beam 5, to cover a larger surface area of the workpiece and thus to be able to increase the scanning speed and thus reduce the treatment cycle. .
  • the invention recommends for this purpose a distance of recoil "r" of the piece relative to the focal point, which is of the order of 250mm, and in any case between 200 and 300 mm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)

Claims (5)

  1. Verfahren zum Verdichten von anodischen Farben mittels Sandstrahlen, das umfasst, mindestens zwei Strahlen (3) eines Schleifmaterials in Richtung eines Teils (1) zu leiten, das von dieser Farbe bedeckt ist, wobei diese Strahlen konvergent ausgerichtet sind und sich in einem Brennpunkt (4) treffen, dadurch gekennzeichnet, dass dieser Brennpunkt sich vor dem Teil (1) befindet.
  2. Verdichtungsverfahren gemäß Anspruch 1, bei dem die Ausrichtung der Strahlen (3) des Schleifmaterials eine Symmetrie bezogen auf die Richtung, die senkrecht zu der zu behandelnden Oberfläche liegt, aufweist.
  3. Verdichtungsverfahren gemäß Anspruch 2, bei dem die Strahlen (3) des Schleifmaterials zwei sind und miteinander einen 90°-Winkel bilden.
  4. Verdichtungsverfahren gemäß einem der Ansprüche 1 bis 3, bei dem der Abstand des Brennpunktes (4) bezogen auf die Oberfläche des zu bearbeitenden Teils (1) zwischen 200 und 300 mm liegt.
  5. Verdichtungsverfahren gemäß Anspruch 4, bei dem der Streuungsdruck über 2 bar liegt.
EP13729999.6A 2012-05-29 2013-05-29 Verfahren zum verdichten anodischer farben einschliesslich einer sandstrahlenkollision Active EP2855083B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1254921A FR2991216B1 (fr) 2012-05-29 2012-05-29 Procede de compactage de peintures anodiques avec collision des jets de sablage
PCT/FR2013/051192 WO2013178941A1 (fr) 2012-05-29 2013-05-29 Procédé de compactage de peintures anodiques avec collision des jets de sablage

Publications (2)

Publication Number Publication Date
EP2855083A1 EP2855083A1 (de) 2015-04-08
EP2855083B1 true EP2855083B1 (de) 2016-06-15

Family

ID=46963809

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13729999.6A Active EP2855083B1 (de) 2012-05-29 2013-05-29 Verfahren zum verdichten anodischer farben einschliesslich einer sandstrahlenkollision

Country Status (10)

Country Link
US (1) US9427845B2 (de)
EP (1) EP2855083B1 (de)
JP (1) JP6175132B2 (de)
CN (1) CN104349869B (de)
BR (1) BR112014029428B1 (de)
CA (1) CA2874833C (de)
FR (1) FR2991216B1 (de)
IN (1) IN2014DN10682A (de)
RU (1) RU2627072C2 (de)
WO (1) WO2013178941A1 (de)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3028776B1 (fr) * 2014-11-25 2018-12-07 Safran Aircraft Engines Systeme pour peindre sur un banc de peinture rotatif une extremite evasee d'arbre creux
FR3040013B1 (fr) * 2015-08-13 2018-02-23 Safran Aircraft Engines Procede de compactage d'une peinture anti-corrosion d'une piece de turbomachine
FR3088564B1 (fr) * 2018-11-16 2020-12-25 Safran Aircraft Engines Procede de compactage d'une peinture anti-corrosion d'une piece de turbomachine
FR3102694B1 (fr) * 2019-10-30 2022-06-03 Safran Aircraft Engines Procede de compactage d’un revetement anti-corrosion
FR3102687B1 (fr) 2019-10-31 2021-10-15 Safran Aircraft Engines Procede de compactage d’une peinture anti-corrosion d’une piece de turbomachine
FR3122342A1 (fr) 2021-04-30 2022-11-04 Safran Aircraft Engines Procede de compactage d’une peinture anti-corrosion d’une piece de turbomachine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3754976A (en) 1971-12-06 1973-08-28 Nasa Peen plating
US5098797A (en) 1990-04-30 1992-03-24 General Electric Company Steel articles having protective duplex coatings and method of production
US6604986B1 (en) 1997-11-20 2003-08-12 Nederlandse Organisatie Voor Toegepast-Natuurwetenschappelijk Onderzoek Tno Process and device for working a workpiece
WO2009112945A2 (en) 2008-03-12 2009-09-17 Enbio Limited Nozzle configurations for abrasive blasting
EP2226409A2 (de) 2009-03-06 2010-09-08 General Electric Company Erosions- und korrosionsbeständige Turbinenkompressorschaufel und Herstellungsverfahren dafür
US20110236192A1 (en) 2008-09-05 2011-09-29 Snecma Compressor housing resistant to titanium fire, high-pressure compressor including such a housing and aircraft engine fitted with such a compressor

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Publication number Priority date Publication date Assignee Title
US1654509A (en) * 1924-08-30 1927-12-27 Bound Brook Oil Less Bearing Antifriction bearing and method of forming the same
US3020182A (en) * 1958-09-26 1962-02-06 Gen Electric Ceramic-to-metal seal and method of making the same
SU814698A1 (ru) * 1978-06-20 1981-03-23 Bulkin Valentin A Устройство дл гидроабразивнойОбРАбОТКи дЕТАлЕй
DE3469145D1 (en) * 1984-08-14 1988-03-10 Johan Szucs Stone and metal cleaning system
DE3539464A1 (de) * 1985-11-07 1987-05-14 Hollingsworth Gmbh Verfahren zum behandeln der kanten eines saegezahndrahtes
GB8627308D0 (en) * 1986-11-14 1986-12-17 Alcan Int Ltd Composite metal deposit
JPH0762559A (ja) * 1993-08-27 1995-03-07 Inter Metallics Kk 粉体皮膜形成方法
RU2104831C1 (ru) * 1993-11-05 1998-02-20 Борис Михайлович Солодов Способ резки струей жидкости с абразивом
US5592841A (en) * 1994-07-14 1997-01-14 Champaigne; Jack M. Shot peening method
US5526664A (en) * 1994-09-07 1996-06-18 Progressive Technologies, Inc. Method of forming a textured pattern on a metal plate which pattern is transformed to a plastic part, and a press plate and plastic part produced thereby
US6123999A (en) * 1997-03-21 2000-09-26 E. I. Du Pont De Nemours And Company Wear resistant non-stick resin coated substrates
CN1270091A (zh) * 2000-01-03 2000-10-18 刘毅 具有多个喷气嘴的射吸喷吵嘴
JP2010502468A (ja) * 2006-09-11 2010-01-28 エンバイオ リミテッド 表面ドーピング方法

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3754976A (en) 1971-12-06 1973-08-28 Nasa Peen plating
US5098797A (en) 1990-04-30 1992-03-24 General Electric Company Steel articles having protective duplex coatings and method of production
US5098797B1 (en) 1990-04-30 1997-07-01 Gen Electric Steel articles having protective duplex coatings and method of production
US6604986B1 (en) 1997-11-20 2003-08-12 Nederlandse Organisatie Voor Toegepast-Natuurwetenschappelijk Onderzoek Tno Process and device for working a workpiece
WO2009112945A2 (en) 2008-03-12 2009-09-17 Enbio Limited Nozzle configurations for abrasive blasting
US20110104991A1 (en) 2008-03-12 2011-05-05 Enbio Limited Nozzle configurations for abrasive blasting
US20110236192A1 (en) 2008-09-05 2011-09-29 Snecma Compressor housing resistant to titanium fire, high-pressure compressor including such a housing and aircraft engine fitted with such a compressor
EP2226409A2 (de) 2009-03-06 2010-09-08 General Electric Company Erosions- und korrosionsbeständige Turbinenkompressorschaufel und Herstellungsverfahren dafür

Also Published As

Publication number Publication date
JP6175132B2 (ja) 2017-08-02
BR112014029428B1 (pt) 2020-07-07
RU2014150516A (ru) 2016-07-20
CA2874833A1 (fr) 2013-12-05
WO2013178941A1 (fr) 2013-12-05
IN2014DN10682A (de) 2015-08-28
BR112014029428A2 (pt) 2018-05-15
RU2627072C2 (ru) 2017-08-03
US9427845B2 (en) 2016-08-30
US20150158146A1 (en) 2015-06-11
CN104349869A (zh) 2015-02-11
JP2015517925A (ja) 2015-06-25
FR2991216B1 (fr) 2014-07-04
FR2991216A1 (fr) 2013-12-06
CN104349869B (zh) 2017-02-15
EP2855083A1 (de) 2015-04-08
CA2874833C (fr) 2020-10-27

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