CN104342713A - Method removing aluminum oxide-titanium oxide ceramic seal coating - Google Patents
Method removing aluminum oxide-titanium oxide ceramic seal coating Download PDFInfo
- Publication number
- CN104342713A CN104342713A CN201410519088.8A CN201410519088A CN104342713A CN 104342713 A CN104342713 A CN 104342713A CN 201410519088 A CN201410519088 A CN 201410519088A CN 104342713 A CN104342713 A CN 104342713A
- Authority
- CN
- China
- Prior art keywords
- coating
- titanium oxide
- oil removing
- ultrasonic
- remove
- 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.)
- Pending
Links
Abstract
The invention provides a method for removing an aluminum oxide-titanium oxide ceramic seal coating. By combining ultrasonic and chemical processes, the method overcomes the defect that the conventional chemical process can not remove the aluminum oxide-titanium oxide ceramic surface layer. The method comprises the following steps: 1) oil removal; 2) coating removal: immersing a coated part in a 300-550 ml/L nitric acid solution, and carrying out ultrasonic treatment under the frequency of 20-40 KHz at 20-55 DEG C; and 3) residual coating removal: removing the residual coating, which can not be removed by the step above, by sand blasting.
Description
Technical field
The present invention relates to a kind of ceramic mould thermally sprayed coating minimizing technology, the particularly minimizing technology of alumina-silica titanium coating.
Background technology
Aluminium oxide-titanium oxide seal coating (Al2O3-TiO2) is a kind of Novel hot sprayed coating material of double-deck, complicated components, and belong to ceramic coating, its surface layer is alumina-silica titanium layer, and bottom is nickel aluminium lamination.This coating is mainly used in the sealing of the rotatable parts gas circuit such as the high and low pressure turbine cell cube of aircraft engine, realizes radius clearance and to obturage control, can lower the critical material of specific fuel consumption (SFC).If typical engine high pressure turbine blade-tip gap decreased average 0.254 mm, turbine efficiency just can improve about 1%; If turbine radius clearance increases by 0.127 mm specific fuel consumption (SFC) and about increases 0.5%, if pneumatic plant radius clearance increases by 0.076 mm, specific fuel consumption (SFC) about increases 1%.This makes to obtain increasing use within the engine from the coating technology of matrix material thinking.
This seal coating has two-layer, and bottom is made up of a certain proportion of metallographic phase and the nonmetallic phase with self-lubricating and wear-resisting effect usually; Surface layer is made up of the aluminium titanium metal oxide compound that hardness is higher.Seal coating selects matrix material mostly, and main component is metallographic phase, nonmetallic phase and hole.Wherein have can the performance such as sprayability, bonding strength, erosion wear resistance for metallographic phase, and conventional has nickel, aluminium etc. and alloy thereof.Nonmetallic phase provides shock-resistant, wear-resistant, anti-Adhesion property, as graphite, polybenzoate, aluminum oxide, titanium oxide etc.These novel thermally sprayed coatings to control pneumatic plant radius clearance, lower specific fuel consumption (SFC), heat insulation, obturage, wear-resisting etc. there is vital role.Because as one of the important technology of engine, seal coating can improve in aircraft gas turbines the stopping property rotated between fixing part, significantly improves the performance of engine.But thermally sprayed coating in use there will be wearing and tearing, falls the faults such as block and cause degradation, must again repair, the thermally sprayed coating of these tape jams must first be removed totally, more again sprays new coating with plasma spraying method, to meet the use of the next life cycle of engine.
Aluminium oxide-titanium oxide ceramic mould thermally sprayed coating of obturaging is that about (the bilayer structure combination that the aluminium oxide-titanium oxide coating surface layer of 0.16mm ~ 0.34mm and the Ni-Al bottom of thickness 0.1mm ~ 0.2mm are formed, actual parts bottom and surface thickness can reach about 3 ㎜ by thickness.Nickel bottom layer of aluminum and aluminium oxide-titanium oxide surface layer, all prepare with plasma spraying method.20MPa is greater than in conjunction with firm intensity between nickel aluminium undercoat and aluminium oxide-titanium oxide surface layer coating, between the Ni-Al primer coating of nickel aluminium and matrix.Alumina-silica titanium coating belongs to ceramic mould coating, extremely strong to the solidity to corrosion of the pharmaceutical chemicalss such as various acid-alkali salts, and coating is thicker, and coating removal difficulty is large.In actual production, the mechanical means that adopts is removed more, has that poor removal effect, working efficiency are not high, labour intensity large, easy damaged part even causes the shortcomings such as part rejection.
Summary of the invention
The object of the invention is the deficiency existed for existing machinery removal method, provide a kind of removal speed fast, and do not corrode the chemical method minimizing technology with injuring part matrix.
Above-mentioned purpose of the present invention can be reached by following measures, and a kind of method removing aluminium oxide-titanium oxide ceramic mould compound sealing coating material, comprises the steps:
1) oil removing: adopt electrochemical degreasing, electrochemical deoiling or ultrasonic cleaning oil removing; The serious part of greasy dirt first can adopt electrochemical degreasing, electrochemical deoiling or ultrasonic cleaning oil removing with washing gasoline, alcohol, acetone and other organic solvent cleaning oil removing again;
2) decoating: be 20 DEG C ~ 55 DEG C by temperature, concentration is that the salpeter solution of 300ml/L ~ 550ml/L is placed in ultrasonic equipment, ultrasonic frequency is set as 20KHz ~ 40KHz, again part is immersed in the salpeter solution in above-mentioned ultrasonic equipment, soak time is no more than 48 hours, raise tank liquor temperature to 40 DEG C ~ 55 DEG C, the coating removal time can be shortened;
3) remove remaining coating: to the remaining coating still can not removed through above-mentioned operation, adopt the method for sandblasting to remove.
The present invention compared with prior art has following beneficial effect:
This chemical removing coating method, instead of traditional mechanical removal methods, removal speed is fast, do not corrode and injuring part matrix, particularly adopting ultrasonic wave in situation, ultrasonic wave promotes that removing solution permeates to coat inside, removes nickel aluminium coating by chemistry and comes disposable removal double-deck ceramic mould alumina-silica titanium coating, successfully overcome the difficult problem that conventional chemistry cannot remove aluminium oxide-titanium oxide ceramic topcoats.
Specific embodiment mode
For increasing work efficiency, can adopt disposable removal aluminium oxide-titanium oxide coating surface layer and Ni-Al bottom with the following method, concrete steps are as follows:
1) oil removing: adopt electrochemical degreasing, electrochemical deoiling or ultrasonic cleaning oil removing; The serious part of greasy dirt first can adopt electrochemical degreasing, electrochemical deoiling or ultrasonic cleaning oil removing with washing gasoline, alcohol, acetone and other organic solvent cleaning oil removing again;
2) water cleaning: first with hot water cleaning, and then clean with cold water;
3) decoating: it is in the salpeter solution of 450 ml/L that the part of band coating immerses concentration, at 20 DEG C ~ 55 DEG C, coordinates and adopts frequency to be 20KHz ~ 40KHz ultrasonic wave, time 24 h ~ 48 h;
4) neutralize, adopt the sodium carbonate solution of 30g/L ~ 50 g/L to wash, then first with hot water cleaning, then clean with cold water;
5) remove remaining coating: to a small amount of coating of residue, adopt blasting method to remove;
6) dehydrogenation: part, should after having removed coating within 4h after decoating, and put into dehydrogenation stove/baking oven and carry out dehydrogenation, dehydrogenation parameter is: superalloy and plain steel are incubated and are no less than 4 hours at 180 DEG C ~ 200 DEG C; Titanium alloy is incubated 60 min ~ 75 min at 200 DEG C ~ 220 DEG C.
Claims (2)
1. remove a method for aluminium oxide-titanium oxide ceramic mould seal coating, comprise the steps:
1) oil removing: adopt electrochemical degreasing, electrochemical deoiling or ultrasonic cleaning oil removing; The serious part of greasy dirt first can adopt electrochemical degreasing, electrochemical deoiling or ultrasonic cleaning oil removing with washing gasoline, alcohol, acetone and other organic solvent cleaning oil removing again;
2) decoating: be 20 DEG C ~ 55 DEG C by temperature, concentration is that the salpeter solution of 300ml/L ~ 550ml/L is placed in ultrasonic equipment, ultrasonic frequency is set as 20KHz ~ 40KHz, immersed in the salpeter solution in ultrasonic equipment by band coating part by step 1) oil removal treatment, soak time is no more than 48 hours again;
3) remove remaining coating: to the remaining coating still can not removed through above-mentioned operation, adopt the method for sandblasting to remove.
2. the method for removal aluminium oxide-titanium oxide ceramic mould seal coating according to claim 1, is characterized in that, the temperature of salpeter solution is 40 DEG C ~ 55 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410519088.8A CN104342713A (en) | 2014-10-07 | 2014-10-07 | Method removing aluminum oxide-titanium oxide ceramic seal coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410519088.8A CN104342713A (en) | 2014-10-07 | 2014-10-07 | Method removing aluminum oxide-titanium oxide ceramic seal coating |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104342713A true CN104342713A (en) | 2015-02-11 |
Family
ID=52499148
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410519088.8A Pending CN104342713A (en) | 2014-10-07 | 2014-10-07 | Method removing aluminum oxide-titanium oxide ceramic seal coating |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104342713A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106757065A (en) * | 2016-11-22 | 2017-05-31 | 沈阳黎明航空发动机(集团)有限责任公司 | Engine labyrinth tooth disk-like accessory alumina silica titanium coating removal technology |
| CN110714202A (en) * | 2019-09-09 | 2020-01-21 | 中国人民解放军第五七一九工厂 | Method for removing aluminum oxide and titanium dioxide coating |
| CN111036519A (en) * | 2019-11-20 | 2020-04-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for repairing high-pressure turbine working blade anti-oxidation coating in full life cycle |
| CN113458978A (en) * | 2021-05-27 | 2021-10-01 | 中国航发南方工业有限公司 | Method for repairing sealing coating on inner surface of deep hole structure part |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1900384A (en) * | 2006-07-05 | 2007-01-24 | 北京航空航天大学 | Process for removing part surface oxidized skin using supersonic wave and electrolytic combination |
| CN103233299A (en) * | 2013-05-20 | 2013-08-07 | 大连交通大学 | Porous hollow carbon nanofiber as well as preparation method and application thereof |
| CN103422051A (en) * | 2013-08-23 | 2013-12-04 | 中国人民解放军第五七一九工厂 | Method of removing copper-nickel/aluminum-graphite composite seal coating material |
| CN103598927A (en) * | 2013-10-17 | 2014-02-26 | 上海交通大学 | Degradable magnesium alloy nerve conduit for nerve defect repair and preparation method of nerve conduit |
| CN103706594A (en) * | 2012-09-29 | 2014-04-09 | 浙江昱辉阳光能源有限公司 | Cleaning method for original silicon |
| CN103785640A (en) * | 2012-10-31 | 2014-05-14 | 浙江昱辉阳光能源有限公司 | Cleaning method of quasi monocrystalline silicon |
-
2014
- 2014-10-07 CN CN201410519088.8A patent/CN104342713A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1900384A (en) * | 2006-07-05 | 2007-01-24 | 北京航空航天大学 | Process for removing part surface oxidized skin using supersonic wave and electrolytic combination |
| CN103706594A (en) * | 2012-09-29 | 2014-04-09 | 浙江昱辉阳光能源有限公司 | Cleaning method for original silicon |
| CN103785640A (en) * | 2012-10-31 | 2014-05-14 | 浙江昱辉阳光能源有限公司 | Cleaning method of quasi monocrystalline silicon |
| CN103233299A (en) * | 2013-05-20 | 2013-08-07 | 大连交通大学 | Porous hollow carbon nanofiber as well as preparation method and application thereof |
| CN103422051A (en) * | 2013-08-23 | 2013-12-04 | 中国人民解放军第五七一九工厂 | Method of removing copper-nickel/aluminum-graphite composite seal coating material |
| CN103598927A (en) * | 2013-10-17 | 2014-02-26 | 上海交通大学 | Degradable magnesium alloy nerve conduit for nerve defect repair and preparation method of nerve conduit |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106757065A (en) * | 2016-11-22 | 2017-05-31 | 沈阳黎明航空发动机(集团)有限责任公司 | Engine labyrinth tooth disk-like accessory alumina silica titanium coating removal technology |
| CN106757065B (en) * | 2016-11-22 | 2019-06-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Engine labyrinth tooth disk-like accessory aluminium oxide-titanium dioxide coating removal technology |
| CN110714202A (en) * | 2019-09-09 | 2020-01-21 | 中国人民解放军第五七一九工厂 | Method for removing aluminum oxide and titanium dioxide coating |
| CN111036519A (en) * | 2019-11-20 | 2020-04-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for repairing high-pressure turbine working blade anti-oxidation coating in full life cycle |
| CN113458978A (en) * | 2021-05-27 | 2021-10-01 | 中国航发南方工业有限公司 | Method for repairing sealing coating on inner surface of deep hole structure part |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6210488B1 (en) | Method of removing a thermal barrier coating | |
| CN103320778B (en) | A kind of aviation pipe stainless steel passivation process | |
| CN104342713A (en) | Method removing aluminum oxide-titanium oxide ceramic seal coating | |
| CN102817000B (en) | Method for preparing anti-oxidation corrosion coating of high pressure turbine blade | |
| CN104328371A (en) | Hot dip galvanizing technique for implementing corrosion resistance and rust resistance of steel tube | |
| CN102286766A (en) | Aluminum alloy hard anode oxidation film and process method thereof | |
| CN110144510B (en) | Tungsten carbide-chromium carbide-nickel molybdenum composite powder, coating and preparation method thereof | |
| CN103668030A (en) | Improved hot galvanizing method of iron handicraft or furniture | |
| CN104928729A (en) | Electrodeposition-laser remelting strengthening process of Ni-nanometer TiN composite layer on surface of nickel base superalloy | |
| CN103422051B (en) | Remove the method for copper nickel/aluminium graphite compound sealing coating material | |
| CN105032747A (en) | Tower cylinder coating method of large floating wind power station | |
| CN102634784B (en) | Surface treatment method of nuclear bridge | |
| CN104746072A (en) | Magnesium alloy microarc ion plating surface treatment method | |
| CN104593720A (en) | Sand erosion resistant composite coating for aero-engine compressor blades and preparation method of composite coating | |
| CN104018113B (en) | The process of surface treatment of cast iron materials | |
| CN104018108B (en) | A kind of method of offshore platform steel surface modification treatment | |
| CN105420744A (en) | Method for removing ceramic surface layer of thermal barrier coating of turbine blade | |
| RU2471017C1 (en) | Removal method of coatings from titanium nitride from surface of parts from titanium alloys | |
| CN102796982B (en) | Preparation method for an AlSiY coating of directional solidification alloy high-pressure turbine blade | |
| JP6375238B2 (en) | Steam turbine and surface treatment method thereof | |
| CN104178792A (en) | Process for micro-arc oxidation and glazing of magnesium alloy | |
| CN106757026B (en) | A kind of minimizing technology of engine turbine blade AlSiY coating | |
| CN114075690B (en) | Method for electrochemically removing MCrAlY coating | |
| CN109014770A (en) | A kind of restorative procedure of cylinder sleeve of engine | |
| CN104250790A (en) | Steel surface phosphatization technology of pretreatment before thermal spraying |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150211 |