CN102995035A - Treatment method for improving safety of precision-casting high-temperature parts of aero-engine - Google Patents
Treatment method for improving safety of precision-casting high-temperature parts of aero-engine Download PDFInfo
- Publication number
- CN102995035A CN102995035A CN2012104587129A CN201210458712A CN102995035A CN 102995035 A CN102995035 A CN 102995035A CN 2012104587129 A CN2012104587129 A CN 2012104587129A CN 201210458712 A CN201210458712 A CN 201210458712A CN 102995035 A CN102995035 A CN 102995035A
- Authority
- CN
- China
- Prior art keywords
- pickling
- treatment process
- aircraft engine
- hot parts
- point alloy
- 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.)
- Granted
Links
Landscapes
- Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
Abstract
The invention discloses a treatment method for improving safety of precision-casting high-temperature parts of an aero-engine. A fatigue break problem due to the reason that low-melting-point alloy adhered on the surfaces of the parts penetrates into the parts, and heat resistance and corrosion resistance of the parts are changed under a high temperature environment is relieved by pickling. The treatment method mainly comprises the following steps of: soaking the components to salpeter solution with concentration of 750g/l to 780g/l in not less than two pickling baths for pickling in sequence; washing out the low-melting-point alloy elements adhered on the surfaces of the components; soaking the pickled components to an alkaline bath for washing out and neutralizing nitric acid solution on the surfaces of the components by the aqueous alkali; using water-containing compressed air to wash the surfaces of the neutralized and washed components to clear away pickling residue on the surfaces of the components. The precision-casting high-temperature parts of the aero-engine have ensured safety and improved safety after being treated by the treatment method provided by the invention.
Description
Technical field
The present invention relates to the smart casting of aircraft engine hot parts processing treatment technology, more specifically, relate to a kind for the treatment of process that improves the security of the smart casting of aircraft engine hot parts.
Background technology
Work in the part in the hot environment in the aircraft engine, the irregular part of contour structures complexity all is to adopt smart casting machine-shaping usually, some position of smart type casting moulding part, as assemble the position and also need to carry out further precision work, could satisfy matching requirements, such as the high-temperature alloy blades in the engine, its integral shroud and tenon all need to carry out the requirement that precision work could be satisfied assembling.When precision work is carried out at these positions, usually need to be used in a certain position welding " square chest " of part the processing location." square chest " will be removed from part after Finishing Parts Machining finishes, and removes from part for the ease of " square chest ", and square chest generally adopts " tin ", " bismuth " alloy material to make." tin ", " bismuth " are low melting point element.
In order to guarantee the safety of aircraft engine, the part that works in the hot environment all must carry out test run in the ground installation.The applicant leaf destruction fault occurred in the installation test run in the R﹠D process of certain model aircraft engine.In order to address this problem, the applicant has concentrated the research and development designer of each side, researching and analysing from many aspects the reason that causes the leaf destruction fault to produce, find finally by analyzing and testing, is that the low melting point alloy element that the blade incision position exists causes the blade brittle rupture.Analyze after further study, the low melting point alloy element that causes the blade brittle rupture that the blade incision position exists, that blade is failed the low melting point alloy that blade surface is residual when removing " square chest " in the course of processing and thoroughly removed, cause low melting point alloy to infiltrate the part organization internal, heat-resisting, the solidity to corrosion of part self under hot environment, have been changed, thereby cause the part repeated stress failure, reduced the security of smart casting hot parts, and then the security of serious harm engine.
Summary of the invention
The present invention is based on the above-mentioned discovery that causes the smart casting of aircraft engine hot parts brittle rupture reason, a kind for the treatment of process that improves the security of the smart casting of aircraft engine hot parts has been proposed, to solve owing to low melting point alloy infiltrates the part organization internal, under hot environment, change heat-resisting, the solidity to corrosion of part self, thereby cause the problem of part repeated stress failure.
" square chest " material commonly used is mainly " tin ", " bismuth " alloy at present.Generally, chlorion and iron ion have stronger corrodibility to ferrous materials, and nitrate ion has preferably passivation to it, and the passivation of general stainless steel components all contains the nitric acid component, and for this reason, the present invention selects nitric acid as Acidwash solution.
The treatment process of the smart casting of the raising aircraft engine that the present invention proposes hot parts security, its content mainly comprises:
(1) part is immersed in successively in the salpeter solution that concentration in the pickling tank that is no less than 2 is 750g/l ~ 780g/l and carries out pickling, eccysis is attached to the low melting point alloy on the piece surface;
(2) after element pickling finishes, part is immersed in the alkaline bath in the alkaline solution, in and the salpeter solution on the eccysis piece surface, to eliminate salpeter solution from now on to the corrosion of part;
(3) part with the surface with hydraulic pressure contracting air scour part, cleans the pickling residue on the piece surface after the alkaline solution neutralization is washed.
Because pickling is equivalent to make the low melting point alloy element be distributed to equably whole solution and piece surface from piece surface by the mode of dissolving, the process that belongs to a dilution, low melting point alloy content and the content in the salpeter solution on the piece surface are basically identical, for this reason, as long as carry out the pickling of enough time, low melting point alloy on the piece surface is added in the salpeter solution fully, just can reaches the purpose that detects piece surface low melting point alloy content by the low melting point alloy content that detects in the final Acidwash solution.Therefore, in technique scheme of the present invention, can adopt the content that detects the low melting point alloy on the piece surface by the content concn of the low melting point alloy in the salpeter solution behind the detection element pickling.It is generally acknowledged in the practice, when the concentration of low melting point alloy in the salpeter solution is not more than 1ppm, just can think that the low melting point alloy on the piece surface has just thoroughly been removed.This supposition, the applicant is proven in part post-production and commissioning process, is feasible.
In technique scheme of the present invention, because also there is certain corrosive nature in nitric acid to the part base solid of stainless steel, in the treating processes to part, the low melting point alloy that need to guarantee piece surface is removed thoroughly and the etching off amount of part base solid is surpassed certain thickness.Therefore part accumulative total pickling time should not surpass the part base solid permission etching off determined time of amount.Usually part accumulative total pickling time is no more than the 1 required time of μ m bed thickness of part base solid etching off.
In technique scheme of the present invention, during part after the pickling carried out and the selecting of soda solution, consider the cleaning of piece surface after the pickling, preferred sodium carbonate solution or ammoniacal liquor.Preferably with weight concentration be 40 ~ 60% sodium carbonate solution to pickling after part neutralize and wash, both can obtain fine neutralization and wash effect, can not generate residue at piece surface again.
In technique scheme of the present invention, part preferably is immersed in successively in 2 to 4 the pickling tank and carries out pickling in the salpeter solution.In acid cleaning process, for fear of the impact of impurity on the element pickling effect, pickling is generally the salpeter solution of newly joining with salpeter solution, particularly the pickling in last and second pickling tank generally should be the salpeter solution of newly joining with salpeter solution, and what the salpeter solution in last pickling tank should be cleaning at least newly joins salpeter solution.In the acid cleaning process of part, the salpeter solution concentration in each pickling tank can be identical, also can be different, and for easy to operate, the salpeter solution concentration in each pickling tank is preferably the same, carries out pickling with the salpeter solution of same concentrations.But also can be different.The time of part pickling in each pickling tank, not strict restriction, just the time of accumulative total pickling surpasses the determined time, normally part in first pickling tank pickling time greater than the time in rear pickling in each pickling tank.
After the present invention finishes, the contriver has carried out the test of part base solid removal amount according to ARP1755 " clean-out system causes the test method of materials for aeroengines loss " to method of the present invention, the result shows: be to soak 120 minutes in the salpeter solution of 780g/l in concentration, the monolateral removal amount of piece surface is no more than 1 μ m, is not enough to the size of part is impacted.Detect by the atomic absorption mode, detected result proves, adopts method of the present invention to remove " square chest " and remains in low melting point alloy on the piece surface, and final cleaning performance is desirable.
Key of the present invention is to find the reason that causes the blade brittle rupture to produce.Of the present invention finishing, just be based on the contriver and accurately finding the reason that causes the blade brittle rupture to produce, Here it is penetrates into part organization internal low melting point alloy and causes the blade brittle rupture, and low melting point alloy is failed when to be blade remove " square chest " in the course of processing due to the low melting point alloy that blade surface is residual thoroughly removes, cause part under hot environment, to change heat-resisting, the solidity to corrosion of part self, thereby cause the part repeated stress failure.The contriver is based on above-mentioned discovery, just a kind ofly can comparatively thoroughly remove the piece surface low melting point alloy by what a series of experimental study was explored out, the processing method that can not affect greatly part base solid has again been guaranteed part security in use.
The present invention is directed to the smart treatment process of casting the hot parts security of raising aircraft engine that causes the smart casting of aircraft engine hot parts brittle rupture reason to propose, remove the low melting point alloy that is attached to piece surface by pickling, solved because low melting point alloy infiltrates the part organization internal, under hot environment, change heat-resisting, the solidity to corrosion of part self, thereby the problem that causes the part repeated stress failure has guaranteed the part safety in utilization.Method of the present invention sums up and mainly contains following technique effect:
1, adopt method of the present invention that the low melting point alloy that is attached on the piece surface is carried out pickling, the low melting point alloy that is attached on the piece surface is removed thoroughly, has guaranteed the part safety in utilization.
2, adopt method of the present invention, in the acid cleaning process, control part base solid material removal amount is no more than 1 μ m, both can guarantee part self dimensional precision, can guarantee again the intensity of part.
3, method is simple for acid cleaning process of the present invention, has good operability.
Specific implementation method
Below in conjunction with embodiment the present invention is specifically described, so that personnel's the understanding of the present invention of affiliated technical field.Be necessary what this particularly pointed out to be; embodiment is just for the present invention will be further described; can not be interpreted as limiting the scope of the invention; affiliated art skilled person; to improvement and adjustment that the present invention makes non-intrinsically safe, should still belong to protection scope of the present invention according to the invention described above content.
Embodiment 1
Certain model blade of aviation engine, adopt the stainless steel precision type casting moulding, the integral shroud of blade and tenon adopt " square chest " location secondary process, and blade shroud and tenon precision work are removed " square chest " after finishing at the blade from blade, and the material of " square chest " is tin alloy.Remove blade and blade with it residual tin alloy adopt the salpeter solution pickling.It is in the salpeter solution of 750g/l that blade is immersed in the interior concentration of three pickling tanks successively, three interior salpeter solutions of pickling tank are the cleaning nitric acid of newly joining, prior to pickling in first pickling tank 30 minutes, then pickling 15 minutes in second pickling tank, again then pickling 15 minutes in the 3rd pickling tank, then blade is immersed in weight concentration in the alkaline bath after pickling finishes and is in 40% the sodium carbonate solution, neutralize and wash being retained in salpeter solution on the blade after the blade pickling, end in 15 minutes is washed in neutralization.Blade cleans with the pressurized air that contains water after alkaline bath takes out comprehensively, removes the vanes pickling, neutralizes and wash the residue that is attached on the blade.After the vanes cleanup acid treatment, mode by atomic absorption detects, show that removal " square chest " remains in the cleaning performance ideal of the low melting point alloy on the blade surface, blade body material single face removal amount is no more than 1 μ m, guarantee blade self dimensional precision and intensity, improved the safety in utilization of blade.
Embodiment 2
Present embodiment is substantially the same manner as Example 1, difference is that the material of " square chest " is bismuth alloy, the concentration of salpeter solution is 780g/l, wherein salpeter solution is salpeter solution after a front B11 is washed last pickling in the process in first pickling tank, salpeter solution in latter two pickling tank is the cleaning salpeter solution of newly joining, blade was prior to pickling in first pickling tank 30 minutes, then pickling 15 minutes in second pickling tank, more then in the 3rd pickling tank pickling finished pickling in 10 minutes.Alkali neutralization is washed the alkaline solution that uses and also be sodium carbonate solution after the pickling, and the weight concentration of sodium carbonate solution is 60%, neutralizes to wash end in 10 minutes.Blade cleans with the pressurized air that contains water after alkaline bath takes out comprehensively.After the vanes cleanup acid treatment, mode by atomic absorption detects, show that removal " square chest " remains in the cleaning performance ideal of the low melting point alloy on the blade surface, blade body material single face removal amount is no more than 1 μ m, guarantee blade self dimensional precision and intensity, improved the safety in utilization of blade.
Claims (10)
1. one kind is improved the smart treatment process of casting the hot parts security of aircraft engine, it is characterized in that:
(1) part is immersed in successively in the salpeter solution that concentration in the pickling tank that is no less than 2 is 750g/l ~ 780g/l and carries out pickling, eccysis is attached to the low melting point alloy on the piece surface;
(2) after element pickling finishes, part is immersed in the alkaline bath in the alkaline solution, in and the salpeter solution on the eccysis piece surface, to eliminate salpeter solution from now on to the corrosion of part;
(3) part with the surface with hydraulic pressure contracting air scour part, cleans the pickling residue on the piece surface after the alkaline solution neutralization is washed.
2. the treatment process of the smart casting of raising aircraft engine according to claim 1 hot parts security is characterized in that: the content that detects the low melting point alloy on the piece surface by the content concn of low melting point alloy in the salpeter solution behind the detection element pickling.
3. raising aircraft engine essence according to claim 2 is cast the treatment process of hot parts security, and it is characterized in that: the low melting point alloy content pickling on the piece surface to the low melting point alloy content concn in the salpeter solution is not more than 1pmm.
4. raising aircraft engine essence according to claim 3 is cast the treatment process of hot parts security, it is characterized in that: part accumulative total pickling time is no more than part base solid and allows the etching off determined time of amount.
5. raising aircraft engine essence according to claim 4 is cast the treatment process of hot parts security, it is characterized in that: part accumulative total pickling time is no more than the 1 required time of μ m bed thickness of part base solid etching off.
6. according to claim 1 to the treatment process of the smart casting of one of 5 described raising aircraft engines hot parts security, it is characterized in that: be sodium carbonate solution or ammoniacal liquor to the alkaline solution of washing that neutralizes of part after the pickling.
7. the treatment process of the smart casting of raising aircraft engine according to claim 6 hot parts security is characterized in that: be the sodium carbonate solution of weight concentration 40 ~ 60% to the alkaline solution of washing that neutralizes of part after the pickling.
8. the treatment process of the smart casting of raising aircraft engine according to claim 7 hot parts security is characterized in that: part is immersed in successively in 2 to 4 the pickling tank and carries out pickling.
9. it is characterized in that according to claim 8 or the treatment process of the smart casting of described raising aircraft engine hot parts security: last at least pickling salpeter solution be clean newly join salpeter solution.
10. raising aircraft engine essence according to claim 1 is cast the treatment process of hot parts security, it is characterized in that: part salpeter solution with same concentrations in each pickling tank carries out pickling, and the used time of pickling is greater than the pickling time in rear each time for the first time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210458712.9A CN102995035B (en) | 2012-11-15 | 2012-11-15 | Treatment method for improving safety of precision-casting high-temperature parts of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210458712.9A CN102995035B (en) | 2012-11-15 | 2012-11-15 | Treatment method for improving safety of precision-casting high-temperature parts of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102995035A true CN102995035A (en) | 2013-03-27 |
| CN102995035B CN102995035B (en) | 2014-10-29 |
Family
ID=47924126
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210458712.9A Active CN102995035B (en) | 2012-11-15 | 2012-11-15 | Treatment method for improving safety of precision-casting high-temperature parts of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102995035B (en) |
Cited By (2)
| 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 |
| CN110524204A (en) * | 2019-08-30 | 2019-12-03 | 中国航发动力股份有限公司 | A kind of blade processing technique |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101713484A (en) * | 2009-12-03 | 2010-05-26 | 北京航空航天大学 | Inhibition to oxidation coking of aviation kerosene by acid cleaning and passivation |
| CN102330087A (en) * | 2011-09-23 | 2012-01-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for removing strained layer on surface of single crystal blade casting through chemical milling |
-
2012
- 2012-11-15 CN CN201210458712.9A patent/CN102995035B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101713484A (en) * | 2009-12-03 | 2010-05-26 | 北京航空航天大学 | Inhibition to oxidation coking of aviation kerosene by acid cleaning and passivation |
| CN102330087A (en) * | 2011-09-23 | 2012-01-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for removing strained layer on surface of single crystal blade casting through chemical milling |
Non-Patent Citations (2)
| Title |
|---|
| 林百春: "不锈钢表面处理：酸洗、钝化与抛光", 《材料开发与应用》 * |
| 陈玉天: "不锈钢表面处理应用技术简介", 《材料保护》 * |
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 |
| 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 |
| CN110524204A (en) * | 2019-08-30 | 2019-12-03 | 中国航发动力股份有限公司 | A kind of blade processing technique |
| CN110524204B (en) * | 2019-08-30 | 2021-06-08 | 中国航发动力股份有限公司 | Blade machining process |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102995035B (en) | 2014-10-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105603409A (en) | Normal-temperature alkaline chromium-free passivation solution and passivation method for aluminum alloy | |
| CN104313582A (en) | Novel aluminum alloy alkaline etching additive and preparation method thereof | |
| CN102995035B (en) | Treatment method for improving safety of precision-casting high-temperature parts of aero-engine | |
| CN104005038A (en) | Pretreatment method in aluminum alloy surface treatment and alkaline etching solution adopted by same | |
| CN105386030A (en) | Stainless steel surface processing method | |
| CN104685103A (en) | Surface treatment process for components composed of aluminium having detection of impermissible overheating | |
| CN107849979B (en) | The method for repairing and mending of turbo blade | |
| CN102817034A (en) | Chemical milling technology for surface plasticity deformation layer of single crystal cast blade | |
| CN103639131B (en) | A kind of blade air film hole and the sedimental minimizing technology of small gaps environment | |
| CN103952711A (en) | Continuous online treatment technique for metal surface | |
| CN105296205A (en) | Cleaning agent for mechanical equipment, and preparation method of cleaning agent | |
| CN107745223B (en) | A kind of restorative procedure for Middle casing rear end Internal Hole Deformation | |
| CN105671541A (en) | Stainless steel passivating technique | |
| CN110804734A (en) | Composite passivation method for stainless steel material | |
| CN104923520B (en) | Cleaning method for residual abrasive materials on turbine blades after being subjected to abrasive flow machining | |
| CN109023400A (en) | A kind of metalwork processing of surface polishing | |
| CN103789752B (en) | A kind of magnesium alloy nickel plating solution and nickel plating process | |
| RU2525033C1 (en) | Method of maintenance cleaning and passivation of drum boiler pipe inner surface and method of maintenance cleaning and passivation of pipe inner surface of combined-cycle plant waste-heat boiler (versions) | |
| CN102226277A (en) | Magnesium alloy chemical oxidation method | |
| CN102220574A (en) | Chemical nickel-phosphorus plating method on surface of zirconium-aluminum alloy | |
| CN102677074A (en) | Method for chemically removing carbon deposit in inner chamber of torch nozzle of ignition coil for aircraft engine | |
| CN105624655A (en) | Chemical nickel-plating process of iron workpiece | |
| CN108150288B (en) | Method for removing carbon deposition from engine conduit | |
| CN203018398U (en) | Multifunctional cleaning device | |
| KR102045742B1 (en) | How to repair turbine blades |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |