CN108115481A - A kind of method for solving cooled turbine blade thermal barrier coating plug-hole - Google Patents
A kind of method for solving cooled turbine blade thermal barrier coating plug-hole Download PDFInfo
- Publication number
- CN108115481A CN108115481A CN201611073601.0A CN201611073601A CN108115481A CN 108115481 A CN108115481 A CN 108115481A CN 201611073601 A CN201611073601 A CN 201611073601A CN 108115481 A CN108115481 A CN 108115481A
- Authority
- CN
- China
- Prior art keywords
- hole
- thermal barrier
- barrier coating
- air film
- coating
- 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
- 239000012720 thermal barrier coating Substances 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000000576 coating method Methods 0.000 claims abstract description 33
- 239000011248 coating agent Substances 0.000 claims abstract description 32
- 238000005498 polishing Methods 0.000 claims abstract description 27
- 239000010432 diamond Substances 0.000 claims abstract description 15
- 229910003460 diamond Inorganic materials 0.000 claims abstract description 14
- 238000009760 electrical discharge machining Methods 0.000 claims abstract description 6
- 239000000956 alloy Substances 0.000 claims description 5
- 239000011148 porous material Substances 0.000 claims description 5
- 229910045601 alloy Inorganic materials 0.000 claims description 4
- 238000009713 electroplating Methods 0.000 claims description 3
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 claims 1
- 239000010931 gold Substances 0.000 claims 1
- 229910052737 gold Inorganic materials 0.000 claims 1
- 239000011435 rock Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 8
- 239000010410 layer Substances 0.000 description 10
- 230000008021 deposition Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 239000002245 particle Substances 0.000 description 4
- 239000011247 coating layer Substances 0.000 description 3
- 238000012876 topography Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 238000010892 electric spark Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005065 mining Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B5/00—Machines or devices designed for grinding surfaces of revolution on work, including those which also grind adjacent plane surfaces; Accessories therefor
- B24B5/36—Single-purpose machines or devices
- B24B5/48—Single-purpose machines or devices for grinding walls of very fine holes, e.g. in drawing-dies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B27/00—Other grinding machines or devices
- B24B27/033—Other grinding machines or devices for grinding a surface for cleaning purposes, e.g. for descaling or for grinding off flaws in the surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24D—TOOLS FOR GRINDING, BUFFING OR SHARPENING
- B24D5/00—Bonded abrasive wheels, or wheels with inserted abrasive blocks, designed for acting only by their periphery; Bushings or mountings therefor
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to aero-engine cooled turbine blade thermal barrier coating coating technology, more particularly to a kind of method for solving cooled turbine blade and applying plug-hole during thermal barrier coating.This method is polished by using polishing of the surface coated with diamond wear proof coating for the air film internal surface of hole for being coated thermal barrier coating, effectively remove the extra thermal barrier coating in air film hole, make air film hole inner wall more smooth simultaneously, and polish electric spark-erosion perforation when the remelted layer that introduces.It is polished using polishing of the surface coated with diamond wear proof coating for the air film internal surface of hole for being coated thermal barrier coating, can effectively solve the problems, such as cooled turbine blade thermal barrier coating plug-hole, the time is short, and does not destroy original shaped film-hole.
Description
Technical field
The invention belongs to aero-engine cooled turbine blade thermal barrier coating coating technology, more particularly to a kind of solution gas
The method of plug-hole during cold turbo blade coating thermal barrier coating.
Background technology
Turbo blade is the kernel component of aero-engine, is subjected to the impact of high temperature and pressure high-speed fuel gas for a long time and invades
Erosion, Service Environment very severe.It can not meet the use of advanced aero engine to solve to be used alone high-temperature alloy material
Demand, turbine blade surface use air film cooling technology and Thermal Barrier Coating Technologies bar none.The combination of both technologies should
With blade surface can be made to reduce by 500 DEG C or so of temperature, turbo blade has been effectively ensured can be more than basis material fusing point
It securely and reliably works under working environment.
Since the electric conductivity of thermal barrier coating is weaker, and its thickness, in 0.1~0.2mm or so, turbo blade is generally first at present
Carry out air film hole manufacturing procedure, rear progress thermal barrier coating working procedure of coating.During coat coating, coating is inevitably deposited on
Air film internal surface of hole causes air film hole aperture to reduce, while changes shaped film-hole, influences cooling air-flow direction, and then influences
Turbine blade air film cools effect.
At present, main use amplifies air film hole aperture with cooled turbine blade air film hole caused by making up thermal barrier coating in advance
Layer Shrinkage Problem.But the method need to count air film hole varying aperture rule before and after coating thermal barrier coating, and difference is vented fenestra
The coated technique of also inconsistent, the different production unit of shrinkage cavity rule also brings along the difference of shrinkage cavity value, though it can seek unity of standard by force,
But stringent control coating layer thickness is needed, this ensures that coating layer thickness is difficult to coat coating technique, poor controllability.It is meanwhile right
The required precision of electric spark-erosion perforation also accordingly improves, that is, reduces tolerance value, the control requirement to electric spark-erosion perforation process
It is tightened up, easily occur overproof part in process.It is also desirable to study coating layer thickness, air film hole site and original air film hole aperture
Influence of the size to shrinkage cavity rule inquires into its technological feasibility, amplified shaped film-hole and size to airflow direction and cold
But influential effect also needs further to verify.
The content of the invention
It is an object of the invention to provide it is a kind of it is cost-effective solve cooled turbine blade thermal barrier coating plug-hole method,
It is polished using polishing of the surface coated with diamond wear proof coating for the air film internal surface of hole for being coated thermal barrier coating, Ke Yiyou
Extra thermal barrier coating in effect removal air film hole, while can also make air film hole inner wall more smooth, and polish to a certain extent
Fall the remelted layer introduced during electric spark-erosion perforation.
The technical scheme is that：
A kind of method for solving cooled turbine blade thermal barrier coating plug-hole is applied by using surface coated with diamond wear proof
The polishing of layer is polished for the air film internal surface of hole for being coated thermal barrier coating, effectively removes the extra thermal barrier coating in air film hole,
Make air film hole inner wall more smooth simultaneously, and polish electric spark-erosion perforation when the remelted layer that introduces.
The method of the solution cooled turbine blade thermal barrier coating plug-hole, polishing pin main body are good using high intensity, toughness
Good, the hot candied high temperature alloy silk haveing excellent performance, electroplating surface a layer thickness is uniform, the diamond wear proof coating of stable quality.
The method of the solution cooled turbine blade thermal barrier coating plug-hole, diameter and the blade air film hole aperture of pin of polishing
Size corresponds, and is made choice according to blade air film hole pore size.
Advantages of the present invention and advantageous effect are：
1st, for the shrinkage cavity in thermal barrier coating of turbine blade coating process, existing advance amplification air film hole aperture approach technique
The shortcomings that poor controllability, the present invention propose the method for solving cooled turbine blade thermal barrier coating plug-hole, and this method is applied by surface
The polishing of diamond wear proof coating is covered with for the air film internal surface of hole polishing for being coated thermal barrier coating, can effectively remove air film
Extra thermal barrier coating in hole, while can also make air film hole inner wall more smooth, and polish off electric spark to a certain extent and beat
The remelted layer introduced during hole.
2nd, using polishing of the surface coated with diamond wear proof coating for the air film internal surface of hole for being coated thermal barrier coating
Polishing, can effectively solve the problems, such as cooled turbine blade thermal barrier coating plug-hole, the time is short, and does not destroy original shaped film-hole.
3rd, equipment requirement needed for the method for the present invention is low, easy to operate, and quality relatively easily controls.
Description of the drawings
Fig. 1 is forward and backward for electro beam physics vapour deposition coating thermal barrier coating, blade air film hole surface topography and coating thermal boundary
Cross Section Morphology after coating.Wherein, (a) figure is the blade air film hole surface topography applied before thermal barrier coating；(b) figure is coating thermal boundary
Blade air film hole surface topography after coating；(c) figure is the Cross Section Morphology applied after thermal barrier coating；(d) figure is that coating thermal boundary applies
Cross Section Morphology after layer.
Fig. 2 (a)-(b) is to use electro beam physics on the turborotor surface for meeting design air film hole pore size
After gas phase deposition technology coating thermal barrier coating, then using polishing of the surface coated with diamond wear proof coating for table in air film hole
Face carry out following process after and air film hole photomacrograph of not polishing.
Fig. 3 is polishing pin macro morphology and diamond particles wear-resistant coating Cross Section Morphology.In figure, 1 polishing pin；2 diamonds
Particle wear-resistant coating.
Fig. 4 is the photomacrograph of spraying thermal barrier coating and rear blade air film hole of polishing.
Specific embodiment
In specific implementation process, the method for present invention solution cooled turbine blade thermal barrier coating plug-hole, by using table
Polishing of the face coated with diamond wear proof coating can be effectively removed for the air film internal surface of hole polishing for being coated thermal barrier coating
Extra thermal barrier coating in air film hole, while can also make air film hole inner wall more smooth, and electrical fire is polished off to a certain extent
The remelted layer introduced during flower punching.Polishing pin main body is using high intensity, toughness is good, the hot candied high temperature alloy silk haveing excellent performance,
Its electroplating surface a layer thickness is uniform, the diamond wear proof coating of stable quality.The diameter of polishing pin and blade air film hole aperture
Size corresponds, and is made choice according to blade air film hole pore size.
As shown in Figure 1, thermal barrier coating is sprayed in certain turbine blade surface using electro beam physics vapour deposition (EB-PVD)
Afterwards, deposition has coating in air film hole, and blade air film hole aperture is reduced to 0.30mm by 0.38mm, and air film hole aperture shape occurs
Variation.
As shown in Fig. 2 (a)-(b), after applying thermal barrier coating, the air film hole of blade surface is closed substantially to be blocked.Polishing pin
After polishing, extra coating is removed in air film hole, while air film hole inner wall is more smooth, and polishes off punching to a certain extent
When the remelted layer that introduces.
As shown in figure 3, diamond particles wear-resistant coating 2 is evenly distributed on the surface of polishing pin 1 (high temperature alloy silk).
As shown in figure 4, two rows of air film hole one rows adjacent to blade, without any processing, a mining is coated with surface
The polishing of wear-resisting diamond particles carries out following process for air film internal surface of hole.As can be seen from Fig., after applying thermal barrier coating,
The air film hole of blade surface is obviously reduced.It polishes after stylus printer mill, extra coating is removed in air film hole.It is found by practical operation
The processing method is simple, and operation is flexible.
Embodiment the result shows that, be equipped with 80 blades by every engine, turbo blade processing quality saved after being promoted into
This 0.5 ten thousand yuan calculating can save 400,000 yuan per component parts for assembly of a machine blade.The technology also extends to other association areas, has higher
Economic benefit.
Claims (3)
- A kind of 1. method for solving cooled turbine blade thermal barrier coating plug-hole, which is characterized in that by using surface coated with gold For the air film internal surface of hole polishing for being coated thermal barrier coating, it is extra in air film hole to effectively remove for the polishing of hard rock wear-resistant coating Thermal barrier coating, while make air film hole inner wall more smooth, and polish electric spark-erosion perforation when the remelted layer that introduces.
- 2. the method described in accordance with the claim 1 for solving cooled turbine blade thermal barrier coating plug-hole, which is characterized in that polishing pin Main body is using high intensity, toughness is good, the hot candied high temperature alloy silk haveing excellent performance, electroplating surface a layer thickness uniformly, quality Stable diamond wear proof coating.
- 3. the method described in accordance with the claim 1 for solving cooled turbine blade thermal barrier coating plug-hole, which is characterized in that polishing pin Diameter and blade air film hole pore size correspond, made choice according to blade air film hole pore size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611073601.0A CN108115481A (en) | 2016-11-29 | 2016-11-29 | A kind of method for solving cooled turbine blade thermal barrier coating plug-hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611073601.0A CN108115481A (en) | 2016-11-29 | 2016-11-29 | A kind of method for solving cooled turbine blade thermal barrier coating plug-hole |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108115481A true CN108115481A (en) | 2018-06-05 |
Family
ID=62226720
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611073601.0A Pending CN108115481A (en) | 2016-11-29 | 2016-11-29 | A kind of method for solving cooled turbine blade thermal barrier coating plug-hole |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108115481A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109307577A (en) * | 2018-08-24 | 2019-02-05 | 北京航空航天大学 | An air cooling device for high temperature vibration test |
| CN118700004A (en) * | 2024-08-06 | 2024-09-27 | 南京航空航天大学 | A device and method for liquid particle flow boiling finishing of turbine blade air cooling channel |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06226631A (en) * | 1993-02-09 | 1994-08-16 | Ishikawajima Harima Heavy Ind Co Ltd | Drilling method for heat resistant ceramic layers |
| EP1767743A1 (en) * | 2005-09-26 | 2007-03-28 | Siemens Aktiengesellschaft | Method to produce a coated gas turbine component having opening holes, apparatus to perform the method and coated turbine blade having cooling holes |
| EP1887097A2 (en) * | 2006-07-28 | 2008-02-13 | General Electric Company | Method for concurrent thermal spray and cooling hole cleaning |
| CN202240884U (en) * | 2011-09-16 | 2012-05-30 | 西安远航真空钎焊技术有限公司 | Grinding head for machining linear cutting titanium alloy leaf-shaped hole |
| CN104968916A (en) * | 2013-02-26 | 2015-10-07 | 三菱日立电力系统株式会社 | Turbine blade machining method, machining tool, and turbine blade |
| CN105886991A (en) * | 2016-04-15 | 2016-08-24 | 华能国际电力股份有限公司 | Method for plugging surface micropores in thermal spraying process |
-
2016
- 2016-11-29 CN CN201611073601.0A patent/CN108115481A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06226631A (en) * | 1993-02-09 | 1994-08-16 | Ishikawajima Harima Heavy Ind Co Ltd | Drilling method for heat resistant ceramic layers |
| EP1767743A1 (en) * | 2005-09-26 | 2007-03-28 | Siemens Aktiengesellschaft | Method to produce a coated gas turbine component having opening holes, apparatus to perform the method and coated turbine blade having cooling holes |
| EP1887097A2 (en) * | 2006-07-28 | 2008-02-13 | General Electric Company | Method for concurrent thermal spray and cooling hole cleaning |
| CN202240884U (en) * | 2011-09-16 | 2012-05-30 | 西安远航真空钎焊技术有限公司 | Grinding head for machining linear cutting titanium alloy leaf-shaped hole |
| CN104968916A (en) * | 2013-02-26 | 2015-10-07 | 三菱日立电力系统株式会社 | Turbine blade machining method, machining tool, and turbine blade |
| CN105886991A (en) * | 2016-04-15 | 2016-08-24 | 华能国际电力股份有限公司 | Method for plugging surface micropores in thermal spraying process |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109307577A (en) * | 2018-08-24 | 2019-02-05 | 北京航空航天大学 | An air cooling device for high temperature vibration test |
| CN118700004A (en) * | 2024-08-06 | 2024-09-27 | 南京航空航天大学 | A device and method for liquid particle flow boiling finishing of turbine blade air cooling channel |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180605 |
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| RJ01 | Rejection of invention patent application after publication |