CN113909600A - Quality evaluation method for turbine blade electrosparking gas film hole - Google Patents
Quality evaluation method for turbine blade electrosparking gas film hole Download PDFInfo
- Publication number
- CN113909600A CN113909600A CN202111177059.4A CN202111177059A CN113909600A CN 113909600 A CN113909600 A CN 113909600A CN 202111177059 A CN202111177059 A CN 202111177059A CN 113909600 A CN113909600 A CN 113909600A
- Authority
- CN
- China
- Prior art keywords
- hole
- film hole
- sample block
- roundness
- roughness
- 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
- 238000000034 method Methods 0.000 title claims abstract description 33
- 238000013441 quality evaluation Methods 0.000 title claims abstract description 13
- 238000004080 punching Methods 0.000 claims abstract description 18
- 238000005520 cutting process Methods 0.000 claims abstract description 7
- 238000005498 polishing Methods 0.000 claims abstract description 5
- 238000012360 testing method Methods 0.000 claims description 15
- 238000012545 processing Methods 0.000 claims description 12
- 239000011148 porous material Substances 0.000 claims description 4
- 230000002977 hyperthermial effect Effects 0.000 claims description 2
- 230000002688 persistence Effects 0.000 claims description 2
- 238000011056 performance test Methods 0.000 claims 1
- 238000010892 electric spark Methods 0.000 abstract description 19
- 230000008569 process Effects 0.000 abstract description 10
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 abstract description 3
- 239000010931 gold Substances 0.000 abstract description 3
- 229910052737 gold Inorganic materials 0.000 abstract description 3
- 230000003287 optical effect Effects 0.000 abstract description 2
- 238000005507 spraying Methods 0.000 abstract description 2
- 238000010998 test method Methods 0.000 abstract description 2
- 238000009661 fatigue test Methods 0.000 abstract 1
- 238000003754 machining Methods 0.000 description 12
- 238000005553 drilling Methods 0.000 description 8
- 238000004364 calculation method Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 238000001816 cooling Methods 0.000 description 4
- 238000011156 evaluation Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000005259 measurement Methods 0.000 description 4
- 238000012854 evaluation process Methods 0.000 description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 2
- 244000137852 Petrea volubilis Species 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000003518 caustics Substances 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 239000012459 cleaning agent Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000005923 long-lasting effect Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
- B23H9/14—Making holes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H11/00—Auxiliary apparatus or details, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q17/00—Arrangements for observing, indicating or measuring on machine tools
- B23Q17/20—Arrangements for observing, indicating or measuring on machine tools for indicating or measuring workpiece characteristics, e.g. contour, dimension, hardness
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a quality evaluation method for an air film hole machined by a turbine blade through electric spark. The invention is divided into five steps: firstly, punching a plurality of small holes on a rectangular sample block by using an electric spark punching process to be evaluated, then placing the rectangular sample block under a body mirror to shoot pictures at two sides of the hole, and measuring the roundness and the taper of the hole; secondly, cutting and splitting a sample block along the edge of the hole by using a line, properly grinding and polishing the section to expose the inner wall of the hole, observing the appearance of the inner wall under an optical microscope or an electron microscope, and measuring the roughness of the inner wall of the hole by using a laser confocal microscope; thirdly, cutting a sample block along the hole edge to prepare a metallographic sample, and measuring the thickness of a recast layer under an electron microscope after polishing, corroding and spraying gold; fourthly, preparing a new sample block for carrying out endurance fatigue and high cycle fatigue tests; finally, the wells were analyzed comprehensively by combining all the data. The invention can provide an effective test method for evaluating the quality of electric spark punching.
Description
Technical Field
The invention belongs to the technical field of small hole electromachining, and particularly relates to a quality evaluation method for an air film hole machined by a turbine blade through electric spark machining.
Background
With the continuous improvement of the performance of the aero-engine, the requirement on the temperature before the turbine is higher and higher, and documents show that the thrust of the engine can be improved by about 10 percent when the total temperature before the turbine is improved by 55 ℃. The hot end part of the engine adopts the air film cooling technology widely, and how to effectively reduce the recasting layer (thickness) of the air film hole cooling in the important parts such as the turbine and the like and improve the processing quality has great significance for ensuring the quality of the engine.
At present, the traditional methods of laser drilling, electric spark drilling, electric-hydraulic beam drilling, femtosecond laser drilling and the like are mainly adopted for the machining of the blade air film hole cooling, and each method has respective characteristics. The traditional laser drilling efficiency is high, but the recasting layer is thicker; the recast layer after electric spark punching is relatively thin; the electro-hydraulic beam punching has no recasting layer, but has low efficiency; the femtosecond laser drilling does not basically form a recast layer under the condition of low power, but has low drilling efficiency and high cost. In order to improve the punching efficiency, a femtosecond laser punching process with higher power is under study, and the engineering application is not realized yet. The electric spark punching is a widely used punching method, which is a machining method that the pulse spark discharge generated between a tool and a workpiece continuously causes local and instantaneous high temperature to remove the material at the discharge point of the workpiece in a melting and gasifying manner so as to meet the requirements on the size and shape of the workpiece. Low cost, high efficiency and capability of processing conductive materials with any hardness. At the same time, however, the disadvantages are not negligible, and the electrospark holes have recast layers of a certain thickness and microcracks. If the mass of the bore is too low, it will equate to damage to the engine. The nickel-based high-temperature alloy material used by the aircraft engine has high hot crack sensitivity, and the damage of the air film hole can cause the corrosion and the rupture of the air film hole under the high-temperature, high-pressure and high-rotation-speed environment of the aircraft engine, so that the engine can generate accidents.
The electric spark punching utilizes a processing mechanism of heat energy and electric energy, the periphery of an electrode can reach high temperature of ten thousand degrees instantly, the material at the edge of the hole is melted or gasified, and then is solidified under the action of cooling liquid. Therefore, the electric spark machining has a recasting layer which is generated by melting and then solidifying, and because of uneven cooling and heating around the hole in the machining process, residual stress exists in the recasting layer and even develops into microcracks. However, different parameter settings of electric spark drilling have different damage degrees to materials, and the existing scientific research data shows that the damage degree of small holes processed at high processing speed to materials is larger due to high pulse current, long pulse width and short pulse interval. The small holes processed by low pulse current, short pulse width and long pulse interval, namely low processing speed, have small damage degree to the material. Therefore, there is a certain contradiction between the processing rate and the processing quality, and it is necessary for the production shop to increase the processing rate as much as possible while satisfying the specified quality, so as to increase the efficiency of the shop or production unit. At present, a complete air film hole quality evaluation system and method do not exist, so a method needs to be established to evaluate the air film hole quality, and production is carried out by using processing parameters capable of producing high yield for production units.
Disclosure of Invention
In view of the above-mentioned situation of the prior art, the present invention aims to provide a quality evaluation method for the electric discharge machining of the film hole of the turbine blade, so as to determine the processing parameters of the film hole with good machining quality and high machining rate according to the evaluation result.
A quality evaluation method for a turbine blade electrosparking air film hole comprises the following steps:
(1) the roundness and taper evaluation process of the small electric spark hole is as follows:
when the electric spark is used for punching a sample block, a marking pen is used for marking the outlet direction and the inlet direction of an electrode pair hole, then the surface of the sample block is cleaned by clear water, alcohol or a cleaning agent to prevent the interference of foreign matters for observation, and then the sample block is observed under a mirror with a split type and a picture of the outlet and the inlet of the hole is shot. The mean diameter, maximum diameter, minimum diameter, area and perimeter of the holes were calculated with the photo processing software. The roundness, taper and score can be calculated according to the following formula:
Roundness＝(dmax-dmin)/2
in the formula: roundness is the Roundness of the hole exit or entrance, dmax(μm) is the maximum diameter of the hole measured, dmin(um) is the smallest diameter of the hole measured.
Taper＝|(dtn-dout)/h|
In the formula: taper is the Taper of the hole, din(μm) is the average diameter of the inlet of the measured hole, doutThe (. mu.m) is the average diameter of the outlet of the wells measured and h (. mu.m) is the thickness of the coupon.
25 is an empirical value of the thickness of the gas film hole; 1250 with the best score value M1The calculation is reversed for 50.
In the formula: m1Scoring the roundness of the hole, M2The wells are scored.
0.015 is the gas film hole taper empirical value; 1.5 best scoring value M2The calculation is reversed for 50.
(2) The quality evaluation process of the inner wall of the electric spark small hole comprises the following steps:
the block is cut along the edge of the hole by linear cutting, the cut surface is sanded, the cut surface is milled inwards from the edge of the hole to the diameter of the hole, a semicircular groove is formed, the groove is cleaned, then the groove can be observed under an optical microscope or an electron microscope, and the roughness of the inner wall of the hole can be measured by adopting a non-contact mode, such as a laser confocal microscope and other devices. The roughness score of the pores can be calculated by the following formula:
in the formula: m3The roughness score for the hole, and Ra (μm) the hole inner wall roughness.
2 is an empirical value; 200 is divided by the best score value M3The calculation is reversed for 50.
(3) The thickness evaluation process of the recast layer of the electric spark small hole comprises the following steps:
and cutting the other sample block along the edge of the hole to prepare a metallographic sample, and exposing the section. Grinding the section with sand paper, grinding from the edge of the hole to the diameter of the hole, polishing, corroding, spraying gold, observing under an electron microscope to obtain the recast layer with the structure of the hole edge different from that of the base body, and measuring the thickness of the recast layer. The recast thickness score for a hole can be calculated by the following equation:
in the formula: m4For the roughness score of the hole, thickness (μm) is the recast layer thickness.
15 is the empirical value of the thickness of the recast layer of the gas film hole; 1500 is represented by the best score value M4The calculation is reversed for 50.
(4) Evaluation process of the endurance performance:
the method comprises the steps of making a permanent sample block according to a navigation mark HB 5150-. The durability performance score of its pores can be calculated by the following formula:
in the formula: m4For the hyperthermic persistence of the pores, TiDuration of non-perforated coupons, T is duration of perforated coupons.
(5) Multi-angle evaluation and comprehensive analysis
And comprehensively analyzing all test data, and defining the weight according to test conditions and requirements by using a score calculation formula as follows. The existing research shows that the roughness of the inner wall of the hole, the thickness of the recast layer and the high-temperature endurance test data are mutually related, and two to three tests can roughly reflect the quality of the hole.
M＝a1M1+a2M2+a3M3+a4M4+a5M5
In the formula: m is the total weight of the hole quality, and a1, a2, a3, a4 and a5 are the weights of hole roundness, taper, inner wall roughness, recast layer thickness and high-temperature durability respectively.
The quality evaluation method for the turbine blade electric spark machining air film hole can comprehensively judge the quality of the air film hole at multiple angles, compares various test results with each other, and can greatly improve the accuracy of the evaluation result.
Drawings
FIG. 1 is a schematic view of the entire air film hole quality evaluation process;
FIG. 2 is a schematic view of the perforation of a coupon;
FIG. 3 is a schematic view of a wire cut of a coupon;
FIG. 4 is a schematic grinding view of a cut coupon;
FIG. 5 is a schematic view showing measurement of the thickness of a recast layer.
Detailed Description
For a clearer understanding of the objects, technical solutions and advantages of the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and embodiments.
The invention provides a quality evaluation method for an air film hole machined by a turbine blade through electric spark, which is used for evaluating five aspects of hole roundness, conicity, inner wall roughness, recasting layer thickness and high-temperature durability of the air film hole machined by electric spark. The performance of the five aspects of the air film hole is respectively scored, then the total score of the air film hole is calculated by formula weighting so as to comprehensively evaluate the quality of the air film hole, and the comprehensive evaluation flow is shown in figure 1.
As shown in FIG. 1, the quality evaluation method for the turbine blade electrosparking gas film hole mainly comprises the steps of measuring the roundness and the taper of the hole, measuring the roughness of the inner wall of the hole, measuring the thickness of a recast layer and performing a high-temperature endurance experiment. The roundness and the taper reflect the concentration and the stability of electrode discharge, the appearance and the roughness of the inner wall of the hole reflect the uniform degree of electrode discharge, the thickness of a recasting layer reflects the intensity of heating of the inner wall of the hole, and a high-temperature endurance test can simulate the influence degree of the gas film hole on the endurance performance of the material under the service condition.
Carrying out roundness and taper measurements
As shown in fig. 2, the schematic diagram of the punching of the sample block can be used to process a plurality of small holes on the same rectangular sample block, each process parameter is processed into vertical rows, each row has at least two holes, and a plurality of different process parameters are processed into horizontal rows to form an array of holes.
The sample block parameters in this example are: the diameter of the hole is 0.4mm, the distance between the two holes is 1.8mm, 1 row of holes are drilled in each process, 5 holes are drilled in each row to obtain a plurality of groups of data, the result is more accurate, and the sample block is made of nickel-based high-temperature alloy and is 2.0mm thick.
The electric spark punching process parameter range is as follows: the machining current is 3-7A, the pulse width is 4-20 us, the pulse interval is 6-20 us, and the punching parameters are set as follows: the machining current 3A, the pulse width is 12us, the pulse interval is 18us, the machining current is randomly selected within the range, the punching quality is moderate according to experience, and the final comprehensive score value calculated theoretically is 40-60.
And cleaning the surface of the sample block by using clear water and alcohol, and marking the outlet and inlet directions of the hole by using a marking pen. The specimen block is observed under a body mirror and a photograph is taken, which must be scaled. Then the maximum, minimum and average diameters of the outlet and inlet of the hole, the area and perimeter of the outlet and inlet of the hole are measured by software image pro plus, and then the roundness, taper and score of the hole are calculated by formulas. The exit roundness for this example was 33.73, the entrance roundness was 17.53, and the taper was 0.00927, the resulting minutesNumber M1＝50.67，M2＝61.80。
Carrying out a measurement of the roughness of the inner wall of the hole
The coupons were cut with a row of wells along the edge of the well by wire cutting, as shown in figure 3, with care being taken that the wire cut did not touch the well. Then, the surface of the steel sheet is polished by sand paper, and a polishing machine is used as much as possible to obtain a smooth surface. After the hole is half-ground, the grinding is stopped, as shown in fig. 4, and then the foreign matter in the groove is washed clean. The inner wall roughness is measured in this example using a confocal laser apparatus such as an OLYMPUS OLS 4100. In this example, the cut-off wavelength λ a of the laser confocal apparatus was set to 800 μ M, the measured roughness was 1.96 μ M, and the obtained fraction M was3＝50.50。
Carrying out a measurement of the thickness of the recast layer in the spark keyhole
As shown in fig. 5, a perforated sample block, which has been cut with a row of different electric discharge processes, is cut again with a wire cutting with the cut surface facing outward to make a metallographic sample, the cut surface is ground with sandpaper or a polisher to obtain a smooth surface, half of the hole is ground and the surface is polished, and then the metallographic sample is corroded with a corresponding corrosive agent, sprayed with gold, and observed under an electron microscope and photographed. Since the recast layer had unevenness, the average thickness of the recast layer was measured by image pro plus in this example to be 7.47um, and the fraction M was obtained4＝66.76。
Carrying out a high temperature endurance test procedure
In the embodiment, a plurality of durable sample blocks are manufactured in advance, a small part of samples are kept without punching, small holes are punched in the rest samples at the middle positions of a sample examination section by using electric spark parameters to be evaluated, and then a high-temperature durable experiment is carried out strictly according to a navigation mark HB 5150-1996. In this example, the test temperature was 980 ℃, the applied stress was 300MPa, the duration of the non-perforated coupon was 150.8h, the duration of the perforated coupon was 77.93h, and the fraction M obtained was5＝51.68。
From the test results, the roundness score M150.67 roughness score M3＝50.50，M551.68, the three scoring results are close, the single best result is 60 points, and different tests can be mutually verifiedAnd (5) checking and evaluating the consistency of the results.
Implementing multi-angle comprehensive assessment
The weights for this example are set as: a is1＝0.1、a2＝0.1、a3＝0.1、a4＝0.2、a50.5. Therefore, the final score of the punching parameter is 55.49, which is close to the theoretical calculation result, thereby proving the feasibility of the method of the invention and being consistent with the actual processing condition.
If the quality of the gas film hole is to be roughly known, part of tests can be selected according to test conditions and test expenses, the long-lasting test with high cost and long time consumption can be eliminated, and the tests with low cost and short time consumption, such as the thickness of a recast layer of the hole, the roughness of the inner wall of the hole and the like, can be selected and measured.
Claims (6)
1. A quality evaluation method for a turbine blade electrosparking air film hole comprises the following steps:
(1) punching a gas film hole on the sample block by adopting the same processing technological parameters of the gas film hole, and measuring the roundness and the taper of the two sides of the outlet and the inlet of the gas film hole;
(2) splitting a sample block along the edge of the air film hole, grinding and polishing the section to expose the inner wall of the air film hole, and measuring the roughness of the inner wall of the hole;
(3) cutting the sample block along the edge of the air film hole to prepare a metallographic sample, and measuring the thickness of a recast layer;
(4) carrying out a high-temperature endurance test on the sample block to obtain high-temperature endurance performance test data of the sample block;
(5) and selecting more than 3 items of roundness, taper, hole inner wall roughness, recasting layer thickness and high-temperature durability, respectively calculating scores of the holes, and respectively weighting to obtain the mass fraction of the gas film hole.
2. The method of claim 1, wherein the roundness score and the taper score are calculated by:
wherein: m1For roundness rating, M2For Taper score, Roundness is the Roundness of the exit or entrance of the film hole, and Taper is the Taper of the film hole.
3. The method of claim 1, wherein the roughness score is calculated by:
wherein: m3For roughness scores, Ra is the roughness of the inner wall of the hole in μm.
4. The method of claim 1, wherein the recast layer thickness score is calculated by:
wherein: m4For roughness score, thickness is the recast layer thickness in μm.
5. The method of claim 1, wherein the high temperature durability performance score is calculated by:
wherein: m4For the hyperthermic persistence of the pores, TiDuration of non-perforated coupons, T is duration of perforated coupons.
6. The method of claim 1, wherein said parameters selected in step (5) are roundness, taper, bore wall roughness, recast thickness and high temperature durability.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111177059.4A CN113909600A (en) | 2021-10-09 | 2021-10-09 | Quality evaluation method for turbine blade electrosparking gas film hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111177059.4A CN113909600A (en) | 2021-10-09 | 2021-10-09 | Quality evaluation method for turbine blade electrosparking gas film hole |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113909600A true CN113909600A (en) | 2022-01-11 |
Family
ID=79238973
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111177059.4A Pending CN113909600A (en) | 2021-10-09 | 2021-10-09 | Quality evaluation method for turbine blade electrosparking gas film hole |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113909600A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117890173A (en) * | 2024-01-12 | 2024-04-16 | 中国航发北京航空材料研究院 | Preparation method of nickel-based superalloy turbine blade metallographic phase for protecting aluminum-silicon coating |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0950934A1 (en) * | 1998-04-17 | 1999-10-20 | United Technologies Corporation | Method and apparatus of predicting a characteristic of a product attribute formed by a machining process using a model of the process |
| WO2000032342A1 (en) * | 1998-12-02 | 2000-06-08 | Mitsubishi Denki Kabushiki Kaisha | Machining state judging device for electrical discharge machine |
| CN102248476A (en) * | 2010-03-09 | 2011-11-23 | 纳格尔机械及工具制造厂有限责任公司 | Method and apparatus for the measurement-aided fine machining of workpiece surfaces, and measuring system |
| CN106312573A (en) * | 2016-10-21 | 2017-01-11 | 湖北三江航天万峰科技发展有限公司 | Inverted inner taper hole machining device and machining and detecting method |
| CN107813114A (en) * | 2017-12-04 | 2018-03-20 | 宁国市华成金研科技有限公司 | The processing method that a kind of aero engine turbine blades remove remelted layer air film hole |
| CN211331676U (en) * | 2019-08-28 | 2020-08-25 | 东莞台一盈拓科技股份有限公司 | Aviation blade puncher installs gas film hole site aperture on-line measuring's device additional |
| DE102021210205A1 (en) * | 2021-09-15 | 2023-03-16 | Robert Bosch Gesellschaft mit beschränkter Haftung | Assess fillets of inner bore edges using machine learning using vibration data or the like |
-
2021
- 2021-10-09 CN CN202111177059.4A patent/CN113909600A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0950934A1 (en) * | 1998-04-17 | 1999-10-20 | United Technologies Corporation | Method and apparatus of predicting a characteristic of a product attribute formed by a machining process using a model of the process |
| WO2000032342A1 (en) * | 1998-12-02 | 2000-06-08 | Mitsubishi Denki Kabushiki Kaisha | Machining state judging device for electrical discharge machine |
| CN102248476A (en) * | 2010-03-09 | 2011-11-23 | 纳格尔机械及工具制造厂有限责任公司 | Method and apparatus for the measurement-aided fine machining of workpiece surfaces, and measuring system |
| CN106312573A (en) * | 2016-10-21 | 2017-01-11 | 湖北三江航天万峰科技发展有限公司 | Inverted inner taper hole machining device and machining and detecting method |
| CN107813114A (en) * | 2017-12-04 | 2018-03-20 | 宁国市华成金研科技有限公司 | The processing method that a kind of aero engine turbine blades remove remelted layer air film hole |
| CN211331676U (en) * | 2019-08-28 | 2020-08-25 | 东莞台一盈拓科技股份有限公司 | Aviation blade puncher installs gas film hole site aperture on-line measuring's device additional |
| DE102021210205A1 (en) * | 2021-09-15 | 2023-03-16 | Robert Bosch Gesellschaft mit beschränkter Haftung | Assess fillets of inner bore edges using machine learning using vibration data or the like |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117890173A (en) * | 2024-01-12 | 2024-04-16 | 中国航发北京航空材料研究院 | Preparation method of nickel-based superalloy turbine blade metallographic phase for protecting aluminum-silicon coating |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Li et al. | State-of-art, challenges, and outlook on manufacturing of cooling holes for turbine blades | |
| Zhang et al. | Effect of assisted transverse magnetic field on distortion behavior of thin-walled components in WEDM process | |
| Gurav et al. | Quality evaluation of precision micro holes drilled using pulsed Nd: YAG laser on aerospace nickel-based superalloy | |
| CN104061853A (en) | Method for measuring sub-surface affected layer depth and morphology of optical material | |
| CN113909600A (en) | Quality evaluation method for turbine blade electrosparking gas film hole | |
| Manikandan et al. | Machinability evaluation and comparison of Incoloy 825, Inconel 603 XL, Monel K400 and Inconel 600 super alloys in wire electrical discharge machining | |
| Gao et al. | Abrasive water jet drilling of ceramic thermal barrier coatings | |
| Mouralova et al. | Analysis of cut orientation through half-finished product using WEDM | |
| Liu et al. | The modification of corrosion resistance of 17-4PH stainless steel by cutting process | |
| Yang et al. | Study on surface work hardening of titanium alloy milled by micro-textured ball milling cutter | |
| Balaji et al. | Abrasive water jet piercing of straight and inclined holes on Yttria-Stabilized Zirconia coated Ni-based superalloy | |
| Zhang et al. | Machining uniformity and property change of abrasive media for micro-porous structures | |
| Selvarajan et al. | Fuzzy logic optimization with regression analysis on EDM machining parameters of Si 3N 4-TiN ceramic composites | |
| Manu et al. | Influence of jet impact angle on part geometry in abrasive waterjet turning of aluminium alloys | |
| CN109079143A (en) | The method for removing precinct laser fusion formation of parts surface of internal cavity crackle | |
| CN111929190B (en) | Method for evaluating abradability of sealing coating and application thereof | |
| Selvarajan et al. | Enhanced Jaya optimization in electrical discharge hole making of MoSi2–SiC composite with surface morphology analysis | |
| Carlini et al. | WED-machining performance by reciprocating molybdenum wire on Inconel 718 with water or hydrocarbon dielectrics | |
| Hao et al. | Vibratory finishing for the cavity of aero-engine integral casting casing: mechanism analysis and performance evaluation | |
| Desai et al. | Experimental investigation & optimization of micro-hardness and surface roughness under electric discharge machining: to enhance superalloy superfer 800 lightweight industrial applications | |
| Xue et al. | Integrated rapid 3D mapping and laser additive repair of gas turbine engine components | |
| US6729175B2 (en) | Test piece for inspection penetrant performance assessment and comparison | |
| Grobelny et al. | Investigations of surface topography of titanium alloy manufactured with the use of 3D print | |
| Tao et al. | Surface integrity evolution during creep feed profile grinding of γ-TiAl blade tenon | |
| Jasiczek et al. | A new approach to characterization of gas turbine components affected by pitting corrosion |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |