CN209936056U - Ultra-precise machining device for micro-holes of air film of aero-engine blade - Google Patents
Ultra-precise machining device for micro-holes of air film of aero-engine blade Download PDFInfo
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- CN209936056U CN209936056U CN201920665622.4U CN201920665622U CN209936056U CN 209936056 U CN209936056 U CN 209936056U CN 201920665622 U CN201920665622 U CN 201920665622U CN 209936056 U CN209936056 U CN 209936056U
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Abstract
An ultra-precise machining device for micro holes of an air film of an aircraft engine blade relates to the technical field of micro hole machining. It includes: a frame; the lifting device is arranged on the rack; the micro cutter is assembled on the lifting device and used for processing micro holes of the workpiece; a microelectrode film sleeve which is sleeved on the micro-cutter and is used for guiding and discharging the processing scraps in the micropores and precisely grinding the walls of the micropores; the object stage is borne on the rack, arranged below the micro cutter and used for placing a workpiece; the electromagnetic guiding device is arranged below the objective table; and the five-axis machine tool is arranged on the rack, is used for bearing the electromagnetic guiding device and is used for driving the electromagnetic guiding device to guide the plasma of the micro-cutter along the micro-hole design direction. By adopting the technical scheme, the microelectrode film sleeve can play a role in chip guide and precise grinding of micropores, and has the advantages of ensuring the micropore machining precision and improving the micropore machining depth and micropore smoothness.
Description
Technical Field
The utility model relates to a micropore processing technology field, concretely relates to super precision machining device of aeroengine blade gas film micropore.
Background
With the development of aerospace, electronic communication, optics, medical instruments and the like, the micro-hole machining is more widely applied, the micro-hole is used as one type of micro-hole which is difficult to machine, the traditional mechanical micro-drilling is extremely difficult to meet the machining requirement, the micro-electrical discharge machining belongs to non-contact machining, has no mechanical machining force, is higher in precision, can machine conductive materials with any hardness, and has unique advantages in the aspect of micro-hole machining.
In the conventional micropore machining process, due to the factors that the diameter of the micro drill bit is small, the micropore distance is small, the material of a workpiece to be machined is difficult to machine and the like, the efficiency is low, the micro drill bit is easy to break, the requirement on the precision of equipment is very high, and the machining precision, the process and the like of micropores are difficult to guarantee at the same time. In the conventional micro electric discharge machining (electrode) method, a gap is formed between a micro hole and an electrode when the micro hole is machined. When reaching a certain depth, processing chips such as oxides and the like in the micropores are difficult to discharge, so that the micropores are difficult to deeply process products with large aperture ratio. The smooth finish of the micropores cannot be discharged immediately, and the phenomena of difficult promotion, easy generation of microcracks and the like are caused. Therefore, a brand new micropore solution is provided to solve the technical problem.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to prior art's defect and not enough, provide an aeroengine blade gas film micropore ultra-precision machining device, can derive the oxidation piece in the micropore smoothly through with little cutter selectivity pivoted microelectrode membrane cover, lead just and filled formula (compensation) micropore and electrode clearance, precision grinding micropore pore wall. The device has the advantages of simple structure, easy realization of equipment stability, contribution to processing of the micropores with the diameter ratio of the deep holes and improvement of the fineness of the micropores.
In order to achieve the above object, the utility model adopts the following technical scheme: an ultra-precision machining device for micro holes of an air film of an aircraft engine blade comprises: a frame; the lifting device is arranged on the rack; the micro cutter is assembled on the lifting device and used for processing micro holes of the workpiece; a microelectrode film sleeve which is sleeved on the micro-cutter and is used for guiding and discharging the processing scraps in the micro-pores and grinding the walls of the micro-pores; the object stage is borne on the rack, arranged below the micro cutter and used for placing a workpiece; the electromagnetic guiding device is arranged below the objective table; and the five-axis machine tool is arranged on the rack, is used for bearing the electromagnetic guiding device and is used for driving the electromagnetic guiding device to guide the plasma of the micro-cutter along the micro-hole design direction.
In a further aspect, the micro-blade is electrically connected to a first ultrasonic generator.
The utility model discloses a further setting, it has second ultrasonic generrator to go up the electricity connection on the work piece.
The utility model discloses a further setting, microelectrode membrane cover excircle is equipped with leads bits passageway.
The utility model discloses a further setting, it is the screw thread form to lead the bits passageway.
The utility model discloses a further setting, it is many arriss strip to lead bits passageway.
In a further arrangement of the utility model, the microelectrode film sleeve is made of wear-resistant material.
The utility model discloses a further setting, little cutter is nanocomposite.
After the technical scheme is adopted, the utility model discloses beneficial effect does:
1. compared with the prior art, the utility model discloses in, establish microelectrode membrane cover through the cover on the little cutter, when little cutter rotates and carries out micropore man-hour, microelectrode membrane cover rotates along with little cutter selectivity, and then discharges the oxidation processing bits that produce in the micropore from leading the bits passageway, is favorable to breaching through the difficult problem of the big difficult processing of hole depth ratio.
2. The ultrasonic (impact) grinding processing is adopted, firstly, the barrier of non-conductive coatings with high temperature resistance, wear resistance and high hardness of an aircraft engine (composite) blade is broken through, and when the micro-cutter and a microelectrode film sleeve (guide) enter a conductive layer for micro-spark processing, the micro-cutter and the microelectrode film sleeve (guide) are processed. The ultrasonic grinding technology accelerates the process of micro-spark processing, and simultaneously, the micro-electrode film sleeve grinds sparks off to generate a cladding layer for the second time, thereby being beneficial to improving the fineness of the micropores, and leading the fineness of the micropores to reach the nanometer level. According to the design requirement of the micropores, specific wear-resistant and high-temperature-resistant composite materials are added in the grinding process, the material and the performance of the micropores can be changed, the cooling performance of the micropores of the air film of the engine blade is further improved, fuel oil is saved, and the safety performance and the cruising ability of the aerospace engine are improved again.
3. The utility model discloses in, remove along micropore design direction through driving electromagnetic guiding device on the five-axis machine tool to guide plasma (little electric spark) that little cutter produced, with flexible microelectrode, under the perfect cooperation of membrane cover, realize aeroengine blade air film micropore is perpendicular, streamlined, perhaps the innovation of crooked processing wantonly.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.
FIG. 1 is a schematic overall structure diagram of the first embodiment;
FIG. 2 is a schematic view showing the structure of a microelectrode film holder in accordance with one embodiment;
FIG. 3 is a schematic view showing the structure of a microelectrode film holder in the second embodiment.
Description of reference numerals: 1. a frame; 2. a lifting device; 3. a micro-cutter; 4. a microelectrode film sleeve; 5. an object stage; 6. an electromagnetic guiding device; 7. a five-axis machine tool; 8. a first ultrasonic generator; 9. a second ultrasonic generator; 10. a chip guide channel; 11. and (5) a workpiece.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications of the present embodiment as necessary without making a contribution thereto after reading the present specification, but all are protected by patent laws within the scope of the claims of the present invention.
The first embodiment is as follows: the embodiment relates to an ultra-precision machining device for an air film micro-hole of an aircraft engine blade, as shown in fig. 1-2, comprising: a frame 1; the lifting device 2 is arranged on the frame 1; assemble the little cutter 3 on elevating gear 2, the microelectrode membrane cover 4 on little cutter 3 is located to the cover, bear in frame 1 and locate 3 below supplies the objective table 5 that work piece 11 placed of little cutter, locate the electromagnetism guider 6 of objective table 5 below, and set up the five-axis machine tool 7 that supplies electromagnetism guider 6 to bear in frame 1, little cutter 3 is used for carrying out micropore processing to work piece 11, microelectrode membrane cover 4 is arranged in guiding the micropore in the processing bits discharge, five-axis machine tool 7 is used for driving electromagnetism guider 6 and removes thereby play the guide effect to the plasma of little cutter 3 along micropore design direction.
As shown in fig. 1, the micro-cutter 3 is electrically connected to a first ultrasonic generator 8, that is, the workpiece 11 is subjected to micro-hole machining through ultrasonic grinding, in this embodiment, the micro-cutter 3 is a conical tip electrode with high concentricity, which is beneficial to performing a core fixing effect when the workpiece 11 is punched, and the micro-cutter 3 is made of a nano composite material, so that abrasion of a cutter head can be effectively reduced, it should be noted that a rotating motor is arranged at the upper end of the micro-cutter 3, and an output shaft of the rotating motor is assembled with the micro-cutter 3, so as to drive the micro-cutter 3 to rotate when the workpiece 11 is subjected to micro-hole machining.
The lifting device 2 is used for realizing the lifting of the micro-cutter 3 along the depth direction of the micro-hole under the control of the controller, when the micro-cutter 3 enters the micro-hole, the microelectrode film sleeve 4 fixed on the micro-cutter 3 rotates together with the micro-cutter 3, as shown in figure 2, the outer edge of the microelectrode film sleeve 4 is provided with a scrap guide channel 10, in this embodiment, the chip guide channel 10 is threaded, so that under the high-speed rotation of the microelectrode film sleeve 4, on one hand, the oxidized chips generated in the micropores can be discharged from the chip guide channel 10, further being beneficial to breaking through the difficult problem of difficult processing of large depth-diameter ratio of the hole, on the other hand, grinding the melting layer generated by micro-spark (plasma) processing twice between the microelectrode film sleeve 4 and the non-conductive material to be beneficial to improving the smooth finish of the micropore, the micro-pore finish can reach the nanometer level, and the potential safety hazard of the micro-pores of the air film of the engine blade is particularly eliminated. Because the plasma (micro-electric spark) processing work piece (blade) is just in the liquid cooling soaking, the generation of microcracks is avoided in the process. If a specific wear-resistant high-temperature-resistant composite material is added in the grinding process, the composite nano material permeates into the micropores, the material of the micropores is changed, meanwhile, the method is suitable for the field of repairing the walls of the micropores of aviation blades and the like, is favorable for improving the cooling performance of the micropores of the air film of the engine blade, saving engine fuel, saving energy, protecting environment and simultaneously improving the safety performance and the cruising ability of the aerospace engine again.
It should be noted that, as shown in fig. 1, a certain space is provided between the electromagnetic guiding device 6 and the plummer, the electromagnetic guiding device 6 is disposed on the five-axis machine tool 7, and then a user can control the five-axis machine tool 7 to drive the electromagnetic guiding device 6 to move along the micropore design direction according to the micropore design direction, so that the electromagnetic guiding device 6 guides the vertical or curved direction of the plasma through the electromagnetic effect, and the workpiece 11 is processed into micropores in the vertical or curved direction. In the present embodiment, the lifting device 2 and the five-axis machine tool 7 are both in the prior art, and therefore, detailed description thereof is omitted.
As shown in FIG. 1, a second ultrasonic generator 9 is electrically connected to the workpiece 11, and the second ultrasonic generator 9 can apply vibration to the workpiece 11 during discharging chips from the micropores, so that the chips can be discharged from the microelectrode film sleeve 4 in the micropores conveniently. In this embodiment, the microelectrode film sleeve 4 is made of a high-hardness and wear-resistant material and comprises graphene or diamond, when the microelectrode enters the workpiece 11, the microelectrode film sleeve 4 guides the micro-cutter 3 to ensure the precision of the micropore, and meanwhile, the problem of micro-gap between the micropore and the micro-cutter 3 is solved well.
Example two: the embodiment relates to an ultra-precision machining device for an air film micro-hole of an aircraft engine blade, as shown in fig. 1 and 3, comprising: a frame 1; the lifting device 2 is arranged on the frame 1; the micro-cutting tool 3 is assembled on the lifting device 2, a microelectrode film sleeve 4 sleeved on the micro-cutting tool 3 is borne on the rack 1 and is arranged on an object stage 5 below the micro-cutting tool 3 for placing a workpiece 11, an electromagnetic guiding device 6 below the object stage 5 is arranged, and a five-axis machine tool 7 which is arranged on the rack 1 and is used for bearing the electromagnetic guiding device 6 is arranged, the micro-cutting tool 3 is used for processing micropores on the workpiece 11, the microelectrode film sleeve 4 is used for guiding the processed chips in the micropores to be discharged and carrying out precise grinding on the walls of the micropores, and the five-axis machine tool 7 is used for driving the electromagnetic guiding device 6 to move along the micropore design direction so as to guide plasma (micro-electric sparks) of the micro-cutting tool.
The lifting device 2 is used for lifting the micro-cutter 3 along the depth direction of the micro-hole under the control of the controller, when the micro-cutter 3 enters the micro-hole, the microelectrode film sleeve 4 fixedly arranged on the micro-cutter 3 rotates together with the micro-cutter 3, and as shown in fig. 3, the outer edge of the microelectrode film sleeve 4 is provided with a scrap guide channel 10.
The difference between this embodiment and the first embodiment is that, as shown in fig. 3, the chip guide channel 10 on the microelectrode film cover 4 is in the shape of a polygon. Therefore, under the high-speed rotation of the microelectrode film sleeve 4, on one hand, oxidized chips generated in micropores can be discharged from the chip guide channel 10, so that the difficulty that the depth-diameter ratio of the pores is large and the pores are difficult to process is overcome, on the other hand, a fusion coating layer is generated secondarily by the grinding sparks between the microelectrode film sleeve 4 and a non-conductive material, so that the smoothness of the micropores is improved, the smoothness of the micropores can reach the nanometer level, and the potential safety hazard of the micropores of an air film of an engine blade is particularly eliminated.
The working principle of the present embodiment is roughly as follows: the ultrasonic grinding processing and the electromagnetic guiding device 6 are combined to guide plasma (micro electric spark) generated by the micro cutter 3, so that the innovation of vertical, streamline or random bending processing of the air film micropores of the aero-engine blade is realized, the barrier of coatings such as high-temperature-resistant, wear-resistant and non-conductive coatings of the aero-engine (composite) blade is broken through, and the innovative requirements of the air film micropores and aerodynamics of the future engine blade can be met. And the micro-electrode film sleeve 4 is sleeved on the micro-cutter 3, when the micro-cutter 3 rotates to carry out micro-pore processing, the micro-electrode film sleeve 4 selectively rotates along with the micro-cutter 3, and then oxidized chips generated in micro-pores are discharged from the chip guide channel 10, so that the problem that the large hole depth-diameter ratio is difficult to process is favorably solved, the process of micro-spark processing is accelerated by an ultrasonic grinding technology, meanwhile, a secondary cladding layer is generated by sparks generated by grinding between the micro-electrode film sleeve 4 and the oxidized chips, the smoothness of the micro-pores is favorably improved, the smoothness of the micro-pores can reach the nanometer level, and potential safety hazards such as micro-cracks of the micro-pores of an air. If the specific wear-resistant high-temperature-resistant nano composite material is added in the grinding process, the composite nano material can effectively permeate into the micropores. Meanwhile, the method can be used in the field of trimming of the walls of the micropores such as the blade and the like. And potential safety hazards such as micro-cracks of gas film micropores of the engine blade are particularly eliminated. Thereby improving the cooling performance of the air film micropores of the engine blade and saving the engine fuel. Energy conservation and environmental protection, and simultaneously, the safety performance and the endurance capacity of the aerospace engine are improved again.
The above description is only for the purpose of illustrating the technical solutions of the present invention and not for the purpose of limiting the same, and other modifications or equivalent substitutions made by those skilled in the art to the technical solutions of the present invention should be covered by the claims of the present invention without departing from the spirit and scope of the technical solutions of the present invention.
Claims (8)
1. The utility model provides an aeroengine blade gas film micropore ultra-precision machining device which characterized in that includes: a frame (1);
the lifting device (2) is arranged on the rack (1);
the micro cutter (3) is assembled on the lifting device (2) and is used for carrying out micro-hole machining on a workpiece (11);
a microelectrode membrane sleeve (4) which is sleeved on the micro-cutter (3) and is used for guiding and discharging the processing scraps in the micro-pores and grinding the walls of the micro-pores;
the object stage (5) is borne on the rack (1), arranged below the micro cutter (3) and used for placing a workpiece (11);
an electromagnetic guide device (6) arranged below the objective table (5); and the number of the first and second groups,
and the five-axis machine tool (7) is arranged on the rack (1), is used for bearing the electromagnetic guiding device (6), and is used for driving the electromagnetic guiding device (6) to guide the plasma of the micro-cutter (3) along the micro-hole design direction.
2. The ultra-precise machining device for the micro holes of the air film of the blade of the aircraft engine according to claim 1, characterized in that the micro cutter (3) is electrically connected with a first ultrasonic generator (8).
3. The ultra-precise machining device for the micro holes of the air film of the blade of the aircraft engine as claimed in claim 1, wherein a second ultrasonic generator (9) is electrically connected to the workpiece (11).
4. The ultra-precise machining device for the micro holes of the air film of the blade of the aircraft engine according to claim 1, characterized in that a chip guide channel (10) is arranged on the outer edge of the microelectrode film sleeve (4).
5. The ultra-precision machining device for the air film micro-holes of the aeroengine blade as claimed in claim 4, wherein the chip guide channel (10) is in a thread shape.
6. The ultra-precision machining device for the air film micro holes of the aero-engine blade as claimed in claim 4, wherein the chip guide channel (10) is in a shape of a polygonal bar.
7. The ultra-precise processing device for the micro holes of the air film of the blade of the aircraft engine according to claim 1, wherein the microelectrode film sleeve (4) is made of wear-resistant material.
8. The ultra-precise machining device for the micro holes of the air film of the blade of the aircraft engine as claimed in claim 1, wherein the micro cutter (3) is made of a nano composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920665622.4U CN209936056U (en) | 2019-05-09 | 2019-05-09 | Ultra-precise machining device for micro-holes of air film of aero-engine blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920665622.4U CN209936056U (en) | 2019-05-09 | 2019-05-09 | Ultra-precise machining device for micro-holes of air film of aero-engine blade |
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| Publication Number | Publication Date |
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| CN209936056U true CN209936056U (en) | 2020-01-14 |
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| CN201920665622.4U Expired - Fee Related CN209936056U (en) | 2019-05-09 | 2019-05-09 | Ultra-precise machining device for micro-holes of air film of aero-engine blade |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112475500A (en) * | 2020-11-19 | 2021-03-12 | 潍坊科技学院 | Large-thickness workpiece linear cutting joint cutting electrical erosion matter discharging device |
| CN112809111A (en) * | 2021-01-20 | 2021-05-18 | 南方科技大学 | Ultrasonic-plasma electrolytic combined machining method and machining device for workpiece |
| CN113664304A (en) * | 2021-09-18 | 2021-11-19 | 上海交通大学 | Grinding and high-speed electric spark in-situ composite processing device |
| CN114425697A (en) * | 2021-12-27 | 2022-05-03 | 绍兴徐业模具有限公司 | Novel pulse machine tool for machining tire mold |
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2019
- 2019-05-09 CN CN201920665622.4U patent/CN209936056U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112475500A (en) * | 2020-11-19 | 2021-03-12 | 潍坊科技学院 | Large-thickness workpiece linear cutting joint cutting electrical erosion matter discharging device |
| CN112475500B (en) * | 2020-11-19 | 2021-12-28 | 潍坊科技学院 | Large-thickness workpiece linear cutting joint cutting electrical erosion matter discharging device |
| CN112809111A (en) * | 2021-01-20 | 2021-05-18 | 南方科技大学 | Ultrasonic-plasma electrolytic combined machining method and machining device for workpiece |
| CN112809111B (en) * | 2021-01-20 | 2022-05-20 | 南方科技大学 | Ultrasonic-plasma electrolytic combined machining method and machining device for workpiece |
| CN113664304A (en) * | 2021-09-18 | 2021-11-19 | 上海交通大学 | Grinding and high-speed electric spark in-situ composite processing device |
| CN114425697A (en) * | 2021-12-27 | 2022-05-03 | 绍兴徐业模具有限公司 | Novel pulse machine tool for machining tire mold |
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Granted publication date: 20200114 Termination date: 20200509 |