CN113670620B - Novel device for generating rotational flow distortion - Google Patents
Novel device for generating rotational flow distortion Download PDFInfo
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- CN113670620B CN113670620B CN202110842737.8A CN202110842737A CN113670620B CN 113670620 B CN113670620 B CN 113670620B CN 202110842737 A CN202110842737 A CN 202110842737A CN 113670620 B CN113670620 B CN 113670620B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The invention discloses a novel device for generating rotational flow distortion, which comprises a casing and a plurality of rotational flow components uniformly arranged on the casing in the circumferential direction; the rotational flow component comprises a mounting plate, rotational flow blades, a limiting bearing, a first connecting rod, a coupler, a stepping motor, a driving bevel gear, a driven bevel gear, a second connecting rod and an angle sensor; the rotational flow blade comprises a front section blade, a rear section blade, a front section fixing shaft and a rear section rotating shaft. The invention can generate the same-direction integral vortex, the reverse integral vortex, the opposite vortex, the offset opposite vortex and the like by adjusting the mounting angle of the rear-section blade of the swirl blade, and can improve the strength of the vortex; the consistency of the blades is changed by adjusting the number of the swirl blades; a closed-loop control system is formed by the angle sensor and the stepping motor, so that the adjusting precision of the mounting angle of the blade can be improved, and the precision of generating various vortexes can be improved.
Description
Technical Field
The invention relates to the field of air inlet pipes of jet propulsion devices, in particular to a novel device for generating rotational flow distortion, which is used for influencing the gas flow in an inlet pipeline of an aircraft engine.
Background
The air inlet/engine matching problem is always one of the main problems restricting the research and development of the aero-engine, and the flow field condition provided by the air inlet for the engine directly influences the working performance and stable working condition of the engine. Intake distortion, which is an unstable factor in an intake duct, can be generally classified into total pressure distortion, total temperature distortion and rotational flow distortion. The initial rotational flow distortion is not the key point in the air inlet/engine compatibility evaluation, and with the increasing requirements of advanced fighters on high maneuverability, supersonic cruise, stealth and other performances, the S-shaped air inlet is adopted by the fighters at home and abroad, and the investigation shows that the serious rotational flow distortion exists in the air inlet under the special conditions of extreme attack angle, missile launching and the like in the maneuvering flight of the advanced fighter. The strength of the rotational flow distortion is not only related to the shape of the air inlet, but also influenced by flight conditions and postures, and in order to research the influence of the rotational flow distortion on the performance and the stability of the engine, researchers at home and abroad begin to develop rotational flow distortion generators in various forms to simulate the rotational flow distortion and test the performance of the engine. The variable camber vane type rotational flow distortion generator has the advantages of capability of manufacturing various vortexes, adjustable swirl strength, convenience in adjustment and the like, but the conventional variable camber vane type rotational flow distortion generator realizes the change of the camber angle of the vane by controlling the rotation of the vane through the open loop of the stepping motor, and has large error and low precision.
In 1987, Genssler in germany originally generated twin vortices using a delta wing swirl distortion generator, and found that the twin vortex strength can be changed by adjusting the angle of attack of the delta wing. In 2002, AEDC designs a vane type rotational flow distortion generator, and rotational flow is generated by utilizing wake vortex of a vane and leakage vortex at the end part, and the rotational flow with the tangential direction reaching 25 degrees is generated in experiments. A vane type rotational flow distortion generator designed by a ginger key and the like in south navigation can generate integral vortexes with different strengths, opposite vortexes and offset opposite vortexes by changing the structure and the layout of vanes.
Disclosure of Invention
The invention aims to solve the technical problem of providing a novel device for generating rotational flow distortion, namely, providing a sectional variable camber blade and a novel device and a novel method for adjusting the installation angle of the blade on the basis of the original variable camber blade type rotational flow distortion generator, which can change the camber and simultaneously realize the change of the blade height, and are used for researching the influence of the circumferential blade height of the rotational flow distortion generator on the generation of the vortex and improving the strength and the precision of the generated vortex.
The invention adopts the following technical scheme for solving the technical problems:
a rotational flow distortion generator comprises a casing and a plurality of rotational flow components;
the casing is in a hollow cylinder shape with openings at two ends, and the plurality of cyclone assemblies are uniformly arranged on the casing in the circumferential direction;
the rotational flow component comprises a mounting plate, rotational flow blades, a limiting bearing, a first connecting rod, a coupler, a stepping motor, a driving bevel gear, a driven bevel gear, a second connecting rod and an angle sensor;
the mounting plate is a right-angle plate and comprises a first fixing plate and a second fixing plate which are vertically and fixedly connected with each other, wherein the first fixing plate is fixedly connected with the outer wall of the casing, and a through hole for mounting the limiting bearing is formed in the first fixing plate;
the limiting bearing is arranged in the through hole of the first fixing plate, and the outer ring of the limiting bearing is fixedly connected with the first fixing plate;
the rotational flow blades comprise front blades, rear blades, a front fixed shaft and a rear rotating shaft, wherein the front blades and the rear blades are the same in length and are arranged in the casing; the inner wall of the casing is provided with a fixing hole matched with the front section fixing shaft and a through hole matched with the rear section rotating shaft; one end of the front section fixed shaft is fixedly connected with the casing through a fixed hole matched with the casing on the casing, and the other end of the front section fixed shaft is fixedly connected with the tail part of the front section blade; one end of the rear section rotating shaft is fixedly connected with the tail part of the rear section blade, the other end of the rear section rotating shaft sequentially penetrates through a through hole on the casing, which is matched with the casing, and an inner ring of the limiting bearing and then is coaxially and fixedly connected with one end of the first connecting rod, the rear section rotating shaft and the casing, which is matched with the through hole, form a revolute pair, and the rear section rotating shaft and the inner ring of the limiting bearing are coaxially and fixedly connected;
the stepping motor is fixed on the second fixing plate, and an output shaft of the stepping motor is coaxially and fixedly connected with the other end of the first connecting rod through the coupler and is used for outputting torque to the rear-section blade to adjust the installation angle of the rear-section blade;
the driving bevel gear and the driven bevel gear are hollow bevel gears, and the number of teeth is equal; the driving bevel gear is sleeved on the first connecting rod and is coaxially and fixedly connected with the first connecting rod; the angle sensor is fixed on the second fixing plate, and an input shaft of the angle sensor is coaxially and fixedly connected with one end of the second connecting rod; the other end of the second connecting rod is coaxially and fixedly connected with the driven bevel gear; the driving bevel gear and the driven bevel gear are meshed with each other.
As a further optimization scheme of the rotational flow distortion generator, the front-section blade and the rear-section blade are three-section blades and comprise a main blade, a first-stage blade and a second-stage blade;
the main blade and the first-stage blade are both hollow and have open tips;
a first slide way is arranged on the inner wall of the main blade along the length direction of the main blade, a second slide way is arranged on the inner wall of the first-stage blade along the length direction of the first-stage blade, and a sliding block capable of freely sliding and a locking mechanism capable of locking the sliding block on the first slide way and the second slide way are arranged on the first slide way and the second slide way respectively;
the first-stage blade is arranged in the main blade, and the outer wall of the first-stage blade is fixedly connected with the sliding block on the first slide way, so that the first-stage blade can slide out of and into the tip part of the main blade; the locking mechanism on the first slideway is used for locking the position of the first-stage blade relative to the main blade;
the secondary blade is arranged in the primary blade, and the outer wall of the secondary blade is fixedly connected with the sliding block on the second slide way, so that the secondary blade can slide out of and into the tip part of the primary blade; and the locking mechanism on the second slideway is used for locking the position of the second-stage blade relative to the first-stage blade.
As a further optimization scheme of the rotational flow distortion generator, the number of rotational flow components is preferably 16.
Compared with the prior art, the invention adopting the technical scheme has the following technical effects:
1. each swirl blade is independently controlled by the stepping motor, so that all swirl blades work independently without mutual influence and are convenient to disassemble, maintain and replace;
2. the mounting angle of the rear-section blade of the rotational flow blade is adjusted through a closed-loop control system consisting of the stepping motor and the angle sensor, so that the accurate positioning of the angle can be realized, the adjustment precision of the mounting angle of the rear-section blade of the rotational flow blade is improved, and the precision of various vortexes simulated by the rotational flow distortion generator is further improved;
3. the swirl blades are sectional type variable camber blades, the height of the circumferential blades can be changed without stopping the machine and replacing the blades in the test process, the consistency of the blades can be changed by adjusting the number of the swirl components, and the engine test under different conditions is completed.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the structure of the swirl assembly and the casing;
FIG. 3 is a partial view A-A of FIG. 2;
FIG. 4 is a schematic structural view of the swirl vanes of the present invention in a contracted state;
FIG. 5 is a schematic view of the structure of the swirl vane of the present invention in an extended state.
In the figure, 1-sectional type variable camber blade, 2-casing, 3-angle sensor, 4-stepping motor, 5-coupler, 6-mounting plate, 7-driven bevel gear, 8-driving bevel gear, 9-second connecting rod, 10-first connecting rod, 11-front blade, 12-rear blade, 13-front fixed shaft, 14-rear rotating shaft, 15-main blade of front blade, 16-first blade of front blade, 17-second blade of front blade, 18-main blade of rear blade, 19-first blade of rear blade, and 20-second blade of rear blade.
Detailed Description
The technical scheme of the invention is further explained in detail by combining the drawings as follows:
the present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.
As shown in FIG. 1, the invention discloses a rotational flow distortion generator, which comprises a casing and a plurality of rotational flow components;
the casing is in a hollow cylinder shape with openings at two ends, and the plurality of cyclone assemblies are uniformly arranged on the casing in the circumferential direction;
as shown in fig. 2 and 3, the rotational flow assembly includes a mounting plate, a rotational flow blade, a limit bearing, a first connecting rod, a coupling, a stepping motor, a driving bevel gear, a driven bevel gear, a second connecting rod, and an angle sensor;
the mounting plate is a right-angle plate and comprises a first fixing plate and a second fixing plate which are vertically and fixedly connected with each other, wherein the first fixing plate is fixedly connected with the outer wall of the casing, and a through hole for mounting the limiting bearing is formed in the first fixing plate;
the limiting bearing is arranged in the through hole of the first fixing plate, and the outer ring of the limiting bearing is fixedly connected with the first fixing plate;
the rotational flow blades comprise front blades, rear blades, a front fixed shaft and a rear rotating shaft, wherein the front blades and the rear blades are the same in length and are arranged in the casing; the inner wall of the casing is provided with a fixing hole matched with the front section fixing shaft and a through hole matched with the rear section rotating shaft; one end of the front section fixed shaft is fixedly connected with the casing through a fixed hole matched with the casing on the casing, and the other end of the front section fixed shaft is fixedly connected with the tail part of the front section blade; one end of the rear section rotating shaft is fixedly connected with the tail part of the rear section blade, the other end of the rear section rotating shaft sequentially penetrates through a through hole on the casing, which is matched with the casing, and an inner ring of the limiting bearing and then is coaxially and fixedly connected with one end of the first connecting rod, the rear section rotating shaft and the casing, which is matched with the through hole, form a revolute pair, and the rear section rotating shaft and the inner ring of the limiting bearing are coaxially and fixedly connected;
the stepping motor is fixed on the second fixing plate, and an output shaft of the stepping motor is coaxially and fixedly connected with the other end of the first connecting rod through the coupler and is used for outputting torque to the rear-section blade to adjust the installation angle of the rear-section blade;
the driving bevel gear and the driven bevel gear are hollow bevel gears, and the number of teeth is equal; the driving bevel gear is sleeved on the first connecting rod and is coaxially and fixedly connected with the first connecting rod; the angle sensor is fixed on the second fixing plate, and an input shaft of the angle sensor is coaxially and fixedly connected with one end of the second connecting rod; the other end of the second connecting rod is coaxially and fixedly connected with the driven bevel gear; the driving bevel gear and the driven bevel gear are meshed with each other.
It can be seen from fig. 3 how the rear blade section is controlled to rotate.
The front-section blades and the rear-section blades are all three-section blades and comprise main blades, primary blades and secondary blades;
the main blade and the first-stage blade are both hollow and have open tips;
the inner wall of the main blade is provided with a first slide way along the length direction of the main blade, the inner wall of the first-stage blade is provided with a second slide way along the length direction of the main blade, and the first slide way and the second slide way are both provided with a slide block capable of freely sliding and a locking mechanism capable of locking the slide block thereon;
the first-stage blade is arranged in the main blade, and the outer wall of the first-stage blade is fixedly connected with the sliding block on the first slide way, so that the first-stage blade can slide out of and into the tip part of the main blade; the locking mechanism on the first slideway is used for locking the position of the first-stage blade relative to the main blade;
the secondary blade is arranged in the primary blade, and the outer wall of the secondary blade is fixedly connected with the sliding block on the second slide way, so that the secondary blade can slide out of and into the tip part of the primary blade; and the locking mechanism on the second slideway is used for locking the position of the second-stage blade relative to the first-stage blade.
Fig. 4 and 5 are schematic structural views of the swirl vane in the contracted state and the expanded state, respectively.
The number of swirl assemblies is preferably 16. As shown in fig. 1, the consistency is 1 when the rotational flow distortion generator employs 16 rotational flow blades. The consistency can be changed by adjusting the number of the swirl blades, and the consistency is 0.5 when the number of the swirl blades is adjusted to be 8. The height of the circumferential swirl blades can be adjusted, the built-in blades are not drawn out in a normal state, the blades are completely drawn out and can reach 1.5 times of the initial blade height at most, each swirl blade is controlled by a closed-loop control system consisting of an independent stepping motor and an angle sensor, and the blades do not influence each other in work.
The installation angle direction of the rear section blade of the rotational flow blade is positive when the same as the clockwise direction in the figure 1, the rotational flow direction is same as the clockwise direction and is a homodromous vortex, and the rotational flow direction is opposite to the clockwise direction and is a reverse vortex. When the mounting angles of the rear blades of all the swirl blades are controlled to be zero degrees, the inlet airflow angle cannot be influenced, and the axial air inlet is maintained. And if the mounting angles of the rear section blades of all the swirl blades are adjusted to be 20 degrees, the same-direction integral vortex with the swirl strength of 20 degrees is generated. The 16 circumferential swirl blades are divided into two symmetrical groups of 8 swirl blades. Adjusting the mounting angles of the rear section blades of the two groups of swirl blades to be the same in size and opposite in direction to generate opposite vortexes, adjusting the mounting angle of the rear section blade of one group of swirl blades to be 30 degrees, and adjusting the mounting angle of the rear section blade of the other group of swirl blades to be-30 degrees to generate opposite vortexes with the swirl strength of 60 degrees. Different sizes and opposite directions can generate offset vortex alignment, the mounting angle of the rear section blade of one group of swirl blades is adjusted to be 15 degrees, the mounting angle of the rear section blade of the other group of swirl blades is adjusted to be-35 degrees, and then the offset vortex alignment with the swirl strength of 50 degrees is generated.
When the vortex generating device works, airflow flows through the vortex blades of each vortex assembly to form circumferential secondary flow, and the secondary flow in a single direction forms an integral vortex; the secondary flows with opposite directions and the same size form a twin vortex; the secondary flows with opposite directions and different sizes form offset twin vortices. The vortex strength can be changed by adjusting the mounting angle of the rear section blade of each swirl blade, and the mounting angle of the blade is accurately positioned through a closed-loop control system consisting of a stepping motor and an angle sensor, so that the adjusting precision of the mounting angle of the blade is improved. The larger the bending angle of the rear section blade of the swirl blade is, the more obvious the secondary flow is, and the larger the swirl strength is. The height of the swirl vane can also be adjusted, and in the test, the circumferential vanes with different heights can be obtained without stopping and replacing the vanes.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only illustrative of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. A rotational flow distortion generator is characterized by comprising a casing and a plurality of rotational flow components;
the casing is in a hollow cylinder shape with openings at two ends, and the plurality of rotational flow components are uniformly arranged on the casing in the circumferential direction;
the rotational flow component comprises a mounting plate, rotational flow blades, a limiting bearing, a first connecting rod, a coupler, a stepping motor, a driving bevel gear, a driven bevel gear, a second connecting rod and an angle sensor;
the mounting plate is a right-angle plate and comprises a first fixing plate and a second fixing plate which are vertically and fixedly connected with each other, wherein the first fixing plate is fixedly connected with the outer wall of the casing, and a through hole for mounting the limiting bearing is formed in the first fixing plate;
the limiting bearing is arranged in the through hole of the first fixing plate, and the outer ring of the limiting bearing is fixedly connected with the first fixing plate;
the rotational flow blades comprise front blades, rear blades, a front fixed shaft and a rear rotating shaft, wherein the front blades and the rear blades are the same in length and are arranged in the casing; the inner wall of the casing is provided with a fixing hole matched with the front section fixing shaft and a through hole matched with the rear section rotating shaft; one end of the front-section fixed shaft is fixedly connected with the casing through a fixed hole on the casing matched with the front-section fixed shaft, and the other end of the front-section fixed shaft is fixedly connected with the tail part of the front-section blade; one end of the rear section rotating shaft is fixedly connected with the tail part of the rear section blade, the other end of the rear section rotating shaft sequentially penetrates through a through hole on the casing, which is matched with the casing, and an inner ring of the limiting bearing and then is coaxially and fixedly connected with one end of the first connecting rod, the rear section rotating shaft and the casing, which is matched with the through hole, form a revolute pair, and the rear section rotating shaft and the inner ring of the limiting bearing are coaxially and fixedly connected;
the stepping motor is fixed on the second fixing plate, an output shaft of the stepping motor is coaxially and fixedly connected with the other end of the first connecting rod through the coupler and is used for outputting torque to the rear-section blade to adjust the mounting angle of the rear-section blade;
the driving bevel gear and the driven bevel gear are hollow bevel gears, and the number of teeth is equal; the driving bevel gear is sleeved on the first connecting rod and is coaxially and fixedly connected with the first connecting rod; the angle sensor is fixed on the second fixing plate, and an input shaft of the angle sensor is coaxially and fixedly connected with one end of the second connecting rod; the other end of the second connecting rod is coaxially and fixedly connected with the driven bevel gear; the driving bevel gear and the driven bevel gear are meshed with each other;
the front-section blades and the rear-section blades are all three-section blades and comprise main blades, primary blades and secondary blades;
the main blade and the first-stage blade are both hollow and have open tips;
the inner wall of the main blade is provided with a first slide way along the length direction of the main blade, the inner wall of the first-stage blade is provided with a second slide way along the length direction of the main blade, and the first slide way and the second slide way are both provided with a slide block capable of freely sliding and a locking mechanism capable of locking the slide block thereon;
the first-stage blade is arranged in the main blade, and the outer wall of the first-stage blade is fixedly connected with the sliding block on the first slide way, so that the first-stage blade can slide out of and into the tip part of the main blade; the locking mechanism on the first slideway is used for locking the position of the first-stage blade relative to the main blade;
the secondary blade is arranged in the primary blade, and the outer wall of the secondary blade is fixedly connected with the sliding block on the second slide way, so that the secondary blade can slide out of and into the tip part of the primary blade; and the locking mechanism on the second slideway is used for locking the position of the second-stage blade relative to the first-stage blade.
2. The rotational flow distortion generator of claim 1 wherein the number of rotational flow assemblies is 16.
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| CN202110842737.8A CN113670620B (en) | 2021-07-26 | 2021-07-26 | Novel device for generating rotational flow distortion |
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| CN202110842737.8A CN113670620B (en) | 2021-07-26 | 2021-07-26 | Novel device for generating rotational flow distortion |
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| CN113670620A CN113670620A (en) | 2021-11-19 |
| CN113670620B true CN113670620B (en) | 2022-06-17 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104912668A (en) * | 2015-04-24 | 2015-09-16 | 南京航空航天大学 | Variable camber vane type spiral flow distortion generator |
| CN106153346A (en) * | 2016-07-20 | 2016-11-23 | 南京航天航空大学 | A kind of inflatable vane type swirl flow distortion generator and method for generation |
| CN107676284A (en) * | 2017-08-23 | 2018-02-09 | 太原理工大学 | A kind of fan blade adjusting means, counter-rotating fan and fan blade adjusting method |
| CN111579249A (en) * | 2020-06-03 | 2020-08-25 | 中国空气动力研究与发展中心 | Whole vortex flow distortion simulation device of gas compressor convenient to independent control whirl |
| CN112124579A (en) * | 2020-10-23 | 2020-12-25 | 南京航空航天大学 | Real-time variable-speed rotor wing used for flying at high speed |
| CN112484682A (en) * | 2020-11-05 | 2021-03-12 | 中国航发四川燃气涡轮研究院 | Measuring device and measuring method for adjustable blade installation angle |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10253779B2 (en) * | 2016-08-11 | 2019-04-09 | General Electric Company | Inlet guide vane assembly for reducing airflow swirl distortion of an aircraft aft fan |
-
2021
- 2021-07-26 CN CN202110842737.8A patent/CN113670620B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104912668A (en) * | 2015-04-24 | 2015-09-16 | 南京航空航天大学 | Variable camber vane type spiral flow distortion generator |
| CN106153346A (en) * | 2016-07-20 | 2016-11-23 | 南京航天航空大学 | A kind of inflatable vane type swirl flow distortion generator and method for generation |
| CN107676284A (en) * | 2017-08-23 | 2018-02-09 | 太原理工大学 | A kind of fan blade adjusting means, counter-rotating fan and fan blade adjusting method |
| CN111579249A (en) * | 2020-06-03 | 2020-08-25 | 中国空气动力研究与发展中心 | Whole vortex flow distortion simulation device of gas compressor convenient to independent control whirl |
| CN112124579A (en) * | 2020-10-23 | 2020-12-25 | 南京航空航天大学 | Real-time variable-speed rotor wing used for flying at high speed |
| CN112484682A (en) * | 2020-11-05 | 2021-03-12 | 中国航发四川燃气涡轮研究院 | Measuring device and measuring method for adjustable blade installation angle |
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