CN114252269A - Device and method for constructing lateral expansion weak constraint boundary of detonation wave - Google Patents
Device and method for constructing lateral expansion weak constraint boundary of detonation wave Download PDFInfo
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- 230000000977 initiatory effect Effects 0.000 claims abstract description 21
- 239000007789 gas Substances 0.000 claims description 45
- 238000002485 combustion reaction Methods 0.000 claims description 23
- 239000000203 mixture Substances 0.000 claims description 5
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 4
- VGGSQFUCUMXWEO-UHFFFAOYSA-N Ethene Chemical compound C=C VGGSQFUCUMXWEO-UHFFFAOYSA-N 0.000 claims description 4
- 239000005977 Ethylene Substances 0.000 claims description 4
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Abstract
The invention discloses a device and a method for constructing a detonation wave lateral expansion weak constraint boundary, wherein the device comprises a narrow and straight detonation cavity, a first air inlet, a diaphragm, at least two first pressure sensors, a plurality of second pressure sensors, a second air inlet, a lateral flame generating device and a high-energy igniter, the narrow and straight detonation cavity comprises a detonation wave initiation section, a detonation wave development propagation section and a detonation wave stable propagation testing section which are sequentially connected, the diaphragm is arranged between the detonation wave initiation section and the detonation wave development propagation section, the high-energy igniter is arranged at one end of the detonation wave initiation section, the first air inlet is communicated with the interior of the detonation wave initiation section, at least two first pressure sensors are arranged on the detonation wave development propagation section at intervals, the plurality of second pressure sensors are arranged on the detonation wave stable propagation testing section at intervals, and the second air inlet is communicated with the interior of the detonation wave stable propagation testing section, the lateral flame generating device is arranged on the detonation wave stable propagation testing section.
Description
Technical Field
The invention belongs to the technical field of detonation wave propagation characteristics, and particularly relates to a device and a method for constructing a lateral expansion weak constraint boundary of detonation waves.
Background
Detonation waves are supersonic combustion waves that are strongly coupled by shock waves and chemical reactions. In the process of detonation wave propagation, if the strong restraint of the physical fixed wall surface is lost, the airflow in the chemical reaction area expands laterally, so that the peak pressure and propagation speed of the detonation wave are obviously damaged. The Rotary Detonation Engine (RDE) is a new concept Engine based on Detonation combustion, and compared with the conventional power propulsion system based on isobaric combustion, the rotary Detonation Engine has the advantages of high thermal cycle efficiency, large specific thrust, simple structure and the like, and is a research hotspot and frontier in the field of current aerospace propulsion.
In the circumferential continuous rotation propagation process of the detonation waves in the rotary detonation combustor, one side close to exhaust is weakly restrained by a combustion boundary to generate lateral expansion loss, and the detonation waves are propagated unstably and extinguished even in serious conditions, so that the engine cannot normally work and further the propulsion performance of the engine is influenced. In order to reveal the law of influence of lateral expansion caused by lateral combustion in a rotary detonation combustor on the propagation characteristics of detonation waves, researchers currently generally adopt a method of isolating normal-temperature inert gas by using a film, namely, an axial film is placed in a constant-straight detonation channel, one side of the film is filled with inert gas, and the other side of the film is filled with combustible premixed gas, so that a weak constraint boundary is formed during propagation of the detonation waves.
In fact, this method has a number of drawbacks. On one hand, the influence of the thickness of the isolation film on the propagation characteristic of the detonation wave is difficult to control, and the difficulty of placing the film in actual operation is high, so that the height of premixed gas is inconvenient to adjust; on the other hand, the method ignores the interaction of detonation waves with the lateral combustion front in a real combustion chamber. More importantly, the temperature of the weak confinement boundary formed by the lateral combustion front in the real rotary detonation combustor is high, and the influence of the high-temperature weak confinement boundary on the detonation wave propagation stability cannot be reflected in the weak confinement boundary formed by the diaphragm and the inert gas. Therefore, there is a need to provide a more practical and operationally convenient method for studying lateral expansion caused by lateral combustion in a rotary detonation engine.
Disclosure of Invention
The invention aims to provide a novel device and a method for constructing a detonation wave lateral expansion weak constraint boundary, which can simulate the high-temperature weak constraint boundary and are simple to operate, aiming at the characteristic that the temperature of the weak constraint boundary formed by a detonation wave lateral combustion front is higher in the process of researching the influence of lateral expansion on the propagation characteristics of detonation waves.
The technical solution for realizing the purpose of the invention is as follows:
a device for constructing a detonation wave lateral expansion weak constraint boundary comprises a narrow straight detonation cavity, a first air inlet, a diaphragm, at least two first pressure sensors, a plurality of second pressure sensors, a second air inlet, a lateral flame generating device and a high-energy igniter,
the narrow and straight detonation cavity comprises a detonation wave initiation section, a detonation wave development propagation section and a detonation wave stable propagation testing section which are connected in sequence, the diaphragm is arranged between the detonation wave initiation section and the detonation wave development propagation section, the high-energy igniter is arranged at one end of the detonation wave initiation section, the first air inlet is communicated with the inside of the detonation wave initiation section, at least two first pressure sensors are arranged on the detonation wave development propagation section at intervals and used for detecting the pressure in the detonation wave development propagation section, the plurality of second pressure sensors are arranged on the detonation wave stable propagation testing section at intervals and used for detecting the pressure in the detonation wave stable propagation testing section, the second air inlet is communicated with the inside of the detonation wave stable propagation testing section, and the lateral flame generating device is arranged on the detonation wave stable propagation testing section.
Further, the lateral flame generating device comprises a plurality of lateral flame igniters which are sequentially arranged on the detonation wave stable propagation testing section.
Further, a plurality of lateral flame igniters are sequentially and uniformly arranged on the detonation wave stable propagation testing section.
Further, the plurality of lateral flame igniters are disposed opposite the plurality of second pressure sensors.
Further, still include the spoiler, the spoiler sets up in the detonation wave priming segment.
Further, a plurality of second pressure sensors are uniformly arranged on the detonation wave stable propagation testing section at intervals.
Further, the number of the pressure sensors is two, and the pressure sensors are arranged at the tail end of the detonation wave development propagation section.
The method for constructing the detonation wave lateral expansion weak constraint boundary by adopting the device for constructing the detonation wave lateral expansion weak constraint boundary comprises the following steps:
s1: determining the average propagation speed and the propagation time scale of the detonation waves, comprising the following steps of:
s11: introducing detonating mixed gas into the first gas inlet, introducing test premixed gas into the second gas inlet, igniting by using a high-energy igniter to generate combustion waves in a detonation wave detonating section after the gas is filled in the cavity, breaking and transmitting the diaphragm to a detonation wave development and propagation section and a detonation wave stable propagation testing section by the combustion waves, and judging whether the combustion waves are detonation waves or not according to the combustion wave peak pressure and propagation speed measured by the first sensor;
s12: if the detonation wave is detected, measuring a high-frequency dynamic pressure signal of the detonation wave through the first pressure sensor, calculating the average propagation speed of the detonation wave according to a flight time method by utilizing the time interval of the pressure signal detected by the first pressure sensor, further calculating the propagation time scale of the detonation wave according to the total length of the detonation wave initiation section and the detonation wave development propagation section, and returning to S11 if the detonation wave is not detected;
s2: determining the lateral flame propagation speed and the maximum propagation time: calculating the propagation speed of lateral laminar flame generated by a lateral flame igniter according to the components, the temperature and the pressure of the gas fuel in the stable propagation test section, and calculating the maximum propagation time of the lateral flame according to the height of the narrow straight cavity;
s3: determining the ignition timing sequence of the high-energy igniter and the lateral flame igniter: igniting the lateral flame igniter firstly, and then igniting the high-energy igniter, wherein the maximum time interval of ignition of the lateral flame igniter and the high-energy igniter is the difference between the maximum propagation time of the lateral laminar flame obtained at S2 and the propagation time scale of the detonation wave obtained at S1, the minimum time interval is zero, and the maximum time interval and the minimum time interval form the ignition timing sequence reference range of the high-energy igniter and the lateral flame igniter;
s4, completing the construction of the detonation wave lateral expansion weak constraint boundary: under the determined test working condition, introducing detonation mixed gas from the first gas inlet, introducing test premixed combustible gas from the second gas inlet, sequentially controlling the high-energy igniter and the lateral flame igniter to ignite within the ignition timing sequence reference range obtained in S3, after the high-energy igniter ignites, entering a stable propagation testing section through a detonation wave development propagation section, and interacting with lateral flames generated by the lateral flame igniter in the stable propagation testing section to form a weak constraint boundary of lateral expansion of the detonation wave.
Further, the detonation mixed gas is ethylene pure oxygen mixed gas.
Further, varying the firing interval within a timing reference range can adjust the lateral laminar flame height.
Compared with the prior art, the invention has the remarkable advantages that:
considering that the complexity of the working environment of the continuous rotating detonation wave in the RDE and the diversity of the propagation modes enable the mechanism research of the detonation dynamics (particularly close to the detonation limit) to be very difficult, and are not beneficial to quantitative analysis of loss mechanisms influencing stable propagation of the detonation wave and universal critical criteria between losses of the detonation wave propagation limit, the lateral expansion and the like by researchers, the invention provides a device and a method for constructing a lateral expansion weak constraint boundary of the detonation wave, and lateral flame is adopted to actively construct the lateral expansion weak constraint boundary so as to be equivalent to the actual effect of lateral combustion in a rotating detonation engine on the detonation wave; in addition, the timing ignition scheme provided by the invention can effectively control the height of the combustible premixed gas, is convenient for researching the critical propagation condition of the detonation wave, reveals the universality instability and explosion extinguishing criterion of the detonation wave, and provides theoretical reference and technical guidance for the stable working process regulation and control of the rotary detonation engine.
Drawings
FIG. 1 is a schematic structural diagram of the device for constructing the lateral expansion weak confinement boundary of detonation waves according to the invention.
FIG. 2 is a flow chart of a method of constructing a detonation wave lateral expansion weak confinement boundary of the present invention.
Detailed Description
FIG. 1 is a cross-sectional view of the main body of the device of the present invention, wherein the experimental device comprises: the detonation wave propagation testing device comprises an air inlet 1, a detonation wave initiation section 2, a diaphragm 3, a pressure sensor 4, a pressure sensor 5, an air inlet 6, a detonation wave stable propagation testing section 7, a lateral flame igniter 8, a detonation wave development propagation section 9, a reticular spoiler 10 and a high-energy igniter 11. In addition, the device also comprises a digital delay signal generator, and a detonation wave initiation section 2, a detonation wave development propagation section 9 and a detonation wave stable propagation testing section 7 form a narrow and straight detonation cavity.
The air inlet 1 is used for injecting combustible premixed gas with high activity, because the environment of the experiment is a low-pressure environment, the premixed gas with high activity can improve the detonation success rate, and the detonation premixed gas used in the embodiment is ethylene pure oxygen. The air inlet 6 is used for injecting test premixed gas, the test gas and the initiation premixed gas are separated by the diaphragm 3, and in order to prevent the diaphragm 3 from being broken under the action of pressure difference, the pressure of the test premixed gas is similar to that of the initiation premixed gas. The detonation section 2, the propagation section 9 and the testing section 7 are all narrow straight channels with rectangular channel sections, the sizes of the channel sections are completely the same, and the detonation section, the propagation section and the testing section are assembled in a direct connection mode. The high-energy igniter 11 initiates the detonable premixed gas by direct ignition, and in the embodiment, the high-energy capacitor (discharge voltage is about 23kV) is used for ignition. The mesh-shaped spoiler 10 serves to accelerate the formation of the detonation wave. The pressure sensors 4 are two pressure sensors, are arranged at the tail end of the development propagation section 9, and judge whether detonation waves are formed or not according to the peak pressure and the propagation speed measured by the sensors; the pressure sensors 5 are a group of pressure sensors, and in the present embodiment, 6 sensors are selected as a group, and are arranged in an equidistant manner to obtain a high-frequency dynamic pressure signal of the detonation wave and indirectly measure the propagation velocity of the detonation wave. The lateral flame igniters 8 are a group of igniters and are arranged in the test section 7 in an equidistant mode, the distance between every two igniters is 0.1m, the number of the igniters is determined by the length of the test section, and the lateral flame igniters are used for generating lateral flames to construct a detonation wave lateral expansion weak constraint boundary. The digital delay signal generator is used for controlling the ignition timing of the high-energy igniter and the side flame igniter.
The method for constructing the detonation wave lateral expansion weak constraint boundary by adopting the device for constructing the detonation wave lateral expansion weak constraint boundary comprises the following steps:
s1: determining the average propagation speed and the propagation time scale of the detonation waves, comprising the following steps of:
s11: introducing detonation mixed gas into the first gas inlet 1, introducing test premixed gas into the second gas inlet 6, igniting by using a high-energy igniter 11 after the cavity is filled with the gas to generate combustion waves in the detonation wave detonation section 2, breaking and transmitting the diaphragm 3 to the detonation wave development and propagation section 9 and the detonation wave stable propagation testing section 7 by the combustion waves, and judging whether the combustion waves are detonation waves or not according to the combustion wave peak pressure and propagation speed measured by the first sensor 4;
s12: if the detonation wave is detected, a high-frequency dynamic pressure signal of the detonation wave is measured through the first pressure sensor 4, the Time interval of the pressure signal detected by the first pressure sensor 4 is utilized, the average propagation speed of the detonation wave is calculated according to a Time of Flight method (Time of Flight), then the propagation Time scale of the detonation wave is further calculated according to the total length of the detonation wave initiation section 2 and the detonation wave development propagation section 9, and if the detonation wave is not detected, the step returns to S11;
s2: determining the lateral flame propagation speed and the maximum propagation time: the flame generated by the lateral flame igniter 8 is in the initial development stage, so that the flame can be approximately considered to be developed to the periphery in a laminar flow mode, the propagation speed of the lateral laminar flame generated by the lateral flame igniter 8 is calculated through chemical reaction dynamics analysis software Cantera according to the components, the temperature and the pressure of the gas fuel in the stable propagation test section 7, and the maximum propagation time of the lateral flame is calculated through the height of the narrow straight cavity;
s3: determining the ignition timing of the high-energy igniter 11 and the lateral flame igniter 8: the lateral flame igniter 8 is ignited firstly, then the high-energy igniter 11 is ignited, the maximum time interval of ignition of the lateral flame igniter and the high-energy igniter is the difference value of the maximum propagation time of the lateral laminar flame obtained by S2 and the propagation time scale of the detonation wave obtained by S1, the minimum time interval is zero, and the maximum time interval and the minimum time interval form the ignition time sequence reference range of the high-energy igniter 11 and the lateral flame igniter 8;
s4, completing the construction of the detonation wave lateral expansion weak constraint boundary: under a determined test condition, introducing detonation mixed gas from the first gas inlet 1, introducing test premixed combustible gas from the second gas inlet 6, sequentially controlling the high-energy igniter 11 and the lateral flame igniter 8 to ignite within an ignition timing sequence reference range obtained by S3, after the high-energy igniter 11 ignites, entering a stable propagation testing section 7 through a detonation wave development propagation section 9, and interacting with lateral flames generated by the lateral flame igniter 8 in the stable propagation testing section 7 to form a weak constraint boundary of lateral expansion of the detonation wave.
Preferably, the detonation gas mixture is ethylene pure oxygen gas mixture.
Changing the firing interval within a timing reference range enables adjustment of the lateral laminar flame height. The lateral expansion weak constraint boundary can be formed in the reference time sequence range during ignition, the lateral expansion degree can be adjusted by adjusting the lateral flame height, the critical propagation condition of the detonation wave can be conveniently researched, the universality instability and explosion quenching criterion of the detonation wave can be disclosed, and theoretical reference and technical guidance are provided for the stable working process regulation and control of the rotary detonation engine.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. A device for constructing a detonation wave lateral expansion weak constraint boundary is characterized by comprising a narrow and straight detonation cavity, a first air inlet (1), a diaphragm (3), at least two first pressure sensors (4), a plurality of second pressure sensors (5), a second air inlet (6), a lateral flame generating device and a high-energy igniter (11),
the narrow and straight detonation cavity comprises a detonation wave initiation section (2), a detonation wave development propagation section (9) and a detonation wave stable propagation testing section (7) which are sequentially connected, the diaphragm (3) is arranged between the detonation wave initiation section (2) and the detonation wave development propagation section (9), the high-energy igniter (11) is arranged at one end of the detonation wave initiation section (2), the first air inlet (1) is communicated with the interior of the detonation wave initiation section (2), at least two first pressure sensors (4) are arranged on the detonation wave development propagation section (9) at intervals and used for detecting the pressure in the detonation wave development propagation section (9), and a plurality of second pressure sensors (5) are arranged on the detonation wave stable propagation testing section (7) at intervals and used for detecting the pressure in the detonation wave stable propagation testing section (7), and the second air inlet (6) is communicated with the interior of the detonation wave stable propagation testing section (7), the lateral flame generating device is arranged on the detonation wave stable propagation testing section (7).
2. The apparatus for constructing a detonation wave lateral expansion weak confinement boundary according to claim 1, wherein the lateral flame generating apparatus comprises a plurality of lateral flame igniters (8), and the plurality of lateral flame igniters (8) are sequentially arranged on the detonation wave stable propagation test section (7).
3. The apparatus for constructing a detonation wave lateral expansion weak confinement boundary of claim 2,
the lateral flame igniters (8) are sequentially and uniformly arranged on the detonation wave stable propagation testing section (7).
4. The apparatus for constructing a detonation wave lateral expansion weak confinement boundary of claim 3,
the plurality of lateral flame igniters (8) are disposed opposite the plurality of second pressure sensors (5).
5. The apparatus for constructing a detonation wave lateral expansion weak confinement boundary of claim 4,
the detonation device is characterized by further comprising a turbulence generator (10), wherein the turbulence generator (10) is arranged in the detonation wave initiation section (2).
6. The apparatus for constructing a detonation wave lateral expansion weak confinement boundary of claim 4,
the plurality of second pressure sensors (5) are uniformly arranged on the detonation wave stable propagation testing section (7) at intervals.
7. The device for constructing a detonation wave lateral expansion weak confinement boundary according to claim 4, characterized in that the number of the pressure sensors (4) is two, arranged at the end of the detonation wave development propagation section (9).
8. The method for constructing the detonation wave lateral expansion weak constraint boundary by using the device for constructing the detonation wave lateral expansion weak constraint boundary, which is characterized by comprising the following steps of:
s1: determining the average propagation speed and the propagation time scale of the detonation waves, comprising the following steps of:
s11: introducing detonation mixed gas into the first gas inlet (1), introducing test premixed gas into the second gas inlet (6), igniting by using a high-energy igniter (11) after the gas is filled in the cavity to generate combustion waves in the detonation wave detonation section (2), breaking and transmitting the diaphragm (3) to the detonation wave development propagation section (9) and the detonation wave stable propagation testing section (7) by the combustion waves, and judging whether the combustion waves are detonation waves or not according to the combustion wave peak pressure and the propagation speed measured by the first sensor (4);
s12: if the detonation wave is detected, measuring a high-frequency dynamic pressure signal of the detonation wave through the first pressure sensor (4), calculating the average propagation speed of the detonation wave according to a flight time method by utilizing the time interval of the pressure signal detected by the first pressure sensor (4), further calculating the propagation time scale of the detonation wave according to the total length of the detonation wave initiation section (2) and the detonation wave development propagation section (9), and returning to S11 if the detonation wave is not detected;
s2: determining the lateral flame propagation speed and the maximum propagation time: calculating the propagation speed of lateral laminar flame generated by a lateral flame igniter (8) according to the components, the temperature and the pressure of the gas fuel in the stable propagation test section (7), and calculating the maximum propagation time of the lateral flame through the height of the narrow straight cavity;
s3: determining the ignition timing of the high-energy igniter (11) and the lateral flame igniter (8): the lateral flame igniter (8) is ignited firstly, and then the high-energy igniter (11) is ignited, the maximum time interval of ignition of the lateral flame igniter and the high-energy igniter is the difference value of the maximum propagation time of the lateral laminar flame obtained by S2 and the propagation time scale of the detonation wave obtained by S1, the minimum time interval is zero, and the maximum time interval and the minimum time interval form the ignition timing sequence reference range of the high-energy igniter (11) and the lateral flame igniter (8);
s4, completing the construction of the detonation wave lateral expansion weak constraint boundary: under a determined test condition, introducing detonation gas mixture from the first gas inlet (1), introducing premixed combustible gas for test from the second gas inlet (6), sequentially controlling the high-energy igniter (11) and the lateral flame igniter (8) to ignite within an ignition time sequence reference range obtained by S3, after the high-energy igniter (11) ignites, entering a stable propagation test section (7) through a detonation wave development propagation section (9), and interacting with lateral flame generated by the lateral flame igniter (8) in the stable propagation test section (7) to form a weak constraint boundary of lateral expansion of the detonation wave.
9. The method for creating a detonation wave lateral expansion weak confinement boundary of claim 8, wherein the initiation mixture is an ethylene pure oxygen mixture.
10. The method for creating a detonation wave lateral expansion weak confinement boundary of claim 8,
changing the firing interval within a timing reference range enables adjustment of the lateral laminar flame height.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116337656A (en) * | 2023-05-26 | 2023-06-27 | 中国空气动力研究与发展中心超高速空气动力研究所 | Controllable gaseous detonation overpressure simulation device and experimental method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108256275A (en) * | 2018-03-12 | 2018-07-06 | 北京理工大学 | A kind of rotation detonation engine numerical simulation ignition and detonation method |
| CN110220942A (en) * | 2019-06-10 | 2019-09-10 | 上海交通大学 | A kind of detonation excitation system and method based on high-speed jet |
| CN111175435A (en) * | 2020-01-19 | 2020-05-19 | 上海交通大学 | Device and method for measuring propagation characteristics of detonation waves |
| CN111982760A (en) * | 2020-08-21 | 2020-11-24 | 北京理工大学 | Detonation wave loading experimental device |
| CN112082798A (en) * | 2020-09-14 | 2020-12-15 | 中国科学技术大学 | Visual test device for accurately testing unsteady detonation flame arrester effect of combustible gas |
| CN112459927A (en) * | 2020-10-23 | 2021-03-09 | 南京理工大学 | Y-shaped small-size bidirectional predetonation ignition tube |
-
2021
- 2021-12-28 CN CN202111631111.9A patent/CN114252269B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108256275A (en) * | 2018-03-12 | 2018-07-06 | 北京理工大学 | A kind of rotation detonation engine numerical simulation ignition and detonation method |
| CN110220942A (en) * | 2019-06-10 | 2019-09-10 | 上海交通大学 | A kind of detonation excitation system and method based on high-speed jet |
| CN111175435A (en) * | 2020-01-19 | 2020-05-19 | 上海交通大学 | Device and method for measuring propagation characteristics of detonation waves |
| CN111982760A (en) * | 2020-08-21 | 2020-11-24 | 北京理工大学 | Detonation wave loading experimental device |
| CN112082798A (en) * | 2020-09-14 | 2020-12-15 | 中国科学技术大学 | Visual test device for accurately testing unsteady detonation flame arrester effect of combustible gas |
| CN112459927A (en) * | 2020-10-23 | 2021-03-09 | 南京理工大学 | Y-shaped small-size bidirectional predetonation ignition tube |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116337656A (en) * | 2023-05-26 | 2023-06-27 | 中国空气动力研究与发展中心超高速空气动力研究所 | Controllable gaseous detonation overpressure simulation device and experimental method |
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