CN112683541A - Visualization system for shock tube experimental device - Google Patents
Visualization system for shock tube experimental device Download PDFInfo
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- CN112683541A CN112683541A CN202011318068.6A CN202011318068A CN112683541A CN 112683541 A CN112683541 A CN 112683541A CN 202011318068 A CN202011318068 A CN 202011318068A CN 112683541 A CN112683541 A CN 112683541A
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- shock tube
- optical glass
- plane mirror
- tube body
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Abstract
The invention discloses a visualization system for a shock tube experimental device, which comprises a shock tube body, a visual display unit and a visual display unit, wherein the shock tube body is provided with a shock wave incidence end and an end wall; the plane mirror is provided with a first preset gap with the end wall and is obliquely arranged towards the end wall, and the central axis of the plane mirror and the axis of the shock tube body form a preset included angle; and the shooting device is arranged towards the plane mirror, a second preset gap is arranged between the shooting device and the plane mirror, and the shooting central line of the shooting device and the axis of the shock tube body are symmetrically arranged relative to the central axis of the plane mirror, so that the shooting light of the shooting device can penetrate through the optical glass after being reflected by the plane mirror, and the combustion of fuel in the shock tube body is shot and recorded. The whole fuel ignition process shot by the shooting device can be used for assisting in analyzing the ignition characteristics of the fuel, and accurate and reliable experimental data can be obtained.
Description
Technical Field
The invention relates to the technical field of internal combustion engine experiments, in particular to a visualization system for a shock tube experiment device.
Background
The shock tube is a test device which utilizes shock waves to compress and heat reactants to specified temperature and pressure instantly, and can reproduce high-temperature and high-pressure environment in an internal combustion engine. Because the heating time of the shock wave to the gas in the test area is far shorter than the ignition delay time of the common fuel, the ignition delay time of the fuel can be measured by adopting the shock wave tube.
In the existing shock tube experiment, the ignition delay time of fuel is usually calculated by measuring the pressure in an experimental area and an optical signal, but non-ideal factors have certain influence on the accuracy of an experimental result, so that the actual shock tube operation and theoretical prediction have larger deviation. For example, the existence of impurities causes a pre-ignition phenomenon in the shock tube; the gas viscosity effect causes the non-uniform velocity of the shock wave, thereby influencing the experimental result.
When the existing shock tube test device analyzes the ignition characteristics of fuel, the ignition delay time of the fuel is mainly calculated by collecting pressure signals and optical signals, and the main defects are as follows: 1. the ignition delay time of the fuel is only obtained, and the data is single, so that the comprehensive and deep understanding of the ignition process of the fuel is not facilitated; 2. only pressure signals and light signals are collected, and the influence of non-ideal factors in the process of fuel ignition cannot be accurately judged.
Disclosure of Invention
The invention aims to provide a visualization system for a shock tube experimental device, which is beneficial to understanding the actual ignition process in a tube and further reducing the influence caused by experimental errors.
The technical scheme adopted by the invention is as follows: a visualization system for a shock tube experimental apparatus, comprising:
the shock tube body is provided with a shock wave incidence end and an end wall which is arranged oppositely, the shock wave incidence end is used for incidence of shock waves, and the end wall is provided with optical glass;
the plane mirror is provided with a first preset gap with the end wall and is obliquely arranged towards the end wall, and the central axis of the plane mirror and the axis of the shock tube body form a preset included angle; and
the shooting device, the orientation the level crossing sets up, and with it predetermines the clearance to be provided with the second between the level crossing, the shooting device the shooting central line with the axis of shock tube body is about the central axis of level crossing is the symmetry and sets up, makes the shooting light of shooting device can see through optical glass after the reflection of level crossing to shoot the burning of the internal fuel of record shock tube body.
The invention has at least the following beneficial effects: the incident shock wave is emitted from the shock wave incident end and is propagated to the end wall, a reflected shock wave is further formed on the end wall, the reflected shock wave is propagated reversely, and then fuel in the shock wave tube body is ignited. Because this a visual system for shock tube experimental apparatus is provided with shooting device, level crossing and the optical glass who is convenient for observe the fuel burning condition in the shock tube body, and the central axis that shoots the central line of device and shock tube body is the symmetry setting about the central axis of level crossing for the shooting device can pass through the light reflection of level crossing to further see through the actual process of catching fire of the interior fuel of end wall optical glass shooting shock tube body. The whole fuel ignition process shot by the shooting device can be used for assisting in analyzing the ignition characteristics of the fuel, and accurate and reliable experimental data can be obtained.
Further, the preset included angle formed by the central axis of the plane mirror and the axis of the shock tube body is 45 degrees.
Furthermore, the end wall is provided with a convex shoulder structure, the concave of the convex shoulder structure is provided with a containing cavity communicated with the interior of the shock tube body, the end face of the convex shoulder structure is provided with a flange plate, the middle part of the flange plate is provided with a through hole, one end of the optical glass is provided with a flange, the flange of the optical glass is arranged in the containing cavity, one side part of the flange plate, facing the optical glass, extends into the containing cavity and acts on one side of the flange of the optical glass, and the other side of the flange of the optical glass is in sealing butt joint with the bottom of the containing cavity.
Further, the bottom of the accommodating cavity is provided with a groove, and a sealing ring is arranged in the groove.
Further, a gasket is arranged between the optical glass and the flange plate.
Further, the optical glass is fused silica glass.
Further, the fused silica glass is made of the material JGS 1.
Furthermore, both sides of the optical glass are plated with high antireflection films, and the ultraviolet light transmittance of the optical glass is greater than 90%.
Furthermore, the plane mirror is one-side plated with a high antireflection film, and the refractive index of ultraviolet light of the plane mirror is larger than 90%.
Further, the photographing apparatus includes an image intensifier and a high-speed camera.
Drawings
The invention is further illustrated with reference to the following figures and examples:
FIG. 1 is a schematic diagram of the overall assembly of a visualization system for a shock tube experimental apparatus according to an embodiment of the present invention;
fig. 2 is a schematic overall layout diagram of a visualization system for a shock tube experimental apparatus according to an embodiment of the present invention;
fig. 3 is a schematic longitudinal sectional structure of the shock tube body.
Detailed Description
Reference will now be made in detail to the present preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to like elements throughout.
In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as the upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and larger, smaller, larger, etc. are understood as excluding the number, and larger, smaller, inner, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.
Referring to fig. 1 to 3, an embodiment of the invention provides a visualization system for a shock tube experimental apparatus, which is mainly formed by overlapping a shock tube body 100, a plane mirror 200, and a shooting apparatus 300.
The shock tube body 100 has a shock wave incident end 110 and an end wall 120, the shock wave incident end 110 is used for emitting an incident shock wave 600, and the end wall 120 is hermetically provided with a transparent optical glass 400 so as to observe the combustion condition in the shock tube body 100. The fuel is filled in the shock tube body 100, the incident shock wave 600 propagates from the shock wave incident end 110 to the end wall 120, and after reaching the end wall 120, a reflected shock wave is further formed in the end wall 120, and the reflected shock wave propagates in the reverse direction, and then the fuel in the shock tube body 100 is ignited. The fuel is ignited because the incident shock wave 600 is compressed once, the reflected shock wave is compressed once, and after the compression twice, the temperature and the pressure in the shock tube body 100 reach the environment required by ignition, and then the fuel is ignited.
The plane mirror 200 is arranged close to the end wall 120. Specifically, a first preset gap is formed between the plane mirror 200 and the end wall 120, and the plane mirror is inclined toward the end wall 120, and a preset included angle is formed between the central axis of the plane mirror 200 and the axis of the shock tube body 100.
It should be understood that the first predetermined gap is set to keep the plane mirror 200 at a distance from the end wall 120, so as to ensure that the plane mirror 200 does not contact the end wall 120, and avoid damage to the plane mirror 200 due to the over-temperature of the shock tube body 100.
Meanwhile, the shooting device 300 is arranged towards the plane mirror 200, a second preset gap is formed between the shooting device 300 and the plane mirror 200, and the shooting central line of the shooting device 300 and the axis of the shock tube body 100 are symmetrically arranged about the central axis of the plane mirror 200, so that the shooting light of the shooting device 300 can penetrate through the optical glass 400 after being reflected by the plane mirror 200, and the combustion of fuel in the shock tube body 100 is shot and recorded.
The central axis of the plane mirror 200 here refers to an axis perpendicular to the plane mirror 200. The shooting center line of the shooting device 300 and the axis of the shock tube body 100 are symmetrically arranged about the central axis of the plane mirror 200, so that ultraviolet rays transmitted through the optical glass 400 can be smoothly emitted to the shooting lens of the shooting device 300 under the reflection of the plane mirror 200, and accurate shooting and recording are facilitated.
It should be understood that the second predetermined gap is set to ensure that the photographing lens of the photographing device 300 is kept at a proper distance from the plane mirror 200, so that the photographing device 300 can photograph conveniently.
In addition, the shot images of the ignition in the pipe are combined with the traditional pressure and optical signal curves for analysis, so that the ignition process of the fuel can be analyzed in a deep mode, and the method plays an important role in understanding the ignition process of the fuel and judging the experimental accuracy of the shock tube.
The system can shoot the whole ignition process of the fuel in the shock tube, so that the ignition process of the fuel can be observed visually, and in addition, the influence of non-ideal factors on the ignition process can be judged visually.
In this embodiment, the diameter of the plane mirror 200 is 150mm, the first predetermined gap between the plane mirror 200 and the end wall 120 of the shock tube body 100 is 1.5m, and the predetermined included angle between the central axis of the plane mirror 200 and the axis of the shock tube body 100 is 45 °.
When the preset included angle formed by the central axis of the plane mirror 200 and the axis of the shock tube body 100 is 45 degrees, the shooting device 300 is convenient to vertically install on the ground or on the table, and meanwhile, the shock tube body 100 is horizontally installed on the ground or on the table. Since the camera 300 has high light intensity requirements, for example, when the end wall 120 is broken, strong light directly enters the camera 300, which may cause the camera 300 to be damaged. In the technical scheme, the shooting device 300 and the shock tube body 100 are arranged in a staggered mode, so that the situation that light rays in the shock tube body 100 penetrate directly into a camera of the shooting device 300 is effectively avoided.
Specifically, the end wall 120 is formed with a convex shoulder structure, the concave of the convex shoulder structure is formed with a containing cavity 121 communicated with the inside of the shock tube body 100, the end face of the convex shoulder structure is provided with a flange 130, and the middle of the flange 130 is provided with a through hole 131, so that the visualization in the shock tube body 100 is facilitated. One end of the optical glass 400 is formed with a flange 410, the flange 410 of the optical glass 400 is arranged in the accommodating cavity 121, one side part of the flange 130 facing the optical glass 400 extends into the accommodating cavity 121 and acts on one side of the flange 410 of the optical glass 400, so that the other side of the flange 410 of the optical glass 400 is in sealing contact with the bottom of the accommodating cavity 121, and the fuel is ensured not to leak.
In order to ensure good sealing performance, the bottom of the accommodating cavity 121 is provided with a groove, the sealing ring 122 is arranged in the groove, and the other side of the flange 410 of the optical glass 400 is pressed on the sealing ring 122, so that good sealing performance is ensured. The sealing ring 122 is preferably an O-ring made of perfluoro ether rubber.
Further, a gasket 500 is disposed between the optical glass 400 and the flange 130. The gasket 500 is tightly attached to the optical glass 400, and the flange 130 acts on the gasket 500, so that the optical glass 400 is compressed, and the optical glass 400 is prevented from being damaged due to direct contact.
Preferably, the optical glass 400 is fused silica glass. The fused quartz glass is made of a material JGS1, high antireflection films are plated on both sides of the optical glass 400, and the ultraviolet light transmittance of the optical glass 400 is ensured to be more than 90%. Meanwhile, the plane mirror 200 is a single-sided high anti-reflection film plated, and the refractive index of ultraviolet light of the plane mirror 200 is larger than 90%.
It should be noted that the JGS1 material and the high anti-reflection film are both selected to enhance the transmittance of the ultraviolet light. In an actual experiment, ultraviolet light is weak, and the ultraviolet light emitted by the experiment can be recorded by a camera after being transmitted to a certain extent, so that the ultraviolet light is further attenuated, and therefore, the transmittance of the ultraviolet light needs to be ensured to be as large as possible, and the JGS1 and the high anti-reflection film can enhance the transmittance of the ultraviolet light. In addition, because the experiment needs to be carried out at high temperature, and the quartz glass is in a normal temperature environment in daily conditions, the glass is easy to crack when the quartz glass is heated and cooled, and the JGS1 material can effectively prevent the cracking caused by temperature difference.
In the present embodiment, the photographing device 300 includes an image intensifier 320 and a high-speed camera 310. Wherein the image intensifier 320 and the high-speed camera 310 are snap-fit mounted.
While the embodiments of the present invention have been described in detail with reference to the drawings, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (10)
1. A visualization system for a shock tube experimental apparatus, comprising:
the shock tube body is provided with a shock wave incidence end and an end wall which is arranged oppositely, the shock wave incidence end is used for incidence of shock waves, and the end wall is provided with optical glass;
the plane mirror is provided with a first preset gap with the end wall and is obliquely arranged towards the end wall, and the central axis of the plane mirror and the axis of the shock tube body form a preset included angle; and
the shooting device, the orientation the level crossing sets up, and with it predetermines the clearance to be provided with the second between the level crossing, the shooting device the shooting central line with the axis of shock tube body is about the central axis of level crossing is the symmetry and sets up, makes the shooting light of shooting device can see through optical glass after the reflection of level crossing to shoot the burning of the internal fuel of record shock tube body.
2. The visualization system for a shock tube experimental apparatus according to claim 1, wherein: the central axis of the plane mirror and the axis of the shock tube body form a preset included angle of 45 degrees.
3. The visualization system for a shock tube experimental apparatus according to claim 1 or 2, wherein: the end wall is provided with a convex shoulder structure, the concave part of the convex shoulder structure is provided with a containing cavity communicated with the interior of the shock tube body, the end face of the convex shoulder structure is provided with a flange plate, the middle part of the flange plate is provided with a through hole, one end of the optical glass is provided with a flange, the flange of the optical glass is arranged in the containing cavity, one side part of the flange plate, facing the optical glass, extends into the containing cavity and acts on one side of the flange of the optical glass, and the other side of the flange of the optical glass is in sealing butt joint with the bottom of the containing cavity.
4. The visualization system for a shock tube experimental apparatus according to claim 3, wherein: the bottom of the accommodating cavity is provided with a groove, and a sealing ring is arranged in the groove.
5. The visualization system for a shock tube experimental apparatus according to claim 3, wherein: and a gasket is arranged between the optical glass and the flange plate.
6. The visualization system for a shock tube experimental apparatus according to claim 1, 2, 4 or 5, wherein: the optical glass is fused silica glass.
7. The visualization system for a shock tube experimental apparatus according to claim 6, wherein: the fused silica glass is made of the material JGS 1.
8. The visualization system for a shock tube experimental apparatus according to claim 7, wherein: the double surfaces of the optical glass are both plated with high antireflection films, and the ultraviolet transmittance of the optical glass is more than 90%.
9. The visualization system for a shock tube experimental apparatus according to claim 1, 2, 4 or 5, wherein: the plane mirror is a mirror with a single surface plated with a high antireflection film, and the refractive index of ultraviolet light of the plane mirror is larger than 90%.
10. The visualization system for a shock tube experimental apparatus according to claim 1, 2, 4 or 5, wherein: the photographing apparatus includes an image intensifier and a high-speed camera.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011318068.6A CN112683541B (en) | 2020-11-23 | 2020-11-23 | Visualization system for shock tube experimental device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011318068.6A CN112683541B (en) | 2020-11-23 | 2020-11-23 | Visualization system for shock tube experimental device |
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| CN112683541A true CN112683541A (en) | 2021-04-20 |
| CN112683541B CN112683541B (en) | 2023-02-28 |
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| CN202011318068.6A Active CN112683541B (en) | 2020-11-23 | 2020-11-23 | Visualization system for shock tube experimental device |
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Citations (10)
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|---|---|---|---|---|
| FR2310472A1 (en) * | 1975-05-05 | 1976-12-03 | Beekhuis William | IC engine fuel feed system - has fuel introduced through orifices to shock wave tubes with obturators blocking inlet ports |
| US5594196A (en) * | 1995-04-20 | 1997-01-14 | Ireco, Inc. | Shock tube surface connector |
| WO2001050107A1 (en) * | 2000-01-06 | 2001-07-12 | The Johns Hopkins University | Damped paddle wheel for plasma chamber shock tube |
| US20130042665A1 (en) * | 2011-08-15 | 2013-02-21 | Ora, Inc. | Shock Tube Apparatus for Blast Wave Simulation |
| CN202946738U (en) * | 2012-11-30 | 2013-05-22 | 中国航天空气动力技术研究院 | Quick pressure relieving device and piston type shock tube without film |
| CN104990667A (en) * | 2015-06-23 | 2015-10-21 | 西安近代化学研究所 | Shock wave pressure test installation structure for shock tube calibration |
| CN105158090A (en) * | 2015-07-23 | 2015-12-16 | 北京理工大学 | System and method for measuring blast impact resistance of material |
| CN109029551A (en) * | 2018-06-05 | 2018-12-18 | 武汉理工大学 | The intracavitary ignition process camera system of shock tube |
| CN109975473A (en) * | 2019-03-20 | 2019-07-05 | 浙江大学 | A kind of electronic needle of shock tube that can be used under lower pressure punctures film device |
| CN111366263A (en) * | 2020-01-21 | 2020-07-03 | 中国科学院力学研究所 | High-temperature calibration equipment and method for TDLAS temperature measurement based on shock tube |
-
2020
- 2020-11-23 CN CN202011318068.6A patent/CN112683541B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2310472A1 (en) * | 1975-05-05 | 1976-12-03 | Beekhuis William | IC engine fuel feed system - has fuel introduced through orifices to shock wave tubes with obturators blocking inlet ports |
| US5594196A (en) * | 1995-04-20 | 1997-01-14 | Ireco, Inc. | Shock tube surface connector |
| WO2001050107A1 (en) * | 2000-01-06 | 2001-07-12 | The Johns Hopkins University | Damped paddle wheel for plasma chamber shock tube |
| US20130042665A1 (en) * | 2011-08-15 | 2013-02-21 | Ora, Inc. | Shock Tube Apparatus for Blast Wave Simulation |
| CN202946738U (en) * | 2012-11-30 | 2013-05-22 | 中国航天空气动力技术研究院 | Quick pressure relieving device and piston type shock tube without film |
| CN104990667A (en) * | 2015-06-23 | 2015-10-21 | 西安近代化学研究所 | Shock wave pressure test installation structure for shock tube calibration |
| CN105158090A (en) * | 2015-07-23 | 2015-12-16 | 北京理工大学 | System and method for measuring blast impact resistance of material |
| CN109029551A (en) * | 2018-06-05 | 2018-12-18 | 武汉理工大学 | The intracavitary ignition process camera system of shock tube |
| CN109975473A (en) * | 2019-03-20 | 2019-07-05 | 浙江大学 | A kind of electronic needle of shock tube that can be used under lower pressure punctures film device |
| CN111366263A (en) * | 2020-01-21 | 2020-07-03 | 中国科学院力学研究所 | High-temperature calibration equipment and method for TDLAS temperature measurement based on shock tube |
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| Title |
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| 张尊华等: "激波管的调试与甲烷着火延迟时间的测量", 《华中科技大学学报（自然科学版）》 * |
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| CN112683541B (en) | 2023-02-28 |
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