Testing device and testing method for combustion transient spectrum of powdered fuel

Abstract

The invention discloses a testing device and a testing method for a powder fuel combustion transient spectrum, and relates to the technical field of powder fuel spectrum testing. The testing device comprises a shock tube system, a multi-channel oscilloscope, a spectrometer, an I CCD detector, a pressure sensor and a multi-channel digital delay pulse generator; an optical signal generated by powder fuel high-temperature self-ignition is transmitted to an I CCD detector, the time distribution of the measured optical signal and the time distribution of the I CCD detector meet a one-to-one corresponding optical system, and transient spectral information of powder fuel high-temperature self-ignition luminescence at different time is obtained. The device can realize nanosecond-level time resolution, is suitable for a rapidly changing combustion process, can obtain high-quality transient spectrum data by combining a high-resolution spectrometer and an I CCD detector, realizes measurement of a high-resolution transient spectrum of high-temperature self-ignition combustion of the powder fuel, and can be widely applied to transient spectrum measurement of the powder fuel.

Description

Technical Field

[0001] This application relates to the technical field of powder fuel spectral testing, and specifically relates to a testing device and method for transient spectra of powder fuel combustion. Background Art

[0002] The rapid development of the aerospace field has significantly improved people's quality of life, and the power source of aircraft has also become an important research content of aerospace technology. In recent years, with the development of research fields such as Mars exploration and hypersonic aircraft, powder fuel ramjets have also developed rapidly. In the aviation field, the demand for high-speed aircraft has promoted the development of powder fuel ramjets. As a new concept type of ramjet, powder fuel ramjets provide a more ideal power device for high-speed aircraft. Whether the efficient ignition of powder fuel can be achieved quickly determines the application prospect of powder rocket engines. As a typical fuel for powder fuel ramjets, the research on the characteristics of powder fuel has important strategic foresight, and the research on the ignition and combustion characteristics of powder fuel is crucial.

[0003] Regarding the research and analysis of spectral data during the ignition and combustion of powder fuel, there are still the following pain points:

[0004] First: Traditional spectral measurement methods may not be able to achieve nanosecond-level time resolution. The ultra-high temperature self-ignition process of powder fuel often occurs in an extremely short time, and low time resolution will miss many key transient change information and cannot accurately capture important details during the combustion process.

[0005] Second: Some existing measurement systems may be too complex, requiring expensive equipment and complex operations, which not only increases the difficulty and cost of the experiment, but also may limit the repeatability and popularity of the experiment.

[0006] Third: The resolution of existing measurement systems is not high enough to accurately distinguish spectral characteristics of different wavelengths, thus affecting the accurate judgment of chemical species and reaction mechanisms generated during the fuel combustion process. Summary of the Invention

[0007] The main purpose of this application is to provide a testing device and method for transient spectra of powder fuel combustion, aiming to solve the technical problem that traditional methods cannot achieve high-resolution transient spectral measurement of high-temperature self-ignition combustion of powder fuel.

[0008] The technical solution adopted by this application is as follows:

[0009] A testing device for transient spectra of powder fuel combustion includes:

[0010] A shock tube system configured to form a shock wave inside the shock tube using a pressure difference to ignite the powder fuel pre-laid in the shock tube;

[0011] A multi-channel oscilloscope I connected to the shock tube system for receiving and displaying an electrical signal obtained by converting a pressure signal formed by the shock tube system through a piezoelectric transducer;

[0012] A spectrometer I connected to the shock tube system for receiving the optical signal of the powder fuel combustion;

[0013] A multi-channel oscilloscope II connected to the spectrometer I for receiving the optical signal selected and amplified by the spectrometer I;

[0014] An ICCD detector respectively connected to the shock tube system and the multi-channel oscilloscope II for photographing and recording the transient spectral image during the powder fuel combustion, where the ICCD detector includes a spectrometer II and a CCD camera;

[0015] A multi-channel digital delay pulse generator respectively connected to the multi-channel oscilloscope II and the ICCD detector for outputting a pulse trigger voltage signal to control the shutter opening of the ICCD detector after a set delay time.

[0016] Optionally, the shock tube system includes:

[0017] A shock tube body including a drive section, a diaphragm section, and an experimental section, with the diaphragm section located between the drive section and the experimental section;

[0018] A gas configuration and transmission system for introducing gas into the drive section and the experimental section to form high pressure in the drive section and low pressure in the experimental section;

[0019] A powder fuel distribution system arranged at one end of the experimental section far from the diaphragm section for feeding the powder fuel into the experimental section.

[0020] Optionally, four pressure sensors are alternately arranged on the outer wall of the shock tube body within the last one meter of the experimental section.

[0021] Optionally, the distances between the four pressure sensors from the diaphragm section to the end of the experimental section are 25.0 cm, 24.9 cm, and 18.0 cm respectively.

[0022] Optionally, the multi-channel digital delay pulse generator sets the shutter opening trigger voltage and delay time of the I CCD detector according to the corresponding relationship between the pressure sensor and the potential.

[0023] Optionally, an optical observation window is also provided on the shock tube body in the experimental section, and an optical fiber connected to the spectrometer I and the spectrometer II is provided on the optical observation window.

[0024] Optionally, the gas configuration and transmission system includes a gas mixing tank, a vacuum pressure gauge, a vacuum pump, an operation console, gas cylinders and gas pipelines. The operation console is used to operate the vacuum pump to evacuate the shock tube body, and mix the gas in the gas cylinders and then introduce it into the shock tube body through the gas mixing tank.

[0025] Optionally, the powder fuel cloth system includes:

[0026] A telescopic support rod, which is arranged on the end cover at the end of the experimental section;

[0027] A fuel carrier sheet, which is fixedly arranged on the telescopic support rod.

[0028] Optionally, the wavelength ranges of the spectrometer I and the spectrometer II are 200 - 1100 nm, and the highest resolution is 0.1 nm.

[0029] A test method for a test device based on the transient spectrum of the above-mentioned powder fuel combustion,

[0030] Utilize the pressure difference in the shock tube system to form a shock wave to ignite the powder fuel pre-laid in the shock tube system. Based on the pressure signal generated by the shock tube system, after piezoelectric conversion, an electrical signal is formed and reaches the multi-channel digital delay pulse generator from the multi-channel oscilloscope I. After a preset delay duration, a pulse trigger voltage is output to the I CCD detector for photographing. The optical signal generated by the high-temperature self-ignition of the powder fuel is transmitted to the I CCD detector. The time distribution of the measured optical signal and the time distribution of the detector satisfy a one-to-one correspondence optical relationship, and the transient spectral information of the high-temperature self-ignition luminescence of the powder fuel at different times is obtained.

[0031] Compared with the prior art, the beneficial effects of this application are:

[0032] A test device and test method for transient spectra of powder fuel combustion proposed in the embodiments of the present application, through a shock tube system, a multi-channel oscilloscope, a spectrometer, an ICCD detector, and a multi-channel digital delay pulse generator, realize transmitting the optical signal generated by the high-temperature self-ignition of powder fuel to the ICCD detector. The time distribution of the measured optical signal and the time distribution of the ICCD detector satisfy a one-to-one correspondence optical relationship, obtaining transient spectral information of the powder fuel's ultra-high-temperature self-ignition luminescence at different times, capable of achieving a time resolution of nanoseconds, applicable to rapidly changing combustion processes, and by combining a high-resolution spectrometer and an ICCD detector, high-quality transient spectral data can be obtained, thereby improving the understanding and analysis ability of the combustion process. At the same time, the system adopts a shock tube system, a multi-channel oscilloscope, a spectrometer, an ICCD detector, and a multi-channel digital delay pulse generator, and the system integration structure is simple, realizing the effective integration of multiple technologies, enhancing the operability and efficiency of the experiment. Brief Description of the Drawings

[0033] Figure 1 It is a schematic structural diagram of the test device for transient spectra of powder fuel combustion provided by the embodiments of the present application;

[0034] Figure 2 It is a schematic structural diagram of the shock tube system.

[0035] Explanation of the reference numerals in the drawings:

[0036] 1 - drive section, 2 - common membrane section, 3 - experimental section, 4 - pressure sensor, 5 - optical observation window, 6 - quartz fiber cable, 7 - spectrometer II, 8 - CCD camera, 9 - multi-channel digital delay pulse generator, 10 - spectrometer I, 11 - multi-channel oscilloscope I, 12 - multi-channel oscilloscope II, 13 - telescopic support rod, 14 - fuel carrier, 15 - gas cylinder, 16 - vacuum pump, 17 - gas mixing tank, 18 - operating platform. Detailed Embodiments

[0037] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative efforts belong to the scope of protection of the present application.

[0038] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present application are only used to explain the relative positional relationship and movement conditions between components in a specific posture (as shown in the drawings). If the specific posture changes, the directional indications will also change accordingly.

[0039] In this application, unless otherwise clearly defined and limited, terms such as "connection" and "fixation" shall be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0040] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of this application, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and / or" appearing throughout the text includes three parallel scenarios. Taking "A and / or B" as an example, it includes Scenario A, or Scenario B, or the scenario where both A and B are satisfied simultaneously. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of those of ordinary skill in the art to implement. When the combination of technical solutions results in contradictions or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0041] Refer to the attached Figure 1 Accordingly, the embodiment of this application provides a test device for the transient spectrum of powder fuel combustion, including a shock tube system, a multi-channel oscilloscope I 11, a multi-channel oscilloscope II 12, a spectrometer I 10, an ICCD detector, and a multi-channel digital delay pulse generator 9. The shock tube system can provide a combustion environment for the ultra-high temperature self-ignition of fuel. The ICCD detector is composed of a spectrometer II 7 and a CCD camera 8. The combination of the spectrometer and the ICCD detector can obtain high-quality and ultra-high-resolution transient spectrum data, transmit the optical signal generated by the high-temperature self-ignition of the powder fuel to the ICCD detector, and the time distribution of the measured optical signal and the time distribution of the detector satisfy a one-to-one correspondence optical relationship, so as to obtain the transient spectrum information of the powder fuel high-temperature self-ignition luminescence at different times.

[0042] Specifically:

[0043] Such as Figure 2As shown in the figure, the shock tube system includes a shock tube body, a gas configuration and transmission system, and a powder fuel feeding system. The entire shock tube body is composed of a stainless steel tube with an inner diameter of 100 mm and a wall thickness of 15 mm. The shock tube body consists of three parts, namely the driver section 1, the diaphragm section 2, and the test section 3. The test section 3 is also called the driven section 1. The driver section 1 is the high-pressure section during the experiment, and the test section 3 is the low-pressure section during the experiment. The length of the driver section 1 can be selected within the range of 2 - 6 m according to needs for use. The length of the test section 3 is 5 m, and the length of the diaphragm section 2 is 0.1 m.

[0044] The gas configuration and transmission system mainly includes a gas mixing tank 17, a vacuum pressure gauge, a vacuum pump 16, an operation console 18, gas cylinders 15, and various gas pipelines. There are multiple gas cylinders 15 storing hydrogen, oxygen, helium, and argon respectively. The mixing tube is used to mix the reaction gases. The vacuum pump 16 is used to evacuate the shock tube body. The operation console 18 controls the gas mixing and the evacuation of the shock tube body. The vacuum pressure gauge is connected to the gas pipeline to display the vacuum degree of the shock tube body.

[0045] The powder fuel feeding system refers to installing an adjustable telescopic support rod 13 at the end cover of the test section 3 of the shock tube body. The telescopic support rod 13 is provided with a fuel carrier 14 inside the test section 3. Before the experiment, the powder fuel is evenly spread on the fuel carrier 14. During the experiment, the position of the powder fuel can be controlled by adjusting the length of the telescopic support rod 13.

[0046] In the above, the shock tube is divided into three sections by two diaphragms: namely, the driver section 1 (high-pressure section), the common diaphragm section 2, and the test section 3 (low-pressure section). The driver section 1 and the test section 3 are respectively filled with high-pressure driving gas and low-pressure test gas. The high-pressure driving gas is helium and argon, and the low-pressure test gas is hydrogen and oxygen. When the pressure difference across the diaphragm is greater than the pressure that the diaphragm can withstand, the diaphragm ruptures instantaneously, and at the same time, an incident shock wave propagating towards the low-pressure section is generated. The shock wave is reflected at the end cap of the low-pressure section to form a reflected shock wave. After being compressed by the shock wave twice, the test gas reaches the ignition condition, and the fuel is ignited by the reflected shock wave. It should be noted that during the experiment, the fuel must be within the range around the radial position corresponding to the optical observation window 5 in the shock tube to facilitate the spectroscopic measurement. The optical observation window 5 is made of sapphire, which is shock-resistant and can clearly display the spectroscopic image. The powder particles will move forward under the action of the incident shock wave. Before the experiment, the trajectory of the fuel after the incident shock wave needs to be calculated according to the particle properties and experimental conditions, so as to determine the position where the powder particles are placed, so that the combustion position of the powder fuel is at the optical observation window during the experimental measurement. When the incident shock wave sweeps across the fuel, the fuel on the fuel carrier 14 is rapidly dispersed into the surrounding space under the action of the strong shock wave, and it experiences three stages of motion: acceleration, deceleration, and diffusion, and is evenly distributed in the surrounding gas. During the motion process, affected by the high-temperature region behind the shock wave, the fuel will absorb sufficient heat from the high-temperature incident shock wave and rapidly go through three states to reach the gaseous state and undergo gas-phase reactions.

[0047] Therefore, the process of igniting the powder fuel by the shock tube system can be summarized as follows:

[0048] Before the experiment, weigh the solid fuel as needed with an electronic balance, place it evenly on the fuel carrier 14, and then put the fuel carrier 14 into the test section 3 of the shock tube through the telescopic support rod 13. Use the vacuum pump 16 to evacuate the driver section 1 and the test section 3 respectively, and then fill the test section 3 with the test gas. After the test gas is filled, start filling the high-pressure section and the common diaphragm section 2 with the driving gas. When the specified pressure is reached, conduct the membrane rupture experiment. At the moment of membrane rupture, the high-pressure gas pushes the low-pressure gas to generate a shock wave. When the shock wave passes through the fuel carrier 14, the fuel on the thin sheet is lifted and dispersed. Subsequently, the shock wave is reflected back by the end face. When the reflected shock wave passes again, the powder fuel is instantaneously heated to a high temperature, and the fuel ignites and burns at this temperature.

[0049] In this embodiment, as Figure 1 and Figure 2As shown in the figure, there are four pressure sensors 4 installed in the experimental section 3 of the shock tube body. All four pressure sensors 4 are installed within the last one meter of the experimental section 3 of the shock tube, with spacings of 25.0 cm, 24.9 cm, and 18.0 cm respectively. The pressure sensors 4 are connected to piezoelectric converters. The model of the pressure sensor 4 is PCB113. This sensor has the advantages of short response time, high sensitivity, and wide application range. It can transmit the pressure signal to the piezoelectric converter within 1 μs when the shock wave arrives. Then, the piezoelectric converter converts the pressure signal into an electrical signal and displays it on the multi-channel oscilloscope I 11 through a signal transmission line. Among them, the multi-channel oscilloscope I 11 uses Tektron i x TDS5054. By combining the distances of the four pressure sensors 4 and the time intervals between the pressure signal jumps on the oscilloscope, the speed at which the shock wave reaches the optical observation window and the attenuation of the shock wave speed are obtained using the trend average extrapolation method. The magnitude of the attenuation value can reflect the quality of the shock wave.

[0050] Among the above, the spectrometer I 10 and the spectrometer II 7 can identify optical signals with a wavelength range of 200 - 1100 nm, and the highest resolution can reach 0.1 nm, achieving nanoscale optical signal capture. The spectrometer is internally equipped with a diffraction grating with a wavelength of 300 nm and 150 grooves per millimeter, which can cover a wavelength region of 440 nm. The function of the spectrometer is to perform spectral separation, arranging the light entering the slit according to the spectral wavelength. In this test device, a sapphire optical observation window 5 and a quartz fiber optic cable 6 are used to transmit the optical signal generated by the combustion of the powder fuel in the shock tube system to the spectrometer II 7, and it is photographed and recorded by the ICCD detector. At the same time, another quartz fiber optic cable 6 is set at the optical observation window 5 to transmit the optical signal of the fuel combustion during the experiment to the spectrometer I 10. After being selected by the spectrometer, the optical signal is amplified by a photomultiplier tube and transmitted to the multi-channel oscilloscope II 12 through a signal transmission line for display.

[0051] It should be noted that the quartz fiber optic cable 6 and the last pressure sensor 4P4 are on the same cross-section. The spectrometers I 10 and II 7 use Zo l ix Omni-λ320i.

[0052] When performing transient spectral measurement, the pressure is used as the trigger signal of the trigger source. The pressure sensor 4 is a sensing electronic component with fast response, connected to the multi-channel oscilloscope I 11. The multi-channel oscilloscope I 11 is connected to the multi-channel oscilloscope II 12. The multi-channel oscilloscope II 12 is connected to a multi-channel digital delay pulse generator. The multi-channel digital delay pulse generator is connected to the ICCD detector. The multi-channel digital delay pulse generator uses the DG535 type delay pulse generator produced by Stanford Research Systems, Inc., which is used to trigger the opening time of the CCD camera 8 in the ICCD detector.

[0053] Set the trigger voltage and delay time on the multi-channel digital delay pulse generator 9 according to the correspondence between the pressure sensor 4 and the potential. The specification of the pressure sensor P4 is 1 atm, which can be converted into an electrical signal of 756 mV. When the shock wave is incident through the pressure sensor P4, it will generate a corresponding pressure and convert it into a corresponding voltage. At this time, the voltage signal will pass through the multi-channel oscilloscope I 11 and the multi-channel oscilloscope II 12 and then transition to the multi-channel digital delay pulse generator 9. The multi-channel digital delay pulse generator 9 will set the converted electrical signal as the pressure signal for triggering. When the incident shock wave reaches the sensor P4 and the pressure value reaches the trigger pressure signal of the multi-channel digital delay pulse generator 9, the multi-channel digital delay pulse generator 9 will start timing from this moment. After the delay time, the CCD camera 8 will take a picture. The time for the shock wave to be reflected to the pressure sensor P4 is determined, that is, the time from the shock wave incident on the pressure sensor P4 to being reflected to the pressure sensor P4 is the delay time, thereby determining the shutter opening time of the CCD camera 8.

[0054] When the multi-channel digital delay pulse generator 9 reaches the trigger condition, it starts to work. After the set delay time, it outputs a pulse trigger voltage signal to the I CCD detector to control the I CCD shutter opening time; set the exposure gate width of the I CCD detector and output the gate width signal to the multi-channel oscilloscope to achieve the measurement of ultra-high temperature and high-resolution transient imaging spectroscopy.

[0055] Combined with the above content, a test device for the transient spectrum of powder fuel combustion provided by this application has a test method as follows:

[0056] Use the pressure difference in the shock tube system to form a shock wave to ignite the powder fuel pre-laid in the shock tube system. Based on the pressure signal generated by the shock tube system, after piezoelectric conversion, an electrical signal is formed. It reaches the multi-channel digital delay pulse generator 9 from the multi-channel oscilloscope I 11, and after a preset delay duration, a pulse trigger voltage is output to the I CCD detector for taking pictures. The optical signal generated by the high-temperature self-ignition of the powder fuel is transmitted to the I CCD detector. The time distribution of the measured optical signal and the time distribution of the detector satisfy a one-to-one correspondence optical relationship, and the transient spectrum information of the high-temperature self-ignition luminescence of the powder fuel at different times is obtained.

[0057] It can be seen that by combining a fiber optic spectrometer with an I CCD detector with gating function to measure the transient spectrum, nanosecond-level time resolution and spectral resolution can be achieved. Using a multi-channel oscilloscope, a spectrometer with a high-precision wide wavelength range, a high-resolution I CCD detector, a pressure sensor, and a multi-channel digital delay pulse generator, the optical signal generated by the high-temperature self-ignition of the powder fuel is transmitted to the I CCD detector respectively. Finally, the time-resolved spectrum of the ultra-high temperature self-ignition combustion of the powder fuel can be obtained, and the characteristic radiation spectrum signal generated during fuel combustion can be accurately grasped for its transient change over time.

[0058] In summary, a test device and a test method for transient spectra of powder fuel combustion provided by the embodiments of the present application have the following advantages:

[0059] This test device can achieve a time resolution of nanosecond level, is applicable to rapidly changing combustion processes, and by combining a high-resolution spectrometer and an ICCD detector, can obtain high-quality transient spectral data, thereby improving the understanding and analysis ability of the combustion process. At the same time, the system adopts a shock tube system, a multi-channel oscilloscope, a spectrometer, an ICCD detector, and a multi-channel digital delay pulse generator. The system integration structure is simple, realizing the effective integration of multiple technologies, enhancing the operability and efficiency of the experiment.

[0060] At the same time, this test method can be widely applied to different types of powder fuels and combustion conditions, has strong adaptability and flexibility, can monitor the change of optical signals during the high-temperature self-ignition process of powder fuels in real time, provides instant data feedback for researchers, helps to optimize fuel formulations and combustion conditions, helps to deeply study the combustion characteristics of powder fuels, promotes scientific research and technological development in fields such as aerospace and energy. Through one-to-one experimental designs, the complexity of the experiment is simplified, making data acquisition and analysis more efficient.

[0061] The above are only the preferred embodiments of the present application and are not intended to limit the present application. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A test device for transient spectra of powder fuel combustion, characterized in that, Comprising: A shock tube system configured to form a shock wave inside the shock tube using a pressure difference to ignite powder fuel pre-laid in the shock tube; A multi-channel oscilloscope I connected to the shock tube system for receiving and displaying an electrical signal obtained by converting a pressure signal formed by the shock tube system through a piezoelectric transducer; A spectrometer I connected to the shock tube system for receiving the optical signal of the powder fuel combustion; A multi-channel oscilloscope II connected to the spectrometer I for receiving the optical signal selected and amplified by the spectrometer I; An ICCD detector respectively connected to the shock tube system and the multi-channel oscilloscope II for photographically recording the transient spectral image during the powder fuel combustion, wherein the ICCD detector includes a spectrometer II and a CCD camera; A multi-channel digital delay pulse generator respectively connected to the multi-channel oscilloscope II and the ICCD detector for outputting a pulse trigger voltage signal to control the shutter opening of the ICCD detector after a set delay time.

2. The test device for transient spectra of powder fuel combustion according to claim 1, characterized in that The shock tube system includes: A shock tube body including a drive section, a common membrane section, and an experimental section, with the common membrane section located between the drive section and the experimental section; A gas configuration and transmission system for introducing gas into the drive section and the experimental section so that a high pressure is formed in the drive section and a low pressure is formed in the experimental section; A powder fuel feeding system provided at one end of the experimental section away from the common membrane section for feeding powder fuel into the experimental section.

3. The test device for transient spectrum of powder fuel combustion according to claim 2, characterized in that Four pressure sensors are alternately arranged on the outer wall of the shock tube body within the last one meter of the experimental section.

4. The test device for transient spectra of pulverized fuel combustion according to claim 3, wherein From the common membrane section to the end of the experimental section, the spacings of the four pressure sensors are 25.0 cm, 24.9 cm, and 18.0 cm respectively.

5. The test device for transient spectra of powder fuel combustion according to claim 3, characterized in that, The multi-channel digital delay pulse generator sets the shutter opening trigger voltage and delay time of the ICCD detector according to the corresponding relationship between the pressure sensor and the potential.

6. The test device for transient spectra of powder fuel combustion according to claim 2, wherein The shock tube body is also provided with an optical observation window in the experimental section, and the optical observation window is provided with optical fibers connected to the spectrometer I and the spectrometer II.

7. The test device for transient spectrum of powder fuel combustion according to claim 2, characterized in that, The gas configuration and transmission system includes a gas mixing tank, a vacuum pressure gauge, a vacuum pump, an operation console, a gas cylinder, and a gas pipeline. The operation console is used to operate the vacuum pump to evacuate the shock tube body and introduce the gas in the gas cylinder into the shock tube body after mixing through the gas mixing tank.

8. The test device for transient spectra of pulverized fuel combustion according to claim 2, characterized in that, The powder fuel feeding system includes: A telescopic support rod provided on the end cover of the experimental section; A fuel carrier fixed on the telescopic support rod.

9. The test device for transient spectrum of powder fuel combustion according to claim 1, characterized in that, The wavelength ranges of the spectrometer I and the spectrometer II are 200 - 1100 nm, and the highest resolution is 0.1 nm.

10. A test method for a test device of the transient spectrum of powder fuel combustion according to any one of claims 1 - 9, characterized in that Utilize the pressure difference within the shock tube system to form a shock wave to ignite the powder fuel pre-laid within the shock tube system. Based on the pressure signal generated by the shock tube system, after piezoelectric conversion, an electrical signal is formed and reaches the multi-channel oscilloscope I from which it arrives at the multi-channel digital delay pulse generator. After a preset delay duration, a pulse trigger voltage is output to the ICCD detector for photographing. The optical signal generated by the high-temperature self-ignition of the powder fuel is transmitted to the ICCD detector. The time distribution of the measured optical signal and the time distribution of the detector satisfy a one-to-one correspondence optical relationship, and transient spectral information of the high-temperature self-ignition luminescence of the powder fuel at different times is obtained.

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