High-energy combustion quasi-static simulation device under complex working conditions

Abstract

This invention belongs to the fields of physical field modeling and electrical control, and relates to multi-pipe injection technology. Specifically, it is a quasi-static simulation device for high-energy combustion under complex working conditions, including a terminal controller, a main base, a laser controller, a laser, and a photodetector. The main base has a multi-channel flame nozzle ring, which includes an air inlet. The air inlet is equipped with a pressure regulating valve and a flow rate regulating valve, which are connected to an air source. The pressure regulating valve and the flow rate regulating valve are connected to the terminal controller. The laser and photodetector are arranged on both sides of the main base. The emitted laser light is controlled by the laser controller, and the photodetector outputs information to the terminal controller for centralized control of the entire experimental testing process. This invention has a simple structure and is easy to operate. It can construct a miniaturized complex environment in limited spaces such as laboratories that meets the needs of multiple scenarios and has controllable parameters, providing experimental objects with high confidence for related tests.

Description

Technical Field

[0001] This invention belongs to the fields of physical field modeling and electrical control, and relates to multi-pipeline injection technology, specifically a quasi-static simulation device for high-energy combustion under complex working conditions. Background Technology

[0002] As a core component of energy and power devices such as high-temperature boilers, gas turbines, and aero engines, the combustion chamber undertakes the crucial functions of energy conversion and power generation.

[0003] In the field of aero-engines, combustor exit temperature is a key parameter characterizing combustion efficiency and stability, directly affecting the overall performance evaluation, condition monitoring, and maintenance decisions of aero-engines. Taking improving the thrust-to-weight ratio of an aero-engine as an example, one of the main approaches is to increase the temperature rise and exit temperature of the combustor. Studies have shown that, all other things being equal, for every 100°C increase in combustor exit temperature, the thrust of an aero-engine can increase by more than 10%, thus significantly enhancing the maneuverability of the aircraft. Currently, the local high temperature inside the combustor of advanced aero-engines has exceeded 2000°C, and with the continued pursuit of higher thrust-to-weight ratios, the exit temperature will further rise, making the working environment of downstream turbine components increasingly harsh.

[0004] Under extremely complex combustion conditions, the temperature field often exhibits non-uniformity, such as dynamic fluctuations, uneven circumferential distribution, and localized radial shifts. This non-uniformity severely affects the thermodynamic environment of turbine guide vanes and rotor blades, not only restricting the improvement of key performance indicators such as thrust-to-weight ratio, but also becoming a significant bottleneck for the independent development of aero-engine technology.

[0005] Although various temperature sensors suitable for different temperature ranges and response requirements have been developed, existing technologies still generally face challenges such as response lag, limited accuracy, and limited dimensionality in the extreme combustion environment of aero-engines. Furthermore, in actual testing environments, intense vibrations, electromagnetic interference, and complex conditions such as high temperature and high pressure significantly affect the reliability of measurement results, leading to decreased data confidence. Meanwhile, traditional methods often rely on costly testing equipment and frequent calibration and maintenance, consuming significant human and material resources and severely limiting the efficiency and coverage of simultaneous multi-parameter detection. This makes it difficult to achieve accurate, comprehensive sensing of the entire area under the coupling effects of multiple physical fields, such as the combustion chamber outlet, thus hindering further breakthroughs in aero-engine technology.

[0006] Based on the above analysis, in order to address the limitations of existing measurement technologies and overcome the constraints of real testing environments, it is urgent to develop an experimental simulation device that can highly reproduce and simulate the complex multi-physics environment at the outlet of an aero-engine. Summary of the Invention

[0007] To address the limitations of existing measurement technologies and overcome the constraints of real-world testing environments, this invention provides a quasi-static simulation device for high-energy combustion under complex operating conditions. This simulation device features a simple structure, convenient operation, good economic efficiency, and high testing efficiency, and can reconstruct complex combustion environments with multi-physics coupling effects under laboratory conditions.

[0008] This invention is achieved using the following technical solution: a high-energy combustion quasi-static simulation device under complex working conditions, comprising a terminal controller, a main base, a laser controller, a laser, and a photodetector; the main base is provided with a multi-channel flame nozzle ring, which includes an air inlet, a pressure regulating valve and a flow rate regulating valve at the air inlet, the air inlet being connected to a gas source, and the multi-channel flame nozzle ring having multiple gas sources; the pressure regulating valve and the flow rate regulating valve are connected to the terminal controller; the laser and the photodetector are arranged on both sides of the main base, the emitted laser light from the laser is controlled by the laser controller, and the photodetector outputs information to the terminal controller; the terminal controller includes a multi-parameter control module and a detector control and processing module, the multi-parameter control module including a pressure control module, a flow rate control module, and a gas composition control module; the detector control and processing module includes a data processing module, a data storage module, and a photodetector control module. The multi-parameter control module first controls multiple gas sources to mix proportionally, and then the mixed gas is input into a multi-channel flame nozzle ring. The pressure control module and the flow rate control module are used to change the pressure and gas flow rate inside the multi-channel flame nozzle ring, thereby simulating the high-energy combustion temperature field under complex working conditions. The laser and photodetector form an optical path detection, and the laser controller controls the laser to emit laser light. After the laser passes through the high-energy combustion temperature field under complex working conditions, it is converted into an electrical signal by the photodetector and input to the terminal controller. After data storage, the data processing module retrieves important parameter information such as temperature, pressure and gas flow rate, thus completing the detection of the high-energy combustion temperature field under complex working conditions.

[0009] The aforementioned high-energy combustion quasi-static simulation device under complex operating conditions has a main base connected at its lower end to a rotating disc gear mounted on a support. A stepper motor is connected to the disc gear via a transmission, and the stepper motor is fixedly connected to its drive module. A multi-channel flame nozzle ring is mounted on the upper end of the main base. Multiple flame nozzles are evenly distributed around the outer circumference of the ring, coordinating with the stepper motor to drive the rotation of the main base. Different parameter ratios are adjusted through a multi-parameter control module to achieve different combustion conditions for the multiple flames.

[0010] The aforementioned high-energy combustion quasi-static simulation device under complex working conditions has a main base equipped with porous heat dissipation channels.

[0011] The aforementioned high-energy combustion quasi-static simulation device under complex working conditions uses a ZYNQ main controller as its terminal controller.

[0012] The aforementioned quasi-static simulation device for high-energy combustion under complex operating conditions employs the following simulation method: First, a high-energy combustion temperature field is provided by setting different gas compositions; then, different pressures and gas flow rates are set to simulate the high-energy combustion temperature field under complex operating conditions; finally, a laser controller controls a laser to emit laser light, which, after passing through the high-energy combustion temperature field under complex operating conditions, is converted into an electrical signal by a photodetector and input to a terminal controller. After data storage, the data processing module retrieves important parameters such as temperature, pressure, and gas flow rate, completing the detection of the high-energy combustion temperature field under complex operating conditions. This invention achieves the simulation of high-energy combustion temperature fields under different operating conditions by adjusting various parameters in the high-energy combustion temperature field, including gas composition, pressure, and gas flow rate, through a terminal controller. Combining the above simulation methods, and based on actual needs such as the outlet of an aero-engine combustor, the gas composition, pressure, and gas flow rate in the simulation environment are adjusted to form a complex high-energy combustion temperature field that meets experimental requirements. Stable control methods for the complex high-energy combustion temperature field are explored, and a simulation environment under the influence of multiple parameters is constructed and optimized to simulate the temperature at the outlet of the actual aero-engine combustor, thereby further ensuring the stable operation of the aero-engine.

[0013] The present invention provides a quasi-static simulation device for high-energy combustion under complex working conditions, the advantages of which are mainly reflected in the following aspects:

[0014] 1. This simulation device can construct high-energy combustion temperature fields under various complex working conditions in a laboratory environment, forming a multi-parameter composite environment of a certain scale, providing experimental objects with high confidence for testing complex environments affected by multiple factors.

[0015] 2. This simulation device adopts a centralized terminal control method, which can flexibly and conveniently simulate the high-energy combustion temperature field under different complex working conditions, and supports targeted adjustment of parameters.

[0016] 3. This simulation device establishes a quasi-static high-energy combustion temperature field under laboratory conditions. By comprehensively controlling various parameters such as gas composition, pressure, and gas flow rate, it provides a hardware foundation for detecting high-energy combustion temperature fields under different complex working conditions in the laboratory, significantly reducing testing costs and improving the efficiency of technical research. Compared with existing testing technologies, this invention is not limited to theoretical calculations but is closer to practical application scenarios.

[0017] 4. This simulation device is reasonably designed, has a simple structure, and is easy to operate. It can build a miniaturized complex environment system that meets the needs of multiple scenarios and has controllable parameters in limited spaces such as laboratories, providing a reliable research object for related experiments and possessing high practical application value. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the terminal controller structure in the simulation device of the present invention.

[0019] Figure 2 This is a schematic diagram of the overall simulation device of the present invention.

[0020] Figure 3 This is a flowchart of the simulation method of the simulation device of the present invention.

[0021] In the diagram: 1-Terminal controller, 2-Main base, 3-Disc gear, 4-Stepper motor, 5-Drive module, 6-Multi-channel flame nozzle ring, 7-First air inlet, 8-Second air inlet, 9-Laser controller, 10-Conical laser, 11-Photodetector. Detailed Implementation

[0022] To make the above-mentioned objects, features and advantages of the present invention clearer and easier to understand, preferred embodiments are selected below and described in detail with reference to the accompanying drawings.

[0023] A quasi-static simulation device for high-energy combustion under complex operating conditions, such as Figure 2 As shown, the system includes a terminal controller 1, a main base 2, a laser controller 9, a conical laser 10, and a photodetector 11. The main base 2 has a multi-channel flame nozzle ring 6, which includes a first air inlet 7 and a second air inlet 8. Both the first and second air inlets 7 and 8 are equipped with pressure regulating valves and flow rate regulating valves. The first and second air inlets 7 and 8 are connected to an air source. The pressure regulating valves and flow rate regulating valves are connected to the terminal controller 1. The conical laser 10 and the photodetector 11 are arranged on both sides of the main base 2. The emitted laser light from the conical laser 10 is controlled by the laser controller 9. The photodetector 11 outputs information to the terminal controller 1, such as... Figure 1 As shown, the terminal controller 1 includes a multi-parameter control module and a detector control and processing module. The multi-parameter control module includes a pressure control module, a flow rate control module, and a gas component control module. The detector control and processing module includes a data processing module, a data storage module, and a photoelectric detector control module. The simulation device is equipped with multiple independent gas sources, each stored in a dedicated gas cylinder. These cylinders are connected to a gas mixer via hoses. The gas mixer is connected to the terminal controller 1. The gas component control module controls the gas mixer to adjust the mixing ratio, generating a proportionally mixed gas. The terminal controller 1 is responsible for adjusting the proportions of each gas component to achieve precise mixing of multiple gases. The mixed gas is then delivered to the multi-channel flame nozzle ring 6. The terminal controller 1 is also connected to a host computer and uses a ZYNQ main controller.

[0024] The aforementioned quasi-static simulation device for high-energy combustion under complex operating conditions features a simple structure, convenient operation, and advantages such as low coupling, high portability, and high scalability. It can achieve quasi-static simulation of the high-energy combustion temperature field under complex operating conditions with the synergistic effect of multiple parameters. This simulation device provides a low-cost, high-efficiency environmental simulation approach for temperature detection in key components such as high-temperature boilers, gas turbines, and aero-engine combustion chamber outlets, and also provides reliable technical support and environmental foundation for temperature parameter measurement under such complex operating conditions.

[0025] The operator communicates with the terminal controller 1 via a host computer to manipulate the multi-parameter control module, adjusting pressure, gas flow rate, and gas composition to simulate high-energy combustion temperature fields under various complex operating conditions. Simultaneously, the laser controller 9 controls the tunable wavelength of the conical laser 10, achieving high-precision detection of the high-energy combustion temperature field. The terminal controller 1 interacts with the photodetector 11 to buffer and process the data collected by the photodetector 11 in the high-energy combustion temperature field. Based on this process, an integrated "environment-detection" optimization model suitable for real-world scenarios can be established.

[0026] In specific implementation, in this high-energy combustion quasi-static simulation device under complex working conditions, the lower end of the main base 2 is connected to a disc gear 3 rotatably mounted on a support. A stepper motor 4 is connected to the disc gear 3 via a transmission connection, enabling precise control of the disc gear 3's rotational motion. The stepper motor 4 is fixedly connected to its drive module 5. The upper end of the main base 2 is used to install a multi-channel flame nozzle ring 6, with the multi-channel flame nozzles evenly distributed around the outer circumference of the ring. The stepper motor 4 drives the rotational motion of the main base 2, and through the aforementioned multi-parameter control module, different combustion conditions of the multi-channel flames are achieved by adjusting different parameter ratios. A cone laser 10, a laser controller 9, and a terminal controller 1 are fixed on the platform to the right of the main base 2, while a photodetector 11 is fixed on the platform to the left of the main base 2. The cone laser 10 and the photodetector 11 form an optical path detection system; the laser emitted by the cone laser 10 is set by the laser controller 9. The simulation device is equipped with pre-installed wiring channels to fix and arrange the control circuits of the drive module 5, laser controller 9, and terminal controller 1, reducing interference. Through a multi-parameter control module, the gas composition, internal pressure, and gas flow rate of the simulation device can be changed to achieve high-energy combustion temperature field detection under various complex operating conditions. It should be noted that this invention is mainly used for simulating high-energy combustion temperature fields under quasi-static complex operating conditions and supports multi-parameter inversion analysis. The terminal controller 1 can adjust key parameters such as pressure, gas flow rate, and gas composition, thereby achieving effective detection of the high-energy combustion temperature field.

[0027] In the device of this invention, the testing method used is tunable semiconductor laser molecular absorption spectroscopy (TDLAS). TDLAS is a technique that calculates parameters such as gas composition, temperature and pressure by measuring specific absorption lines of a gas. Its working principle is to utilize the tunability of a semiconductor laser to modulate the output wavelength of the laser so that the output wavelength scans the absorption peak of the gas molecules being measured.

[0028] A quantitative relationship between light intensity attenuation and gas composition is established based on the Lambert-Beer law. To achieve continuous detection, a periodic sawtooth wave signal is typically applied to the laser for frequency tuning, resulting in a synchronous linear scanning characteristic in the output spectrum. The laser intensity exhibits a linear dependence on the operating current, causing the intensity to change synchronously with the tuning signal during the scanning process. The integral absorbance of the characteristic gas phase molecular absorption lines after the laser passes through the measured flow field is expressed as:

[0029] (1)

[0030] If the flow field to be measured is a uniform flow field, formula (1) can be simplified to formula (2):

[0031] (2)

[0032] in, For integral absorption rate, For the intensity of emitted light, For the incident light intensity, This is the line shape function of gas absorption spectral lines. To measure the integral absorbance, (atm) represents gas pressure. This represents the molar concentration of the absorbent component. For spectral line intensity, (cm) represents the absorption optical path. As can be seen from equation (2), the absorption integral absorbance obtained by direct absorption spectroscopy is a function of the temperature and partial pressure of the absorbing components in the flow field to be measured. Therefore, the information of each parameter of the field to be measured can be calculated by measuring the absorption integral absorbance of gas phase molecules.

[0033] There are generally two methods for direct absorption spectroscopy to measure the temperature of the flow field under test. One method is to invert the temperature distribution of the flow field under test by using the characteristics of Doppler broadening that varies with temperature. This method only requires one absorption line of gas phase molecules, but it suffers from the problem of being affected by the line shape fitting, resulting in a large measurement error. The other method is the double-line thermometry method. Since the spectral intensity of the gas phase molecule absorption line is a function of temperature, its intensity changes with temperature. Therefore, the temperature can be inverted by using the ratio of the spectral intensities of the two absorption lines, which is a monotonic function of temperature.

[0034] To understand the TDLAS technology used in the device of this invention, a detailed explanation of the multi-parameter acquisition method of high-energy combustion temperature field under complex working conditions based on TDLAS technology is given, taking the dual-line temperature measurement method as an example.

[0035] In direct absorption spectroscopy, the ratio of the integral absorbance of two absorption lines can be calculated using the spectral line intensity formula. The relationship between the intensity ratio of spectral lines and temperature is obtained as follows:

[0036] (3)

[0037] in, , These represent the integral absorbance of the two absorption lines, respectively. , These represent the spectral intensities of the two absorption lines, respectively. , These are two absorption spectra at the reference temperature. The intensity of the spectral lines below, in the HITRAN database, =296K, It is Planck's constant. It's the speed of light. , These represent the low-level transition energies of the two absorption lines. It is Boltzmann's constant. The temperature to be measured is .

[0038] In this invention example, by adjusting the operating temperature and current of the laser controller 9, the laser emitted from the cone laser 10 reaches the selected absorption spectral line. After the laser passes through the high-energy combustion temperature field to be measured, the signal is received by the photodetector 11, and after processing by the data processing module, two absorption integral absorbances are obtained. The ratio of the absorption integral absorbances of the two absorption spectral lines is a single-valued function of temperature. Therefore, the temperature of the high-energy combustion temperature field is calculated based on the measured absorption integral absorbances of the two absorption spectral lines.

[0039] (4)

[0040] In the formula, The temperature to be measured is .

[0041] It can be observed that the ratio of the integral absorbance of the two absorption lines is a single-valued function of temperature. By measuring the integral absorbance of the two absorption lines, the temperature of the flow field to be measured can be calculated. Furthermore, under the condition that the pressure in the flow field to be measured is known or measurable, the gas composition of the gas phase molecules in the flow field to be measured can also be calculated, as shown in equation (5).

[0042] (5)

[0043] Once the pressure of the high-energy combustion field is known or measured using other methods, it becomes possible to acquire information on a variety of parameters in a complex environment.

[0044] Furthermore, to facilitate understanding of the simulation method provided in this embodiment, the present invention provides a flowchart of the high-energy combustion temperature field simulation method under complex operating conditions, see [link to flowchart]. Figure 3 .

[0045] The simulation method mainly includes the following steps:

[0046] First, based on the environmental requirements of the high-energy combustion temperature field under complex working conditions, the parameters such as gas composition, pressure and gas flow rate are initialized, and it is determined whether multiple parameters need to be adjusted for the simulation scenario. By adjusting the parameters, the simulation of various working conditions can be achieved.

[0047] Secondly, determine whether the current environment meets the detection requirements: if so, perform data acquisition; if not, return to the previous step and continue adjusting until the operating conditions meet the detection requirements, thereby providing technical support for the detection of high-energy combustion temperature fields.

[0048] Finally, the host computer controls whether to perform multiple simulation tests; if not, the process ends.

[0049] In summary, this invention enables flexible simulation of key parameters such as temperature, pressure, and gas flow rate through a simulation device. Combined with the aforementioned control methods, it can adapt to the adjustment requirements of various parameters under different complex working conditions, effectively supporting the construction and testing of various working environments.

[0050] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. These modifications or substitutions do not cause the corresponding technical solutions to depart from the spirit and scope of the present invention, and should all be included within the protection scope of the present invention. Therefore, the protection scope of the present invention should be determined by the scope of the claims.

Claims

1. A high-energy combustion quasi-static simulation device under complex working conditions, characterized in that: The system includes a terminal controller (1), a main base (2), a laser controller (9), a laser, and a photodetector (11). The main base (2) is equipped with a multi-channel flame nozzle ring (6), which includes an air inlet. The air inlet is equipped with a pressure regulating valve and a flow rate regulating valve. The air inlet is connected to a gas source. The multi-channel flame nozzle ring (6) has multiple gas sources. The pressure regulating valve and the flow rate regulating valve are connected to the terminal controller (1). The laser and the photodetector (11) are arranged on both sides of the main base (2). The laser emitted by the laser is controlled by the laser controller (9). The photodetector (11) outputs information to the terminal controller (1). The terminal controller (1) is equipped with a multi-parameter control module and a detector control and processing module. The multi-parameter control module includes a pressure control module, a flow rate control module, and a gas composition control module. The detector control and processing module includes a data processing module, a data storage module, and a photodetector control module.

2. The high-energy combustion quasi-static simulation device under complex working conditions according to claim 1, characterized in that: The lower end of the main base (2) is connected to the disc gear (3) which is rotatably mounted on the bracket. The stepper motor (4) is connected to the disc gear (3) for transmission. The stepper motor (4) is fixedly connected to its drive module (5). The multi-channel flame nozzle ring (6) is mounted on the upper end of the main base (2).

3. The high-energy combustion quasi-static simulation device under complex working conditions according to claim 1 or 2, characterized in that: The main base (2) is equipped with a multi-hole heat dissipation channel.

4. The high-energy combustion quasi-static simulation device under complex working conditions according to claim 1 or 2, characterized in that: The terminal controller (1) adopts the ZYNQ main controller.

5. A quasi-static simulation device for high-energy combustion under complex operating conditions according to claim 1 or 2, characterized in that: The simulation method of the simulation device is as follows: First, a high-energy combustion temperature field is provided by setting different gas components; then, different pressures and gas flow rates are set to realize the simulation of the high-energy combustion temperature field under complex working conditions; finally, the laser controller (9) controls the laser to emit laser light, and after the laser passes through the high-energy combustion temperature field under complex working conditions, it is converted into an electrical signal by the photodetector (11) and input to the terminal controller (1). After data storage, the temperature, pressure and gas flow rate parameter information are inverted by the data processing module.

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