Airflow visualization-based aero-engine demonstration model and control method

Abstract

The invention relates to an aero-engine demonstration model based on airflow visualization and a control method, an air inlet cone, a fan, a high-pressure compressor blade, a combustion chamber, a high-pressure turbine, a low-pressure turbine and an exhaust nozzle are sequentially installed in a shell, the aero-engine further comprises an LED module and a light guide module, the shell is transparent, and the light guide module is arranged in the shell. The light guide module is installed on the shell, and the LED module is installed on the light guide module. The LED module emits light rays, the light rays irradiate into the shell after passing through the light guide module, the flowing state of airflow in the shell is observed under the action of the light rays, and the process is executed through the method. The shell is transparent, the LED module is arranged on the shell, light rays are emitted through the LED module, the light rays are reflected and diffused through the light guide module, so that air in an engine is irradiated, the flowing track of the air can be seen, and the visualization effect on the flowing track of the air is good.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine demonstration models, and in particular to an aero-engine demonstration model and a control method based on airflow visualization. Background Art

[0002] Currently, the teaching and research of aero-engines mainly rely on theoretical knowledge, two-dimensional images and a small number of physical models, lacking an intuitive and interactive dynamic display method. Most of the existing engine demonstration models only have the function of structure display and cannot simulate the real operating state, which limits their application value in teaching and scientific research. Therefore, there is a need for an aero-engine model that can operate in a wind tunnel environment and dynamically demonstrate to enhance the intuitiveness of learning and research. There are the following technical defects:

[0003] (1) The strength and high-temperature resistance of existing 3D printing materials are limited, making it difficult to fully simulate the working state of a real engine in a high-temperature and high-speed airflow environment. The components printed by 3D printing may deform or be damaged under the action of high-speed airflow, affecting the reliability of the experiment.

[0004] (2) Many wind tunnel experiments mainly rely on data output, lacking an intuitive visualization display during the test process, unable to attract audiences or improve interactivity. Most traditional wind tunnel devices are not equipped with transparent windows, making it difficult to directly observe the airflow changes of the model during the experiment, affecting the viewing experience. The test airflow is invisible, lacking streamline visualization means such as smoke flow and laser tracing, resulting in a relatively monotonous demonstration effect.

[0005] (3) Due to the poor disassembly or replaceability of components, it is difficult to perform modular optimization according to different teaching needs.

[0006] (4) Due to the relatively single movement of the blades of the existing model and the lack of simulation of aerodynamic characteristics, it is difficult for audiences to understand the airflow changes, compression, combustion and power output processes inside the engine. The lack of airflow visualization and wind tunnel experiment support limits the application effect of the model in teaching.

[0007] The utility model patent with the publication number CN209560858U discloses an aero-engine model for teaching, which includes an engine module and a support base for supporting the engine module; the engine module includes a fairing cone, a fan, a compressor, a turbine, a combustion chamber, a tail nozzle, a motor, an inner shell cover, a speed measurement sensor and an LED lamp; the sliding resistor control box on the support base forms a series circuit with the motor and the LED, and the resistance in the circuit loop is adjusted by pushing the joystick in the sliding resistor controller, so as to control the motor speed and the brightness of the LED lamp, and then simulate the process of pushing the throttle lever to increase fuel and speed in the aircraft and the state process of air flowing through the compressor, combustion chamber, turbine and tail lamp in the real aircraft through the lighting effect of the LED lamp; this patent displays the size of the current air flow through the LED lamp and cannot visually display the air flow trajectory. Summary of the Invention

[0008] The purpose of the present invention is to overcome the defects of the above-mentioned existing technologies and provide an aero-engine demonstration model and control method based on air flow visualization.

[0009] The purpose of the present invention can be achieved by the following technical solutions:

[0010] According to one aspect of the present invention, an aero-engine demonstration model based on air flow visualization is provided. The aero-engine includes an intake cone, a fan, a housing, high-pressure compressor blades, a combustion chamber, a high-pressure turbine, a low-pressure turbine and a tail nozzle. The intake cone, fan, high-pressure compressor blades, combustion chamber, high-pressure turbine, low-pressure turbine and tail nozzle are sequentially installed in the housing. The aero-engine further includes an LED module and a light guide module. The housing is transparent. The light guide module is installed on the housing, and the LED module is installed on the light guide module;

[0011] The LED module emits light, and after passing through the light guide module, the light irradiates into the housing, and the flow state of the air flow in the housing is observed under the action of the light.

[0012] As a preferred technical solution, the light guide module is annular, and the light guide modules are installed on the housing at intervals.

[0013] As a preferred technical solution, the light guide modules are installed on the housing periodically.

[0014] As a preferred technical solution, the light guide module includes optical guiding ridges and recessed units.

[0015] As a preferred technical solution, the aero-engine further includes a guide vane, and the guide vane is installed on the light guide module.

[0016] As a preferred technical solution, the LED module and the light guide module are connected by a snap connection.

[0017] As a preferred technical solution, the aeroengine further includes a water-based atomizer, and the water-based atomizer is installed at the inlet of the fan.

[0018] According to another aspect of the present invention, there is provided a control method for an aeroengine demonstration model based on airflow visualization as described in any one of the above, the method includes a control unit, and the control unit controls the light effect intensity and color change of the corresponding LED module according to the rotational speeds of the fan, the high-pressure compressor blades, the high-pressure turbine, and the low-pressure turbine.

[0019] As a preferred technical solution, the initial color of the LED modules is blue; when the rotational speed continuously increases, the color of the LED module located at the combustion chamber (5) gradually changes from blue to orange-red dynamically.

[0020] As a preferred technical solution, if the rotational speed becomes higher, the brightness of the LED module increases; if the rotational speed becomes smaller, the brightness of the LED module decreases.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. The outer shell of the present invention is transparent, and an LED module is arranged on the outer shell. The LED module emits light, and the light guide module reflects and diffuses the light, so as to irradiate the air inside the engine, and the flow trajectory of the air can be seen, and the visualization effect of the air flow trajectory is better.

[0023] 2. The present invention presets micron-level optical guiding ridges and local micro-concave structures inside the light guide module, which can effectively control the light propagation direction, make the light focus or scatter directionally in a specific area, so as to strengthen the light intensity in the key area or form a structural shadow effect.

[0024] 3. The present invention is provided with a water-based atomizer, and tiny water droplets are added to the air flow, which can further reflect the light of the LED, and it is easier to observe the flow trajectory of the air flow.

[0025] 4. The present invention adjusts the light color of the LED module at the combustion chamber according to the rotational speed, simulates the scene during combustion, and enhances the realism of the simulated flame. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a schematic diagram of the overall structure of the present invention;

[0027] Figure 2 is a schematic diagram of the LCD screen display effect of the present invention;

[0028] Figure 3 is a flow chart of the control process of the present invention;

[0029] Figure 4 Schematic diagram of the electrical control of the present invention;

[0030] 1. Inlet cone; 2. Fan; 3. Low-pressure compressor casing; 4. High-pressure compressor blades; 5. Combustion chamber; 6. High-pressure turbine; 7. Low-pressure turbine; 8. Tail nozzle. Specific implementation manners

[0031] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0032] The present invention is mainly used for classroom demonstrations, exhibition displays, and engine principle teaching. This model is manufactured based on 3D printing and adopts a modular design to simulate and display the structures and working principles of key components such as ducted fans, compressors, combustion chambers, and turbines in aeroengines, highlighting the transfer paths of airflows in each section, the energy conversion process, and the visual feedback effect, enhancing the interactivity and intuitiveness of teaching and display.

[0033] The present invention provides an aeroengine demonstration model and control method based on airflow visualization; the outer shell of the present invention is transparent, and an LED module is provided on the outer shell. The LED module emits light, and the light guide module reflects and diffuses the light, thereby irradiating the air inside the engine, enabling the flow trajectory of the air to be seen, and having a good visualization effect on the airflow trajectory. The present invention presets micron-level optical guiding ridges and local micro-concave structures inside the light guide module, which can effectively control the light propagation direction, making the light focus or scatter directionally in a specific area, thereby strengthening the light intensity in the key area or forming a structural shadow effect. The present invention is provided with a water-based atomizer to add tiny water droplets to the airflow, which can further reflect the light of the LED and make it easier to observe the airflow trajectory. The present invention adjusts the light color of the LED module at the combustion chamber according to the rotational speed to simulate the combustion scenario and enhance the realism of the simulated flame.

[0034] Example 1

[0035] As Figure 1 and Figure 2As shown in the figure, a demonstration model of an aeroengine based on airflow visualization. The aeroengine includes an inlet cone 1, a fan 2, a casing, high-pressure compressor blades 4, a combustion chamber 5, a high-pressure turbine 6, a low-pressure turbine 7, and a tail nozzle 8. The inlet cone 1, the fan 2, the high-pressure compressor blades 4, the combustion chamber 5, the high-pressure turbine 6, the low-pressure turbine 7, and the tail nozzle 8 are sequentially installed in the casing. The aeroengine further includes an LED module and a light guide module. The casing is transparent. The light guide module is installed on the casing, and the LED module is installed on the light guide module;

[0036] The LED module emits light. After the light passes through the light guide module, it irradiates into the casing, and the flow state of the airflow in the casing is observed under the action of the light.

[0037] The light guide module is annular and is spacedly installed on the casing.

[0038] The light guide module is periodically installed on the casing.

[0039] The light guide module includes an optical guiding ridge line and a recessed unit.

[0040] The aeroengine further includes a guide vane, and the guide vane is installed on the light guide module.

[0041] The LED module and the light guide module are connected by a buckle.

[0042] In this embodiment: 1. Model structure: The fan 2, the low-pressure compressor, the high-pressure compressor, the combustion chamber 5, the high-pressure turbine 6, the low-pressure turbine 7, and the tail nozzle 8 are respectively made of 3D printing components, and each section is connected by magnetic attraction or plugging, which is convenient for disassembly and observation.

[0043] 2. Hierarchical drive design: Multiple micro DC motors are arranged in the model to respectively control the high-pressure shaft and the low-pressure shaft. The fan 2 is installed on the low-pressure shaft, the high-pressure compressor blades 4, the high-pressure turbine 6, and the low-pressure turbine 7 are installed on the high-pressure shaft. The high-pressure shaft passes through the combustion chamber 5, and the low-pressure shaft and the high-pressure shaft are connected. And the hierarchical start and variable speed control are realized through the MCU, simulating the physical process in a real engine where the high-pressure shaft starts first and the low-pressure shaft is accelerated by the turbine, avoiding the mechanical problems of the same speed and same direction rotation of all blades in the traditional model. Traditional demonstration models often adopt the method of driving all shaft systems to rotate synchronously by a single motor, and there are the following mechanical problems: The power chain is not real and cannot reflect the relative speed difference of the multi-shaft system of the engine; Lack of dynamic response and cannot display the real start process and thrust adjustment behavior; The pneumatic simulation is distorted and cannot respectively reflect the different working states of the fan and the compressor; The visual performance is dull and lacks the gradualness and rhythm change of segmented rotation; It is difficult to decompose and explain the operation mechanism of the multi-shaft system in teaching.

[0044] 3. LED Airflow Visualization Design: To achieve the visual demonstration of the airflow path and disturbance phenomena in the wind tunnel model, the system integrates multiple groups of light guide modules around the combustion chamber 5 and key airflow channels. The structural design and working process are as follows:

[0045] The light guide module is made of a high light transmittance acrylic diffuser material plate, which has excellent light scattering and uniform expansion capabilities. It can convert the point light emitted by the LED light source into surface light, forming a soft and gradually changing visual effect. The overall structure of the light guide module is annular, which is fitted and installed on the shell, and locally can be embedded or cover the surface of the airflow channel to achieve circumferential lighting. The LED module is also annular in structure and is installed on the light guide module. The high-brightness LED beads of the LED module are evenly arranged along the circumference of the combustion chamber, located outside the light guide module, and are accurately positioned and closely fitted with the light incident end of the light guide module through a snap-fit structure. The directional light beam emitted by the LED irradiates the light incident area of the light guide body at a large angle. Some of the light directly enters the light guide path and, after multiple total reflections and diffusions inside the light guide module, forms a uniform light-emitting area on the surface of the light guide module, creating a "halo band" effect around the airflow channel.

[0046] Micron-level optical guiding ridges and local micro-concave structures are preset inside the light guide module, which can effectively control the light propagation direction, making the light focus or scatter directionally in specific areas, thereby enhancing the light intensity in key areas or forming a structural shadow effect; transparent flow deflectors are also provided at the edges of some light guide plates. These structures can project streamline-shaped light and shadow boundaries under LED illumination, facilitating the observation of the airflow disturbance edge and its evolution process. The light guide module is firmly fixed between the combustion chamber shell and the transparent cover through snaps and forms a one-to-one tight coupling relationship with the LED beads at the light incident end to ensure efficient transmission of light energy into the light guide body. The control of the LED module is dynamically adjusted by the control unit (MCU) according to the current fan speed, airflow direction, and demonstration mode to achieve precise control of light intensity, flicker frequency, and color change. This light effect control strategy can synchronously respond to the airflow state, enhancing the real-time and interactive nature of visual feedback.

[0047] The aeroengine further includes a water-based atomizer, and the water-based atomizer is installed at the inlet of the fan 2.

[0048] In addition, a micro water-based atomizer is installed at the inlet of the fan 2 (i.e., the air inlet of the engine), which sprays suspended particles (tiny water droplets) that can be made visible by LED illumination. Under the cooperation of the light guide system illumination and structural optical guidance, the refraction and scattering trajectories formed by the particle flow moving with the airflow can intuitively show key aerodynamic characteristics such as vortices, jets, and boundary layer changes, significantly enhancing the intuitiveness and interactive effect of teaching demonstrations.

[0049] The model adopts a modular mechanical structure, enabling it to demonstrate the working principle of the engine in stages and featuring high-precision component fitting to ensure stable operation.

[0050] Turbines of different levels adopt independent rotating mechanisms, avoiding the problem of all blades rotating at the same speed and in the same direction in traditional models. The fan blades are 3D printed with carbon fiber reinforced plastic to improve durability and rotational efficiency. Most components are 3D printed with metal to enhance heat resistance. The high-pressure shaft is separated from the low-pressure shaft and connected to the corresponding turbine through a coupling, enabling different rotational speeds at different stages. Precision gear sets or synchronous belts are used to ensure the stability of the transmission system while reducing energy loss. High-precision ball bearings are used to reduce friction and improve rotational stability. The combustion chamber part is made of high-temperature resistant transparent material, allowing viewers to directly observe the combustion and air flow processes. The intake port design is optimized to ensure that the fan can efficiently simulate air flow. The split structure enables each component to be individually disassembled and replaced, facilitating maintenance and upgrade. Different types of turbine blades can be replaced to suit different demonstration requirements.

[0051] The housing also includes a low-pressure compressor brake 3, and the entire housing is made of high-temperature resistant transparent material, which is convenient for light irradiation. The aeroengine of the present invention only serves for demonstration, and the actual combustion process is reflected by the color change of the LED module. An LCD screen and corresponding sensors are also provided. Both the LCD screen and the sensors are communicatively connected to the control unit, and parameters such as the current rotational speed, gas flow rate, temperature, and operating state of the engine are displayed through the LCD screen.

[0052] Embodiment 2

[0053] As Figure 3 and Figure 4 shown, a control method for an aeroengine demonstration model for airflow visualization, the method includes a control unit, and the control unit controls the light effect intensity and color change of the corresponding LED module according to the rotational speeds of the fan 2, the high-pressure compressor blade 4, the high-pressure turbine 6, and the low-pressure turbine 7.

[0054] The initial color of the LED module is blue; when the rotational speed continuously increases, the color of the LED module located at the combustion chamber 5 gradually changes from blue to orange-red dynamically.

[0055] When the rotational speed increases, the brightness of the LED module increases; when the rotational speed decreases, the brightness of the LED module decreases.

[0056] In this embodiment, the model adopts an intelligent electrical control system to achieve functions such as engine starting, ignition, gas simulation, and turbine linkage.

[0057] (1) The microcontroller (MCU) is used as the core control unit, responsible for receiving input instructions and controlling the operating states of each component. Multiple demonstration modes are preset, and different operating states can be selected through the touch screen, buttons or remote control.

[0058] (2) An independent motor drives the high-pressure shaft to simulate the function of the starting motor, and then switches to the turbine drive mode. The high-pressure turbine (HPT) and low-pressure turbine (LPT) are respectively controlled by a DC motor or a brushless DC motor (BLDC motor), enabling them to independently adjust the rotational speed and demonstrating the power transmission process of a real engine. The PWM speed regulation technology is adopted to adjust the turbine speed according to different stages to more realistically simulate the operating characteristics of the engine.

[0059] (3) High-brightness LED lights are set in the combustion chamber to simulate the visual effect of flame ignition during startup. A micro fan is used to simulate the gas flow, so that the gas flow passes through the combustion chamber to drive the high- and low-pressure turbines to rotate, enhancing the sense of reality.

[0060] (4) The LCD screen displays parameters such as the current engine speed, gas flow rate, temperature, and operating state.

[0061] Detect the rotational speed and feedback it to the LCD screen. Measure the simulated temperature change in the combustion chamber. Detect the simulated gas flow condition to ensure the power transmission effect.

[0062] The system is equipped with a manual control mode and an automatic demonstration mode. Users can select the mode through buttons, and the MCU automatically adjusts the motor PWM signal, LED light effect intensity, and fan speed to achieve dynamic adjustment and programmed linkage demonstration.

[0063] The specific control logic is as follows: The MCU dynamically adjusts the PWM duty cycle according to sensor sampling (tachometer, voltage feedback) to finely control the rotational speed of each section of the motor; Fan 2 (low-pressure shaft) and the high-pressure shaft are independently controlled. The high-pressure compressor is driven first during startup, and the low-pressure shaft is automatically triggered to accelerate after the high-pressure speed stabilizes, realizing segmented linkage demonstration; The LED module adopts multi-channel PWM control and has a mapping relationship with the rotational speed: when the rotational speed increases, the LED brightness increases, and the color gradually transitions from blue to orange-red to simulate the flame effect of increasing temperature;

[0064] In the acceleration demonstration mode, the LED color can be dynamically gradually changed (orange-red) according to the program setting to enhance the realism of the simulated flame; The PWM frequency of the entire system is set higher than 1 kHz to avoid the influence of visual stroboscopic effects;

[0065] In the automatic demonstration mode, the MCU starts the high-pressure shaft, low-pressure shaft, and fan section in sequence according to the preset schedule. The LED light effect gradually intensifies and dynamically switches the color temperature, simulating the entire process of "cold start - acceleration operation - steady operation". The control interface supports multi-gear speed and mode selection, facilitating the switching of different demonstration stages according to the explanation rhythm during the teaching process.

[0066] The above is only a specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of various equivalent modifications or substitutions, and these modifications or substitutions should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. An aircraft engine demonstration model based on airflow visualization, the aircraft engine comprising an intake cone (1), a fan (2), a casing, a high-pressure compressor blade (4), a combustion chamber (5), a high-pressure turbine (6), a low-pressure turbine (7) and an exhaust nozzle (8), wherein the intake cone (1), the fan (2), the high-pressure compressor blade (4), the combustion chamber (5), the high-pressure turbine (6), the low-pressure turbine (7) and the exhaust nozzle (8) are sequentially installed in the casing, characterized in that: The aircraft engine further comprises an LED module and a light guide module, the housing is transparent, the light guide module is mounted on the housing, and the LED module is mounted on the light guide module; The LED module emits light, and the light is irradiated into the housing after passing through the light guide module. The flow state of the airflow in the housing is observed under the action of the light.

2. The aircraft engine demonstration model based on airflow visualization according to claim 1, characterized in that: The light guide modules are ring-shaped and are installed on the housing at intervals.

3. The aircraft engine demonstration model based on airflow visualization according to claim 2, characterized in that: The light guide modules are periodically mounted on the housing.

4. The aircraft engine demonstration model based on airflow visualization according to claim 2, characterized in that: The light guide module includes an optical guide ridge and a recessed unit.

5. The aircraft engine demonstration model based on airflow visualization according to claim 2, characterized in that: The aircraft engine further comprises a guide vane, and the guide vane is mounted on the light guide module.

6. The aircraft engine demonstration model based on airflow visualization according to claim 1, characterized in that: The LED module and the light guide module are connected via snap fasteners.

7. The aircraft engine demonstration model based on airflow visualization according to claim 6, characterized in that: The aircraft engine also includes a water-based atomizer, which is installed at the inlet of the fan (2).

8. A control method for an aircraft engine demonstration model based on airflow visualization as claimed in any one of claims 1 to 7, the method comprising a control unit, characterized in that: The control unit controls the light effect intensity and color change of the corresponding LED modules according to the rotation speeds of the fan (2), the high-pressure compressor blades (4), the high-pressure turbine (6) and the low-pressure turbine (7).

9. The control method according to claim 8, characterized in that: The initial color of the LED modules is blue; if the rotation speed continues to increase, the color of the LED modules located in the combustion chamber (5) dynamically changes from blue to orange-red.

10. The control method according to claim 8, characterized in that: If the rotation speed increases, the brightness of the LED module increases; if the rotation speed decreases, the brightness of the LED module decreases.

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