Vibration sensor for aero-engine based on CdTe quantum dot-Mxene

Abstract

The utility model discloses a vibration sensor for an aero-engine based on CdTe quantum dot-Mxene, relates to the technical field of sensors, and aims to solve the problem of real-time monitoring of vibration of the aero-engine. The interdigital electrode is plated on the base surface, and a convex part of the interdigital electrode and the base surface form an accommodating space; the accommodating space is filled with the pressure-sensitive active layer, the pressure-sensitive active layer covers the interdigital electrode, and the surface, deviating from the interdigital electrode, of the pressure-sensitive active layer is a sensing surface. According to the vibration sensor for the aero-engine based on the CdTe quantum dot-Mxene provided by the embodiment of the utility model, when the vibration sensor is subjected to pressure change caused by vibration, the resistance of the pressure-sensitive active layer of the flexible sensor also changes along with the pressure change, and the bridge circuit connected with the flexible sensor can measure the tiny change of the resistance and convert the change into a voltage signal; the signals can be recorded and analyzed for monitoring the operating condition of the engine and performing fault diagnosis.

Description

Technical Field

[0001] The utility model relates to the technical field of sensors, in particular to a vibration sensor for aviation engines based on CdTe quantum dots-Mxene. Background Art

[0002] In the field of vibration signal feature extraction of aircraft engines, domestic researchers have proposed a variety of methods for extracting vibration signal features of aircraft engines, such as wavelet analysis, energy spectrum analysis, etc. These methods can be used to accurately monitor the vibration status of aircraft engines. In the direction of vibration signal diagnosis and fault diagnosis of sensors: Domestic researchers are also committed to developing fault diagnosis algorithms based on vibration signals. These algorithms can extract abnormal or fault features from vibration signals in order to detect and diagnose engine faults in a timely manner. In the development of intelligent health monitoring systems: Some domestic airlines and research institutions have begun to develop intelligent health monitoring systems, using a variety of sensors such as vibration sensors to monitor the working status and health of aircraft engines in real time to improve the reliability and safety of the engines.

[0003] In the field of vibration monitoring technology, international researchers have proposed various technologies for aircraft engine vibration monitoring, such as spectrum analysis and time-frequency analysis. These technologies can help determine the engine's operating status and condition and proactively detect potential faults. Some international research has also focused on processing and analyzing aircraft engine vibration data to obtain more accurate conclusions and diagnostic results. The application of big data processing and analysis technologies has also gradually attracted the attention of international scholars. Foreign researchers are also interested in fault diagnosis and prediction using aircraft engine vibration data. By analyzing and modeling vibration signals, the type of engine fault can be determined in advance, allowing appropriate repair and maintenance measures to be implemented, thereby reducing the losses caused by the failure. Overall, research on aircraft engine vibration sensors is actively ongoing both domestically and internationally, and has achieved significant progress. This research provides effective means and technical support for aircraft engine performance monitoring, fault diagnosis, and health management.

[0004] Quantum dot-modified MXene materials have been a research area that has garnered significant attention in recent years. MXene is a two-dimensional inorganic material composed of layered structures such as metal carbides (Ti3C2) or metal nitrides (Mo2C). It exhibits excellent electrical and thermal conductivity and chemical stability, making it widely used in optoelectronic devices and biology. In optoelectronic devices, it has been used in nanolasers, solar cells, infrared detectors, and light-emitting diodes. Its applications in biology are even more extensive, including biosensors, bioprobes, and biomarkers. Research institutions and scholars both domestically and internationally are actively exploring the combination of MXene materials with quantum dots for modification and enhancement to further enhance their performance and functionality. Quantum dots are nanomaterials with a small particle size and unique optoelectronic properties, enabling the manipulation of a material's photoelectric response and band structure. In China, research teams at universities such as the University of Science and Technology of China, Nanjing University, and Wuhan University have conducted research in this area. By combining MXene with metal quantum dots (such as metal sulfide quantum dots, semiconductor quantum dots, etc.), they have achieved the regulation and enhancement of the photoelectric properties of MXene materials, improving their application performance in photocatalytic water splitting, photoelectrochemical sensing, and photocatalytic CO2 reduction. Many research institutions and scholars abroad are also studying quantum dot-modified MXene materials. For example, a research team at the Massachusetts Institute of Technology in the United States used CdS quantum dots to modify MXene materials and achieved efficient photocatalytic water splitting reactions. Overall, quantum dot-modified MXene materials have made considerable progress in research at home and abroad. By introducing and modifying quantum dots, the photoelectric properties of MXene materials can be regulated and their applications in catalysis, energy, and sensing can be expanded. Although there are still many challenges to overcome, this field is expected to provide new ideas and directions for future materials research and applications.

[0005] To verify the design, manufacturing, assembly quality, and operating conditions of aircraft engines and ensure flight safety, engine vibration measurement and monitoring are necessary during the engine development, production, and use. Since the working conditions of aircraft engines are different from those of general rotating machinery, the sensors used for vibration measurement are specially designed and developed.

[0006] Based on the above, the present application proposes a vibration sensor for aircraft engines based on CdTe quantum dots-Mxene with high sensitivity, high stability and high anti-interference ability to solve the problem of real-time monitoring of aircraft engine vibration. Utility Model Content

[0007] The embodiment of the utility model provides a vibration sensor for an aero-engine based on CdTe quantum dots-MXene to solve the problem of real-time monitoring of aero-engine vibration.

[0008] In order to achieve the above-mentioned purpose, the embodiments of the present invention adopt the following technical solutions:

[0009] A vibration sensor for an aircraft engine based on CdTe quantum dots-MXene, comprising:

[0010] a flexible substrate having a base surface;

[0011] an interdigital electrode plated on the base surface and protruding from the base surface, wherein the protruding portion of the interdigital electrode and the base surface form a receiving space;

[0012] a pressure-sensitive active layer, filling the accommodation space and covering the interdigital electrodes, wherein the surface of the pressure-sensitive active layer facing away from the interdigital electrodes is a sensing surface;

[0013] When mechanical pressure is applied to the sensing surface of the pressure-sensitive active layer, the pressure-sensitive active layer is deformed, and the resistance of the pressure-sensitive active layer also changes with the deformation.

[0014] The CdTe quantum dot-MXene-based vibration sensor for aircraft engines provided by the embodiment of the present invention has a pressure-sensitive active layer that is very sensitive to changes in external pressure. Therefore, during the detection of engine vibration, the sensor can be deformed according to changes in the external pressure of the sensor. The vibration of the aircraft engine is characterized by detecting the vibration of the casing. The sensor is installed on the casing. When the casing vibrates, its amplitude changes. This change causes a pressure change on the sensor on the surface of the casing. This pressure change acts on the pressure-sensitive active layer on the sensor. This action mechanically squeezes the pressure-sensitive active layer, causing the pressure-sensitive active layer to deform. When subjected to pressure changes caused by vibration, the resistance of the pressure-sensitive active layer of the flexible sensor will also change accordingly. At this time, the bridge circuit connected to the flexible sensor can measure small changes in resistance and convert them into voltage signals. These signals can be recorded and analyzed for monitoring the operating status of the engine and performing fault diagnosis.

[0015] In some possible designs, an encapsulation layer is further included, which covers and encapsulates the sensing surface of the pressure-sensitive active layer and the side edges of the pressure-sensitive active layer. This arrangement can better encapsulate and protect the entire device.

[0016] Furthermore, the encapsulation layer is formed by stacking at least two polydimethylsiloxane films and is tightly bonded to the pressure-sensitive active layer. Polydimethylsiloxane films have excellent physical and chemical properties, including extremely high chemical stability and being an inert material that is not easily corroded by substances such as air, water, acids, and alkalis. Polydimethylsiloxane films also have excellent electrical properties, including a low dielectric constant, high impedance, and strong resistance to potential differences. Polydimethylsiloxane films also exhibit high cleanliness, low surface free energy, and high transparency.

[0017] In some possible designs, the flexible substrate is a polyethylene terephthalate substrate, which has good creep resistance, fatigue resistance, friction resistance, good electrical insulation performance, and is less affected by temperature.

[0018] In some possible designs, the interdigitated electrodes are coated on the base surface of the flexible substrate by magnetron sputtering. The surface of the polyethylene terephthalate substrate is metallized by magnetron sputtering to obtain the interdigitated electrodes.

[0019] In some possible designs, the pressure-sensitive active layer is spray-printed onto the interdigital electrodes and within the accommodation space. The pressure-sensitive active layer is formed by curing a CdTe quantum dot-MXene mixed solution. The CdTe quantum dot-MXene mixed solution is coated onto the interdigital electrodes using piezoelectric on-demand printing technology, thereby forming the CdTe quantum dot-MXene pressure-sensitive active layer of the flexible pressure sensor. Quantum dot modification can enhance the electrical properties of the MXene material, resulting in higher sensitivity for aircraft engine vibration sensors and optimizing their frequency response range, enabling high-precision vibration detection across a wider frequency range. This provides excellent flexibility and bendability. Combined with the optimized quantum dot modification, the aircraft engine vibration sensor can better adapt to unconventional shapes and small-sized spatial layout requirements, enabling more flexible installation and deployment. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is an exploded view of the structure of a vibration sensor for an aero-engine according to an embodiment of the present utility model;

[0021] Figure 2 This is a flow chart for preparing a vibration sensor for an aircraft engine according to an embodiment of the utility model;

[0022] Figure 3 This is a schematic diagram of the application of the vibration sensor for an aero-engine in an aero-engine according to an embodiment of the utility model;

[0023] The meanings of the reference numerals are as follows:

[0024] In the picture:

[0025] 1. Flexible substrate, 2. Interdigitated electrodes, 3. Pressure-sensitive active layer, 4. Encapsulation layer, a. Base surface, b. Accommodation space, c. Sensing surface. DETAILED DESCRIPTION

[0026] The embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0027] The development of flexible sensors is driven by applications and fundamentally based on material advancements. By the 1980s, traditional sensors had become increasingly sophisticated, and smart sensors integrating sensors and microprocessors began to emerge. In the 1990s, researchers began designing and fabricating large-area, low-cost, and printable flexible sensor arrays. For example, Professor Chih-Ming Ho's research group was the first to fabricate a flexible sensor array for tactile shear stress sensing. They integrated etched thin silicon wafers onto flexible polyimide foils to create silicon microelectromechanical (MEM) islands. This initiative guided the main development direction of flexible sensors for the next decade: integrating micro-silicon-based sensor arrays onto flexible polymer substrates such as polyvinylidene fluoride (PVDF) and polyimide (PI) to form flexible sensing structures. At this time, the flexibility of flexible sensor arrays primarily came from the flexible substrate; the individual sensors themselves were not flexible. Around 2010, materials with excellent mechanical properties began to be used in sensing applications, fundamentally advancing the development of flexible sensors. For example, in 2008, Professor Chang Shuo-Hung's research group fabricated a flexible strain sensor based on single-walled carbon nanotubes; in 2009, Professor Wang Peng's research group fabricated a thin, flexible pressure sensor array based on a carbon black / silicone rubber nanocomposite. Compared to silicon-based sensing materials, carbon-based and their composite materials are easier to prepare, less expensive, and offer greater adjustability. Subsequently, with the emergence of a range of two-dimensional materials such as graphene and MXenes, and the urgent need for flexible sensing driven by rapid technological advancements, flexible sensors have entered a period of truly rapid development: moving beyond the fabrication of flexible sensor arrays, the focus has shifted to the preparation of flexible sensor units with exceptional flexibility and stability.

[0028] Aircraft engines are key components of aircraft, and monitoring their operating status is crucial for flight safety and efficiency. This study leverages the strengths of CdTe quantum dots and MXene to design a new vibration sensor. CdTe quantum dots are a semiconductor nanomaterial with excellent optical and electrical properties. They can shift electron energy levels in response to external mechanical changes, enabling the detection of vibration signals. MXene, a two-dimensional material with high conductivity and mechanical strength, is suitable for forming sensor electrodes and support structures. By leveraging the properties of CdTe quantum dots and MXene, this study designed and fabricated an aircraft engine vibration sensor with high sensitivity, stability, and robust interference resistance. This sensor will be able to monitor the engine's vibration status in real time, providing accurate vibration data to promptly detect and correct potential faults or anomalies, ensuring safe and efficient aircraft engine operation.

[0029] Based on the above, the present invention proposes a vibration sensor for aircraft engines based on CdTe quantum dots-MXene. Figure 1 , comprising a flexible substrate 1, interdigitated electrodes 2 and a pressure-sensitive active layer 3, wherein the flexible substrate 1 has a base surface a; the interdigitated electrodes 2 are plated on the base surface a and protrude from the base surface a, and the protruding portions of the interdigitated electrodes 2 and the base surface a form a receiving space b; the pressure-sensitive active layer 3 fills the receiving space b and covers the interdigitated electrodes 2, and the surface of the pressure-sensitive active layer 3 facing away from the interdigitated electrodes 2 is a sensing surface c; wherein, when mechanical pressure is applied to the sensing surface c of the pressure-sensitive active layer 3, the pressure-sensitive active layer 3 is deformed, and the resistance of the pressure-sensitive active layer 3 also changes with its own deformation.

[0030] The CdTe quantum dot-MXene-based vibration sensor for aircraft engines provided by the embodiment of the present invention has a pressure-sensitive active layer 3 that is very sensitive to changes in external pressure. Therefore, during the detection of engine vibration, the pressure-sensitive active layer 3 can be deformed according to changes in the external pressure of the sensor. The vibration of the aircraft engine is characterized by detecting the vibration of the casing. The sensor is installed on the casing. When the casing vibrates, its amplitude changes. This change causes a pressure change on the sensor on the surface of the casing. This pressure change acts on the pressure-sensitive active layer 3 on the sensor. This action mechanically squeezes the pressure-sensitive active layer 3, causing the pressure-sensitive active layer to deform. When subjected to pressure changes caused by vibration, the resistance of the pressure-sensitive active layer 3 of the flexible sensor will also change accordingly. At this time, the bridge circuit connected to the flexible sensor can measure small changes in resistance and convert them into voltage signals. These signals can be recorded and analyzed for monitoring the operating status of the engine and performing fault diagnosis.

[0031] In order to encapsulate and protect the pressure-sensitive active layer 3, please continue to refer to Figure 1 , exemplarily, it further includes an encapsulation layer 4, which covers and encapsulates the sensing surface c of the pressure-sensitive active layer 3 and the side edges of the pressure-sensitive active layer 3. This arrangement can better encapsulate and protect the entire device.

[0032] More specifically, the encapsulation layer 4 is formed by stacking at least two polydimethylsiloxane films and is tightly bonded to the pressure-sensitive active layer 3. Polydimethylsiloxane films have excellent physical and chemical properties. They have extremely high chemical stability and are an inert material that is not easily corroded by substances such as air, water, acids, and alkalis. Polydimethylsiloxane films also have excellent electrical properties, including a low dielectric constant, high impedance, and strong resistance to potential differences. Polydimethylsiloxane films also have high cleanliness, low surface free energy, and high transparency. In this embodiment of the utility model, two polydimethylsiloxane films are used as an example to cover and encapsulate the sensing surface c of the pressure-sensitive active layer 3.

[0033] The flexible substrate 1 mentioned above is specifically described below by way of example. The flexible substrate 1 is a polyethylene terephthalate substrate, which has good creep resistance, fatigue resistance, and friction resistance, as well as good electrical insulation performance and is less affected by temperature.

[0034] The interdigital electrodes 2 mentioned above are specifically described below with an example. The interdigital electrodes 2 are coated on the base surface a of the flexible substrate 1 by magnetron sputtering. The interdigital electrodes 2 are obtained by metallizing the surface of a polyethylene terephthalate substrate by magnetron sputtering.

[0035] The following is a specific example of the pressure-sensitive active layer 3 mentioned above. The pressure-sensitive active layer 3 is spray-printed onto the interdigital electrodes 2 and within the accommodation space b. The pressure-sensitive active layer 3 is formed by solidifying a CdTe quantum dot-MXene mixed solution. The CdTe quantum dot-MXene mixed solution is coated onto the interdigital electrodes 2 using piezoelectric on-demand printing technology, thereby forming the CdTe quantum dot-MXene pressure-sensitive active layer 3 of the flexible pressure sensor.

[0036] See Figure 2 The following is a detailed explanation of the preparation process of the vibration sensor for aviation engines based on CdTe quantum dots-MXene:

[0037] S1, metallizing the surface of a polyethylene terephthalate (PET) substrate by magnetron sputtering to obtain interdigital electrodes 2;

[0038] S2, using piezoelectric on-demand printing technology to cover the prepared solution on the interdigital electrode 2, thereby obtaining the CdTe quantum dot-MXene pressure-sensitive active layer 3 of the flexible pressure sensor;

[0039] S3, tightly attaching two polydimethylsiloxane (PDMS) films to the CdTe quantum dot-MXene pressure-sensitive active layer 3 to encapsulate and protect the entire device;

[0040] S4. Connect a copper wire to the lead-out pin of interdigital electrode 2 and apply conductive silver glue on the end. Heat it to solidify it, then attach tin foil to the conductive silver glue to prevent the connecting wire from falling off during the measurement process.

[0041] The preparation of the CdTe quantum dot-MXene mixed solution is as follows: 4mL of 0.04mol / L cadmium chloride solution is placed in a three-necked flask, diluted to 50mL with deionized water and stirred. During the stirring process, 100mg of sodium citrate, 4mL of 0.01mol / L sodium tellurite, 50mg of mercaptosuccinic acid and 50mg of sodium borohydride are added. The three-necked flask is connected to a condenser and condensed and refluxed at 100°C. The quantum dot solution is filtered using an aqueous syringe filter, and the filtered quantum dot solution is mixed with the Ti3C2Tx-MXene solution prepared by the wet etching method and stirred thoroughly. After the above operation is completed, it is set aside for later use.

[0042] The CdTe quantum dot-Mxene pressure-sensitive active layer 3 is prepared as follows: The CdTe quantum dot-Mxene pressure-sensitive active layer 3 is printed using inkjet printing technology. The inkjet printing technology pushes functional ink droplets of a CdTe quantum dot-Mxene mixed solution onto the interdigitated electrodes 2 of the PET substrate through a nozzle. The patterned film is quickly and accurately produced through a thermistor or piezoelectric transducer mechanism. The solvent in the deposited FSE fluid ink droplets evaporates, or the ink components polymerize to form a solid. This non-contact printing method provides discrete droplets and reduces material waste, thereby minimizing contamination and damage to the various layers.

[0043] The piezoelectric on-demand printing system used in this embodiment mainly causes the volume of the ink cavity to be reduced by printing, thereby pressing out the ink. It is mainly composed of a storage bottle, an air supply duct device, an electronic control device, and an air control device. The printing device, a heating platform, a motion control device, a correction feedback (real-time monitoring) device, and a droplet nozzle are composed of three components. It is used for the printing of CdTe quantum dot-Mxene mixed solution. The heating platform is composed of a heating plate and a temperature control box for quickly solidifying the printed ink. The motion control device is composed of a computer, a motion control card, a three-axis motor, and a stepper motor for precise positioning of the droplet nozzle and movement of the substrate. The correction feedback (real-time monitoring) device is composed of a CCD camera and image processing software to eliminate the alignment error of the droplet nozzle so that it reaches the specified position for printing. The air control device is used to control the air pressure inside the storage bottle, thereby controlling the rate at which the nozzle ejects droplets, and the electronic control device is used to output a pulse signal.

[0044] To prepare the pressure-sensitive active layer 3, a storage bottle containing a CdTe quantum dot-MXene mixed solution is first connected to the air pipe. A series of printing parameters are then set: voltage amplitude, back pressure, nozzle-to-substrate distance, and spray frequency. A pre-programmed program is then started. The motion control card then drives the stepper motor to move the substrate, and the droplet nozzle begins to print the solution. Meanwhile, a corrective feedback device monitors the distance between the nozzle and the substrate during printing. After printing several layers, the heating stage is heated and maintained at around 55°C to solidify the sample.

[0045] Working principle of CdTe quantum dot-MXene flexible sensor for aviation engine:

[0046] The CdTe quantum dot-MXene flexible sensor for aircraft engines includes a pressure-sensitive active layer 3, which makes the entire sensor very sensitive to changes in external pressure. During engine vibration detection, the sensor can deform according to changes in external pressure. By detecting the vibration of the casing, the vibration of the aircraft engine can be characterized. Figure 3 The sensor is mounted on the casing. When the casing vibrates, its amplitude changes. This change generates a pressure change on the sensor on the casing surface. This pressure change acts on the pressure-sensitive active layer 3 on the sensor, mechanically squeezing the pressure-sensitive active layer 3 and causing deformation. When subjected to pressure changes caused by vibration, the resistance of the pressure-sensitive active layer 3 of the flexible sensor also changes. The bridge circuit connected to the flexible sensor can measure this tiny change in resistance and convert it into a voltage signal. However, the resistance change produced by the sensor can be very small, so an amplifier is needed to increase the signal amplitude for easier detection and processing. After amplification by the amplifier circuit, the amplified signal may still be an analog signal. To digitize the signal for easier processing, analog-to-digital conversion is required. In this embodiment, an analog-to-digital converter (ADC) is used to convert the continuous analog signal into a discrete digital signal. The converted digital signal can be transmitted to the control system for further analysis and processing. These signals include monitoring the frequency and amplitude of the vibration and detecting any abnormal vibration, which facilitates the implementation of necessary measures, such as adjusting system parameters or issuing an alarm.

[0047] After the above process, the sensor can convert the pressure changes on the casing surface caused by engine vibration into electrical signals, so that these signals can be recorded and analyzed for monitoring the operating status of the engine and performing fault diagnosis.

[0048] Vibration sensors made from flexible MXene materials modified with CdTe quantum dots are used for vibration monitoring in aircraft engines. They can obtain engine status parameters in real time, providing raw data for subsequent aircraft engine maintenance. The following are several advantages of CdTe quantum dot-MXene flexible electronic aircraft engine sensors over traditional aircraft engine sensors:

[0049] High sensitivity: Quantum dot modification can enhance the electrical properties of MXene materials, making aircraft engine vibration sensors more sensitive. This means they can more accurately detect and measure aircraft engine vibration signals, allowing potential faults and problems to be discovered and resolved promptly.

[0050] Wide frequency response range: Quantum dot-modified MXene materials can optimize the frequency response range of vibration sensors, enabling them to perform high-precision vibration detection across a wider frequency range. This is particularly important for aircraft engines, as the engine's vibration frequency typically varies under different operating conditions.

[0051] High-temperature stability: MXene materials already possess good high-temperature stability, and quantum dot modification can further enhance their high-temperature performance. This means that vibration sensors used in aircraft engines can still operate reliably in high-temperature environments and will not fail due to temperature increases.

[0052] High energy dissipation efficiency: MXene materials and quantum dot modification can provide higher energy dissipation efficiency, enabling vibration sensors for aircraft engines to more effectively convert vibration energy into electrical energy, thereby improving energy utilization efficiency.

[0053] Flexible adaptability: MXene materials themselves have good flexibility and bendability. Combined with the optimization of quantum dot modification, vibration sensors for aircraft engines can better adapt to the spatial layout requirements of unconventional shapes and small sizes, thereby achieving more flexible installation and layout.

[0054] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0055] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any modifications or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. A vibration sensor for aircraft engines based on CdTe quantum dots-MXene, characterized in that: include: a flexible substrate having a base surface; an interdigital electrode plated on the base surface and protruding from the base surface, wherein the protruding portion of the interdigital electrode and the base surface form a receiving space; a pressure-sensitive active layer, filling the accommodation space and covering the interdigital electrodes, wherein the surface of the pressure-sensitive active layer facing away from the interdigital electrodes is a sensing surface; When mechanical pressure is applied to the sensing surface of the pressure-sensitive active layer, the pressure-sensitive active layer is deformed, and the resistance of the pressure-sensitive active layer also changes with the deformation.

2. The CdTe quantum dot-MXene-based aviation engine vibration sensor according to claim 1, characterized in that: It also includes an encapsulation layer that covers and encapsulates the sensing surface of the pressure-sensitive active layer and the side edge of the pressure-sensitive active layer.

3. The CdTe quantum dot-MXene-based aviation engine vibration sensor according to claim 2, characterized in that: The encapsulation layer is formed by stacking at least two polydimethylsiloxane films and is tightly adhered to the pressure-sensitive active layer.

4. The CdTe quantum dot-MXene-based aviation engine vibration sensor according to claim 1, characterized in that: The flexible substrate is a polyethylene terephthalate substrate.

5. The CdTe quantum dot-MXene-based aviation engine vibration sensor according to claim 1, characterized in that: The interdigital electrodes are coated on the base surface of the flexible substrate in a magnetron sputtering manner.

6. The CdTe quantum dot-MXene-based vibration sensor for aviation engines according to claim 1, characterized in that: The pressure-sensitive active layer is covered on the interdigital electrodes and in the accommodation space by spray printing.

7. The CdTe quantum dot-MXene-based vibration sensor for an aero-engine according to claim 1, characterized in that: The pressure-sensitive active layer is formed by solidifying a CdTe quantum dot-Mxene mixed solution.

Images