A piezoelectrically driven aeroengine particle separator and its active control method

Abstract

The present invention relates to the technical field of control of damage caused by foreign objects impacting aircraft engines, specifically a piezoelectrically driven aircraft engine particle separator and an active control method thereof. The above-mentioned aircraft engine particle separator includes a separator housing, a piezoelectric displacement mechanism for controlling the throat area, a throat profile adjustment mechanism, and a control center; the present invention can obtain the concentration of sand particles in the air, the concentration of sand particles after treatment, and the total intake pressure, and dynamically adjust the throat area by driving and controlling the throat profile adjustment mechanism through the piezoelectric displacement mechanism in combination with the calculation of the control center. This means that the present invention can respond to changes in the intake environment, and can ensure that the engine reaches the optimal operating condition under the premise of not inhaling sand particles exceeding the limit concentration, and achieves a dynamic balance between the optimal operating condition of the engine and the constantly changing sand concentration in the outside world, thereby greatly improving the adaptability of the aircraft in complex environments.

Description

Technical Field

[0001] The present invention relates to the technical field of foreign object impact damage control for aircraft engines, and in particular to a piezoelectrically driven aircraft engine particle separator and an active control method thereof. Background Art

[0002] Helicopters have excellent take-off, landing, hovering and low-altitude flight capabilities and are widely used in both military and civilian fields. Turboshaft engines are the core power equipment of helicopters. Since helicopters need to frequently perform emergency rescue and combat escort flight missions in harsh environments such as deserts and plateaus, sand particles in the external environment are inevitably sucked into the inlet airflow duct under the combined action of rotor airflow disturbance and the strong suction force of the engine, and collide with the compressor blades at high speed, causing erosion damage defects. Defective blades will trigger pulsating airflow excitation and unbalanced fault coupling excitation, causing the engine rotor with a speed of up to 45,000 r / min to vibrate beyond the limit, resulting in reduced engine service life and vibration safety accidents.

[0003] In order to alleviate the failure problems caused by sand erosion damage to the engine compressor, the compressor intake system currently generally adopts an integral inertial particle separator. Its principle is to use a special throat surface design to allow the particles in the intake air to enter the cleaning flow path under the dual influence of inertia and collision with the wall, and then be discharged out of the engine, thereby achieving the effect of purifying the intake air; however, this type of particle separator will cause the engine's intake efficiency to decrease when the helicopter operating environment is good, and it is easy to cause flow channel blockage under non-design conditions, increase total pressure loss, and reduce the engine surge margin; in addition, when the helicopter operates in harsh environments such as desert plateaus, due to the limitations of the fixed throat surface, the particle separator cannot further improve the separation efficiency, resulting in a large amount of sand particles still being inhaled into the compressor, causing blade erosion damage.

[0004] To solve the above problems, the invention patent with publication number CN111648865B discloses a variable particle separator multi-chamber bulge center body structure and its design method, which adjusts the throat profile height by inflating the particle separator bulge structure. However, this technical method mainly has the following problems: 1. If the air in the air chamber is supplied by a separate air compressor, the engine mass will be greatly increased and extremely noisy. If air is drawn from the engine flow path to the bulge structure, the air pressure in the air chamber will be unstable due to changes in the engine operating conditions; 2. The separation efficiency of the particle separator is very sensitive to the throat profile area. Changing the profile area by inflation has the problem of low control accuracy, and the volume of the inflated airbag changes relatively slowly; 3. Helicopters usually switch back and forth between different flight altitudes and different flight environments, and the speed of the throat profile change is required to be fast. However, the inflatable bulge structure particle separator has a slow response speed and cannot promptly respond to the sand erosion damage protection requirements under the rapidly changing working conditions of the engine service environment. Summary of the Invention

[0005] To solve the above technical problems, the present invention adopts the following technical solution: a piezoelectrically driven aircraft engine particle separator, comprising a separator housing, a piezoelectric displacement mechanism, a throat profile adjustment mechanism, and a control center; the separator housing comprises an electrostatic sensor, an outer wall, a front section of an inner wall, a support flange, a rear section of an inner wall, a separation tongue, and a total pressure probe; the electrostatic sensors are two in total, one of which is sleeved and fixed at the front air inlet position of the outer wall, and the other is sleeved and fixed at the rear air outlet position of the separation tongue;

[0006] A support flange is provided on the inner side of the outer wall surface, and the support flange consists of two parts: a mounting platform and a mounting disc. The mounting platform is a hexagonal prism, and mounting discs are fixedly installed at both ends of the mounting platform. The front section of the inner wall and the rear section of the inner wall are respectively detachably fixed on the mounting discs at the front and rear ends.

[0007] The piezoelectric displacement mechanism is arranged between the two mounting discs. There are multiple piezoelectric displacement mechanisms, and the number of piezoelectric displacement mechanisms is equal to the number of sides of the mounting platform. The piezoelectric displacement mechanism includes a cylindrical piezoelectric ceramic actuator, a primary stroke amplification ring, a secondary stroke amplification ring, a cylindrical linear guide and a linear motion block.

[0008] The throat profile adjustment mechanism includes a flexible skin, an umbrella-shaped support surface, an umbrella-shaped support bone, and an umbrella-shaped support rod; the secondary stroke amplification ring is fixedly mounted on the side of the mounting platform, two primary stroke amplification rings are fixedly mounted inside the secondary stroke amplification ring, and a cylindrical piezoelectric ceramic actuator is fixedly mounted inside the primary stroke amplification ring;

[0009] The total pressure probe, the electrostatic sensor, and the cylindrical piezoelectric ceramic actuator are all electrically connected to the control center.

[0010] As a preferred technical solution of the present invention, the primary stroke amplification ring and the secondary stroke amplification ring have the same main structure, both of which are hourglass-shaped ring structures. The two sides of the secondary stroke amplification ring perpendicular to the side of the mounting platform are movable sides, and the other two sides are deformable sides. The deformable sides are composed of two deformable rods, both of which are inclined inward, and the ends of the two that are close to each other are connected by a movable block. When the two movable sides approach each other, the angle between the two deformable rods becomes smaller, so that the two movable block parts approach each other.

[0011] As a preferred technical solution of the present invention, the first-stage stroke amplification ring and the second-stage stroke amplification ring are arranged vertically, the two movable blocks of the two first-stage stroke amplification rings close to each other are fixedly connected to each other, and the remaining two movable blocks are fixedly connected to the movable edges of the second-stage stroke amplification ring, and both the first-stage stroke amplification ring and the second-stage stroke amplification ring have partial material removal at the position where deformation is required; the two ends of the cylindrical piezoelectric ceramic actuator are fixedly mounted on the two movable edges of the first-stage stroke amplification ring.

[0012] As a preferred technical solution of the present invention, a linear motion block is fixedly installed on the movable block of the secondary stroke amplification ring away from the mounting table, a cylindrical linear guide rail is fixedly installed on the mounting disc located on the rear side, the linear motion block is slidably connected to the cylindrical linear guide rail, and the movable block of the secondary stroke amplification ring close to the mounting table is fixedly connected to the side of the mounting table.

[0013] As a preferred technical solution of the present invention, the flexible skin is arranged between the two mounting discs, and two sides of the flexible skin are fixedly connected to the circumferential surfaces of the two mounting discs.

[0014] As a preferred technical solution of the present invention, an umbrella-shaped support rod is fixedly installed on the upper side of the movable block of the secondary stroke amplification ring away from one end of the mounting platform, an umbrella-shaped support bone is fixedly installed on the umbrella-shaped support rod, and the top end of the umbrella-shaped support rod is threadedly connected to an umbrella-shaped support surface, the umbrella-shaped support bone is in contact with the lower side surface of the umbrella-shaped support surface, and the umbrella-shaped support surface is in contact with the flexible skin.

[0015] As a preferred technical solution of the present invention, the separation tongue is cylindrical, arranged on the rear side of the support flange and around the outer side surface of the rear section of the inner wall, and the front end of the separation tongue is bent.

[0016] As a preferred technical solution of the present invention, the total pressure probe is fixedly installed on the inner wall of the separated tongue.

[0017] In addition, the present invention also provides an active control method for a piezoelectrically driven aircraft engine particle separator, comprising the following steps: S1, system initialization and initial state: at the beginning of operation, the throat profile adjustment mechanism props up the flexible skin, putting the flexible skin in a taut state, which is the initial state;

[0018] S2. Real-time monitoring of sand concentration: When the flow channel begins to take in air, two electrostatic sensors are immediately activated. The electrostatic sensor located on the outer wall detects the sand concentration in the inhaled air, while the electrostatic sensor located on the separation tongue detects the sand concentration in the treated air. The two electrostatic sensors continuously monitor the sand concentration in the airflow and provide real-time feedback to the external control center.

[0019] S3. Initial throat area calculation and adjustment: After receiving the sand concentration data, the control center calculates the required throat area under current conditions based on the preset desired separation efficiency. Subsequently, the control center adjusts the voltage of the cylindrical piezoelectric ceramic actuator, causing it to deform in the axial direction. The cylindrical piezoelectric ceramic actuator drives the piezoelectric displacement mechanism to begin operation. The piezoelectric displacement mechanism drives the throat profile adjustment mechanism to lift or relax the flexible skin, thereby retracting the flexible skin, thereby changing the throat profile until the sand concentration of the air inhaled into the engine reaches the preset standard. Once the target width is reached, all mechanisms maintain their current positions and do not move.

[0020] S4. Airflow monitoring and secondary optimization adjustment: After completing the first throat area adjustment, the total pressure probe immediately monitors the total intake pressure and transmits the intake total pressure data back to the control center. The control center uses the intake total pressure data to calculate the current airflow; then, the control center makes a second judgment to evaluate whether the current airflow meets the engine's intake requirements; if the judgment result shows that the airflow is sufficient, the current state is maintained; if the judgment result shows that the airflow is insufficient, the control center will start the calculation again to determine a more optimized and accurate throat area; then, the control center controls the voltage of the cylindrical piezoelectric ceramic actuator again according to the new calculated value, and fine-tunes the displacement of the piezoelectric displacement mechanism by controlling the voltage until the throat area meets the standard of allowing the engine to achieve the preset optimal operating conditions while not inhaling sand particles exceeding the limit concentration; if the above requirements cannot be met after more than 5 calculations and adjustments, the control center will feedback to the aircraft console so that the pilot can be informed and remind the pilot to reduce the engine power or reduce the preset expected separation efficiency;

[0021] S5. State maintenance and continuous monitoring: Once the efficiency of sand separation and the airflow rate reach the preset standards, the piezoelectric displacement mechanism will maintain the current height, so that the throat profile adjustment mechanism remains in this optimized position; this state will continue until the electrostatic sensor detects a change in sand concentration again, at which point the system restarts the cycle of steps S2-S4 until the preset expected separation efficiency is achieved.

[0022] The beneficial effects of the present invention are:

[0023] First, the present invention uses two electrostatic sensors to monitor the sand concentration in the air and the concentration of the treated sand in real time, respectively. The total pressure probe obtains the intake total pressure data, and combines the calculation and feedback of the control center to control the throat profile adjustment mechanism to dynamically adjust the throat area. This means that the present invention can respond to changes in the intake environment and ensure that the engine reaches the optimal operating condition under the premise of not inhaling sand exceeding the limit concentration. A dynamic balance is achieved between the optimal engine operating condition and the constantly changing sand concentration in the external environment, thereby greatly improving the aircraft's adaptability in complex environments.

[0024] 2. The present invention can accurately control the elongation size of the cylindrical piezoelectric ceramic actuator only by controlling the voltage, thereby driving the deformation of the flexible skin to change the throat width, and the operation is simple and convenient; and the displacement resolution of the cylindrical piezoelectric ceramic actuator is extremely high, which is sufficient to achieve precise control of the displacement of the umbrella-shaped bracket surface after multi-stage amplification, thereby making the deformation of the flexible skin more accurate.

[0025] 3. The piezoelectric drive mechanism provided on the base of the present invention has the characteristics of small size, compact structure and fast response speed; these characteristics enable the throat profile adjustment mechanism to quickly adjust the throat profile, because the helicopter flies very fast and the external environment switches very quickly, and the response speed of the piezoelectric ceramic is at the millisecond level. Once the sand concentration exceeds the standard, the throat area can be immediately changed to prevent more sand from entering the engine, which reliably protects the engine and extends its service life; at the same time, the compact design is also conducive to the integration and installation of the present invention in the limited space of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The present invention will be further described below with reference to the accompanying drawings and examples.

[0027] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention.

[0028] Figure 2 It is a schematic diagram of the layout of the piezoelectric displacement mechanism and the throat profile adjustment mechanism of the present invention.

[0029] Figure 3 It is a structural schematic diagram of the piezoelectric displacement mechanism of the present invention.

[0030] Figure 4 It is a schematic diagram of the working stroke of the piezoelectric displacement mechanism of the present invention.

[0031] Figure 5 It is a cross-sectional view of the piezoelectric displacement mechanism and the umbrella-shaped bracket of the present invention.

[0032] In the figure: 1. Separator housing; 11. Electrostatic sensor; 12. Outer wall; 13. Front section of inner wall; 14. Support flange; 141. Mounting platform; 142. Mounting disc; 15. Rear section of inner wall; 16. Separation tongue; 17. Total pressure probe; 2. Piezoelectric displacement mechanism; 21. Cylindrical piezoelectric ceramic actuator; 22. Primary stroke amplification ring; 23. Secondary stroke amplification ring; 24. Cylindrical linear guide; 25. Linear motion block; 3. Throat profile adjustment mechanism; 31. Flexible skin; 32. Umbrella-shaped bracket surface; 33. Umbrella-shaped bracket bone; 34. Umbrella-shaped bracket rod. DETAILED DESCRIPTION

[0033] The embodiments of the present invention are described in detail below.

[0034] See Figure 1-Figure 3 、 Figure 5 A piezoelectrically driven aircraft engine particle separator comprises a separator shell 1, a piezoelectric displacement mechanism 2, a throat profile adjustment mechanism 3, and a control center; the separator shell 1 comprises an electrostatic sensor 11, an outer wall 12, an inner wall front section 13, a support flange 14, an inner wall rear section 15, a separation tongue 16, and a total pressure probe 17; there are two electrostatic sensors 11, one of which is sleeved and fixed at the front air inlet position of the outer wall 12, and the other is sleeved and fixed at the rear air outlet position of the separation tongue 16; the separation tongue 16 is cylindrical, and the separation tongue 16 is arranged on the rear side of the support flange 14 and around the outer side surface of the inner wall rear section 15, and the front end of the separation tongue 16 is bent; the total pressure probe 17 is fixedly installed on the inner side wall of the separation tongue 16.

[0035] The two electrostatic sensors 11 provided in the present invention respectively monitor the sand concentration in the air and the sand concentration after treatment in real time, obtain the total intake pressure data through the total pressure probe 17, and combine the calculation and feedback of the control center to control the throat profile adjustment mechanism 3 to dynamically adjust the throat area. This means that the present invention can respond according to changes in the intake environment, and can ensure that the engine reaches the optimal operating condition under the premise of not inhaling sand exceeding the limit concentration. A dynamic balance is achieved between the optimal operating condition of the engine and the constantly changing sand concentration in the outside world, thereby greatly improving the adaptability of the aircraft in complex environments.

[0036] Specifically, when the flow channel begins to take in air, the electrostatic sensor 11 is immediately activated, continuously monitoring the sand concentration in the incoming airflow and providing real-time feedback to the external control center. After receiving the sand concentration data, the control center calculates the appropriate throat area under the current conditions based on a preset algorithm, the current aircraft flight altitude, and the preset expected separation efficiency. Subsequently, the control center controls the throat profile adjustment mechanism 3 to change the throat profile until the throat reaches the set width. At this time, the sand concentration of the inhaled air and the total intake pressure both meet the preset standards. After reaching the target width, all mechanisms maintain their current positions and do not move.

[0037] After completing the first throat area adjustment, the total pressure probe 17 immediately monitors the total intake pressure and transmits the data back to the control center. The control center uses this total pressure data to calculate the current airflow rate; then, the control center makes a second judgment to evaluate whether the current airflow rate meets the requirements of various performance indicators, such as whether it meets the engine's intake needs; if the judgment result shows that the airflow rate is insufficient or does not meet the standard, the control center will start the calculation again to determine a more optimized and accurate throat area, and then the control center controls the throat profile adjustment mechanism 3 to change the throat profile until the throat reaches the set width, until the sand concentration of the inhaled air and the total intake pressure reach the preset standards.

[0038] See Figures 1-4 A support flange 14 is provided on the inner side of the outer wall surface 12. The support flange 14 consists of two parts: a mounting platform 141 and a mounting disc 142. The mounting platform 141 is a hexagonal prism. The mounting discs 142 are fixedly installed at both ends of the mounting platform 141. The front section 13 of the inner wall and the rear section 15 of the inner wall are respectively detachably fixed on the mounting discs 142 at the front and rear ends. The piezoelectric displacement mechanism 2 is provided between the two mounting discs 142. There are multiple piezoelectric displacement mechanisms 2. The number of piezoelectric displacement mechanisms 2 is equal to the number of sides of the mounting platform 141. The piezoelectric displacement mechanism 2 includes a cylindrical piezoelectric ceramic actuator. 21, a primary stroke amplification ring 22, a secondary stroke amplification ring 23, a cylindrical linear guide 24 and a linear motion block 25; the throat profile adjustment mechanism 3 includes a flexible skin 31, an umbrella-shaped bracket surface 32, an umbrella-shaped bracket bone 33, and an umbrella-shaped bracket rod 34; the secondary stroke amplification ring 23 is fixedly installed on the side of the mounting platform 141, and two primary stroke amplification rings 22 are fixedly installed on the inner side of the secondary stroke amplification ring 23, and a cylindrical piezoelectric ceramic actuator 21 is fixedly installed in the primary stroke amplification ring 22; the total pressure probe 17, the electrostatic sensor 11, and the cylindrical piezoelectric ceramic actuator 21 are all electrically connected to the control center.

[0039] The present invention can accurately control the elongation size of the cylindrical piezoelectric ceramic actuator 21 by simply controlling the voltage, thereby driving the deformation of the flexible skin 31 to change the throat width, and the operation is simple and convenient; and the displacement resolution of the cylindrical piezoelectric ceramic actuator 21 is extremely high, which is sufficient to achieve precise control of the displacement of the umbrella-shaped bracket surface 32 after multi-stage amplification, thereby making the deformation of the flexible skin 31 more accurate.

[0040] See Figure 1-Figure 5 The main structure of the first-stage stroke magnifying ring 22 and the second-stage stroke magnifying ring 23 is the same. Both are hourglass-shaped ring structures. The two sides of the second-stage stroke magnifying ring 23 perpendicular to the side of the mounting platform 141 are movable sides, and the other two sides are deformable sides. The deformable sides are composed of two deformable rods. The two deformable rods are inclined inward, and the ends close to each other are connected by a movable block. When the two movable sides approach each other, the angle between the two deformable rods becomes smaller, so that the two movable blocks are close to each other; the first-stage stroke magnifying ring 22 and the second-stage stroke magnifying ring 23 are arranged vertically, and the two movable blocks of the two first-stage stroke magnifying rings 22 close to each other are fixedly connected to each other, and the other two movable blocks are fixedly connected to each other. The moving block is fixedly connected to the moving edge of the secondary stroke amplification ring 23, and both the primary stroke amplification ring 22 and the secondary stroke amplification ring 23 have partial material removed at the position where deformation is required; the two ends of the cylindrical piezoelectric ceramic actuator 21 are fixedly mounted on the two moving edges of the primary stroke amplification ring 22; the secondary stroke amplification ring 23 is fixedly mounted with an umbrella-shaped support rod 34 on the upper side of the movable block away from the mounting platform 141, and an umbrella-shaped support bone 33 is fixedly mounted on the umbrella-shaped support rod 34. The top end of the umbrella-shaped support rod 34 is threadedly connected with an umbrella-shaped support surface 32, the umbrella-shaped support bone 33 is in contact with the lower side of the umbrella-shaped support surface 32, and the umbrella-shaped support surface 32 is in contact with the flexible skin 31.

[0041] The piezoelectric displacement mechanism 2 provided on the base of the present invention has the characteristics of small size, compact structure and fast response speed; these characteristics enable the throat profile adjustment mechanism 3 to achieve rapid throat profile adjustment, because the helicopter flies very quickly and various working conditions switch very quickly, and the response speed of the cylindrical piezoelectric ceramic actuator 21 is at the millisecond level. Once the sand concentration exceeds the standard, the throat area can be changed immediately, which reliably protects the engine; at the same time, the compact design is also conducive to the integration and installation of the present invention in the limited space of the aircraft engine.

[0042] Specifically, when the throat area needs to be adjusted, the control center adjusts the voltage of the cylindrical piezoelectric ceramic actuator 21 to cause it to deform in the axial direction. The cylindrical piezoelectric ceramic actuator 21 drives the first-stage stroke amplification ring 22 to begin to deform, and then the first-stage stroke amplification ring 22 drives the second-stage stroke amplification ring 23 to deform. The second-stage stroke amplification ring 23 drives the umbrella-shaped support surface 32 through the umbrella-shaped support rod 34 to lift or relax the flexible skin 31 to retract it. The small-sized deformation of the cylindrical piezoelectric ceramic actuator 21 is amplified by the first-stage stroke amplification ring 22 and the second-stage stroke amplification ring 23 to become a large-sized displacement of the umbrella-shaped support surface 32. Since the reaction speed of the cylindrical piezoelectric ceramic actuator 21 is at the millisecond level, the flexible skin 31 can be quickly lifted or retracted, and the throat profile can be quickly adjusted to reliably protect the engine. The umbrella-shaped support bone 33 is used to support and reinforce the umbrella-shaped support surface 32.

[0043] See Figure 3 The secondary stroke amplification ring 23 is fixedly mounted with a linear motion block 25 on the movable block at one end away from the mounting platform 141, and a cylindrical linear guide rail 24 is fixedly mounted on the mounting disc 142 at the rear side. The linear motion block 25 is slidably connected to the cylindrical linear guide rail 24, and the movable block of the secondary stroke amplification ring 23 close to the mounting platform 141 is fixedly connected to the side of the mounting platform 141.

[0044] The cooperation between the cylindrical linear guide rail 24 and the linear motion block 25 can ensure that the displacement is a precise linear motion, thereby ensuring a better and more accurate adjustment effect.

[0045] Specifically, when the cylindrical piezoelectric ceramic actuator 21 drives the piezoelectric displacement mechanism 2 to start working, the linear motion block 25 slides along the cylindrical linear guide rail 24 to correct the motion trajectory of the umbrella-shaped bracket surface 32 so that the motion trajectory always remains straight to ensure the accuracy of the displacement size.

[0046] See Figure 5 The flexible skin 31 is arranged between the two mounting discs 142 , and the two sides of the flexible skin 31 are fixedly connected to the circumferential surfaces of the two mounting discs 142 .

[0047] It should be noted that the flexible skin 31 itself is a special composite material, which is composed of high-strength nylon fabric and silicone rubber with good elasticity. Its surface is also coated with a layer of wear-resistant material, which gives the skin elastic deformation ability and erosion and wear resistance, helping it to maintain long-term reliability and durability under high-speed airflow and high-concentration sand erosion.

[0048] In the non-working state, the flexible skin 31 is propped up to ensure that the flow channel maintains a normal and smooth geometric shape; when working, the flexible skin 31 can bulge upward or shrink downward through the movement of the driving mechanism, thereby changing the throat area; when the concentration of sand particles in the air increases, the control center controls the voltage to increase so that the cylindrical piezoelectric ceramic actuator 21 extends, thereby driving the throat profile adjustment mechanism 3 to lift the flexible skin 31, reducing the throat area, increasing the separation efficiency, and reducing the air intake volume until the preset expected separation efficiency is reached. If the concentration of sand particles in the air decreases, the opposite is true.

[0049] A method for operating a piezoelectrically driven aerospace engine particle separator comprises the following steps:

[0050] S1. System initialization and initial state: At the beginning of operation, the throat profile adjustment mechanism 3 props up the flexible skin 31, so that the flexible skin 31 is in a taut state, which is the initial state;

[0051] S2. Real-time monitoring of sand concentration: When the flow channel begins to take in air, the two electrostatic sensors 11 are immediately activated. The electrostatic sensor 11 located on the outer wall 12 detects the sand concentration in the inhaled air, while the electrostatic sensor 11 located on the separation tongue 16 detects the sand concentration in the treated air. Both sensors continuously monitor the sand concentration in the airflow and provide real-time feedback to the external control center.

[0052] S3. Initial throat area calculation and adjustment: After receiving the sand concentration data, the control center calculates the appropriate throat area under current conditions based on a preset algorithm, the current aircraft's flight altitude, and the preset expected separation efficiency. Subsequently, the control center adjusts the voltage of the cylindrical piezoelectric ceramic actuator 21 to cause it to deform in the axial direction. The cylindrical piezoelectric ceramic actuator 21 drives the primary stroke amplification ring 22 to begin to deform, which then drives the secondary stroke amplification ring 23 to deform. The secondary stroke amplification ring 23 drives the umbrella support surface 32 via the umbrella support rod 34 to lift or relax the flexible skin 31, thereby changing the throat profile until the electrostatic sensor 11 on the separation tongue 16 detects that the sand concentration of the air inhaled into the engine reaches a preset standard. Once the target width is reached, all mechanisms remain in their current positions and do not move.

[0053] S4. Airflow monitoring and secondary optimization adjustment: After completing the first throat area adjustment, the total pressure probe 17 immediately monitors the total intake pressure and transmits the data back to the control center. The control center uses this total pressure data to calculate the current airflow; then, the control center makes a second judgment to evaluate whether the current airflow meets the engine's intake requirements; if the judgment result shows that the airflow is sufficient, the current state is maintained; if the judgment result shows that the airflow is insufficient or does not meet the standard, the control center will start the calculation again to determine a more optimized and accurate throat area; then, the control center controls the voltage of the cylindrical piezoelectric ceramic actuator 21 again according to the new calculated value, and fine-tunes the displacement of the piezoelectric displacement mechanism 2 by controlling the voltage until the throat area meets the standard of allowing the engine to achieve the preset optimal operating condition without inhaling sand particles exceeding the limit concentration; if the above requirements cannot be met after more than 5 calculations and adjustments, the control center will feed this information back to the aircraft console so that the pilot can be informed and remind the pilot to reduce the engine power or reduce the preset expected separation efficiency;

[0054] S5. State maintenance and continuous monitoring: Once the efficiency of separating sand particles and the airflow rate reach the preset standards, the piezoelectric displacement mechanism 2 will maintain the current height, so that the throat profile adjustment mechanism 3 remains in this optimized position; this state will continue to be maintained until the electrostatic sensor 11 detects a change in sand concentration again. At this time, the system restarts the cycle of steps S2-S4. When the sand concentration in the air increases, the voltage increases, causing the cylindrical piezoelectric ceramic actuator 21 to extend, thereby driving the throat profile adjustment mechanism 3 to lift the flexible skin 31, reducing the throat area, thereby increasing the separation efficiency and reducing the air intake volume until the preset expected separation efficiency is reached. If the sand concentration in the air decreases, the opposite is true.

[0055] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. A person skilled in the art may make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention, which are still covered by the scope of protection of the present invention.

Claims

1. A piezoelectrically driven aerospace engine particle separator, characterized in that: The separator comprises a separator housing (1), a piezoelectric displacement mechanism (2), a throat profile adjustment mechanism (3), and a control center; the separator housing (1) comprises an electrostatic sensor (11), an outer wall surface (12), an inner wall front section (13), a support flange (14), an inner wall rear section (15), a separation tongue (16), and a total pressure probe (17); there are two electrostatic sensors (11), one of which is sleeved and fixed at the front air inlet position of the outer wall surface (12), and the other is sleeved and fixed at the rear air outlet position of the separation tongue (16); A support flange (14) is provided on the inner side of the outer wall surface (12), and the support flange (14) is composed of two parts: a mounting platform (141) and a mounting disc (142). The mounting platform (141) is a hexagonal prism, and the mounting discs (142) are fixedly mounted on both the front and rear ends of the mounting platform (141). The front section (13) and the rear section (15) of the inner wall surface are respectively and detachably fixedly mounted on the mounting discs (142) at the front and rear ends. The piezoelectric displacement mechanism (2) is arranged between the two mounting discs (142), a plurality of piezoelectric displacement mechanisms (2) are provided, and the number of the piezoelectric displacement mechanisms (2) is equal to the number of sides of the mounting platform (141), and the piezoelectric displacement mechanism (2) includes a cylindrical piezoelectric ceramic actuator (21), a primary stroke amplification ring (22), a secondary stroke amplification ring (23), a cylindrical linear guide rail (24) and a linear motion block (25); The throat profile adjustment mechanism (3) comprises a flexible skin (31), an umbrella-shaped support surface (32), an umbrella-shaped support bone (33), and an umbrella-shaped support rod (34); the secondary stroke amplification ring (23) is fixedly mounted on the side of the mounting platform (141), two primary stroke amplification rings (22) are fixedly mounted inside the secondary stroke amplification ring (23), and a cylindrical piezoelectric ceramic actuator (21) is fixedly mounted inside the primary stroke amplification ring (22); The total pressure probe (17), the electrostatic sensor (11), and the cylindrical piezoelectric ceramic actuator (21) are all electrically connected to the control center.

2. A piezoelectrically driven aerospace engine particle separator according to claim 1, characterized in that: The primary stroke amplifying ring (22) and the secondary stroke amplifying ring (23) have the same main structure, both of which are hourglass-shaped ring structures. The two sides of the secondary stroke amplifying ring (23) perpendicular to the side of the mounting platform (141) are movable sides, and the other two sides are deformable sides. The deformable sides are composed of two deformable rods. The two deformable rods are inclined inward, and the ends of the two rods that are close to each other are connected by a movable block. When the two movable sides are close to each other, the angle between the two deformable rods becomes smaller, so that the two movable block parts are close to each other.

3. A piezoelectrically driven aerospace engine particle separator according to claim 2, characterized in that: The first-stage amplifying ring (22) and the second-stage amplifying ring (23) are arranged vertically, two movable blocks of the two first-stage amplifying rings (22) that are close to each other are fixedly connected to each other, and the remaining two movable blocks are fixedly connected to the movable sides of the second-stage amplifying ring (23), and both the first-stage amplifying ring (22) and the second-stage amplifying ring (23) have part of their materials removed at positions where deformation is required; and both ends of the cylindrical piezoelectric ceramic actuator (21) are fixedly mounted on the two movable sides of the first-stage amplifying ring (22).

4. A piezoelectrically driven aerospace engine particle separator according to claim 3, characterized in that: A linear motion block (25) is fixedly mounted on a movable block at one end of the secondary stroke amplifying ring (23) away from the mounting platform (141), a cylindrical linear guide rail (24) is fixedly mounted on the mounting disc (142) located at the rear side, the linear motion block (25) is slidably connected to the cylindrical linear guide rail (24), and a movable block at one end of the secondary stroke amplifying ring (23) close to the mounting platform (141) is fixedly connected to a side surface of the mounting platform (141).

5. The piezoelectrically driven aerospace engine particle separator according to claim 1, characterized in that: The flexible skin (31) is arranged between the two mounting discs (142), and two sides of the flexible skin (31) are fixedly connected to the circumferential surfaces of the two mounting discs (142).

6. The piezoelectrically driven aerospace engine particle separator according to claim 3, characterized in that: An umbrella-shaped support rod (34) is fixedly mounted on the upper side of a movable block at one end of the secondary stroke amplifying ring (23) away from the mounting platform (141), an umbrella-shaped support bone (33) is fixedly mounted on the umbrella-shaped support rod (34), and an umbrella-shaped support surface (32) is threadedly connected to the top end of the umbrella-shaped support rod (34), the umbrella-shaped support bone (33) contacts the lower side of the umbrella-shaped support surface (32), and the umbrella-shaped support surface (32) contacts the flexible skin (31).

7. The piezoelectrically driven aerospace engine particle separator according to claim 1, characterized in that: The separation tongue (16) is cylindrical and is arranged on the rear side of the support flange (14) and around the outer side surface of the rear section (15) of the inner wall surface. The front end of the separation tongue (16) is bent.

8. The piezoelectrically driven aero-engine particle separator according to claim 7, characterized in that: The total pressure probe (17) is fixedly mounted on the inner wall of the separation tongue (16).

9. An active control method for a piezoelectrically driven aero-engine particle separator, applied to a piezoelectrically driven aero-engine particle separator according to any one of claims 4 to 8, characterized in that: The steps include: S1. System initialization and initial state: At the beginning of operation, the throat profile adjustment mechanism (3) props up the flexible skin (31), so that the flexible skin (31) is in a taut state, which is the initial state; S2. Real-time monitoring of sand concentration: When the flow channel begins to take in air, the two electrostatic sensors (11) are immediately activated. The electrostatic sensor (11) located on the outer wall (12) detects the sand concentration in the inhaled air, while the electrostatic sensor (11) located on the separation tongue (16) detects the sand concentration in the air after treatment. The two electrostatic sensors (11) continuously monitor the sand concentration in the air flow and provide real-time feedback to the external control center. S3. First throat area calculation and adjustment: After receiving the sand concentration data, the control center calculates the required throat area under the current conditions according to the preset expected separation efficiency; then, the control center adjusts the voltage of the cylindrical piezoelectric ceramic actuator (21) to cause the cylindrical piezoelectric ceramic actuator (21) to deform in the axial direction, and the cylindrical piezoelectric ceramic actuator (21) drives the piezoelectric displacement mechanism (2) to start working, and the piezoelectric displacement mechanism (2) drives the throat profile adjustment mechanism (3) to lift or relax the flexible skin (31) to retract the flexible skin (31), thereby changing the throat profile until the concentration of the sand particles in the air sucked into the engine reaches the preset standard; after reaching the target width, all mechanisms maintain their current positions and do not move; S4. Airflow monitoring and secondary optimization adjustment: After completing the first throat area adjustment, the total pressure probe (17) immediately monitors the total intake pressure and transmits the intake total pressure data back to the control center. The control center uses the intake total pressure data to calculate the current airflow; then, the control center makes a second judgment to evaluate whether the current airflow meets the engine's intake demand; if the judgment result shows that the airflow is sufficient, the current state is maintained; if the judgment result shows that the airflow is insufficient, the control center will start the calculation again to determine a more optimized and accurate throat area; then, the control center controls the voltage of the cylindrical piezoelectric ceramic actuator (21) again according to the new calculated value, and fine-tunes the displacement of the piezoelectric displacement mechanism (2) by controlling the voltage until the throat area meets the standard of allowing the engine to achieve the preset optimal operating condition while not inhaling sand particles exceeding the limit concentration; if the above requirements cannot be met after more than 5 calculations and adjustments, the control center will feedback to the aircraft console to inform the pilot and remind the pilot to reduce the engine power or reduce the preset expected separation efficiency; S5. State maintenance and continuous monitoring: Once the efficiency of separating sand particles and the air flow rate reach the preset standards, the piezoelectric displacement mechanism (2) will maintain the current height, so that the throat profile adjustment mechanism (3) remains in this optimized position; this state will continue to be maintained until the electrostatic sensor (11) detects a change in sand particle concentration again, at which point the system restarts the cycle of steps S2-S4 until the preset desired separation efficiency is achieved.

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