Axial Force Measuring Device for Aeroengine Rotor Based on Distributed Piezoelectric Stack

Abstract

The present invention belongs to the technical field of aero-engine testing. The present invention discloses an axial force measurement device for an aero-engine rotor based on a distributed piezoelectric stack, which includes a base, a sensing assembly, a top cover, a sealing mechanism, and necessary threaded connection structures. The axial force measurement device for the rotor is fixed between a load-bearing casing and a squirrel-cage elastic support. The load-bearing casing is connected to the top cover, and the squirrel-cage elastic support is connected to the sensing assembly by a force-transmitting ejector rod; a pressure-side piezoelectric stack is arranged between the base and the sensing assembly to measure the axial force of the rotor on the pressure side; a tension-side piezoelectric stack is arranged between the top cover and the sensor assembly to measure the axial force of the rotor on the tension side. The present invention overcomes the problems of the existing strain-type sensors being greatly affected by the environment, having poor repeatability, and insufficient accuracy, and has the advantages of high measurement accuracy, being able to obtain the circumferential distribution state of the axial force in real time, being convenient for installation and disassembly, etc., and can be used to test the bidirectional axial force of the rotor at various different speeds.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine testing, and particularly relates to an aero-engine rotor axial force measuring device based on a distributed piezoelectric stack. Background Art

[0002] Air superiority is one of the key factors for victory in modern warfare. The aircraft power system related thereto, namely the advanced aero-engine, has thus become one of the core technologies of modern weaponry. With the development of aero-engines independently designed in China towards high performance, high structural efficiency, high safety, and a wide operating range, the complex load environment and the resulting structural damage and failure have seriously affected the development, mass production, and use of the engines. Among these loads, the aerodynamic loads during the engine operation and the inertial overloads caused by the complex maneuvering flight states of the aircraft are of particular concern. The axial component of these forces on the rotor system is the aero-engine rotor axial force. In the design of aero-engines, the rotor axial force is an important factor affecting the component strength, life, and reliability, restricting the mechanical properties of important structures such as the bearing-support structure, load-bearing frame, load-bearing casing, and mounting structure on the rotor system and the force transmission route. However, due to the excessive complexity of the aero-engine stator-rotor structural system and its working environment, it is difficult to accurately obtain the rotor axial force through theoretical analysis and simulation calculations. Therefore, there is an urgent need for experimental measurement methods.

[0003] Currently, the widely used aero-engine axial force test system needs to replace the original structure with a separately designed bearing-support structure to support the rotor under test. The method is to first measure the strain of the elastic ring installed between the outer ring of the bearing and the bearing housing, and then obtain the measurement result through the conversion between the strain and the axial force. Research shows that such test systems have the following problems:

[0004] Problem 1 of the existing test system: The measurement accuracy cannot be guaranteed. The reasons are as follows: 1) The elastic ring with strain gauges attached is not a standard sensor, and the axial force measurement result is directly affected by factors such as the strain gauge attachment state, the machining quality of the elastic ring, and the bridge circuit difference ([1] Fu Yu, Zhao Dan, Hui Guanglin, et al. Improvement of the Experiment and Calculation of Aero-Engine Rotor Axial Force [J]. Gas Turbine Experiment and Research, 2020, 33(5): 1-5.); 2) During the test process, the axial force cannot be directly obtained and needs to be converted through strain. The strain of the elastic ring under different working conditions is significantly affected by factors such as the configuration of the elastic ring itself, the temperature distribution, and the mechanical load distribution, and these effects cannot be accurately evaluated under all working conditions.

[0005] Problem 2 of the existing test system: It is impossible to ensure measurement accuracy. Since the original bearing-support structure of the engine needs to be replaced, such test systems will encounter many difficulties when applied in the whole-machine bench test and flight test. Moreover, the installation tightness of the inner and outer rings of the bearings used in the test system, the bearing clearance, and the bearing cooling and lubrication system will all change compared with the original system. These changes will alter the motion state of the rotor and the load transfer characteristics, ultimately affecting the accuracy of axial force measurement.

[0006] Problem 3 of the existing test system: It is impossible to ensure the consistency of installation and disassembly. Since the elastic ring is a non-standard part, it generally needs to be recalibrated for different test states of the same batch. When facing different models of tests, it often requires redesigning the elastic ring structure. The measurement system cannot be standardized, the installation and disassembly are time-consuming and laborious, and the dispersion of measurement data is significant.

[0007] In summary, the existing rotor axial force test system cannot meet the requirements in terms of measurement accuracy and precision. The development of modern aero-engines urgently requires axial force measurement data with high precision, good accuracy, and excellent repeatability as the input conditions and output verification for design. Therefore, the present invention provides a beneficial method, which cancels the elastic ring strain sensor for indirect measurement and replaces it with a high-precision axial force measurement device that directly measures using a piezoelectric stack array, has the potential for standardization, and is convenient for installation and disassembly. Summary of the Invention

[0008] The purpose of the present invention is to provide an aero-engine rotor axial force measurement device based on a distributed piezoelectric stack to solve the problems existing in the above-mentioned prior art.

[0009] To achieve the above purpose, the present invention provides the following solution: The present invention provides an aero-engine rotor axial force measurement device based on a distributed piezoelectric stack, which is fixed between the load-bearing casing and the squirrel-cage elastic support, and includes a base, and the base is connected to the load-bearing casing;

[0010] A top cover, the top cover is adapted to the base, and a sealing mechanism is provided between the top cover and the base, and the top cover is connected to the flange of the squirrel-cage elastic support;

[0011] A sensing component, after the top cover and the base are adapted, a sealed cavity is formed, the sensing component is located in the sealed cavity, and is respectively connected to the base and the top cover; the sensing component includes a curved beam, and a number of piezoelectric stacks are circumferentially and equidistantly distributed on both sides of the curved beam, and the piezoelectric stacks are connected to an external information processing device through signal lines;

[0012] The curved beam is a rigid-flexible integrated structure.

[0013] Preferably, the piezoelectric stack arranged between the curved beam and the base is a pressure-side piezoelectric stack; and the piezoelectric stack arranged between the curved beam and the top cover is a tension-side piezoelectric stack.

[0014] Preferably, the curved beam comprises a plurality of bridge-shaped short beams, a flexible transition section is fixedly connected between two adjacent bridge-shaped short beams, a pedestal is fixedly connected between two adjacent flexible transition sections, and the bridge-shaped short beams and the pedestal are respectively connected to the base and the top cover.

[0015] Preferably, the plurality of bridge-shaped short beams, the flexible transition section and the pedestal are an integrally formed structure.

[0016] Preferably, the sealing mechanism comprises an outer ring sealing ring and an inner ring sealing ring embedded between the base and the top cover.

[0017] Preferably, the top cover is connected to the flange edge of the squirrel cage elastic support through a first fastening mechanism, and the base is connected to the load-bearing casing through a second fastening mechanism.

[0018] Preferably, the first fastening mechanism comprises a force transmission push rod, one side of which connects the top cover and the curved beam, and the other side of which penetrates through the flange edge of the squirrel cage elastic support and is fixed with a locking nut I.

[0019] Preferably, the second fastening mechanism comprises a locking screw, a locking plate is sleeved on the locking screw, and the locking screw passes through the top cover, the curved beam and the base in sequence and is connected to the load-bearing casing.

[0020] The beneficial effects of the present invention are:

[0021] 1. The rotor axial force measuring device of the present invention can measure the axial forces of the tension side and the pressure side in a balanced and stable manner by setting a curved beam, and setting a number of pressure-side piezoelectric stacks and a number of tension-side piezoelectric stacks equidistantly on both sides of the curved beam in the circumferential direction, as well as its special force transmission path: the curved beam has a rigid-flexible integrated structure, which can achieve effective load balancing between different piezoelectric stacks; since a number of pressure-side piezoelectric stacks and a number of tension-side piezoelectric stacks are encapsulated in a sealed cavity, no secondary debugging is required after calibration, and it has high stability and consistency of multiple tests; at the same time, the piezoelectric stack is a multi-layered structure, which can achieve accurate measurement of axial load. Therefore, the present invention can effectively improve the accuracy of axial force measurement.

[0022] 2. By designing the spatial distribution of the sensor components and the high-rigidity closed shell composed of a base and a top cover, the measuring device has high integrity and is easy to install and disassemble. The relatively sensitive bearing-support structure can be installed without changing the device, so the impact on the engine rotor system is small and the measurement accuracy is high.

[0023] 3. By setting up piezoelectric stacks distributed circumferentially along the curved beam, a new function is achieved: it can give high-precision measurement results of the circumferential distribution of the axial force in real time, and based on this, the vector direction of the axial force can be judged. It can provide a measurement basis for the angular deformation occurring at the bearing when the rotor pitches or bends, which cannot be achieved by existing measurement means. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The drawings forming a part of this application are used to provide a further understanding of this application. The schematic embodiments of this application and their descriptions are used to explain this application and do not constitute an improper limitation to this application. In the drawings:

[0025] Figure 1 It is a schematic diagram of the axial force measurement scheme for an aero-engine rotor;

[0026] Figure 2 It is the structural appearance diagram of the embodiment of the present invention;

[0027] Figure 3 It is the schematic structural decomposition diagram of the embodiment of the present invention;

[0028] Figure 4 It is Figure 3 the schematic structural diagram of the sensor assembly in

[0029] Figure 5 It is Figure 4 the schematic structural diagram of the curved beam in

[0030] Figure 6 It is Figure 3 the schematic structural diagram of the base in

[0031] Figure 7 It is Figure 2 the A-A cross-sectional view in

[0032] Figure 8 It is Figure 2 the B-B cross-sectional view in

[0033] Figure 9 It is Figure 2 the C-C cross-sectional view in

[0034] Among them, 1 - load-bearing casing; 2 - rotor axial force measuring device; 3 - squirrel-cage elastic support; 4 - thrust bearing; 5 - aero-engine rotor; 6 - top cover; 61 - top cover through-hole Ⅰ; 62 - top cover through-hole Ⅱ; 7 - base; 71 - base through-hole; 8 - curved beam; 81 - curved beam through-hole; 82 - curved beam screw hole; 83 - bridge-shaped short beam; 84 - flexible transition section; 85 - pedestal; 9 - sealing ring for force-transmitting push rod; 10 - sealing ring for locking screw; 11 - outer ring sealing ring; 12 - inner ring sealing ring; 13 - piezoelectric stack on the pressure side; 14 - piezoelectric stack on the tension side; 15 - force-transmitting push rod; 16 - locking nut Ⅰ; 17 - locking screw; 18 - lock washer; 19 - locking nut Ⅱ. Specific embodiments

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention 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 of 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.

[0036] To make the above objects, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below with reference to the drawings and specific embodiments.

[0037] Referring to Figures 1-9 , the present invention provides an aero-engine rotor axial force measuring device based on a distributed piezoelectric stack, which is fixed between the load-bearing casing 1 and the squirrel-cage elastic support 3, and includes a base 7, and the base 7 is connected to the load-bearing casing 1;

[0038] A top cover 6, the top cover 6 is adapted to the base 7, and a sealing mechanism is provided between the top cover 6 and the base 7, and the top cover 6 is connected to the flange of the squirrel-cage elastic support 3;

[0039] A sensing assembly, after the top cover 6 and the base 7 are adapted, a sealed cavity is formed, the sensing assembly is located in the sealed cavity, and is respectively connected to the base 7 and the top cover 6; the sensing assembly includes a curved beam 8, and a plurality of piezoelectric stacks are circumferentially and equidistantly distributed on both sides of the curved beam 8, and the piezoelectric stacks are connected to an external information processing device (not shown in the figure) through signal lines;

[0040] The curved beam 8 is a rigid-flexible integrated structure.

[0041] As a further optimized solution, the piezoelectric stack provided between the curved beam 8 and the base 7 is the piezoelectric stack 13 on the pressure side; the piezoelectric stack provided between the curved beam 8 and the top cover 6 is the piezoelectric stack 14 on the tension side.

[0042] Furthermore, the curved beam 8 includes a plurality of bridge-shaped short beams 83. A flexible transition section 84 is fixedly connected between two adjacent bridge-shaped short beams 83. A pedestal 85 is fixedly connected between two adjacent flexible transition sections 84. The bridge-shaped short beams 83 and the pedestal 85 are respectively connected to the base 7 and the top cover 6.

[0043] Furthermore, the plurality of bridge-shaped short beams 83, the flexible transition sections 84 and the pedestal 85 are of an integrally formed structure; the bridge-shaped short beams 83, the flexible transition sections 84 and the pedestal 85 are made of the same material, and the structural stiffness of the flexible transition section 84 is relatively low.

[0044] Specifically, as Figures 3-5 shown, in order to facilitate the installation of the pressure-side piezoelectric stack 13 and the tension-side piezoelectric stack 14, a plurality of shallow grooves (not marked in the figure) are respectively formed on both sides of the curved beam 8, and are respectively located on the bridge-shaped short beams 83. At the same time, the positions of the shallow grooves on both sides of the curved beam 8 are arranged in one-to-one correspondence. The pressure-side piezoelectric stack 13 is embedded in the shallow groove on the convex surface of the bridge-shaped short beam 83, and the tension-side piezoelectric stack 14 is embedded in the shallow groove on the concave surface of the bridge-shaped short beam 83; in addition, in order to facilitate the assembly of the rotor axial force measuring device 2, a plurality of curved beam through holes 81 are formed on the bridge-shaped short beam 83, and a curved beam screw hole 82 is formed on the pedestal 85. When assembling, first select the number of the bridge-shaped short beams 83, the flexible transition sections 84 and the pedestal 85, and then complete the processing through integral processing. Then, shallow grooves, curved beam through holes 81 and curved beam screw holes 82 are respectively formed on the processed curved beam 8. After connecting the curved beam 8, the base 7 and the top cover 6 by using the first fastening mechanism and the second fastening mechanism, they are respectively fixed to the bearing housing 1 and the squirrel cage elastic support 3 to complete the assembly of the rotor axial force measuring device 2. Among them, the bridge-shaped short beam 83 is preferably 8 sections, and is a bridge-shaped short beam 83 with relative rigidity; the flexible transition section 84 is preferably 16 sections, the pedestal 85 is preferably 8 sections, and then the above-mentioned number of bridge-shaped short beams 83, flexible transition sections 84 and pedestal 85 are completed through integral processing; the curved beam through holes 81 are 8, and the curved beam screw holes 82 are 8; at the same time, the radial dimension of the curved beam 8 is adapted to the flange of the squirrel cage elastic support 3; the pressure-side piezoelectric stack 13 is preferably 16, and is evenly distributed in the circumferential direction, and the included angle between the perpendicular bisectors of the circumferentially adjacent pressure-side piezoelectric stacks 13 is 22.5°; the tension-side piezoelectric stack 14 is preferably 16, and is evenly distributed in the circumferential direction, and the included angle between the perpendicular bisectors of the circumferentially adjacent tension-side piezoelectric stacks 14 is 22.5°; the shallow grooves on the convex surface of the bridge-shaped short beam 83 of the curved beam 8 are 16, which are adapted to the pressure-side piezoelectric stack 13, and the groove depth is 1.5 mm; the shallow grooves on the concave surface of the bridge-shaped short beam 83 of the curved beam 8 are 16, which are adapted to the tension-side piezoelectric stack 14, and the groove depth is also 1.5 mm.

[0045] In a further optimized solution, the sealing mechanism includes an outer ring sealing ring 11 and an inner ring sealing ring 12 embedded between the base 7 and the top cover 6.

[0046] Specifically, as Figure 7 shown, the base 7 and the top cover 6 are adapted to each other at their contact surfaces. The base 7 and the top cover 6 respectively open a sealing groove (not marked in the figure) on the outer ring contact surface to fix the outer ring sealing ring 11. At the same time, the base 7 and the top cover 6 respectively open a sealing groove (not marked in the figure) on the inner ring contact surface to fix the inner ring sealing ring 12. This can ensure the sealing performance of the entire rotor axial force measuring device 2, making it less affected by other structures, and thus improving the measurement accuracy of the piezoelectric stack 14 on the tension side and the piezoelectric stack 13 on the pressure side. In addition, in order to facilitate the installation and adaptation of the curved beam 8 to the base 7 and the top cover 6 in the above solution, a number of shallow grooves are also opened on the base 7. The number of shallow grooves at the position corresponding to the piezoelectric stack 13 on the pressure side of the base 7 is 16, and the groove depth is 1.5 mm. The axial clearance between the base 7 and the curved beam 8 is adapted to the installation process of the piezoelectric stack 13 on the pressure side, that is, the shallow grooves on the base 7 are correspondingly arranged with the shallow grooves on the convex surface of the bridge-shaped short beam 83. In this way, when the curved beam 8, the top cover 6 and the base 7 are adapted, one side of the piezoelectric stack 13 on the pressure side is fixed in the shallow groove on the convex surface of the bridge-shaped short beam 83, and the other side is embedded in the shallow groove on the base 7. A number of shallow grooves are also opened on the top cover 6. The number of shallow grooves at the position corresponding to the piezoelectric stack 14 on the tension side of the top cover 6 is 16, and the groove depth is 1.5 mm. The axial clearance between the top cover 6 and the curved beam 8 is adapted to the installation process of the piezoelectric stack 14 on the tension side. That is, the shallow grooves on the top cover 6 are correspondingly arranged with the shallow grooves on the concave surface of the bridge-shaped short beam 83. In this way, when the curved beam 8, the top cover 6 and the base 7 are adapted, one side of the piezoelectric stack 14 on the tension side is fixed in the shallow groove on the concave surface of the bridge-shaped short beam 83, and the other side is embedded in the shallow groove on the top cover 6.

[0047] In a further optimized solution, the flange edge of the top cover 6 and the squirrel-cage elastic support 3 are connected by a first fastening mechanism, and the base 7 and the load-bearing casing 1 are connected by a second fastening mechanism.

[0048] Furthermore, the first fastening mechanism includes a force-transmitting ejector rod 15. One side of the force-transmitting ejector rod 15 connects the top cover 6 and the curved beam 8, and the other side passes through the flange edge of the squirrel-cage elastic support 3 and is fixed by a locking nut I 16.

[0049] Still further, the second fastening mechanism includes a locking screw 17. A lock washer 18 is sleeved on the locking screw 17. The locking screw 17 sequentially passes through the top cover 6, the curved beam 8 and the base 7 and then connects to the load-bearing casing 1.

[0050] Specifically, as Figure 3 shown, a number of top cover through holes II 62 are opened on the top cover 6, and the top cover through holes II 62 are correspondingly arranged with the curved beam screw holes 82, as Figure 8As shown in the figure, the threads at both ends of the force transmission push rod 15 are right-handed threads; the boss of the force transmission push rod 15 is adapted to the axially sunken circular groove (not marked in the figure) of the top cover through hole II 62, the axial clearance is not less than 0.5 mm, and the radial clearance is not more than 0.2 mm; when connecting the top cover 6 to the flange of the squirrel cage elastic support 3, one end of the force transmission push rod 15 passes through the top cover through hole II 62 and the curved beam screw hole 82 respectively, and one side of the force transmission push rod 15 is screwed through the curved beam screw hole 82 until the boss of the force transmission push rod 15 abuts against the axially sunken circular groove of the top cover 6, while the screw rod on the other side of the force transmission push rod 15 directly penetrates the flange of the squirrel cage elastic support 3, and then it is fixed by using the lock nut I 16. In this way, one side of the top cover 6 of the assembled rotor axial force measuring device 2 is connected to the flange of the squirrel cage elastic support 3; at the same time, in order to ensure the sealing and stability after installation, a force transmission push rod 15 sealing ring 9 is installed at the contact surface part of the boss of the force transmission push rod 15 and the hole edge of the top cover through hole II 62. As Figure 3 and Figure 9 shown, in order to facilitate assembly, a number of base through holes 71 are provided on the base 7, and a number of top cover through holes I 61 are provided on the top cover 6, and the centers of the top cover through holes I 61, the base through holes 71 and the curved beam through holes 81 are on the same center line. As Figure 9 shown, when connecting the base 7 to the bearing housing 1, the locking screw 17 passes through the top cover through hole I 61, the curved beam through hole 81 and the base through hole 71 in sequence to connect the curved beam 8, the top cover 6 and the base 7, and then passes through the bearing housing 1, and finally is tightened by using the lock nut II 19. In order to ensure stability and sealing, a lock washer 18 is installed on the locking screw 17, and a locking screw 17 sealing ring 10 is sleeved at the contact surface part of the lock washer 18 and the hole edge of the top cover through hole I 61.

[0051] The working principle of the rotor axial force measuring device 2 disclosed by the present invention is as follows:

[0052] 1. During the operation of the engine, when the rotor generates an axial force on the pressure side to the left, the axial force is transmitted from the engine rotor, the thrust bearing 4, the squirrel cage elastic support 3, the force transmission push rod 15, and the curved beam 8 to the pressure side piezoelectric stack 13, so that the pressure side piezoelectric stack 13 is squeezed to obtain the real-time pressure side force measurement result. After that, the axial force is transmitted from the pressure side piezoelectric stack 13 and the base 7 to the frame of the bearing housing 1, and the measured pressure side force measurement result is fed back to the external signal processing device, and the tester can directly observe and record the value on the signal processing device.

[0053] 2. During the operation of the engine, when the rotor generates a rightward tension-side axial force, the axial force is transmitted to the tension-side piezoelectric stack 14 via the engine rotor, thrust bearing 4, squirrel cage elastic support 3, force transmission push rod 15, and curved beam 8, so that the tension-side piezoelectric stack 14 is squeezed to obtain a real-time tension-side force measurement result; thereafter, the axial force is transmitted to the frame of the load-bearing casing 1 via the tension-side piezoelectric stack 14, top cover 6, locking plate 18, locking screw 17, and locking nut II 19.

[0054] The rotor axial force measuring device 2 of the present invention can measure the axial forces on the tension side and the pressure side in a balanced and stable manner by setting a curved beam 8, and setting a plurality of pressure-side piezoelectric stacks 13 and a plurality of tension-side piezoelectric stacks 14 equidistantly in the circumferential direction on both sides of the curved beam 8, and its special force transmission path: at the same time, the curved beam 8 has a rigid-flexible integrated structure, that is, it is formed in one piece with a plurality of rigid bridge-shaped short beams 83 and a plurality of flexible transition sections 84, so that effective load balancing between different piezoelectric stacks can be achieved; and since a plurality of pressure-side piezoelectric stacks 13 and a plurality of tension-side piezoelectric stacks 14 are arranged in a sealed cavity, no secondary debugging is required after calibration, and it has high stability and consistency of multiple tests; at the same time, the piezoelectric stack is a multi-piece laminated structure, which can achieve accurate measurement of the axial load. Therefore, the present invention can effectively improve the accuracy of axial force measurement. In addition, by designing the spatial distribution of the sensor components and the high-rigidity closed shell composed of the base 7 and the top cover 6, the measuring device has a high integrity and is easy to install and disassemble. The relatively sensitive bearing-support structure can be installed without changing the device, so the impact on the engine rotor system is small and the measurement accuracy is high.

[0055] 3. This embodiment can also measure the circumferential distribution of the axial force. During the operation of the engine, the axial force is transmitted to the force transmission push rod 15 via the engine rotor, bearings, and squirrel cage elastic support 3; at this time, when the rotor tilts, the force transmitted to the force transmission push rod 15 by the squirrel cage elastic support 3 at different circumferential positions will produce distribution changes, and these distribution changes are transmitted to the circumferentially distributed tension side piezoelectric stack 14 or pressure side piezoelectric stack 13 by the curved beam 8, so as to be identified.

[0056] In the description of the present invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0057] The above embodiments are only descriptions of the preferred embodiments of the present invention and do not limit the scope of the present invention. Without departing from the spirit of the design of the present invention, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. An axial force measuring device for an aeroengine rotor based on a distributed piezoelectric stack, which is fixed between a load-bearing casing (1) and a squirrel-cage elastic support (3), and is characterized in that: It includes a base (7), and the base (7) is connected to the load-bearing casing (1); a top cover (6), the top cover (6) is adapted to the base (7), and a sealing mechanism is provided between the top cover (6) and the base (7), and the top cover (6) is connected to the flange edge of the squirrel-cage elastic support (3); a sensing assembly, after the top cover (6) and the base (7) are adapted, a sealed cavity is formed, the sensing assembly is located in the sealed cavity and is respectively connected to the base (7) and the top cover (6); the sensing assembly includes a curved beam (8), and a number of piezoelectric stacks are circumferentially and equidistantly distributed on both sides of the curved beam (8), and the piezoelectric stacks are connected to an external information processing device through signal lines; the curved beam (8) is a rigid-flexible integrated structure; the piezoelectric stack provided between the curved beam (8) and the base (7) is a pressure-side piezoelectric stack (13); the piezoelectric stack provided between the curved beam (8) and the top cover (6) is a tension-side piezoelectric stack (14).

2. The axial force measuring device for an aeroengine rotor based on a distributed piezoelectric stack according to claim 1, characterized in that: The curved beam (8) includes a number of bridge-shaped short beams (83), a flexible transition section (84) is fixedly connected between adjacent two of the bridge-shaped short beams (83), a pedestal (85) is fixedly connected between adjacent two of the flexible transition sections (84), and the bridge-shaped short beams (83) and the pedestal (85) are respectively connected to the base (7) and the top cover (6).

3. The axial force measuring device for an aeroengine rotor based on a distributed piezoelectric stack according to claim 2, characterized in that: A number of the bridge-shaped short beams (83), the flexible transition sections (84) and the pedestal (85) are of an integrally formed structure.

4. The axial force measuring device for an aeroengine rotor based on a distributed piezoelectric stack according to claim 1, wherein: The sealing mechanism includes an outer ring sealing ring (11) and an inner ring sealing ring (12) embedded between the base (7) and the top cover (6).

5. The axial force measuring device for an aero-engine rotor based on a distributed piezoelectric stack according to claim 1, characterized in that: The flange edge of the top cover (6) and the squirrel-cage elastic support (3) is connected through a first fastening mechanism, and the base (7) and the load-bearing casing (1) are connected through a second fastening mechanism.

6. The axial force measuring device for an aeroengine rotor based on a distributed piezoelectric stack according to claim 5, characterized in that: The first fastening mechanism includes a force-transmitting ejector rod (15), one side of the force-transmitting ejector rod (15) connects the top cover (6) and the curved beam (8), and the other side penetrates through the flange edge of the squirrel-cage elastic support (3) and is fixed by a lock nut I (16).

7. The axial force measuring device for an aero-engine rotor based on a distributed piezoelectric stack according to claim 5, characterized in that: The second fastening mechanism includes a locking screw (17), a lock washer (18) is sleeved on the locking screw (17), and the locking screw (17) sequentially penetrates through the top cover (6), the curved beam (8) and the base (7) and then is connected to the load-bearing casing (1).

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