Aero-engine roller bearing fulcrum dynamic load measurement device

Abstract

The present invention discloses an aircraft engine roller bearing fulcrum dynamic load measuring device, comprising a measuring device, wherein the measuring device is fixed between the engine load-bearing frame and the squirrel cage elastic support mounting edge, the bottom end of the squirrel cage elastic support mounting edge is mounted on the aircraft engine rotor through a roller bearing, and the measuring device comprises a first locking nut, a base, an inner ring locking bolt, a base annular platform, an outer ring locking bolt, a second locking nut, a top cover, a top cover annular platform, a base sealing ring, a top cover sealing ring, an outer ring sealing ring, a sensor outer ring, an inner ring sealing ring, a sensor inner ring and a shear piezoelectric crystal array. The aircraft engine roller bearing fulcrum dynamic load measuring device realizes load pickup by synchronously adopting shearing and ballast of piezoelectric crystals, and can achieve accurate measurement of the fulcrum dynamic load while ensuring a high pressure bearing strength. Therefore, the present invention can effectively improve the fulcrum dynamic load measurement accuracy.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engine testing, in particular to a device for measuring dynamic loads on roller bearing fulcrums of an aero-engine. Background Art

[0002] With the development of aviation technology, aero-engine performance is constantly improving, with thrust-to-weight ratios increasing, fuel consumption rates decreasing, and reliability requirements becoming increasingly stringent. Driven by the need for lightweight and high efficiency, the rotor structural systems of modern advanced aero-engines often feature high speeds and strong structural rigidity. During operation, high-speed rotor systems experience significant bending deformation. In the high-speed region, a rotational moment of inertia increases with speed, causing strong rotor vibration. This manifests itself as a significant increase in the dynamic load at the bearing support structure, seriously threatening the reliability of the rotor system and even the entire engine structure. Therefore, it is necessary to accurately determine the dynamic load at the fulcrum in real time to monitor engine rotor vibration and provide improvements for rotor structural state control. Given the complexity of the aero-engine structure and its operating environment, theoretical analysis and simulation calculations require real-time, accurate data as input conditions and output verification, thus creating an urgent need for experimental measurement methods for dynamic load at the fulcrum.

[0003] Currently, in the rotor systems of ship-mounted gas turbines, there are devices that use piezoelectric crystals as bearing fulcrum dynamic load measurement devices. However, such devices are too complex and highly dependent on the structure of the gas turbine, making them unsuitable for use in aircraft engine rotor systems. The aircraft engine fulcrum dynamic load test system currently in use in engineering uses strain gauges applied to the engine bearing seat to measure the strain value of the bearing seat strain gauge, and then obtains the measurement result by converting the strain of the bearing seat to the bearing fulcrum dynamic load. Practical applications have shown that this type of test system has the following problems:

[0004] The first problem with existing testing systems is the difficulty of disassembling the test device and the complexity of error analysis. Because the location of the strain gauge significantly influences the dynamic load measurement results at the fulcrum, extremely high precision is required for each assembly position. Furthermore, due to the complexity of the working environment, obtaining accurate data requires extensive error analysis. Furthermore, the error analysis results can vary significantly depending on the temperature and load distribution under different working conditions.

[0005] The second problem with existing testing systems is poor measurement accuracy. Because the dynamic load acting on the bearing fulcrum cannot be directly measured during the test, it must be converted using the strain of the bearing seat. This load conversion between two different components is inherently error-prone, directly affecting measurement accuracy. Furthermore, the strain under different operating conditions is significantly affected by factors such as the bearing seat's structural configuration, temperature distribution, and the spatial and temporal distribution of the dynamic load on the bearing fulcrum. This makes it impossible to guarantee the accuracy of data measurements under real-time changing operating conditions.

[0006] In summary, the existing fulcrum dynamic load test system cannot meet the requirements in terms of measurement accuracy, and the installation is complicated, and the error is greatly affected by the load environment. However, the development of modern aviation engines urgently needs fulcrum dynamic load measurement data with high precision, good accuracy and excellent repeatability as input conditions and output verification for the full envelope engine rotor structure state control. To this end, the present invention provides a device that can effectively improve the fulcrum dynamic load measurement accuracy, and effectively reduce the influence of environmental and assembly factors on the measurement results, thereby increasing the accuracy of the measurement. In addition, this solution can provide high-precision measurement results of the fulcrum dynamic load distribution along the circumferential direction in real time through the shear piezoelectric crystal array, and the rotation vector direction of the fulcrum dynamic load can be judged accordingly. Summary of the Invention

[0007] The object of the present invention is to provide a device for measuring the dynamic load of a roller bearing fulcrum of an aircraft engine, so as to solve the problems raised in the above-mentioned background technology.

[0008] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: an aircraft engine roller bearing fulcrum dynamic load measuring device, comprising a measuring device, wherein the measuring device is fixed between the engine load-bearing frame and the squirrel cage elastic support mounting edge, the bottom end of the squirrel cage elastic support mounting edge is mounted on the aircraft engine rotor through a roller bearing, the measuring device comprises a first locking nut, a base, an inner ring locking bolt, a base annular platform, an outer ring locking bolt, a second locking nut, a top cover, a top cover annular platform, a base sealing ring, a top cover sealing ring, an outer ring sealing ring, The sensor outer ring, inner ring sealing ring, sensor inner ring and shear piezoelectric crystal array, the load-bearing frame is connected to the top cover and the base through the outer ring locking bolt and the second locking nut, the base annular platform is embedded in one side of the sensor outer ring, the top cover annular platform is embedded and installed on one side of the top cover, the inner ring locking bolt and the first locking nut fix the top cover annular platform and the base annular platform to the squirrel cage elastic support mounting edge, the sensor outer ring, inner ring sealing ring, sensor inner ring and shear piezoelectric crystal array are embedded and installed between the top cover and the base in sequence.

[0009] Preferably, the sensor outer ring, the sensor inner ring and the shear piezoelectric crystal array constitute a sensor assembly.

[0010] Preferably, the shear piezoelectric crystal array is arranged between the outer ring of the sensor and the inner ring of the sensor.

[0011] Preferably, a sensor outer ring milling groove and a sensor outer ring through hole are opened in the sensor outer ring, a sensor inner ring through hole and a sensor inner ring milling groove are opened in the sensor inner ring, one end of the shear piezoelectric crystal array is adapted to the inner ring milling groove opened in the sensor outer ring, and the other end of the shear piezoelectric crystal array is adapted to the outer ring milling groove opened in the sensor inner ring.

[0012] Preferably, the shear piezoelectric crystal array is connected to an external information processing device via a signal line.

[0013] Preferably, the base and the top cover are sealed by an outer ring sealing ring and an inner ring sealing ring.

[0014] Preferably, the base and the base annular platform are sealed by a base sealing ring.

[0015] Preferably, the top cover and the top cover annular platform are sealed by a top cover sealing ring.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. This aircraft engine roller bearing fulcrum dynamic load measurement device, by providing a force transmission path between the sensor inner ring, the shear piezoelectric crystal array, and the sensor outer ring, can evenly and stably measure the fulcrum dynamic load transmitted by the squirrel cage elastic support structure. Because the sensor assembly stack is encapsulated in a sealed housing, no secondary debugging is required after calibration, resulting in high stability and consistency across multiple tests. By using the piezoelectric crystal's shearing and ballasting to synchronously pick up loads, the device can accurately measure the fulcrum dynamic load while ensuring high compressive strength. Therefore, the present invention can effectively improve the accuracy of fulcrum dynamic load measurement.

[0018] 2. This aircraft engine roller bearing fulcrum dynamic load measurement device has high integrity and is easy to install and disassemble by designing the spatial distribution of sensor components and a high-rigidity sealed housing. The device can be installed without changing the sensitive bearing-support structure, thereby having little impact on the engine rotor system and high measurement accuracy.

[0019] 3. This aircraft engine roller bearing fulcrum dynamic load measurement device achieves new functions by setting up a shear piezoelectric crystal array distributed circumferentially along the outer side of the sensor's inner ring. It can provide high-precision measurement results of the fulcrum dynamic load distribution along the circumferential direction in real time, and can use this to determine the rotation vector direction of the fulcrum dynamic load. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the dynamic load measurement scheme for the rotor support of an aircraft engine.

[0021] Figure 2 It is a structural appearance diagram of an embodiment of the present invention.

[0022] Figure 3 It is a schematic diagram of the structural decomposition of an embodiment of the present invention.

[0023] Figure 4 yes Figure 3Schematic diagram of the structure of the inner ring of the sensor.

[0024] Figure 5 yes Figure 3 Schematic diagram of the structure of the outer ring of the sensor.

[0025] Figure 6 yes Figure 3 Schematic diagram of the structure of the middle base.

[0026] Figure 7 yes Figure 3 Schematic diagram of the structure of the middle top cover.

[0027] Figure 8 yes Figure 2 AA section view in.

[0028] Figure 9 yes Figure 2 BB cross-section view in.

[0029] Figure 10 yes Figure 2 CC section view in.

[0030] In the figure: 1. load-bearing frame; 2. sensor assembly; 3. squirrel cage elastic support; 4. roller bearing; 5. aircraft engine rotor; 6. first locking nut; 7. base; 71. base outer ring through hole; 72. base inner ring through hole; 8. inner ring locking bolt; 9. base annular platform; 10. outer ring locking bolt; 11. second locking nut; 12. top cover; 121. top cover outer ring through hole; 122. top cover inner ring through hole; 13. top cover annular platform; 14. base sealing ring; 15. top cover sealing ring; 16. outer ring sealing ring; 17. sensor outer ring; 171. sensor outer ring milling groove; 172. sensor outer ring through hole; 18. inner ring sealing ring; 19. sensor inner ring; 191. sensor inner ring through hole; 192. sensor inner ring milling groove; 20. shear piezoelectric crystal array. DETAILED DESCRIPTION

[0031] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0032] The present invention provides a technical solution: Figures 2 to 10The present invention provides a shear piezoelectric crystal aero-engine roller bearing fulcrum dynamic load measuring device, comprising a measuring device, the measuring device being fixedly mounted between an engine load-bearing frame 1 and a squirrel cage elastic support mounting edge 3, the bottom end of the squirrel cage elastic support mounting edge 3 being mounted on an aero-engine rotor 5 via a roller bearing 4, the measuring device comprising a first locking nut 6, a base 7, an inner ring locking bolt 8, a base annular platform 9, an outer ring locking bolt 10, a second locking nut 11, a top cover 12, a top cover annular platform 13, a base sealing ring 14, a top cover sealing ring 15, an outer ring sealing ring 16, The sensor outer ring 17, the inner ring sealing ring 18, the sensor inner ring 19 and the shear piezoelectric crystal array 20, the base 7 and the top cover 12 are sealed by the outer ring sealing ring 16 and the inner ring sealing ring 18, and the base 7 and the base annular platform 9 are sealed by the base sealing ring 14. The load-bearing frame 1 is connected to the top cover 12 and the base 7 through the outer ring locking bolt 10 and the second locking nut 11. The base annular platform 9 is embedded in one side of the sensor outer ring 17, and the top cover annular platform 13 is embedded in one side of the top cover 12. There is a hole between the top cover 12 and the top cover annular platform 13. The top cover sealing ring 15 is sealed, and the inner ring locking bolt 8 and the first locking nut 6 fix the top cover annular platform 13 and the base annular platform 9 to the squirrel cage elastic support mounting edge 3. The sensor outer ring 17, the inner ring sealing ring 18, the sensor inner ring 19 and the shear piezoelectric crystal array 20 are sequentially embedded and installed between the top cover 12 and the base 7. The sensor outer ring 17 is provided with a sensor outer ring milling groove 171 and a sensor outer ring through hole 172. The sensor inner ring 19 is provided with a sensor inner ring through hole 191 and a sensor inner ring milling groove 192. The shear piezoelectric crystal array 20 is provided with a sensor inner ring through hole 191 and a sensor inner ring milling groove 192. One end is adapted to the milling groove 171 opened in the outer ring 17 of the sensor, and the other end of the shear piezoelectric crystal array 20 is adapted to the milling groove 192 opened in the outer ring 19 of the sensor. The outer ring 17 of the sensor, the inner ring 19 of the sensor and the shear piezoelectric crystal array 20 constitute the sensor component 2. The outer ring 17 of the sensor, the inner ring 19 of the sensor and the shear piezoelectric crystal array 20 constitute the sensor component 2. The shear piezoelectric crystal array 20 is connected to the external information processing device through a signal line. The shear piezoelectric crystal array 20 is arranged between the outer ring 17 of the sensor and the inner ring 19 of the sensor.

[0033] The high-precision fulcrum dynamic load testing device for aerospace engine roller bearings providing shear piezoelectric crystals provided by the present invention is fixed between an engine load-bearing frame 1 and a squirrel cage elastic support mounting edge 3. The engine load-bearing frame 1 is connected to the top cover 12 and the base 7 by an outer ring locking bolt 10 and a second locking nut 11. The top cover annular platform 13 and the base annular platform 9 are fixed to the squirrel cage elastic support mounting edge 3 using an inner ring locking bolt 8 and a first locking nut 6.

[0034] Further preferably, the preferred sensor inner / outer ring configuration and shear piezoelectric crystal array form in this embodiment are:

[0035] 1. The sensor inner ring 19 is made of 16 short right-angle beams, 8 bolt bases, and 8 relatively flexible transition sections through integrated processing. The sensor inner ring 19 has 8 sensor inner ring through-holes 191. Two milling grooves 192 are opened on both sides of the 16 short right-angle beams on the sensor inner ring 19. The grooves 192 are 1.5 mm deep. The radial dimensions of the sensor inner ring 19 are compatible with the squirrel cage elastic support mounting edge 3.

[0036] 2. The sensor outer ring 17 is completed by integrated processing of 16 right-angle short beams, 8 bolt bases, and 8 relatively flexible transition sections. The sensor outer ring 17 has 8 sensor outer ring through holes 172; two milling grooves 171 are opened on both sides of the 16 right-angle short beams on the sensor outer ring 17, and the groove depth of the milling groove 171 is 1.5mm; the radial dimension of the sensor outer ring 17 is compatible with the mounting edge 3 of the load-bearing frame.

[0037] 3. There are 32 shear piezoelectric crystal arrays 20 in total, which are evenly distributed in the milling groove of the inner ring 19 of the sensor in the circumferential direction.

[0038] Further preferably, the preferred base and top cover structures in this embodiment are:

[0039] 1. The base 7 contacts the sensor outer ring 17. A 3mm deep annular groove is opened on the base 7 near the squirrel cage elastic support mounting edge 3. Eight base outer ring through holes 71 and eight base outer ring through holes 72 are evenly distributed circumferentially in the annular groove. The axial clearance between the base 7 and the sensor inner ring 19 is compatible with the shear piezoelectric crystal installation process. The base 7 has a circular milling groove at each of the eight base inner ring through holes 72 to fix the base sealing ring 14, and there are a total of eight circular milling grooves.

[0040] 2. The top cover 12 is in contact with the outer ring 17 of the sensor; the top cover 12 has 8 4mm deep countersunk holes evenly distributed circumferentially at 3 locations near the mounting edge of the load-bearing frame, and each countersunk hole has a top cover inner ring through hole 122, for a total of 8 holes; the top cover 12 has 8 top cover outer ring through holes 121 evenly distributed circumferentially; the axial clearance between the top cover 12 and the inner ring 19 of the sensor is compatible with the shear piezoelectric crystal installation process; the top cover 12 has a circular milling groove at each of the 8 top cover inner ring through holes 122 to fix the top cover sealing ring 15, for a total of 8 circular milling grooves.

[0041] 3. The base 7 and the top cover 12 are adapted to each other at the contact surface; the base 7 and the top cover 12 respectively open a sealing groove at the outer ring contact surface to fix the outer ring sealing ring 16; the base 7 and the top cover 12 respectively open a sealing groove at the inner ring contact surface to fix the inner ring sealing ring 18.

[0042] The preferred connection scheme of the measuring device with the load-bearing frame and the squirrel cage elastic support flange in this embodiment is as follows:

[0043] 1. The connection between the measuring device and the load-bearing casing: specifically, the outer ring locking bolt 10 passes through the base outer ring through hole 71 on the base 7, the sensor outer ring through hole 172 on the sensor outer ring 17, the top cover outer ring through hole 121 on the top cover 12 and the through hole on the load-bearing frame, and is then tightened by the second locking nut 11.

[0044] 2. Connection between the measuring device and the squirrel cage elastic support flange: Specifically: the top cover annular platform 13 is placed in the sensor inner ring through-hole 191 on the side of the load-bearing frame installation, and the base annular platform 9 is placed in the sensor inner ring through-hole 191 on the side of the squirrel cage elastic support installation. The inner ring locking bolt 8 passes through the through-hole on the top cover annular platform 13, the base annular platform 9, and the through-hole on the squirrel cage elastic support installation side, and is tightened by the first locking nut 6.

[0045] This embodiment achieves accurate measurement of the dynamic load of the support through the following working principle:

[0046] 1. During engine operation, when the rotor system generates a radial fulcrum dynamic load acting on the bearing, the fulcrum dynamic load is transmitted to the top cover annular platform 13 and the base annular platform 9 via the engine rotor 5, the roller bearing 4, the squirrel cage elastic support 3 and the inner ring locking bolt 8. Since the top cover annular platform 13 and the base annular platform 9 are placed in the sensor inner ring through-hole 191, the fulcrum dynamic load is transmitted to the sensor inner ring 19 via the top cover annular platform 13 and the base annular platform 9. The sensor inner ring 19 presses the shear piezoelectric crystal array 20, causing the shear piezoelectric crystal array 20 to be squeezed and sheared, thereby obtaining a real-time fulcrum dynamic load result; thereafter, the fulcrum dynamic load is transmitted to the load-bearing frame 1 via the sensor outer ring 17, the outer ring locking bolt 10 and the top cover 12.

[0047] 2. This embodiment can measure the real-time circumferential variation of the fulcrum dynamic load. During engine operation, the direction of the fulcrum dynamic load continuously changes circumferentially due to the precession of the engine rotor. This fulcrum dynamic load is transmitted to the inner ring locking bolt 8 via the engine rotor 5, roller bearing 4, and squirrel cage elastic support 3. Since the force transmitted to the inner ring locking bolt 8 varies in real time along the circumference, the radial load transmitted to the sensor inner ring 19 also varies in real time along the circumference. These real-time distributed changes are transmitted by the sensor inner ring 19 to the 32 circumferentially distributed shear piezoelectric crystals 20, thereby being identified.

[0048] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft engine roller bearing fulcrum dynamic load measuring device, comprising a measuring device, characterized in that: The measuring device is fixed between the engine load-bearing frame (1) and the squirrel cage elastic support mounting edge (3), the bottom end of the squirrel cage elastic support mounting edge (3) is mounted on the aircraft engine rotor (5) through a roller bearing (4), and the measuring device comprises a first locking nut (6), a base (7), an inner ring locking bolt (8), a base annular platform (9), an outer ring locking bolt (10), a second locking nut (11), a top cover (12), a top cover annular platform (13), a base sealing ring (14), a top cover sealing ring (15), an outer ring sealing ring (16), a sensor outer ring (17), an inner ring sealing ring (18), a sensor inner ring (19) and a shear piezoelectric crystal array (2 0), the load-bearing frame (1) is connected to the top cover (12) and the base (7) through the outer ring locking bolt (10) and the second locking nut (11), the base annular platform (9) is embedded in one side of the sensor outer ring (17), the top cover annular platform (13) is embedded and installed on one side of the top cover (12), the inner ring locking bolt (8) and the first locking nut (6) fix the top cover annular platform (13) and the base annular platform (9) to the squirrel cage elastic support mounting edge (3), and the sensor outer ring (17), the inner ring sealing ring (18), the sensor inner ring (19) and the shear piezoelectric crystal array (20) are embedded and installed in sequence between the top cover (12) and the base (7); The sensor outer ring (17) is provided with a sensor outer ring milling groove (171) and a sensor outer ring through hole (172); the sensor inner ring (19) is provided with a sensor inner ring through hole (191) and a sensor inner ring milling groove (192); one end of the shear piezoelectric crystal array (20) is adapted to the sensor outer ring milling groove (171) provided on the outer ring of the sensor outer ring (17); and the other end of the shear piezoelectric crystal array (20) is adapted to the sensor inner ring milling groove (192) provided on the inner ring of the sensor (19); There are 32 shear piezoelectric crystal arrays (20) in total, which are evenly distributed in the milling grooves in the inner ring (19) of the sensor in the circumferential direction.

2. The aircraft engine roller bearing fulcrum dynamic load measuring device according to claim 1, characterized in that: The sensor outer ring (17), the sensor inner ring (19) and the shear piezoelectric crystal array (20) constitute a sensor assembly (2).

3. The device for measuring dynamic load of a roller bearing fulcrum of an aircraft engine according to claim 2, characterized in that: The shear piezoelectric crystal array (20) is arranged between the sensor outer ring (17) and the sensor inner ring (19).

4. The aircraft engine roller bearing fulcrum dynamic load measuring device according to claim 1, characterized in that: The shear piezoelectric crystal array (20) is connected to an external information processing device via a signal line.

5. The device for measuring dynamic load of a roller bearing fulcrum of an aircraft engine according to claim 1, characterized in that: The base (7) and the top cover (12) are sealed by an outer ring sealing ring (16) and an inner ring sealing ring (18).

6. The device for measuring dynamic load of a roller bearing fulcrum of an aircraft engine according to claim 1, characterized in that: The base (7) and the base annular platform (9) are sealed via a base sealing ring (14).

7. The device for measuring dynamic load of a roller bearing fulcrum of an aircraft engine according to claim 1, characterized in that: The top cover (12) and the top cover annular platform (13) are sealed via a top cover sealing ring (15).

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