Aero-engine spring rotor simulation test device with internal and external excitation simulation

Abstract

The simulation test device for aero-engine elastic support rotor with internal and external excitation simulation comprises a rotating drive system, an elastic support rotor system, a support base, a fulcrum excitation simulation device, an external excitation simulation device, a test system and a base. The external excitation device can simulate the vibration environment and the exciting flight load in which the engine rotor is located. The internal fulcrum excitation simulation device can simulate the impact load borne by the fulcrum, and in combination with a rotating disc, a rubbing rod and the like, can effectively simulate the periodic excitation generated by the rotor, and can effectively simulate the complex excitation environment of the aero-engine elastic support rotor. The device is provided with a fulcrum load force sensor, a rotor vibration displacement sensor, an acceleration sensor, a squirrel cage strain sensor and the like, can comprehensively test the rotor vibration, the squirrel cage strain, the load and the like, and realize vibration coupling analysis. The elastic rotor system comprises a rotor, a squirrel cage, a web plate, a casing and the like, and is similar to the structure of an aero-engine, and can effectively simulate the elastic support of the engine and the structural characteristics of the rotor.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing and measurement technology. Background Technology

[0002] The aero-engine rotor system is a crucial structural component ensuring the safe and stable operation of the aero-engine. It features a complex support structure, commonly employing an elastic support structure (hereinafter referred to as the elastic support structure). This structure comprehensively adjusts the system's critical speed to ensure safety margins and improve operational stability. The internal rotor and support structures are complex, and their dynamic characteristics are closely related to the dynamic performance and vibration issues of the rotor system and even the entire engine. The dynamic excitation of the aero-engine rotor is complex, including internal shaft excitation loads caused by rotor imbalance, misalignment, and rubbing, as well as external excitations such as impact forces on the support points, impacts during aircraft landing, and maneuvering flight loads.

[0003] Currently, it is impossible to directly obtain vibration data of the rotor structure on a real aero-engine, and real experimental research is limited. At present, various simulation test devices are commonly used to carry out test devices, such as aero-engine dual rotor-support-casing test devices. Most of these test devices do not have the ability to simulate internal and external impact mechanisms, and it is difficult to simulate the complex excitation dynamic characteristics of the engine rotor and support. Therefore, there is an urgent need to develop an aero-engine rotor simulation test device with internal and external excitation simulation capabilities. Summary of the Invention

[0004] To address the problems mentioned above, this invention provides an aero-engine missile rotor simulation test device with internal and external excitation simulation devices and fulcrum load testing devices. This device can conduct external maneuvering flight, impact simulation, and fulcrum excitation and rotor excitation tests, thereby realizing the vibration characteristic test of aero-engine missile rotors.

[0005] The technical solution adopted by the present invention to achieve the above objectives is as follows: an aero-engine missile rotor simulation test device with internal and external excitation simulation, including a rotary drive system 1, a missile rotor system 2, and a fulcrum excitation simulation device 4. The missile rotor system 2 has webs 21 at both ends, and two squirrel cages 23 are respectively installed on the inner side of the webs 21 at both ends. A force sensor 22 is installed between one side of the web 21 and the squirrel cage 23. The inner ends of the squirrel cages 23 on both sides are connected to the bearing seats 24. The bearings 25 are installed inside the bearing seats 24. One end of the rotating shaft 26 is connected to the bearing 25 on one side, and the other end of the rotating shaft 26 is connected to the bearing 25 on the other side and passes through the web 21 on the same side to connect with the rotary drive system 1. The fulcrum excitation simulation device 4 is installed on the upper part of the squirrel cage 23 corresponding to the force sensor 22. The radial exciter 41 of the fulcrum excitation simulation device 4 is located above the squirrel cage 23. The lower part of the radial exciter 41 is connected to the radial excitation rod 42, and the lower end of the radial excitation rod 42 is connected to the bearing seat 24.

[0006] The spring-loaded rotor system 2 is mounted on the support base 3, which is a trapezoidal concave structure. The web plates 21 on both sides of the spring-loaded rotor system 2 are fixed to both ends of the internal concave structure 32.

[0007] Support plates 44 are symmetrically installed on the outside of the cage 23 located on one side of the force sensor 22 on the support base 3. A vibrator connecting plate 43 is installed between the upper ends of the two support plates 44, and a radial vibrator 41 is installed on the vibrator connecting plate 43.

[0008] The support base 3 has a base platform 7 on its lower side, and a horizontal sliding guide rail 53 is provided on the base platform 7. A slider 54 is installed at the bottom of the support base 3, and the support base 3 and the base platform 7 are slidably connected through the slider 54 and the sliding guide rail 53. An external excitation simulation device 5 is installed on the base platform 7 on one side of the support base 3. The horizontal exciter 51 of the external excitation simulation device 5 is connected to the horizontal excitation rod 52, and the front end of the horizontal excitation rod 52 is connected to the support base 3.

[0009] A turntable 27 is mounted on the rotating shaft 26, and a casing 28 is installed between the web plates 21 on both sides. The casing 28 is located outside the cage 23 and the turntable 27. A friction rod 29 is installed on the casing 28 with a gap in the same radial plane as the turntable 27.

[0010] A strain gauge 62 is installed on the cage 23 on one side of the force sensor 22. A sensor mounting bracket 63 is installed on the inner side of the web plate 1. Vibration displacement sensors 61 are installed on the sensor mounting bracket 63 in the horizontal and vertical directions of the rotating shaft 26, respectively. An acceleration sensor 64 is installed on the bearing seat 24.

[0011] The force sensor 22 is a triaxial force sensor.

[0012] The turntable 27 has a threaded hole on its end face for setting rotor imbalance.

[0013] The lower end of the radial excitation rod 42 is connected to the radial excitation rod connection hole 210 of the bearing seat 24 via a radial connecting pin 45; the transverse excitation rod 52 is connected to the support base 3 via a transverse connecting pin 56.

[0014] The aircraft engine missile rotor simulation test device with internal and external excitation simulation of the present invention has the following beneficial effects:

[0015] (1) The present invention has an external excitation device that can simulate the vibration environment and flight load of the engine rotor; an internal support excitation simulation device that can simulate the impact load on the support; in addition, combined with the rotor excitation simulation device such as the unbalanced disk and the rubbing device of the rotor system, it can effectively simulate the periodic excitation of the rotor and effectively simulate the complex excitation environment of the aero-engine support rotor.

[0016] (2) The test system of the present invention has a fulcrum load force sensor, a rotor vibration displacement sensor, an acceleration sensor, a squirrel cage strain sensor and other test sensors, which can comprehensively test rotor vibration, squirrel cage strain, load and other data to realize vibration coupling analysis.

[0017] (3) The present invention has an elastic rotor system including a rotor, a squirrel cage, a web plate, a casing and other structures similar to those of an aero-engine, which can effectively simulate the elastic support of the engine and the structural features of the rotor. Attached Figure Description

[0018] Figure 1 This is a structural diagram of the aero-engine missile rotor simulation test device (without casing) with internal and external excitation simulation according to the present invention.

[0019] Figure 2 This is a structural diagram of the aircraft engine missile rotor simulation test device (with internal and external excitation simulation) of the present invention.

[0020] Figure 3 This is a front cross-sectional view of the flexible rotor system for an aero-engine of the present invention.

[0021] Figure 4 This is an axial cross-sectional view of the flexible rotor system for an aero-engine of the present invention.

[0022] Figure 5 This is a cross-sectional view of the elastic support for the aero-engine of the present invention.

[0023] Figure 6 This is a structural diagram of the support base of the present invention.

[0024] Figure 7 This is a structural diagram of the fulcrum excitation simulation device of the present invention.

[0025] Figure 8 This is a structural diagram of the external excitation simulation device of the present invention.

[0026] Figure 9 This is a diagram showing the installation structure of the test system of the present invention.

[0027] In the diagram: 1. Rotary drive system; 2. Spindle rotor system; 21. Web plate; 22. Force sensor; 23. Squirrel cage; 24. Bearing housing; 25. Bearing; 26. Shaft; 27. Turntable; 28. Casing; 29. ​​Friction rod; 210. Radial excitation rod connection hole; 3. Support base; 31. Mounting hole; 32. Internal concave structure; 33. External excitation device connection hole; 34. Slider connection hole; 4. Pivot excitation simulation device; 41. Radial exciter; 42. Radial excitation rod; 43. Exciter connecting plate; 44. Support plate; 45. Radial connecting pin; 5. External excitation simulation device; 51. Transverse exciter; 52. Transverse excitation rod; 53. Sliding guide rail; 54. Slider; 56. Transverse connecting pin; 6. Testing system; 61. Vibration displacement sensor; 62. Strain; 63. Sensor mounting bracket; 64. Accelerometer; 7. Base platform. Detailed Implementation

[0028] The aero-engine missile rotor simulation test device with internal and external excitation simulation of the present invention is as follows: Figure 1 , 2 As shown, the system includes a rotary drive system 1, a spring-loaded rotor system 2, a support base 3, a fulcrum excitation simulation device 4, an external excitation simulation device 5, a test system 6, and a base platform 7. The rotary drive system 1, located at one end of the spring-loaded rotor system 2, drives the system to rotate. It employs a variable frequency drive to simulate different speed conditions. The spring-loaded rotor system 2 has a rotor, squirrel cage, web, and casing, similar in structure to an aero-engine, effectively simulating the engine's elastic support and rotor structural characteristics. Combined with rotor excitation simulation devices such as the unbalanced disc and rubbing device, it effectively simulates the periodic excitation generated by the rotor. The support base 3 supports the spring-loaded rotor system 2 and the fulcrum excitation simulation device 4, and is connected to the external excitation simulation device 5. The fulcrum excitation simulation device 4 is located on the upper part of the spring-loaded rotor system 2 and connected to the fulcrum of the system. It applies impact loads to the elastic support, simulating the excitation borne by the fulcrum. The external excitation simulation device 5 is located on one side of the base 3 and connected to the base 3. It is used to apply external excitation to the base and its missile support rotor system 2, etc., to simulate the vibration environment of the engine rotor and the excitation flight load.

[0029] like Figure 3-5As shown, the spring-supported rotor system 2 includes a web 21, a force sensor 22, a squirrel cage 23, a bearing housing 24, a bearing 25, a rotating shaft 26, a turntable 27, a casing 28, and a friction rod 29. There are two webs 21 located on both sides of the spring-supported rotor system 2. Two squirrel cages 23 are installed on the inner side of each web 21. A force sensor 22 is installed between one side of the web 21 and the squirrel cage 23. The inner ends of the squirrel cages 23 on both sides are connected to the bearing housing 24. The bearing 25 is installed inside the bearing housing 24. One end of the rotating shaft 26 is connected to the bearing 25 on one side, and the other end of the rotating shaft 26 is connected to the bearing 25 on the other side. It also passes through the web 21 on the same side and is connected to the rotary drive system 1. A fulcrum excitation simulation device 4 is installed on the upper part of the squirrel cage 23 on the side corresponding to the force sensor 22. The radial exciter 41 of the fulcrum excitation simulation device 4 is located above the squirrel cage 23. The lower part of the radial exciter 41 is connected to the radial excitation rod 42, and the lower end of the radial excitation rod 42 is connected to the bearing housing 24. Force sensor 22 is a triaxial force sensor used to test axial and radial fulcrum loads under different operating conditions. The squirrel cage 23 is a typical elastic support structure for aero-engines. The other end of the squirrel cage 23 is connected to the bearing housing 24 via bolts. The bearing 25 is installed and fixed inside the bearing housing 24. The supporting bearing 24 is a rolling bearing used to support the rotation of the rotating shaft 26. A turntable 27 is mounted on the rotating shaft 26. Threaded holes are provided on the end face of the turntable 27 to set rotor imbalance and simulate rotor imbalance excitation. The casing 28 has two web plates 21 connected to its two end faces, housing the squirrel cage 23, bearing housing 24, bearing 25, rotating shaft 26, turntable 27, and other components. The casing 28 has a split upper and lower structure, facilitating internal rotor system debugging and sensor installation. The casing has mounting holes for installing a friction rod 29, which is on the same radial plane as the turntable 27. By adjusting the gap between the friction rod 29 and the turntable 27, the degree of rotor friction is simulated.

[0030] like Figure 6 As shown, the support base 3 of the present invention has a trapezoidal concave structure. Its upper surface has a connecting interface and mounting holes 31 for mounting the support spring rotor system 2 and the fulcrum excitation simulation device 4. The internal concave structure 32 is used to accommodate part of the spring rotor system 2. The base 3 has an external excitation device connection hole 33 for connecting to an external excitation device. Its lower part has multiple slider connection holes 34 for connecting to sliders 54.

[0031] Place Figure 7As shown, the fulcrum excitation simulation device 4 comprises an exciter 41, an excitation rod 42, an exciter connecting plate 43, a support plate 44, and a connecting pin 45. The exciter 41 is mounted on the upper part of the spring-supported rotor system 2. The exciter rod 42 is fixed to the top of the exciter 41, and the exciter rod 42 is connected to the exciter rod connecting hole 210 on the bearing seat 24 via the connecting pin 45. The exciter 41 is connected to the exciter connecting plate 43, which is connected to the support plate 44. The support plate 44 is fixedly connected to the upper surface of the support base 3. The exciter 41 generates displacement excitation at a certain frequency. The bearing seat 24 and the squirrel cage 25 are elastic supports, allowing for a certain radial displacement, thereby realizing the fulcrum excitation simulation of the spring-supported rotor system 2.

[0032] like Figure 8 As shown, the external excitation simulation device 5 comprises an exciter 51, an excitation rod 52, a sliding guide rail 53, a slider 54, and a connecting pin 56. The exciter 51 is fixed to the base 7, positioned on one side of the support base 3. The excitation rod 52 is fixed to the top of the exciter 51 and connected to the support base 33 via the connecting pin 56. The sliding guide rail 53 is fixedly mounted on the base 7, and the slider 54 is located at the lower part of the support base 3 and connected to it. The sliding guide rail 53 and the slider 54 form a sliding mechanism that allows the support base 3 to move horizontally. The exciter 51 generates displacement excitation at a certain frequency, and the support base 3 generates excitation at a certain frequency along with the sliding mechanism, thereby simulating the external excitation of the spring-supported rotor system 2.

[0033] like Figure 9 As shown, the testing system 6 includes a force sensor 22, a vibration displacement sensor 61, a strain sensor 62, a sensor mounting bracket 63, and an acceleration sensor 64. The force sensor 22 is used to test the axial and radial loads of the fulcrum. The vibration displacement sensor 61 is an eddy current sensor used to test the vibration displacement of the shaft. The strain sensor 62 is used to measure the strain of the squirrel cage. The acceleration sensor 64 is used to test the vibration acceleration of the bearing housing. The vibration displacement sensor 61 is installed in the horizontal and vertical directions of the rotor and connected to the web plate 21 via the sensor mounting bracket 63.

[0034] This invention has been described through embodiments. Those skilled in the art will understand that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of the invention. Furthermore, under the teachings of this invention, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of the invention. Therefore, this invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of this invention.

Claims

1. An aero-engine missile rotor simulation test device with internal and external excitation simulation, characterized in that: The system includes a rotary drive system (1), a spring-supported rotor system (2), and a fulcrum excitation simulation device (4). The spring-supported rotor system (2) is mounted on a support base (3). Both ends of the spring-supported rotor system (2) have webs (21). Two squirrel cages (23) are installed on the inner sides of the webs (21) at both ends. A force sensor (22) is installed between one side of the web (21) and the squirrel cage (23). The inner ends of the squirrel cages (23) on both sides are connected to the bearing seats (24). The bearings (25) are installed inside the bearing seats (24). One end of the rotating shaft (26) is connected to the bearing (25) on one side, and the other end of the rotating shaft (26) is connected to the bearing (25) on the other side and passes through the web (21) on the same side to connect with the rotary drive system (1). The fulcrum excitation simulation device (4) is installed on the upper part of the squirrel cage (23) on the side corresponding to the force sensor (22). The radial exciter (41) of the fulcrum excitation simulation device (4) is located above the squirrel cage (23). 41) The lower part is connected to the radial excitation rod (42), and the lower end of the radial excitation rod (42) is connected to the bearing seat (24); the support base (3) is provided with a base platform (7) on the lower side, and a transverse sliding guide rail (53) is provided on the base platform (7). The support base (3) is installed with a slider (54) at the bottom, and the support base (3) and the base platform (7) are slidably connected by the slider (54) and the sliding guide rail (53); an external excitation simulation device (5) is installed on the base platform (7) on one side of the support base (3). The transverse exciter (51) of the external excitation simulation device (5) is connected to the transverse excitation rod (52). The front end of the transverse excitation rod (52) is connected to the support base (3). A turntable (27) is installed on the rotating shaft (26). A casing (28) is installed between the web plates (21) on both sides. The casing (28) is located outside the cage (23) and the turntable (27). A friction rod (29) is installed on the casing (28) with the same radial plane gap as the turntable (27).

2. The aero-engine missile rotor simulation test device with internal and external excitation simulation according to claim 1, characterized in that: The support base (3) is a trapezoidal concave structure, and the web plates (21) on both sides of the spring-supported rotor system (2) are fixed to both ends of the internal concave structure (32).

3. The aero-engine missile rotor simulation test device with internal and external excitation simulation according to claim 2, characterized in that: Support plates (44) are symmetrically installed on the outside of the cage (23) on the support base (3) located on the side of the force sensor (22). A vibrator connecting plate (43) is installed between the upper ends of the two support plates (44), and a radial vibrator (41) is installed on the vibrator connecting plate (43).

4. The aero-engine missile rotor simulation test device with internal and external excitation simulation according to claim 1, characterized in that: Strain (62) is installed on the cage (23) on one side of the force sensor (22), and sensor mounting bracket (63) is installed on the inner side of the web (1). Vibration displacement sensor (61) is installed on the sensor mounting bracket (63) in the horizontal and vertical directions of the rotating shaft (26), respectively; and acceleration sensor (64) is installed on the bearing seat (24).

5. The aero-engine missile rotor simulation test device with internal and external excitation simulation according to claim 1, characterized in that: The force sensor (22) is a triaxial force sensor.

6. The aero-engine missile rotor simulation test device with internal and external excitation simulation according to claim 5, characterized in that: The turntable (27) has a threaded hole on its end face for setting rotor imbalance.

7. The aero-engine missile rotor simulation test device with internal and external excitation simulation according to claim 1, characterized in that: The lower end of the radial excitation rod (42) is connected to the radial excitation rod connection hole (210) of the bearing seat (24) through a radial connecting pin (45); the transverse excitation rod (52) is connected to the support base (3) through a transverse connecting pin (56).

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