A multi-fault simulation experimental device for a turbine pump rotor system

Abstract

The invention discloses a multi-fault simulation experimental device for a turbine pump rotor system. The output shaft of a servo motor is connected to the input end of a planetary gear speed increaser, the output end of the planetary gear speed increaser is connected to one end of a main shaft of a turbine pump rotor system, the other end of the main shaft of the turbine pump rotor system is connected to a magnetic powder brake after passing through a turbine pump housing, a main shaft support fault bearing and a main shaft loading bearing are arranged between the inner wall of the turbine pump housing and the main shaft of the turbine pump rotor system, an oxygen pump centrifugal wheel and a fuel pump blade fracture centrifugal wheel are arranged in the turbine pump housing, and the two centrifugal wheels are sleeved on the main shaft of the turbine pump rotor system; a friction ring is fixed on the inner wall of the turbine pump housing, the friction ring is directly opposite to the oxygen pump centrifugal wheel, and a control system is connected to a servo motor. The device simulates dynamic and static friction faults, blade fractures and bearing faults of a turbine pump under variable speed conditions.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid rocket engine fault diagnosis and relates to a multi-fault simulation experimental device for a turbine pump rotor system. Background Art

[0002] With the rapid development of aerospace technology, the competition for space resources among countries around the world is becoming increasingly fierce. There is an urgent need to improve the reliability and safety of launch vehicles, otherwise a system failure may lead to catastrophic consequences and huge economic losses. At the same time, with the further development of the country's modernization process, the breakthrough development of frontier fields such as aerospace technology has been vigorously promoted, and the demand for condition monitoring, fault analysis and early warning, maintenance and repair of liquid rocket engines has become increasingly strong. As a key core component of liquid rocket engines, turbopumps work in extreme physical environments with high speed, large temperature difference and strong vibration, and are one of the main factors of rocket engine failure. Since the running time of turbopumps is extremely short both in test runs and in rocket launches, and the high reliability requirements of design and manufacturing and the use of new components, there are few actual fault samples of turbopumps. As a result, the technical research on condition monitoring and fault diagnosis of turbopumps has been greatly restricted. The research on the transformation of turbopump system fault diagnosis into laboratory environment is rarely involved in academia and engineering. The existing experimental equipment of turbopump rotor system is mainly used to study the dynamic characteristics of turbopump, and cannot simulate typical faults such as rotor friction, blade fracture and bearing defects under the variable speed condition of turbopump. It cannot adapt to the requirements of typical fault mechanism of turbopump, fault sample database system construction and diagnosis method research in laboratory environment. Summary of the invention

[0003] The purpose of the present invention is to overcome the shortcomings of the above-mentioned prior art and provide a multi-fault simulation experimental device for a turbine pump rotor system, which can simulate dynamic and static friction failures, blade breakage and bearing failures of a turbine pump under variable speed conditions.

[0004] To achieve the above-mentioned purpose, the present invention discloses a multi-fault simulation experimental device for a turbine pump rotor system, including a servo motor, a planetary gear speed increaser, a faulty bearing for main shaft support, a centrifugal wheel with broken fuel pump blades, a main shaft of a turbine pump rotor system, a turbine pump housing, a friction ring and a control system;

[0005] The output shaft of the servo motor is connected to the input end of the planetary gear speed increaser, the output end of the planetary gear speed increaser is connected to one end of the main shaft of the turbine pump rotor system, the other end of the main shaft of the turbine pump rotor system is connected to a magnetic powder brake after passing through the turbine pump housing, a main shaft support bearing and a main shaft loading bearing are arranged between the inner wall of the turbine pump housing and the main shaft of the turbine pump rotor system, an oxygen pump centrifugal wheel is arranged in the turbine pump housing, and the oxygen pump centrifugal wheel is sleeved on the main shaft of the turbine pump rotor system; a friction ring is fixed on the inner wall of the turbine pump housing, the friction ring is directly opposite to the oxygen pump centrifugal wheel, and the control system is connected to the servo motor.

[0006] The friction ring is fixed on the inner wall of the turbine pump housing through a friction top screw assembly, and the friction ring faces the centrifugal wheel of the oxygen pump.

[0007] The friction top screw assembly includes two connecting screws and an intermediate screw for adjusting the clearance between the moving and stationary parts, wherein the two connecting screws pass through the side wall of the turbine pump housing and are inserted into the friction ring, and a spring is arranged between the head of the connecting screw and the outer wall of the turbine pump housing; the intermediate screw contacts the surface of the friction ring after passing through the turbine pump housing, and the intermediate screw is threadedly connected to the turbine pump housing.

[0008] The output shaft of the servo motor is connected to the input end of the planetary gear speed increaser through a coupling.

[0009] A bearing seat is arranged on the inner wall of the turbine pump housing, and a main shaft supporting bearing and a main shaft loading bearing are located on the bearing seat.

[0010] It also includes a turbine, an oxygen pump inducer and a fuel pump inducer. The turbine, the oxygen pump inducer, the oxygen pump centrifugal wheel, the fuel pump blade fracture centrifugal wheel and the fuel pump inducer are sequentially arranged on the main shaft of the turbine pump rotor system.

[0011] The turbine and the main shaft of the turbopump rotor system are fixed by pin connection.

[0012] The oxygen pump centrifugal wheel and the main shaft of the turbine pump rotor system and the fuel pump blade-breaking centrifugal wheel and the main shaft of the turbine pump rotor system are respectively connected by keys.

[0013] The oxygen pump inducer and the oxygen pump centrifugal wheel as well as the fuel pump inducer and the fuel pump blade-breaking centrifugal wheel are connected and the torque is transmitted through the mortise and tenon structure.

[0014] The control system includes an electric control cabinet, buttons, indicator lights and a power switch arranged on the electric control cabinet, and a controller arranged in a box; the output end of the controller is connected to the control end of the servo motor, and the controller is connected to the buttons, indicator lights and the power switch.

[0015] The present invention has the following beneficial effects:

[0016] During the specific operation of the multi-fault simulation experimental device for the turbine pump rotor system described in the present invention, the control system controls the servo motor to work, and drives the main shaft of the turbine pump rotor system and the faulty main shaft support bearings, main shaft loading bearings and oxygen pump centrifugal wheel on the main shaft of the turbine pump rotor system to perform variable speed operation through the planetary gear speed increaser. In this process, according to the experimental needs, the maximum speed of the speed regulating servo motor, the acceleration time when the maximum speed is reached, and the deceleration time when the speed drops to zero can be set by the control system. The severity of various faults can be set by replacing the faulty main shaft support bearings with different fault degrees and by adjusting the gap between the friction ring and the oxygen pump centrifugal wheel, so as to study the multi-fault simulation of the turbine pump rotor system in the process of variable speed at different speeds, so as to simulate the dynamic and static friction faults, blade breakage and bearing faults of the turbine pump under variable speed conditions, thereby meeting the requirements of fault diagnosis technology research and operation teaching in the laboratory environment of the turbine pump. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural diagram of the present invention;

[0018] Figure 2 It is a structural diagram of the friction top screw assembly 8 in the present invention;

[0019] Figure 3 It is a structural diagram of the oxygen pump centrifugal wheel 15;

[0020] Figure 4 is a structural diagram of the oxygen pump inducer 16;

[0021] Figure 5 It is a structural diagram of the main shaft 4 of the turbo pump rotor system;

[0022] Figure 6 A structural diagram of a centrifugal wheel 12 with broken fuel pump blades;

[0023] Figure 7 A structural diagram of a faulty bearing 6 for main shaft support;

[0024] Figure 8 This is a structural diagram of turbine 5.

[0025] Among them, 1 is the servo motor, 2 is the coupling, 3 is the planetary gear speed increaser, 4 is the main shaft of the turbine pump rotor system, 5 is the turbine, 6 is the faulty bearing for main shaft support, 7 is the friction ring, 8 is the friction top screw assembly, 9 is the turbine pump housing, 10 is the large positioning nut, 11 is the main shaft loading bearing, 12 is the fuel pump blade broken centrifugal wheel, 13 is the fuel pump inducer, 14 is the magnetic powder brake, 15 is the oxygen pump centrifugal wheel, 16 is the oxygen pump inducer, 17 is the power switch, and 18 is the control system. DETAILED DESCRIPTION

[0026] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiment of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiment of the present invention. Obviously, the described embodiment is only an embodiment of a part of the present invention, not all embodiments, and is not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concepts disclosed in the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work should fall within the scope of protection of the present invention.

[0027] The accompanying drawings show schematic diagrams of structures according to embodiments disclosed in the present invention. These figures are not drawn to scale, and some details are magnified and some details may be omitted for the purpose of clear expression. The shapes of various regions and layers shown in the figures and the relative sizes and positional relationships therebetween are only exemplary, and may deviate in practice due to manufacturing tolerances or technical limitations, and those skilled in the art may additionally design regions / layers with different shapes, sizes, and relative positions according to actual needs.

[0028] refer to Figures 1 to 8 The multi-fault simulation experimental device for the turbine pump rotor system of the present invention comprises a servo motor 1, a coupling 2, a planetary gear speed increaser 3, a turbine pump housing 9, and a main shaft 4 of the turbine pump rotor system arranged in the turbine pump housing 9, a turbine 5, an oxygen pump centrifugal wheel 15, an oxygen pump inducer 16, a fuel pump blade fracture centrifugal wheel 12, a fuel pump inducer 13, a main shaft support fault bearing 6, a main shaft loading bearing 11, a positioning large nut 10, a friction ring 7, a friction top screw assembly 8 and a magnetic powder brake 14 for simulating the load torque brought by the fluid;

[0029] The output shaft of the servo motor 1 is connected to the input end of the planetary gear speed increaser 3 through the coupling 2, and the output end of the planetary gear speed increaser 3 is connected to one end of the main shaft 4 of the turbine pump rotor system. The output speed of the servo motor 1 is increased by the planetary gear speed increaser 3 to ensure the ultra-high speed working condition of the main shaft 4 of the turbine pump rotor system. The other end of the main shaft 4 of the turbine pump rotor system is connected to a magnetic powder brake 14 after passing through the turbine pump housing 9. A main shaft support bearing 6 and a main shaft loading bearing 11 are arranged between the turbine pump housing 9 and the main shaft 4 of the turbine pump rotor system. A bearing seat is arranged on the inner wall of the turbine pump housing 9. The main shaft support bearing 6 and the main shaft loading bearing 11 are located on the bearing seat. The main shaft 4 of the turbine pump rotor system is loaded by the main shaft support bearing 6 and the magnetic powder brake 14 to simulate the load effect of the real fluid on the turbine pump.

[0030] In this embodiment, the turbine 5, the oxygen pump inducer 16, the oxygen pump centrifugal wheel 15, the fuel pump blade fracture centrifugal wheel 12 and the fuel pump inducer 13 are sequentially arranged on the main shaft 4 of the turbine pump rotor system.

[0031] The turbine 5 is fixed to the main shaft 4 of the turbo pump rotor system through a pin connection.

[0032] The oxygen pump inducer 16 and the oxygen pump centrifugal wheel 15 as well as the fuel pump inducer 13 and the fuel pump blade-breaking centrifugal wheel 12 are connected to transmit torque through mortise and tenon structures.

[0033] The oxygen pump centrifugal wheel 15 and the main shaft 4 of the turbine pump rotor system as well as the fuel pump blade-breaking centrifugal wheel 12 and the main shaft 4 of the turbine pump rotor system are connected by keys to achieve circumferential positioning.

[0034] The first positioning large nut 10 is located between the fuel pump inducer 13 and the inner wall of the turbo pump housing 9, and the second positioning large nut 10 is located between the main shaft loading bearing 11 and the oxygen pump centrifugal wheel 15. The two positioning large nuts 10 are sleeved on the main shaft 4 of the turbo pump rotor system.

[0035] There are two faulty bearings 6 for main shaft support. The fixing form of the faulty bearings 6 for main shaft support adopts a method of fixing one end and floating the other end to ensure the good working stability of the main shaft 4 of the turbine pump rotor system and eliminate the adverse effects and damage caused by large shaft expansion and contraction due to a long shaft or temperature factors. The oxygen pump bearing is an angular contact ball bearing, and the inner and outer rings are fixed in both directions by a sleeve and a clamping ring, bearing part of the radial force and all the axial force. The fuel pump bearing is a deep groove ball bearing, and both sides of the bearing outer ring are not fixed, and it only bears part of the radial force.

[0036] The control system 18 includes an electric control cabinet, buttons, indicator lights, a power switch 17 arranged on the electric control cabinet, and a controller arranged in the box; the output end of the controller is connected to the control end of the servo motor 1 to realize variable frequency speed regulation of the servo motor 1, and the controller is connected to the buttons, indicator lights and the power switch 17.

[0037] The friction ring 7 is fixed to the inner wall of the turbine pump housing 9 by a friction top screw assembly 8, and the friction ring 7 is opposite to the oxygen pump centrifugal wheel 15; the friction top screw assembly 8 includes two connecting screws and an intermediate screw for adjusting the clearance between the moving and static parts, the screws on both sides pass through the turbine pump housing 9 and are threadedly connected with the friction ring 7 to achieve the positioning of the friction ring 7, there is a spring between the heads of the connecting screws on both sides and the turbine pump housing 9, the spring is pressed and fixed on the turbine pump housing 9 by the heads of the connecting screws, the intermediate screw is threadedly connected to the turbine pump housing 9 and pressed on the surface of the friction ring 7, when the thread depth of the intermediate screw is adjusted, the springs on the connecting screws on both sides are compressed accordingly, thereby achieving the adjustment of the clearance between the friction ring 7 and the oxygen pump centrifugal wheel 15.

[0038] The rotor crack and turbine pump blade fracture faults were simulated by preparing the centrifugal wheel 12 with a fuel pump blade fracture. The blade fracture of the faulty part occurred at the inlet blade root and was distributed along the blade axis. The crack was straight and penetrated the blade thickness. It was basically perpendicular to the inlet edge along the front and rear streamlines. The faulty part showed low-temperature brittle cracking characteristics. The oxygen pump bearing in the main shaft support faulty bearing 6 was prepared as a faulty part with inner ring, outer ring and rolling element defects to simulate the turbine pump bearing failure. The bearing damage was processed by electrospark to produce single-point damage of different diameters, including single-defect bearing faulty parts and composite-defect faulty parts.

[0039] The specific working process of the present invention is:

[0040] In actual operation, before the power switch 17 is turned on, the faulty bearing 6 for the main shaft support of normal or different fault types and different fault degrees is replaced as needed, and the gap between the friction ring 7 and the oxygen pump centrifugal wheel 15 can be adjusted by the friction top screw assembly 8, so as to control the severity of the bearing fault and the dynamic and static friction fault, and realize the setting of single fault, blade breakage, bearing damage and dynamic and static friction composite fault; when the power switch 17 is turned on, the maximum speed of the servo motor 1, the acceleration time when the maximum speed is reached and the deceleration time when the speed drops to zero are set in the control system 18. After the parameter setting is completed, the control system 18 controls the servo motor 1 to work, and the servo motor 1 drives the planetary gear speed increaser 3 and the main shaft 4 of the turbine pump rotor system to run at variable speeds, so as to obtain the fault experimental data of the turbine pump rotor system during the variable speed process at different speeds. After the operation is completed, the power switch 17 is turned off.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A multi-fault simulation experimental device for a turbine pump rotor system, characterized in that: It comprises a servo motor (1), a planetary gear speed increaser (3), a faulty bearing for main shaft support (6), a centrifugal wheel with broken fuel pump blades (12), a main shaft of a turbine pump rotor system (4), a turbine pump housing (9), a friction ring (7) and a control system (18); The output shaft of the servo motor (1) is connected to the input end of the planetary gear speed increaser (3), the output end of the planetary gear speed increaser (3) is connected to one end of the main shaft (4) of the turbine pump rotor system, the other end of the main shaft (4) of the turbine pump rotor system passes through the turbine pump housing (9) and is connected to a magnetic powder brake (14), a main shaft support fault bearing (6) and a main shaft loading bearing (11) are arranged between the inner wall of the turbine pump housing (9) and the main shaft (4) of the turbine pump rotor system, an oxygen pump centrifugal wheel (15) is arranged in the turbine pump housing (9), and the oxygen pump centrifugal wheel (15) is sleeved on the main shaft (4) of the turbine pump rotor system; a friction ring (7) is fixed on the inner wall of the turbine pump housing (9), the friction ring (7) is directly opposite to the oxygen pump centrifugal wheel (15), and a control system (18) is connected to the servo motor (1); The friction ring (7) is fixed to the inner wall of the turbine pump housing (9) through a friction top screw assembly (8), and the friction ring (7) faces the oxygen pump centrifugal wheel (15).

2. The multi-fault simulation experimental device for a turbine pump rotor system according to claim 1 is characterized in that: The friction top screw assembly (8) comprises two connecting screws and an intermediate screw for adjusting the clearance between the moving and stationary parts, wherein the two connecting screws pass through the side wall of the turbine pump housing (9) and are inserted into the friction ring (7), and a spring is arranged between the head of the connecting screw and the outer wall of the turbine pump housing (9); the intermediate screw contacts the surface of the friction ring (7) after passing through the turbine pump housing (9), and the intermediate screw is threadedly connected to the turbine pump housing (9).

3. The multi-fault simulation experimental device for a turbine pump rotor system according to claim 1 is characterized in that: The output shaft of the servo motor (1) is connected to the input end of the planetary gear speed increaser (3) via a coupling (2).

4. The multi-fault simulation experimental device for a turbine pump rotor system according to claim 1 is characterized in that: A bearing seat is arranged on the inner wall of the turbine pump housing (9), and a main shaft supporting fault bearing (6) and a main shaft loading bearing (11) are located on the bearing seat.

5. The multi-fault simulation experimental device for a turbine pump rotor system according to claim 1 is characterized in that: The invention also comprises a turbine (5), an oxygen pump inducer (16) and a fuel pump inducer (13), wherein the turbine (5), the oxygen pump inducer (16), the oxygen pump centrifugal wheel (15), the fuel pump blade fracture centrifugal wheel (12) and the fuel pump inducer (13) are sequentially arranged on the main shaft (4) of the turbine pump rotor system.

6. The multi-fault simulation experimental device for a turbine pump rotor system according to claim 5 is characterized in that: The turbine (5) is fixed to the main shaft (4) of the turbine pump rotor system through a pin connection.

7. The multi-fault simulation experimental device for a turbine pump rotor system according to claim 5, characterized in that: The oxygen pump centrifugal wheel (15) and the main shaft (4) of the turbine pump rotor system, as well as the fuel pump blade-breaking centrifugal wheel (12) and the main shaft (4) of the turbine pump rotor system are connected respectively via keys.

8. The multi-fault simulation experimental device for a turbine pump rotor system according to claim 7 is characterized in that: The oxygen pump inducer (16) and the oxygen pump centrifugal wheel (15) as well as the fuel pump inducer (13) and the fuel pump blade-breaking centrifugal wheel (12) are connected through mortise and tenon structures to transmit torque.

9. The multi-fault simulation experimental device for a turbine pump rotor system according to claim 1, characterized in that: The control system (18) comprises an electric control cabinet, buttons, indicator lights and a power switch (17) arranged on the electric control cabinet, and a controller arranged in the box; the output end of the controller is connected to the control end of the servo motor (1), and the controller is connected to the buttons, indicator lights and the power switch (17).

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