An adjustable electrically assisted turbocharger rotor experimental device

Abstract

The present invention discloses an adjustable electrically assisted turbocharger rotor test device, comprising a compressor disc end, a turbine disc end, and an electric motor. An axial adjustment support platform is provided at the bottom of the compressor disc end, and a vertical adjustment support platform is provided at the bottom of the turbine disc end. The compressor disc end comprises a left base, a compressor base, and a compressor disc. The left base comprises a first floating ring bearing sleeved on a central shaft, a first fixing flange, and a first sleeve. The turbine disc end comprises a right base, a turbine base, and a turbine disc. The right base comprises a second floating ring bearing sleeved on a central shaft, a second fixing flange, and a second sleeve. The axial adjustment support platform comprises a left support platform, a horizontal adjustment platform, and a base. The vertical adjustment support platform comprises a right support platform and a vertical adjustment platform. The present invention aims to provide a turbocharger rotor test device capable of adjusting bearing span, bearing coaxiality, and rotor imbalance.

Description

Technical Field

[0001] The invention relates to the technical field of rotating machinery test benches, and in particular to an adjustable electrically assisted turbocharger rotor test device. Background Art

[0002] With the development of the automotive industry and internal combustion engines, exhaust gas turbocharging technology has been widely adopted in engine design due to its advantages in fuel economy, environmentally friendly exhaust emissions, and improved engine performance. However, due to issues such as variable load environments, harsh operating conditions, and significant hysteresis, turbocharger rotor systems are prone to fatigue failure, overspeed damage, and other failures. To address the engineering challenges of traditional turbochargers, high-speed electric motor-assisted turbochargers have emerged. The design of new electrically assisted turbochargers requires consideration of more complex shafting assembly parameters and assembly process variations, leading to significant overall vibration issues and vibration damage to some components. Losses and other practical engineering issues in actual engineering can alter the initial structure of the rotor system, leading to uncertainty in the structural vibration response. Furthermore, as vibration issues become more prominent, the contact state between mating shafting components during machining and assembly also changes. This contact nonlinearity significantly impacts the vibration characteristics of the rotor system. The parameter uncertainty introduced by the connection structure also poses challenges to the structural dynamics design of the turbocharger. The overall vibration characteristics are highly dependent on variations in shafting assembly parameters, the impact of the shafting assembly process, and stability.

[0003] Existing turbocharger rotor test equipment has many problems: 1. Because the traditional test bench adopts an integrated design method, the contact effect between axial components is completely ignored, making it impossible to conduct experimental research and testing on the contact characteristics of the rotor test bench under different working conditions; 2. There are angle or position deviations when the bearing seat is installed, which leads to imbalance of the rotor system under static conditions. At the same time, the parameter matching relationship between the form and size of the seat hole eccentricity and the influence of dynamic characteristics is difficult to verify through experiments; 3. The shaft system components are difficult or even impossible to adjust, making it difficult to verify the experimental results under different parameters. Therefore, there is an urgent need for a turbocharger rotor test equipment that can change the bearing span and bearing coaxiality, as well as the rotor imbalance. Summary of the Invention

[0004] The purpose of the present invention is to overcome the deficiencies in the prior art and to provide a turbocharger rotor testing device capable of changing the bearing span and bearing coaxiality, as well as the rotor unbalance.

[0005] To achieve the above object, the present invention is implemented through the following technical solutions:

[0006] An adjustable electrically assisted turbocharger rotor experimental device includes a compressor disc end, a turbine disc end, and a motor. The compressor disc end and the turbine disc end are both provided with a central axis and are axially connected to the motor. An axial adjustment support platform is provided at the bottom of the compressor disc end, and a vertical adjustment support platform is provided at the bottom of the turbine disc end.

[0007] The compressor disc end includes a left base, a compressor base and a compressor disc, the left base is arranged outside the central shaft, the outer circumferential surface of the left base is provided with an oil supply nozzle, the left base is provided with a first floating ring bearing, a first fixing flange and a first sleeve sleeved on the central shaft, the first fixing flange and the first sleeve are respectively located on both sides of the first floating ring bearing and lock the position of the first floating ring bearing, the compressor base is connected to one side of the left base, the side ends of the compressor base and the left base are both closed by an end cover, the compressor disc is arranged in the compressor base, the compressor base and the compressor disc are fixed to the side end of the central shaft by a thrust limit bearing and a locking piece on the end cover, the side end of the first fixing flange is provided with an oil outlet plate and an oil sealing cover, the compressor base presses the oil sealing cover and the oil outlet plate onto the first fixing flange, and the left base is provided with an oil guide passage passing through the first fixing flange and the oil outlet plate at the oil supply nozzle, and the oil guide passage is sealed by the oil sealing cover;

[0008] The turbine disc end includes a right machine base, a turbine base and a turbine disc. The right machine base is arranged outside the central shaft. The outer peripheral surface of the right machine base is provided with an oil supply nozzle. The right machine base is provided with a second floating ring bearing, a second fixed flange and a second sleeve which are sleeved on the central shaft. The second fixed flange and the second sleeve are respectively located on both sides of the second floating ring bearing and lock the position of the second floating ring bearing. The turbine base is located on one side of the right machine base. A pressure rotating shaft seal for sealing is provided between the right machine base and the turbine base. The side ends of the right machine base and the turbine base are both closed by end covers. The turbine disc is arranged in the turbine base. The turbine base and the turbine disc are fixed to the central shaft by locking pieces on the end covers. The right machine base is provided with an oil guide channel which directly passes through the second floating ring bearing and the second fixed flange at the oil supply nozzle. The oil guide channel is sealed by a pressure rotating shaft seal.

[0009] Furthermore, the axial adjustment support platform includes a left support platform, a horizontal adjustment platform and a base. The left support platform is fixedly connected to the bottom of the left machine base. The horizontal adjustment platform is provided with an adjustment knob for adjusting the axial position. The base is arranged at the bottom of the horizontal adjustment platform and is provided with a clamping knob for locking the position of the horizontal adjustment platform.

[0010] Furthermore, the vertical adjustment support platform includes a right support platform and a vertical adjustment platform. The right support platform is fixedly connected to the bottom of the right machine base through a connecting piece. The vertical adjustment platform is provided with an adjustment knob for adjusting the vertical position.

[0011] Furthermore, the first sleeve and the second sleeve can be configured as two sections of unequal lengths, and the two sections of the sleeve are both configured on both sides of the corresponding floating ring bearing.

[0012] Furthermore, the first sleeve is arranged on the side of the end cover of the first floating ring bearing facing the left machine base, and the second sleeve is arranged on the side of the end cover of the second floating ring bearing facing the right machine base.

[0013] Furthermore, the compressor disc and the turbine disc are both provided with a plurality of detachable counterweight bolts.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] The present invention realizes the adjustment of the concentricity of the front and rear split-type bearing seat holes through the vertical adjustment support platform, which can realize the measurement and analysis experiments of the dynamic characteristics of the rotor system under different eccentricities, and realizes the setting of different bearing spans by adjusting the relative position between the compressor disc and the turbine disc through the axial adjustment support platform; the sleeves in the compressor disc end and the turbine disc end can also be adjusted to two sections of sleeves according to experimental requirements, and the two sections of sleeves are respectively located on both sides of the floating ring bearing. By changing the thickness of the sleeves on both sides of the floating ring bearing, different bearing span changes can be achieved; the compressor disc and the turbine disc are equipped with counterweight bolts. By adjusting the weight and number of the counterweight bolts, the imbalance of the rotating shaft is simulated, and a typical assembly failure experiment is simulated, thereby finally achieving the adjustment of different parameters in the shaft system. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of the present invention;

[0017] Figure 2 is a cross-sectional view of the compressor disc end of the present invention;

[0018] Figure 3 is a cross-sectional view of the turbine disc end of the present invention;

[0019] Figure 4 Schematic diagram of the structure of the vertical adjustment support platform in the present invention;

[0020] Figure 5 It is a structural schematic diagram of the axially adjustable support platform in the present invention.

[0021] Reference numerals:

[0022] 1- compressor disc end, 2- turbine disc end, 3- motor, 4- vertical adjustment support platform, 5- axial adjustment support platform, 6- center shaft, 7- end cover, 8- locking piece, 9- compressor disc, 10- compressor base, 11- left base, 12- oil supply nozzle, 13- fixing piece, 14- sealing ring, 15- first sleeve, 16- first floating ring bearing, 17- first fixing flange, 18- oil outlet plate, 19- oil seal Cover, 20-thrust limit bearing, 21-oil guide channel, 22-right machine base, 23-second fixed flange, 24-turbine base, 25-turbine disc, 26-pressure rotary shaft seal, 27-second floating ring bearing, 28-second sleeve, 29-right support platform, 30-connecting part, 31-vertical adjustment platform, 32-adjustment knob, 33-left support platform, 34-horizontal adjustment platform, 35-base, 36-tightening knob. DETAILED DESCRIPTION

[0023] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0024] like Figures 1 to 5 As shown, an adjustable electrically assisted turbocharger rotor experimental device includes a compressor disc end 1, a turbine disc end 2, and a motor 3. The compressor disc end 1 and the turbine disc end 2 are jointly provided with a central shaft 6 and are axially connected to the motor 3. An axial adjustment support platform 5 is provided at the bottom of the compressor disc end 1, and a vertical adjustment support platform 4 is provided at the bottom of the turbine disc end 2.

[0025] The compressor disc end 1 includes a left base 11, a compressor base 10 and a compressor disc 9. The left base 11 is arranged outside the central shaft 6. The outer peripheral surface of the left base 11 is provided with an oil supply nozzle 12. The left base 11 is provided with a first floating ring bearing 16, a first fixing flange 17 and a first sleeve 15 sleeved on the central shaft 6. The first fixing flange 17 and the first sleeve 15 are respectively located on both sides of the first floating ring bearing 16 and lock the position of the first floating ring bearing 16. The compressor base 10 is connected to one side of the left base 11. The compressor base 10 and the left base 11 The side ends of the compressor are closed by end covers 7. The compressor disc 9 is arranged in the compressor base 10. The compressor base 10 and the compressor disc 9 are fixed to the side ends of the central shaft 6 by thrust limit bearings 20 and locking members 8 on the end covers 7. The side ends of the first fixed flange 17 are provided with an oil outlet plate 18 and an oil sealing cover 19. The compressor base 10 presses the oil sealing cover 19 and the oil outlet plate 18 onto the first fixed flange 17. The left base 11 is provided with an oil guide channel 21 passing through the first fixed flange 17 and the oil outlet plate 18 at the oil supply nozzle 12. The oil guide channel 21 is sealed by the oil sealing cover 19.

[0026] The turbine disc end 2 includes a right machine base 22, a turbine base 24 and a turbine disc 25. The right machine base 22 is arranged outside the central shaft 6. The outer peripheral surface of the right machine base 22 is provided with an oil supply nozzle 12. The right machine base 22 is provided with a second floating ring bearing 27, a second fixed flange 23 and a second sleeve 28 sleeved on the central shaft 6. The second fixed flange 23 and the second sleeve 28 are respectively located on both sides of the second floating ring bearing 27 and lock the position of the second floating ring bearing 27. The turbine base 24 is located on the other side of the right machine base 22. On the middle side, a pressure rotary shaft seal 26 for sealing is provided between the right machine base 22 and the turbine base 24. The side ends of the right machine base 22 and the turbine base 24 are closed by the end cover 7. The turbine disc 25 is arranged in the turbine base 24. The turbine base 24 and the turbine disc 25 are fixed to the central shaft 6 by the locking piece 8 on the end cover 7. The right machine base 22 is provided with an oil guide channel 21 directly connected to the second floating ring bearing 27 and the second fixed flange 23 at the oil supply nozzle 12. The oil guide channel 21 is sealed by the pressure rotary shaft seal 26.

[0027] The axial adjustment support platform 5 includes a left support platform 33, a horizontal adjustment platform 34, and a base 35. The left support platform 33 is fixedly connected to the bottom of the left machine base 11. The horizontal adjustment platform 34 is provided with an adjustment knob 32 for adjusting the axial position. The base 35 is provided at the bottom of the horizontal adjustment platform 34 and is provided with a clamping knob 36 for locking the position of the horizontal adjustment platform 34. The vertical adjustment support platform 4 includes a right support platform 29 and a vertical adjustment platform 31. The right support platform 29 is fixedly connected to the bottom of the right machine base 22 via a connector 30. The vertical adjustment platform 31 is provided with an adjustment knob 32 for adjusting the vertical position.

[0028] like Figure 4 and Figure 5 As shown, the vertical adjustment support platform 4 in the present invention is used to adjust the vertical position to achieve the adjustment of the initial coaxiality of the floating ring bearings of the compressor base 10 and the turbine base 24 in the vertical direction. The axial adjustment support platform 5 is used to adjust the axial position to achieve the span adjustment of the initial floating ring bearings of the compressor base 10 and the turbine base 24 in the axial direction. The vertical adjustment support platform 4 can adopt the AZ60-AC model adjustment platform of Yuhan Precision Machinery, and the axial adjustment support platform 5 can adopt the LX60-L-25 model adjustment platform of Yucheng Industry. The first floating ring bearing 16 is filled with oil from the oil guide channel 21 and the oil supply nozzle 12 on the left machine base 11, and cooperates with the oil outlet plate 18 and the oil seal cover 19 to form an oil film. The second floating ring bearing 27 is filled with oil from the oil guide channel 21 and the oil supply nozzle 12 of the right machine base 22, and cooperates with the pressure rotary shaft seal 26 to form an oil film.

[0029] The first sleeve 15 and the second sleeve 28 can both be configured as two sections of unequal length, and the two-section sleeves are both disposed on both sides of the corresponding floating ring bearings. The first sleeve 15 is disposed on the side of the first floating ring bearing 16 facing the end cover 7 of the left machine base 11, and the second sleeve 28 is disposed on the side of the second floating ring bearing 27 facing the end cover 7 of the right machine base 22. The first sleeve 15 and the second sleeve 28 are divided into two sections and are respectively located on both sides of the floating ring bearing. By varying the thickness of the sleeves on both sides of the floating ring bearing, different bearing span changes can be achieved. The first sleeve 15 and the second sleeve 28 are both disposed close to the end cover 7, enabling easy disassembly and reassembly, and facilitating adjustment of the position of the floating ring bearing to change the bearing span.

[0030] The compressor disc 9 and the turbine disc 25 are both provided with a plurality of detachable counterweight bolts. By adjusting the weight and number of the counterweight bolts, the shaft imbalance is simulated and a typical assembly failure experiment is conducted.

[0031] By adjusting different shafting parameters during the experiment, the present invention can perform different experiments:

[0032] (1) Split-type machining of bearing seat hole misalignment experiment: By adjusting the adjustment knob 32 in the vertical adjustment support platform 4, the right support platform 29 is adjusted to move in the vertical direction, thereby simulating the misalignment of the central axis 6 with the left machine base 11 and the right machine base 22. The experiment of the influence of the bearing concentricity on the impeller dynamic characteristics, the motor rotor amplitude and the axis trajectory at different speeds can be carried out.

[0033] (2) Front and rear impeller imbalance experiment: By adjusting the weight and number of counterweight bolts on the compressor disk 9 and the turbine disk 25, the unbalanced mass of the central shaft 6 is constructed. Experiments can be conducted on the influence of the front and rear impeller imbalance on the impeller dynamic characteristics, motor rotor amplitude and axis trajectory at different speeds.

[0034] (3) Experiments on different spans of floating ring bearings: By adjusting the adjustment knob 32 in the axial adjustment support platform 5, the left support platform 33 is adjusted to move in the axial direction. At the same time, the first sleeve 15 and the second sleeve 28 are split into two sleeve sections. By using a combination of sleeves of different sizes, the positions of the first floating ring bearing 16 and the second floating ring bearing 27 are adjusted, thereby changing the bearing spans of the compressor disc end 1 and the turbine disc end 2. In this way, experiments are conducted on the influence of the floating ring bearing span on the impeller dynamic characteristics, the motor rotor amplitude and the axis trajectory at different speeds.

[0035] During the experiment, multiple eddy current sensors can be installed on the compressor disk 9 and the turbine disk 25 to measure the lateral displacement of the compressor disk end 1 and the turbine disk end 2. Displacement sensors can also be installed to measure the vibration displacement of the central axis in the x and y directions.

[0036] After setting the initial parameters of the shaft system and the imbalance on the disk, the signal acquisition system records the vibration displacement of the central shaft in the x and y directions under different parameters, as well as the lateral displacement data of the compressor disk end 1 and the turbine disk end 2, to provide data support for the electrically assisted turbocharger rotor model. The signal acquisition system and method can adopt existing technologies, such as the Tester data acquisition system or the LMS SCADAS data acquisition system.

[0037] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An adjustable electrically assisted turbocharger rotor experimental device, comprising a compressor disc end (1), a turbine disc end (2) and a motor (3), characterized in that: The compressor disc end (1) and the turbine disc end (2) are both provided with a central shaft (6) and are axially connected to the motor (3); an axial adjustment support platform (5) is provided at the bottom of the compressor disc end (1), and a vertical adjustment support platform (4) is provided at the bottom of the turbine disc end (2); The compressor disc end (1) includes a left base (11), a compressor base (10) and a compressor disc (9). The left base (11) is arranged outside the central shaft (6). The outer peripheral surface of the left base (11) is provided with an oil supply nozzle (12). The left base (11) is provided with a first floating ring bearing (16) sleeved on the central shaft (6), a first fixed flange (17) and a first sleeve (15). The first fixed flange (17) and the first sleeve (15) are respectively located on both sides of the first floating ring bearing (16) and lock the position of the first floating ring bearing (16). The compressor base (10) is connected to one side of the left base (11). The side of the compressor base (10) and the left base (11) The ends are sealed by end covers (7), the compressor disc (9) is arranged in the compressor base (10), the compressor base (10) and the compressor disc (9) are fixed to the side end of the central shaft (6) through the thrust limit bearing (20) and the locking member (8) on the end cover (7), the side end of the first fixed flange (17) is provided with an oil outlet plate (18) and an oil sealing cover (19), the compressor base (10) presses the oil sealing cover (19) and the oil outlet plate (18) onto the first fixed flange (17), and the left base (11) is provided with an oil guide channel (21) passing through the first fixed flange (17) and the oil outlet plate (18) at the oil supply nozzle (12), and the oil guide channel (21) is sealed by the oil sealing cover (19); The turbine disc end (2) includes a right machine base (22), a turbine base (24) and a turbine disc (25). The right machine base (22) is arranged outside the central shaft (6). The outer peripheral surface of the right machine base (22) is provided with an oil supply nozzle (12). The right machine base (22) is provided with a second floating ring bearing (27) sleeved on the central shaft (6), a second fixed flange (23) and a second sleeve (28). The second fixed flange (23) and the second sleeve (28) are respectively located on both sides of the second floating ring bearing (27) and lock the position of the second floating ring bearing (27). The turbine base (24) is located in the middle of the right machine base (22). On one side, a pressure rotary shaft seal (26) for sealing is provided between the right machine base (22) and the turbine base (24). The side ends of the right machine base (22) and the turbine base (24) are both sealed by an end cover (7). A turbine disc (25) is provided in the turbine base (24). The turbine base (24) and the turbine disc (25) are fixed to the central shaft (6) by a locking piece (8) on the end cover (7). An oil guide passage (21) is provided at the oil supply nozzle (12) of the right machine base (22) and is directly connected to the second floating ring bearing (27) and the second fixed flange (23). The oil guide passage (21) is sealed by a pressure rotary shaft seal (26).

2. The adjustable electrically assisted turbocharger rotor experimental device according to claim 1, characterized in that: The axial adjustment support platform (5) comprises a left support platform (33), a horizontal adjustment platform (34) and a base (35); the left support platform (33) is fixedly connected to the bottom of the left machine base (11); the horizontal adjustment platform (34) is provided with an adjustment knob (32) for adjusting the axial position; the base (35) is arranged at the bottom of the horizontal adjustment platform (34) and is provided with a pressing knob (36) for locking the position of the horizontal adjustment platform (34).

3. The adjustable electrically assisted turbocharger rotor test device according to claim 1, characterized in that: The vertical adjustment support platform (4) comprises a right support platform (29) and a vertical adjustment platform (31). The right support platform (29) is fixedly connected to the bottom of the right machine base (22) via a connecting piece (30). The vertical adjustment platform (31) is provided with an adjustment knob (32) for adjusting the vertical position.

4. The adjustable electrically assisted turbocharger rotor test device according to claim 1, characterized in that: The first sleeve (15) and the second sleeve (28) can both be arranged into two sections of unequal lengths, and the two sections of the sleeve are both arranged on both sides of the corresponding floating ring bearing.

5. The adjustable electrically assisted turbocharger rotor test device according to claim 4, characterized in that: The first sleeve (15) is arranged on the side of the first floating ring bearing (16) facing the end cover (7) of the left machine base (11), and the second sleeve (28) is arranged on the side of the second floating ring bearing (27) facing the end cover (7) of the right machine base (22).

6. The adjustable electrically assisted turbocharger rotor test device according to claim 1, characterized in that: The compressor disc (9) and the turbine disc (25) are both provided with a plurality of detachable counterweight bolts.

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