Adjustable electric auxiliary turbocharger rotor experiment device

Abstract

The invention discloses an adjustable electric auxiliary turbocharger rotor experiment device, which comprises a gas compressor disc end, a turbine disc end and a motor, and is characterized in that the bottom of the gas compressor disc end is provided with an axial adjustment support table, and the bottom of the turbine disc end is provided with a vertical adjustment support table; the compressor disc end comprises a left machine base, a compressor base and a compressor disc. A first floating ring bearing, a first fixing flange and a first sleeve which are arranged on the center shaft in a sleeving mode are arranged in the left machine base. The turbine disc end comprises a right machine base, a turbine base and a turbine disc. A second floating ring bearing, a second fixing flange and a second sleeve which are arranged on the center shaft in a sleeving mode are arranged in the right machine base. The axial adjusting support table comprises a left support table, a horizontal adjusting table and a base; the vertical adjusting supporting table comprises a right supporting table body and a vertical adjusting table body. The invention aims to provide the turbocharger rotor experiment device capable of changing the bearing span, the bearing coaxiality and the unbalance amount of the rotor.

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 automobile industry and internal combustion engines, exhaust gas turbocharging technology has been widely used in engine design due to its advantages in fuel economy, exhaust emission environmental protection and engine performance improvement. However, due to the influence of the variable load environment, harsh working environment and significant hysteresis effect, the turbocharger rotor system is prone to fatigue failure, overspeed damage and other faults. In order to solve the engineering problems of traditional turbochargers, the design of high-speed motor-assisted turbochargers came into being. The design of new electric-assisted turbochargers needs to consider more complex shaft assembly parameters and assembly process errors, which will lead to prominent overall vibration problems and vibration damage of some components. Losses and other practical engineering problems in actual engineering will change the initial structure of the rotor system, resulting in uncertainty in the structural vibration response. And with the prominence of vibration problems, the contact state between the shaft system mating parts will also change during processing and assembly. This contact nonlinearity will have a greater impact on the vibration characteristics of the rotor system, and the parameter uncertainty caused by the connection structure will also bring challenges to the structural dynamics design of the turbocharger. The overall vibration characteristics are highly dependent on the changes in the assembly parameters of the shaft system parts, the influence of the assembly process of the shaft system parts, and the stability.

[0003] There are many problems with the existing turbocharger rotor test device: 1. Since the traditional test bench adopts an integrated design method, the contact effect between the axial components is completely ignored, and it is impossible to carry out 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 the imbalance of the rotor system under static conditions. At the same time, the parameter matching relationship between the form of the seat hole eccentricity and the size of the eccentricity and the influence of dynamic characteristics is also difficult to verify through experiments; 3. The shaft system components are difficult or even impossible to adjust, and it is difficult to verify the experimental results under different parameters. Therefore, there is an urgent need for a turbocharger rotor test device 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 above-mentioned prior art and to provide a turbocharger rotor test device capable of changing the bearing span and the 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 comprises a compressor disc end, a turbine disc end and a motor, wherein the compressor disc end and the turbine disc end are jointly 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 comprises a left machine base, a compressor base and a compressor disc, the left machine base is arranged outside the central shaft, an oil supply nozzle is arranged on the outer peripheral surface of the left machine base, a first floating ring bearing, a first fixed flange and a first sleeve which are sleeved on the central shaft are arranged in the left machine base, the first fixed 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 machine base, the side ends of the compressor base and the left machine 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 member on the end cover, an oil outlet plate and an oil sealing cover are arranged on the side end of the first fixed flange, the compressor base presses the oil sealing cover and the oil outlet plate onto the first fixed flange, and an oil guide passage which passes through the first fixed flange and the oil outlet plate is arranged at the oil supply nozzle of the left machine base, and the oil guide passage is sealed by the oil sealing cover;

[0008] The turbine disk end includes a right machine base, a turbine seat and a turbine disk. 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 seat is located on one side of the right machine base. A pressure rotating shaft seal for sealing is arranged between the right machine base and the turbine seat. The side ends of the right machine base and the turbine seat are both closed by end covers. The turbine disk is arranged in the turbine seat. The turbine seat and the turbine disk are fixed to the central shaft by locking pieces on the end covers. The right machine base is provided with an oil guide passage which directly passes through the second floating ring bearing and the second fixed flange at the oil supply nozzle. The oil guide passage 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, and 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 a side of an end cover of the first floating ring bearing facing the left machine base, and the second sleeve is arranged on a side of an 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, and can realize the measurement and analysis experiments of the dynamic characteristics of the rotor system under different eccentricities. The relative position between the compressor disk and the turbine disk is adjusted by the axial adjustment support platform to realize the setting of different bearing spans; the sleeves in the compressor disk end and the turbine disk end can also be adjusted to two-section sleeves according to experimental requirements, and the two sections of the 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 realized; the compressor disk and the turbine disk 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 simulation experiment is carried out, and finally the adjustment of different parameters in the shaft system is realized. 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 It is a structural schematic diagram 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 disk, 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 comprises a compressor disc end 1, a turbine disc end 2 and a motor 3, wherein the compressor disc end 1 and the turbine disc end 2 are jointly provided with a central axis 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 machine base 11, a compressor base 10 and a compressor disc 9. The left machine base 11 is arranged outside the central shaft 6. The outer peripheral surface of the left machine base 11 is provided with an oil supply nozzle 12. The left machine base 11 is provided with a first floating ring bearing 16, a first fixed flange 17 and a first sleeve 15 sleeved on the central shaft 6. 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 machine base 11. The compressor base 10 and the left machine base 11 The side ends of the compressor 10 are closed by the end cover 7, the compressor plate 9 is arranged in the compressor base 10, the compressor base 10 and the compressor plate 9 are fixed to the side end of the central shaft 6 by 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 on the first fixed flange 17, and the left base 11 is provided with an oil guide passage 21 passing through the first fixed flange 17 and the oil outlet plate 18 at the oil supply nozzle 12, and the oil guide passage 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 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 at the other side of the right machine base 22. On the middle side, a pressure rotary shaft seal 26 for sealing is arranged 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 disk 25 is arranged in the turbine base 24. The turbine base 24 and the turbine disk 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 through a connecting member 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 base 11, and cooperates with the oil outlet plate 18 and the oil sealing 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 base 22, and cooperates with the pressure rotary shaft seal 26 to form an oil film.

[0029] Among them, the first sleeve 15 and the second sleeve 28 can be set to two sections of unequal lengths, and the sleeves divided into two sections are both arranged on both sides of the corresponding floating ring bearing. The first sleeve 15 is arranged on the side of the end cover 7 of the first floating ring bearing 16 facing the left machine base 11, and the second sleeve 28 is arranged on the side of the end cover 7 of the second floating ring bearing 27 facing 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 changing 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 arranged close to the end cover 7, which can be easily disassembled and reassembled, and it is convenient to adjust the position of the floating ring bearing to change the bearing span.

[0030] A plurality of detachable counterweight bolts are provided on the compressor disk 9 and the turbine disk 25. The weight and number of the counterweight bolts are adjusted to simulate the unbalance of the rotating shaft and to conduct a simulated typical assembly failure experiment.

[0031] By adjusting different shaft system 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 effect of the bearing concentricity on the impeller dynamic characteristics, the motor rotor amplitude and the axis trajectory at different speeds can be tested.

[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, and the influence of the front and rear impeller imbalance on the impeller dynamic characteristics, motor rotor amplitude and axis trajectory at different speeds can be tested.

[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 simultaneously 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 set up by drilling holes 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. Similarly, displacement sensors can also be set up to measure the vibration displacement of the central axis in the x and y directions.

[0036] The initial parameters of the shaft system and the unbalance amount on the disk are set. After completing the above adjustments and settings, the vibration displacements 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 are recorded through the signal acquisition system to provide data support for the electric-assisted turbocharger rotor model. The signal acquisition system and method can adopt existing technologies, such as: Tester data acquisition system or 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 principle of the present invention should be included in the protection scope 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 jointly provided with a central axis (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) comprises a left machine base (11), a compressor base (10) and a compressor disc (9). The left machine base (11) is arranged outside the central shaft (6). The outer peripheral surface of the left machine base (11) is provided with an oil supply nozzle (12). The left machine base (11) is provided with a first floating ring bearing (16) sleeved on the central shaft (6), a first fixing flange (17) and a first sleeve (15). 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 machine base (11). The side surfaces of the compressor base (10) and the left machine base (11) are The ends are sealed by an end cover (7), a compressor plate (9) is arranged in a compressor base (10), the compressor base (10) and the compressor plate (9) are fixed to the side end of the central shaft (6) by means of a thrust limit bearing (20) and a locking member (8) on the end cover (7), an oil outlet plate (18) and an oil sealing cover (19) are arranged at the side end of the first fixed flange (17), the compressor base (10) presses the oil sealing cover (19) and the oil outlet plate (18) onto the first fixed flange (17), an oil guide passage (21) passing through the first fixed flange (17) and the oil outlet plate (18) is arranged at the left base (11) at the oil supply nozzle (12), and the oil guide passage (21) is sealed by the oil sealing cover (19); The turbine disk end (2) comprises a right machine base (22), a turbine base (24) and a turbine disk (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 arranged 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 arranged 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) directly connected to the second floating ring bearing (27) and the second fixed flange (23) is arranged at the oil supply nozzle (12) of the right machine base (22). The oil guide passage (21) is sealed by a pressure rotary shaft seal (26).

2. The adjustable electrically assisted turbocharger rotor test 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 clamping 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); and 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 in two sections of unequal lengths, and the sleeves divided into two sections are 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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