Air compressor bearing cooling air exhaust channel integrated exhaust noise reduction structure

Abstract

The utility model belongs to the technical field of air compressors, and particularly provides an air compressor bearing cooling air exhaust channel integrated exhaust noise reduction structure which comprises a volute and a bearing cooling air flow channel, and the bearing cooling air flow channel is arranged on the volute. A vortex end airflow inlet and a vortex end airflow outlet are formed in the volute, the bearing cooling airflow channel comprises a bearing seat air passing cavity, a bearing cooling air exhaust channel and a bearing cooling air annular outlet, and the direction of the bearing cooling air annular outlet is consistent with that of the vortex end airflow outlet. After the bearing is cooled and heated by the bearing cooling gas, the bearing cooling gas passes through the bearing cooling gas flow channel comprising the bearing seat gas passing cavity and the bearing cooling gas exhaust channel and passes through the bearing cooling gas annular outlet, the gas flow direction of the bearing cooling gas annular outlet is parallel to the vortex end gas flow outlet, the two gas flows do not collide with each other, and the noise is greatly reduced.

Description

TECHNICAL FIELD

[0001] The utility model belongs to air compressor technical field, especially relate to a kind of air compressor bearing cooling gas discharge passage integrated exhaust noise reduction structure. BACKGROUND

[0002] Fuel cell is a kind of efficient and clean energy conversion device, and its core directly generates electric energy through hydrogen-oxygen electrochemical reaction. Proton exchange membrane fuel cell (PEMFC) has become the key development direction of vehicle-mounted power system due to its low-temperature start and high power density characteristics. As a key auxiliary component in the system, the air compressor provides high-pressure oxygen-rich air for the cathode of the stack, and its performance directly affects the output power and efficiency of the fuel cell system.

[0003] Modern air compressors generally use high-speed centrifugal design, and the intake air is compressed to 2.5-3.5 bar pressure range by aerodynamic impeller. To cope with the ultra-high speed operating condition of more than 100,000 revolutions per minute, advanced models use gas suspension bearing technology, and the dynamic pressure air bearing generates significant friction heat during operation. To this end, a specially designed bearing cooling air system introduces part of the compressed air to form a cooling air flow for forced convection heat dissipation. After completing heat exchange, the cooling air flow is usually discharged in two ways: 1) independent bypass discharge, which directly discharges the heated gas outside the system. This is suitable for two-stage compression and expanders; 2) air compressor integrated passage discharge, which discharges the heated gas to the air compressor outlet. This is only suitable for expanders, because only expanders have the function of using the discharged air from the stack to do work again before discharging, so they have an exhaust port. The common practice is to introduce the heated gas from the bearing to the tail exhaust of the fuel cell system through the gas nozzle installed on the motor hole and connected to the rubber tube. This method increases the number of parts such as rubber tubes and clamps, and requires holes on the motor and tail exhaust pipe for installing the gas nozzle to connect the rubber tube. In addition, due to the damage of the rubber tube or the improper installation of the clamp, it is easy to cause air leakage and rubber tube falling off. Moreover, the installation of these parts increases the complexity and rhythm of the customer system. The existing improvement scheme is to integrate the bearing cooling heated gas exhaust path into the volute. However, the exhaust direction of the exhaust port is perpendicular to the direction of the turbine exhaust gas, which will cause air flow collision at the volute outlet and generate noise. Moreover, the exhaust gas from the bearing after cooling and the turbine exhaust gas form a 90-degree angle, and the pressure of the turbine exhaust gas is higher than that of the exhaust gas from the bearing after cooling. This will cause the exhaust gas from the bearing after cooling to be difficult to discharge due to low pressure, and the cooling effect of the bearing is affected. UTILITY MODEL CONTENTS

[0004] The utility model discloses a kind of air compressor bearing cooling gas exhaust passage integrated exhaust noise reduction structures, which is simple in structure, and ensures that the temperature rising gas after bearing cooling and the gas exhausted by turbine are horizontal and in the same direction, and no collision occurs to generate noise.

[0005] Technical scheme: To achieve the above object, the utility model provides an air compressor bearing cooling gas exhaust passage integrated exhaust noise reduction structure, which comprises a volute and a bearing cooling gas flow channel.

[0006] The volute is provided with a vortex end airflow inlet and a vortex end airflow outlet, and the bearing cooling gas flow channel comprises a bearing seat air passage cavity, a bearing cooling gas exhaust passage and a bearing cooling gas annular outlet.

[0007] Further, the volute is also provided with an annular partition wall, which is located at the bearing cooling gas annular outlet.

[0008] Further, the volute is provided with a vortex end airflow cavity, and a turbine is arranged in the vortex end airflow cavity.

[0009] Further, the left side of the central shaft is provided with a bearing seat, and the bearing seat air passage cavity is arranged on the bearing seat.

[0010] Further, the left side of the bearing seat is provided with a bearing cooling gas accumulation cavity, which is communicated with the bearing seat air passage cavity.

[0011] Further, the right side of the volute is provided with a mixing cavity, which is communicated with the bearing cooling gas annular outlet and the vortex end airflow outlet respectively.

[0012] Further, the bearing seat air passage cavity is a right-angle passage, the bearing cooling gas exhaust passage comprises an inclined section and a curved section, the diameter of the curved section is larger than that of the inclined section, and the bearing cooling gas annular outlet is coaxial with the vortex end airflow outlet.

[0013] Further, the volute and the bearing cooling gas flow channel are integrally cast.

[0014] The technical scheme has the beneficial effects that, compared with the prior art, the air compressor bearing cooling gas discharge channel integrated exhaust noise reduction structure has the following beneficial effects:

[0015] 1) The structure of the air compressor bearing cooling gas discharge channel integrated exhaust noise reduction structure, the bearing cooling gas is discharged through the bearing seat air passage cavity, the bearing cooling gas exhaust channel and the bearing cooling gas annular outlet, the airflow direction is changed through the annular partition wall, the direction of the bearing cooling gas and the turbine gas discharge is consistent, the collision of the two airflows is avoided to achieve the noise reduction purpose.

[0016] 2) Since the speed of the turbine exhaust airflow is higher than the speed of the bearing cooling gas exhaust airflow, when the turbine exhaust airflow passes below the bearing cooling gas annular outlet, a negative pressure area is formed here, the negative pressure promotes the rapid discharge of the bearing cooling gas, and the faster the bearing cooling gas after heating is discharged, the better the cooling effect on the bearing. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 A structure diagram of the air compressor bearing cooling gas discharge channel integrated exhaust noise reduction structure is shown in the utility model.

[0018] Figure 2 A structure diagram of the right side of the volute is shown in the utility model.

[0019] Figure 3 A structure diagram of the left side of the volute is shown in the utility model.

[0020] Figure 4 A structure diagram of the annular partition wall is shown in the utility model.

[0021] Figure 5 A structure diagram of the bearing cooling gas exhaust channel and the bearing cooling gas annular outlet is shown in the utility model.

[0022] In the drawing: 100-volute, 101-vortex end airflow inlet, 102-vortex end airflow outlet, 103-annular partition wall, 104-vortex end airflow cavity, 105-turbine, 106-bearing seat, 107-bearing cooling gas accumulation cavity, 108-mixing cavity;

[0023] 200-bearing cooling gas flow channel, 201-bearing seat air passage cavity, 202-bearing cooling gas exhaust channel, 203-bearing cooling gas annular outlet. DETAILED DESCRIPTION

[0024] It should be understood that the specific embodiments described herein are merely intended to explain the utility model, and are not intended to limit the utility model.

[0025] As Figures 1-3, 5 shown: a compressor bearing cooling gas exhaust channel integrated exhaust noise reduction structure, comprising a volute 100 and bearing cooling gas flow channel 200, the bearing cooling flow channel 200 is provided on the volute 100;

[0026] The volute 100 is provided with a vortex end airflow inlet 101 and a vortex end airflow outlet 102, and the bearing cooling gas flow channel 200 comprises a bearing seat air passage 201, a bearing cooling gas exhaust channel 202 and a bearing cooling gas annular outlet 203. The direction of the bearing cooling gas annular outlet 203 is consistent with the direction of the vortex end airflow outlet 102.

[0027] Using the noise reduction structure of the present embodiment, the direction of the bearing cooling gas and the turbine gas exhaust can be made consistent, avoiding the collision of the two gases to emit noise to achieve the purpose of noise reduction. At the same time, since the speed of the turbine exhaust gas flow is higher than the speed of the bearing cooling gas exhaust gas flow, when the turbine exhaust gas flow passes below the bearing cooling gas annular outlet 203, a negative pressure area will be formed here, and the negative pressure will promote the rapid exhaust of the bearing cooling gas. The faster the exhaust of the bearing cooling gas after heating, the better the cooling effect on the bearing.

[0028] In particular, as Figure 1 、 4 , the volute 100 is further provided with an annular partition wall 103, the annular partition wall 103 is located at the bearing cooling gas annular outlet 203, and the tail of the annular partition wall 103 and the outer wall surface of the volute jointly form the bearing cooling gas annular outlet 203. In this embodiment, the thickness of the annular partition wall 103 is 3mm, and the bearing cooling gas passes through the bearing seat air passage 201 and the bearing cooling gas exhaust channel 202. Due to the existence of the annular partition wall 103, the bearing cooling gas will be squeezed to the annular outlet 203 parallel to the annular partition wall 103, thereby changing the exhaust direction of the bearing cooling gas and making the exhaust direction of the bearing cooling gas consistent with that of the turbine gas.

[0029] Preferably, the volute 100 is provided with a vortex end airflow cavity 104, the vortex end airflow cavity 104 is provided with a turbine 105, the vortex end airflow cavity 104 is in communication with the vortex end airflow inlet 101, and the turbine 105 is sleeved on the center shaft.

[0030] Preferably, the left side of the center shaft is provided with a bearing seat 106, the bearing seat air passage 201 is provided on the bearing seat 106, and the bearing seat 106 is tightly attached to the left side of the volute 100.

[0031] Preferably, the left side of the bearing seat 106 is provided with a bearing cooling gas gathering cavity 107, and the bearing cooling gas gathering cavity 107 is in communication with the bearing seat air passage 201.

[0032] Preferably, the right side of the volute 100 is provided with a mixing cavity 108, which is communicated with the bearing cooling gas annular outlet 203 and the volute end gas flow outlet 102 respectively.

[0033] In addition, the bearing seat gas passing cavity 201 is a right-angle passage, the bearing cooling gas exhaust passage 202 comprises an inclined section and a curved section, the diameter of the curved section is greater than that of the inclined section, and the bearing cooling gas annular outlet 203 is coaxial with the volute end gas flow outlet 102. The exhaust passage is combined by three passages with different sizes and shapes, so that the gas flow is smoothly discharged.

[0034] Specifically, the volute 100 and the bearing cooling gas flow channel 200 are integrally cast, which ensures the structural strength and is relatively low in manufacturing cost and difficulty.

[0035] The embodiment can also be used for a high-power hydrogen fuel system. In order to improve efficiency and save parasitic power consumption, the high-power hydrogen fuel system adopts an air compressor with recoverable energy. A typical feature of the air compressor with recoverable energy is that the power consumption of the motor is reduced by using the gas discharged by the stack to expand and do work. The volute 100 in the scheme can be used for the volute structure of the air compressor with recoverable energy. The structure simultaneously integrates an exhaust passage for the bearing cooling and temperature rising gas. Through the passage, the bearing cooling and temperature rising gas can be directly discharged to the mixing cavity 108 of the air compressor expander through the bearing cooling gas flow channel 200, including the bearing seat gas passing cavity 201, the bearing cooling gas exhaust passage 202 and the bearing cooling gas annular outlet 203, and the expander expands and does work. The volute end working gas enters the volute 100 through the volute end gas flow outlet 101, enters the volute end gas flow cavity 104 and the turbine 105 after doing work, and then reaches the mixing cavity 108 through the volute end gas flow outlet 102, and is discharged from the system after being mixed with the bearing cooling gas exhaust gas flow. The bearing seat gas passing cavity 201, the bearing cooling gas exhaust passage 202 and the bearing cooling gas annular outlet 203 are combined to form an exhaust passage, and the annular partition wall 103 assists in changing the direction of the gas flow. The final direction of the bearing cooling gas flow is parallel to the direction of the turbine exhaust gas flow, so that the two gas flows are parallel and do not collide with each other, thereby avoiding the noise problem.

[0036] The above only describes preferred embodiments of the present application, and it should be pointed out that, for ordinary skilled persons in the technical field, a number of improvements can be made without departing from the principles of the present application, and these improvements should also be considered as the protection scope of the present application.

Claims

1. An integrated exhaust noise reduction structure for the cooling gas discharge channel of an air compressor bearing, characterized in that, It includes a volute housing (100) and a bearing cooling airflow channel (200), wherein the bearing cooling airflow channel (200) is disposed on the volute housing (100); The vortex housing (100) is provided with a vortex end airflow inlet (101) and a vortex end airflow outlet (102). The bearing cooling airflow channel (200) includes a bearing housing air passage (201), a bearing cooling air exhaust channel (202), and a bearing cooling air annular outlet (203). The direction of the bearing cooling air annular outlet (203) is consistent with the direction of the vortex end airflow outlet (102).

2. The integrated exhaust noise reduction structure for the air compressor bearing cooling gas discharge channel according to claim 1, characterized in that, The volute (100) is also provided with an annular partition wall (103), which is located at the bearing cooling gas annular outlet (203). The tail of the annular partition wall (103) and the outer wall of the volute together form the bearing cooling gas annular outlet (203).

3. The integrated exhaust noise reduction structure for the air compressor bearing cooling gas discharge channel according to claim 1, characterized in that, The vortex housing (100) is provided with a vortex end airflow cavity (104), and a turbine (105) is provided in the vortex end airflow cavity (104). The vortex end airflow cavity (104) is connected to the vortex end airflow inlet (101), and the turbine (105) is sleeved on the central rotating shaft.

4. The integrated exhaust noise reduction structure for the air compressor bearing cooling gas discharge channel according to claim 3, characterized in that, A bearing housing (106) is provided on the left side of the central rotating shaft. The air passage cavity (201) of the bearing housing is provided on the bearing housing (106). The bearing housing (106) is closely attached to the left side of the volute (100).

5. The integrated exhaust noise reduction structure for the air compressor bearing cooling gas discharge channel according to claim 4, characterized in that, The bearing housing (106) has a bearing cooling gas gathering chamber (107) on the left side, and the bearing cooling gas gathering chamber (107) is connected to the bearing housing air passage chamber (201).

6. The integrated exhaust noise reduction structure for the air compressor bearing cooling gas discharge channel according to claim 1, characterized in that, The right side of the vortex shell (100) is provided with a mixing cavity (108), which is connected to the bearing cooling gas annular outlet (203) and the vortex end airflow outlet (102) respectively.

7. The integrated exhaust noise reduction structure for the air compressor bearing cooling gas discharge channel according to claim 1, characterized in that, The bearing housing air passage (201) is a right-angle channel. The bearing cooling gas exhaust channel (202) includes an inclined section and a curved section. The diameter of the curved section is larger than that of the inclined section. The bearing cooling gas annular outlet (203) is coaxial with the vortex end airflow outlet (102).

8. The integrated exhaust noise reduction structure for the air compressor bearing cooling gas discharge channel according to claim 1, characterized in that, The vortex shell (100) and the bearing cooling airflow channel (200) are integrally cast.

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