Dry powder electromagnetic vibration iron removal equipment

Abstract

The invention relates to the technical field of material iron removal, and discloses dry powder electromagnetic vibration iron removal equipment which solves the technical problem that in the prior art, time control is not accurate in the customized closing and residue discharging operation procedure, and the dry powder electromagnetic vibration iron removal equipment comprises a rack, a machine body, a coil, a material selecting cavity, a medium assembly and a vibration motor; a magnetic material outlet pipe and a material outlet pipe are arranged at the bottom end of the sorting cavity, a material distributing valve is arranged at the joint of the magnetic material outlet pipe and the material outlet pipe, and the material distributing valve is used for controlling the material discharging direction of the sorting cavity to select the material discharging direction of the magnetic material outlet pipe or select the material discharging direction of the material outlet pipe; a weighing sensor is mounted at the bottom of the machine body; and a controller is mounted outside the machine body, is in communication connection with the weighing sensor, and is used for controlling the coil to be powered off. According to the technical scheme, through the arrangement of the weighing sensor and the controller, predictive control over the residue discharging operation procedure is achieved, and the good automatic control effect is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of material iron removal, and more specifically, it relates to a dry powder electromagnetic vibration iron removal device. Background Art

[0002] A dry powder electromagnetic vibration iron removal device is a purification device used to remove iron impurities from powder materials. Its application scenarios mainly include processing enterprises using microparticle crushers, other slurry products that generate powder due to mechanical friction, processing industries containing iron elements naturally generated or mixed in engineering, as well as the food and medicine fields, chemical fields, and battery material fields, etc.

[0003] During operation, the powder material is conveyed to the magnetic field area of the device, and ferromagnetic impurities are adsorbed, thereby achieving separation. To realize the automatic shutdown of the powder iron removal device, in the existing powder iron removal devices, when the powder iron removal device enters the residue discharging process during the iron removal treatment of the powder material, a timer is usually used to control the residue discharging time. However, since the actual residue discharging time required for each batch of powder materials is different, the accuracy of this timer-controlled automatic shutdown scheme for the powder iron removal device is actually low. For example, there are situations where the device shuts down before the residue discharging is completed or the device shuts down some time after the residue discharging operation is completed. Therefore, there is room for improvement. Summary of the Invention

[0004] The present invention aims to provide a dry powder electromagnetic vibration iron removal device to solve the technical problem of inaccurate time control in the customized shutdown of the residue discharging operation process as proposed in the background art.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] A dry powder electromagnetic vibration iron removal device includes a frame, a body, a coil, a material selection chamber, a medium component, and a vibration motor; the frame supports and installs the body, the vibration motor is installed on the bottom surface of the body, and when the vibration motor operates, it drives the entire body to vibrate; the material selection chamber is installed through the body, the top end of the material selection chamber extends out of the top surface of the body, the top end of the material selection chamber is the feed inlet, the bottom end of the material selection chamber extends out of the bottom surface of the body, a magnetic substance outlet pipe and a material outlet pipe are provided at the bottom end of the material selection chamber, and a diverter valve is provided at the connection of the magnetic substance outlet pipe and the material outlet pipe. The diverter valve is used to control the discharge direction of the material selection chamber to select the discharge direction of the magnetic substance outlet pipe or the discharge direction of the material outlet pipe;

[0007] A weighing sensor is installed at the bottom of the body, and the weighing sensor is used to weigh the overall mass of the body and the substances attached to the surface and inside of the body;

[0008] A controller is externally installed on the fuselage. The controller is communicatively connected to a weighing sensor. The controller is used to determine whether the detection data of the weighing sensor is close to the self-weight of the fuselage. If so, it indicates that the residue discharging operation is completed, and the controller controls the connection to the coil and cuts off the power supply of the coil.

[0009] Further, in the present invention: the medium assembly includes a medium, a medium rod, a lifting handle, and a medium spacer ring. The medium is integrally cylindrical. The medium rod axially passes through the medium. The medium rod is used to combine the structural units of the medium together. The lifting handle is installed at the top of the medium rod. The lifting handle is used to lift and remove the entire medium assembly for maintenance.

[0010] Further, in the present invention: the medium is composed of multiple stacked structural units, and a medium spacer ring is provided between adjacent structural units.

[0011] Further, in the present invention: the medium is a disc-shaped medium.

[0012] Further, in the present invention: the medium is a rod-shaped medium.

[0013] Further, in the present invention: the weighing sensor periodically collects the body weight G of the fuselage; the controller is used to calculate the weight data difference ΔG between adjacent time points, and then calculate the weight difference ratio C% between adjacent weight differences. According to the obtained weight difference ratio C%, the weight data difference ΔG at the previous time point, and the body weight G of the fuselage currently collected periodically, the controller predicts the body weight G at the next time point and predicts the body weight G at a preset multiple of future time points. When the body weight at a certain future time point reaches close to the body weight, the power supply of the coil is cut off periodically according to the time difference T between the current time point and the certain future time point.

[0014] Further, in the present invention: the calculation formula of the body weight X is as follows:

[0015] Body weight X = G - ΔG * C%;

[0016] Where G represents the self-weight of the fuselage at any time point, ΔG represents the difference between the self-weight of the fuselage at any time point and the self-weight of the fuselage at the previous time point, and C% represents the ratio between the adjacent body self-weight differences at any time point.

[0017] Further, in the present invention: C% represents the average value of the ratios between the adjacent body self-weight differences at any multiple of time points.

[0018] Further, in the present invention: inside the fuselage and outside the material selection chamber, insulating oil is filled around the coil. An expansion tank and an oil pump are provided outside the fuselage. The expansion tank is communicated with the space inside the fuselage for filling insulating oil, and the expansion tank provides a temporary storage space for the insulating oil to expand due to heat. The oil pump is used to provide the power for the insulating oil to circulate inside the fuselage.

[0019] Further, in the present invention: a cantilever is equipped at the top of the fuselage, and the cantilever is used to lift the medium assembly through a lifting handle for cleaning.

[0020] In summary, the present invention has the following beneficial effects:

[0021] By setting a weighing sensor and a controller, the present invention realizes predictive control of the residue discharging operation process and has a good automatic control effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a three-dimensional structural schematic diagram of a dry powder electromagnetic vibration iron removal device;

[0023] Figure 2 is a front view schematic diagram of a dry powder electromagnetic vibration iron removal device;

[0024] Figure 3 is Figure 2 a cross-sectional view;

[0025] Figure 4 is a side view schematic diagram of a dry powder electromagnetic vibration iron removal device;

[0026] Figure 5 is a structural schematic diagram of a medium assembly;

[0027] Figure 6 is a structural schematic diagram of a disc-shaped medium;

[0028] Figure 7 is a structural schematic diagram of a rod-shaped medium.

[0029] Reference numerals: 1, frame; 2, fuselage; 3, coil; 4, material selection chamber; 5, medium assembly; 5-1, medium; 5-11, disc-shaped medium; 5-12, rod-shaped medium; 5-2, medium rod; 5-3, lifting handle; 5-4, medium gasket ring; 6, vibration motor; 7, feed inlet; 8, magnetic material outlet pipe; 9, material outlet pipe; 10, diverter valve; 11, insulating oil; 12, expansion tank; 13, oil pump; 14, cantilever. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0030] The present invention will be further described in detail below in conjunction with the embodiments and the drawings, but the embodiments of the present invention are not limited thereto.

[0031] A dry powder electromagnetic vibration iron removal device, combined with Figures 1-4 As shown in the figure, it includes a frame 1, a fuselage 2, a coil 3, a material selection chamber 4, a medium component 5, and a vibration motor 6. The frame 1 supports and installs the fuselage 2, and the vibration motor 6 is installed on the bottom surface of the fuselage 2. When the vibration motor 6 works, it drives the entire fuselage 2 to vibrate. The material selection chamber 4 is installed through the fuselage 2. The top end of the material selection chamber 4 extends out of the top surface of the fuselage 2, and the top end of the material selection chamber 4 is the feed port 7. The bottom end of the material selection chamber 4 extends out of the bottom surface of the fuselage 2. A magnetic material outlet pipe 8 and a material outlet pipe 9 are provided at the bottom end of the material selection chamber 4. A diverter valve 10 is provided at the connection of the magnetic material outlet pipe 8 and the material outlet pipe 9. The diverter valve 10 is used to control the discharge direction of the material selection chamber 4 to select the discharge direction of the magnetic material outlet pipe 8 or the discharge direction of the material outlet pipe 9.

[0032] The overall working principle is as follows:

[0033] (1) During the working time: Power on the vibration motor 6. The vibration motor 6 drives the entire fuselage 2 and the medium component 5 inside it to vibrate. At the same time, power on the coil 3 to make the medium component 5 magnetic. The diverter valve 10 controls the discharge direction of the material selection chamber 4 to select the discharge direction of the material outlet pipe 9, and then add powder to the feed port 7. The powder is processed by the medium component 5 and then discharged through the material outlet pipe 9.

[0034] Among them, when the powder is no longer added from the feed port 7, it enters the residue discharging working time. During the residue discharging working time, set the residue discharging working time, that is, set the power supply time of the coil 3 at this time. When the timing time arrives, the coil 3 is automatically controlled to cut off the power. After the coil 3 cuts off the power, it enters the impurity discharging time.

[0035] (2) During the impurity discharging time: Stop adding powder to the feed port 7. The diverter valve 10 controls the discharge direction of the material selection chamber 4 to select the discharge direction of the magnetic material outlet pipe 8. The impurities in the material selection chamber 4 are discharged through the magnetic material outlet pipe 8. At this time, it officially enters the impurity discharging time. During the impurity discharging time, set the impurity discharging working time, that is, set the power supply time of the vibration motor 6 at this time. When the timing time arrives, the vibration motor 6 is automatically controlled to cut off the power, and the impurity discharging is completed.

[0036] Combined with Figure 3 and Figures 5-7As shown, the medium component 5 is installed inside the material selection chamber 4 and within the fuselage 2. The medium component 5 includes a medium 5-1, a medium rod 5-2, a lifting handle 5-3, and a medium gasket ring 5-4. The medium 5-1 is generally cylindrical and is composed of a stack of multiple structural units, such as a disc-shaped medium 5-11 and a rod-shaped medium 5-12. A medium gasket ring 5-4 is provided between adjacent structural units. The medium rod 5-2 axially penetrates the medium 5-1, and the medium rod 5-2 is used to combine the various structural units of the medium 5-1. The lifting handle 5-3 is installed at the top of the medium rod 5-2, and the lifting handle 5-3 is used to lift and remove the entire medium component 5 for maintenance.

[0037] Combined with Figure 2 and Figure 3 As shown, the present invention also has, inside the fuselage 2 and outside the material selection chamber 4, insulating oil 11 filled around the coil 3. An expansion tank 12 and an oil pump 13 are provided outside the fuselage 2. The expansion tank 12 is connected to the space inside the fuselage 2 for filling the insulating oil 11, and the expansion tank 12 provides a temporary storage space for the expansion of the insulating oil due to heat. The oil pump 13 is used to provide the power for the insulating oil 11 to circulate inside the fuselage 2.

[0038] The present invention is also equipped with a cantilever 14 at the top of the fuselage 2. The cantilever 14 is used to lift the medium component 5 through the lifting handle 5-3 for cleaning.

[0039] To achieve the automatic shutdown of the powder iron removal device, when the powder iron removal device enters the residue discharging working time, during the residue discharging working time, the residue discharging working time is set, that is, the power supply time of the coil 3 is set at this time. When the timing time arrives, the coil 3 is automatically controlled to cut off the power. However, since the actual residue discharging working time required for each batch of powder is different, the accuracy of this timer-based timing control scheme for the automatic shutdown of the powder iron removal device is actually relatively low. For example, there are situations where the device shuts down before the residue discharging is completed or the device shuts down some time after the residue discharging operation is completed.

[0040] Therefore, the present invention further takes the following improvement measures. A weighing sensor is installed at the bottom of the fuselage 2. The weighing sensor is used to weigh the overall mass of the fuselage 2 and the components attached to the surface and inside of the fuselage 2 (the influence of the vibration of the vibration motor 6 on the weighing is minimized as much as possible by separately setting an elastic damping scheme in the prior art). Thus, the powder iron removal device senses the change in the weight of the fuselage 2 itself through the weighing sensor. When the weight of the fuselage 2 approaches its own weight, it indicates that the residue discharging operation is basically completed, and at this time, the coil 3 is automatically controlled to cut off the power.

[0041] Under this improvement measure, under normal circumstances, this automatic shutdown solution is already very perfect. However, in some abnormal situations, the weight of the fuselage 2 is indeed difficult to reach a weight close to the fuselage 2 itself. The reason is that when there are more iron impurities inside the fuselage 2 or powder blocking the medium 5-1 is accumulated, at this time, even if the powder (powder that can actually be discharged, excluding a small part of the blocked powder) is completely discharged, but because the weight of the fuselage 2 itself cannot reach a weight close to the fuselage 2 itself, the powder iron removal equipment will not automatically shut down, and the coil 3 will not be automatically controlled to cut off the power, causing the powder iron removal equipment to continue to work and consume electricity.

[0042] Therefore, the present invention further carries out the following improvement measures: after entering the waste discharge process, the weighing sensor collects the fuselage weight G at regular intervals, and the controller is set to calculate the weight data difference ΔG at adjacent time points, and then calculates the weight difference ratio C% between adjacent weight differences; based on the obtained weight difference ratio C%, the weight data difference ΔG at the previous time point and the fuselage weight G collected at the current regular intervals, the fuselage weight G at the next time point can be predicted, as well as the fuselage weight G at multiple preset time points in the future; when the fuselage weight at a certain time point in the future is close to the fuselage weight, the powder material iron removal equipment is automatically shut down according to the time difference T between the current time point and a certain time point in the future, that is, the automatic control coil 3 is powered off.

[0043] The following is an example of a specific application case. It is assumed that the weight of the fuselage is 50KG. After entering the waste removal process, the weight of the fuselage 2 is collected every 1s.

[0044] The fuselage weight data collected by the weighing sensor at regular intervals are: 100KG, 95KG, 90.5KG, 86.5KG, 83KG, 80KG, 77.5KG, 75.1KG, 72.8KG, 70.7KG, 68.7KG, 66.8KG, 65KG, 63KG, 61.1KG, 59.3KG, 57.6KG, 56KG, 54.5KG, 53.1KG, 51.8KG, 50.6KG (assuming that the fuselage weight is less than or equal to 50.6KG, it can be judged as close to the fuselage weight).

[0045] At this time, first calculate the weight data differences between adjacent time points, which are respectively: 5KG (100KG - 95KG), 4.5KG (95KG - 90.5KG), 4KG (90.5KG - 86.5KG), 3.5KG (86.5KG - 83KG), 3KG (83KG - 80KG), 2.5KG (80KG - 77.5KG), 2.4KG (77.5KG - 75.1KG), 2.3KG (75.1KG - 72.8KG), 2.1KG (72.8KG - 70.7KG), 2KG (70.7KG - 68.7KG), 1.9KG (68.7KG - 66.8KG), 1.8KG (66.8KG - 65KG), 2KG (65KG - 63KG), 1.9KG (63KG - 61.1KG), 1.8KG (61.1KG - 59.3KG), 1.7KG (59.3KG - 57.6KG), 1.6KG (57.6KG - 56KG), 1.5KG (56KG - 54.5KG), 1.4KG (54.5KG - 53.1KG), 1.3KG (53.1KG - 51.8KG), 1.2KG (51.8KG - 50.6KG).

[0046] Finally, calculate the weight difference ratios between adjacent weight differences, which are respectively: 4.5KG / 5KG, 4KG / 4.5KG, 3.5KG / 4KG, 3KG / 3.5KG, 2.5KG / 3KG, 2.4KG / 2.5KG, 2.3KG / 2.4KG, 2.1KG / 2.3KG, 2KG / 2.1KG, 1.9KG / 2KG, 1.8KG / 1.9KG, 2KG / 1.8KG, 1.9KG / 2KG, 1.8KG / 1.9KG, 1.7KG / 1.8KG, 1.6KG / 1.7KG, 1.5KG / 1.6KG, 1.4KG / 1.5KG, 1.3KG / 1.4KG, 1.2KG / 1.3KG.

[0047] Therefore, based on the weight difference ratio obtained from any one time point, such as 93.75%, or the average value of the weight difference ratios obtained from any multiple time points; and based on the weight difference value of the previous time point, such as 1.5KG, and the body weight data 54.5KG collected at the current timing, the body weight X at the next time point can be predicted as X = 54.5KG - 1.5KG * 93.75% = 54.5KG - 1.41KG = 53.09KG. By analogy, the body weight X at multiple future time points can be predicted.

[0048] The calculation formula for the body weight X is as follows:

[0049] Fuselage weight X=G-ΔG*C%; wherein G represents the fuselage weight at any time point, ΔG represents the difference between the fuselage weight at any time point and the fuselage weight at the previous time point, and C% represents the ratio between adjacent fuselage weight differences at any time point, or the average value of the ratios between adjacent fuselage weight differences at any multiple time points.

[0050] According to the calculation formula of the fuselage weight X, the fuselage deadweight at multiple time points in the future can be predicted, but the predicted value has a slight deviation from the actual value, so it is necessary to preset the number of predicted future time points in the computer program. In this embodiment, it is assumed that the fuselage weight at the next 10 time points needs to be predicted. When the fuselage weight at the next 10 time points is predicted to be less than or equal to 50.6KG (considered to be close to the fuselage weight), the time difference between the current time point and a certain time point in the future, that is, the time of 10 time points is timed, and the powder material iron removal equipment is controlled to automatically shut down. When there are more iron impurities inside the powder material iron removal equipment or when the powder material blocks the medium and accumulates, the powder material iron removal equipment will not automatically shut down, causing the powder material iron removal equipment to continue to work and consume electricity, thereby improving the intelligence of the powder material iron removal equipment.

[0051] When the predicted fuselage weight at the next 10 time points is not less than or equal to 50.6KG (considered to be close to the fuselage weight), reset and restart the prediction from the next time point until the predicted fuselage weight at the next 10 time points is less than the set threshold (50.6KG). When the set threshold appears, the timing starts and the prediction function is turned off.

[0052] The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should also be regarded as the protection scope of the present invention.

Claims

1. A dry powder electromagnetic vibration iron removal equipment, characterized in that: The invention comprises a frame (1), a body (2), a coil (3), a material selection chamber (4), a medium component (5), and a vibration motor (6); the frame (1) supports and installs the body (2); the vibration motor (6) is installed on the bottom surface of the body (2); when the vibration motor (6) is in operation, the body (2) is driven to vibrate as a whole; the material selection chamber (4) is installed through the body (2); the top of the material selection chamber (4) extends out of the top surface of the body (2); the top of the material selection chamber (4) is a material inlet (7); the bottom of the material selection chamber (4) extends out of the bottom surface of the body (2); a magnetic material outlet pipe (8) and a material outlet pipe (9) are arranged at the bottom of the material selection chamber (4); a material distribution valve (10) is arranged at the connection between the magnetic material outlet pipe (8) and the material outlet pipe (9); the material distribution valve (10) is used to control the discharge direction of the material selection chamber (4) to select the discharge direction of the magnetic material outlet pipe (8) or the discharge direction of the material outlet pipe (9); A weighing sensor is installed at the bottom of the fuselage (2), and the weighing sensor is used to weigh the overall mass of the fuselage (2) and the surface and interior of the fuselage (2); A controller is installed outside the machine body (2), and the controller is connected to the weighing sensor for communication. The controller is used to determine whether the detection data of the weighing sensor is close to the deadweight of the machine body (2). If so, it indicates that the waste removal operation is completed. The controller controls the connection to the coil (3) and controls the coil (3) to cut off power.

2. A dry powder electromagnetic vibration iron removal equipment according to claim 1, characterized in that: The medium assembly (5) comprises a medium (5-1), a medium rod (5-2), a lifting handle (5-3) and a medium gasket (5-4); the medium (5-1) is cylindrical as a whole; the medium rod (5-2) passes through the medium (5-1) in the axial direction; the medium rod (5-2) is used to combine the various structural units of the medium (5-1) together; the lifting handle (5-3) is installed at the top of the medium rod (5-2); and the lifting handle (5-3) is used to lift, dismantle and maintain the entire medium assembly (5).

3. A dry powder electromagnetic vibration iron removal equipment according to claim 2, characterized in that: The medium (5-1) is composed of multiple layers of structural units stacked together, and medium gaskets (5-4) are arranged between adjacent structural units.

4. A dry powder electromagnetic vibration iron removal equipment according to claim 2, characterized in that: The medium (5-1) is a disk-shaped medium (5-11).

5. The dry powder electromagnetic vibration iron removal equipment according to claim 2 is characterized in that: The medium (5-1) is a rod-shaped medium (5-12).

6. The dry powder electromagnetic vibration iron removal equipment according to claim 1, characterized in that: The weighing sensor collects the fuselage weight G of the fuselage (2) at a fixed time; the controller is used to calculate the weight data difference ΔG at adjacent time points, and then calculate the weight difference ratio C% between adjacent weight differences. According to the obtained weight difference ratio C%, the weight data difference ΔG at the previous time point and the fuselage weight G collected at the current fixed time, the controller predicts the fuselage weight G at the next time point, and predicts the fuselage weight G at multiple preset time points in the future. When the fuselage weight at a certain time point in the future is close to the fuselage weight, the control coil (3) is de-energized at a fixed time according to the time difference T between the current time point and the certain time point in the future.

7. A dry powder electromagnetic vibration iron removal equipment according to claim 6, characterized in that: The calculation formula of the fuselage weight X is as follows: Body weight X = G-ΔG*C%; Where G represents the fuselage deadweight at any time point, ΔG represents the difference between the fuselage deadweight at any time point and the fuselage deadweight at the previous time point, and C% represents the ratio between the weight differences of adjacent fuselage deadweights at any time point.

8. A dry powder electromagnetic vibration iron removal equipment according to claim 7, characterized in that: Where C% represents the average value of the ratio between the weight differences of adjacent fuselage weights at any multiple time points.

9. The dry powder electromagnetic vibration iron removal equipment according to claim 1, characterized in that: Insulating oil (11) is distributed around the coil (3) inside the body (2) and outside the material selection cavity (4), and an expansion tank (12) and an oil pump (13) are arranged outside the body (2). The expansion tank (12) is connected to a space inside the body (2) for filling the insulating oil (11). The expansion tank (12) provides a temporary storage space for the insulating oil that expands due to heat, and the oil pump (13) is used to provide power for the insulating oil (11) to circulate inside the body (2).

10. The dry powder electromagnetic vibration iron removal equipment according to claim 2, characterized in that: A cantilever (14) is provided on the top of the fuselage (2), and the cantilever (14) is used to lift the medium assembly (5) for cleaning by lifting the lifting handle (5-3).

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