Turbocharger abrasion damage detection equipment

Abstract

The utility model discloses a turbocharging wear damage detection device, which comprises a turbine shell, turbine blades are arranged in the turbine shell, warning lamps are arranged on the circumferential outer wall of the turbine shell and are distributed in an annular array, an annular mounting groove hole is formed in the circumferential inner wall of the turbine shell, and the annular mounting groove hole is communicated with the turbine shell. A wear detection mechanism is arranged in the annular mounting groove hole, the wear detection mechanism is formed by combining eighteen wear detection assemblies in an annular array mode, a first connecting column is arranged on each wear detection assembly, and a cylindrical mounting groove hole is formed in the center of one end of each first connecting column; an elastic partition plate and a connecting plate are arranged in the cylindrical mounting groove hole, and the elastic partition plate is located on one side of the connecting plate. According to the utility model, whether friction is generated between the turbine blade and the turbine shell or not can be effectively detected, and the situation that the turbine blade is damaged due to the friction between the turbine blade and the turbine shell is avoided.

Description

Technical Field

[0001] This utility model belongs to the field of turbocharger wear and damage detection equipment, specifically a device for detecting turbocharger wear and damage. Background Technology

[0002] During turbocharger operation, the main wear components include bearings, bearing faces, shaft, and impeller. Bearings and bearing faces: If dust or dirt mixes with the lubricating oil, it will cause severe wear on the bearings and bearing faces, leading to deterioration of clearances. Additionally, low oil pressure or insufficient oil supply can also cause bearing damage. Shaft and bearings: Insufficient lubricating oil or delayed oil supply can cause the shaft and bearings to overheat, ultimately damaging them. Aged engine oil can also cause oil passage blockage, affecting lubrication and heat dissipation, ultimately leading to turbocharger damage. Impeller: Friction between the impeller and the turbocharger housing can cause impeller damage. This is usually accompanied by a metallic grinding sound, indicating excessive wear on the rotor bearing or thrust bearing.

[0003] A search revealed a patent publication number CN215248894U for an elevator traction sheave wear detection device. The device includes a traction sheave and a mounting frame. An adjustment base is fixedly mounted on the mounting frame, and a wear detection platform is fixedly connected to the top of the mounting platform of the adjustment base. A set of wear detection mechanisms is fixedly connected to each set of wheel grooves on the wear detection platform. The wear detection mechanisms can detect the wear of the wheel grooves of the traction sheave, and the detection effect can be displayed intuitively through indicator lights. Real-time detection of wheel groove wear can also be achieved.

[0004] Currently, wear detection of turbochargers is generally performed by manually moving the turbine blades to check for wobbling, which indicates excessive wear of the rotor bearings or thrust bearings inside the turbocharger. This detection method cannot detect excessive wear of the rotor bearings or thrust bearings inside the turbocharger in a timely manner. When the rotor bearings or thrust bearings inside the turbocharger are excessively worn, friction between the turbine blades and the turbine housing can easily lead to turbine blade damage, causing certain economic losses. Therefore, a wear and damage detection device for turbochargers is designed. Utility Model Content

[0005] In view of the defects or deficiencies of existing turbocharger wear and damage detection equipment, the purpose of this utility model is to provide a turbocharger wear and damage detection equipment that can not only effectively detect whether friction occurs between the turbine blades and the turbine housing, but also avoid the turbine blade damage caused by friction between the turbine blades and the turbine housing.

[0006] To achieve the above-mentioned objectives, the present invention adopts the following technical solution:

[0007] This utility model provides a device for detecting wear and damage in turbochargers, including a turbine housing, turbine blades disposed inside the turbine housing, warning lights disposed on the outer circumferential wall of the turbine housing in a ring array, and an annular mounting slot provided on the inner circumferential wall of the turbine housing, a wear detection mechanism disposed inside the annular mounting slot, and the wear detection mechanism being composed of an annular array of eighteen wear detection components.

[0008] The wear detection component is provided with a first connecting post. A cylindrical mounting slot is opened at the center of one end of the first connecting post. An elastic partition and a connecting plate are provided inside the cylindrical mounting slot. The elastic partition is located on one side of the connecting plate and is connected to the connecting plate by a spring. One side surface of the connecting plate is connected to an arc plate through a second connecting post. A control button is provided on the end wall of the cylindrical mounting slot.

[0009] Preferably, the elastic partition and the first connecting column are fixedly connected, and the outer circumferential wall of the connecting plate and the inner circumferential wall of the cylindrical mounting slot are clearance-fitted.

[0010] Preferably, the outer wall of the arc-shaped plate and the wall of the annular mounting slot are in clearance fit.

[0011] Preferably, four limiting blocks are installed on the circumferential outer wall of the connecting plate, and the four limiting blocks are arranged in a ring array. The other end of the limiting block is installed in the limiting groove, and a damping pad is provided on one side inner wall of the limiting groove.

[0012] Preferably, the outer wall of the limiting block and one side of the outer wall of the damping pad are in an overfit, and the outer wall of the limiting block and the groove wall of the limiting groove are in a clearance fit.

[0013] Preferably, the limiting groove is formed on the circumferential inner wall of the cylindrical mounting groove, and there are four limiting grooves, which are arranged in a ring array.

[0014] Preferably, the inner wall of the arc-shaped plate and the circumferential outer wall of a region of the turbine blade are in clearance fit.

[0015] Compared with existing technologies, one or more of the above technical solutions have the following beneficial effects:

[0016] 1. In this utility model, through a series of structural arrangements, when friction occurs between the turbine blades and the turbine housing, the turbine blades will exert a certain force on the arc plate. When the arc plate is subjected to a certain force, it will transmit the force to the elastic partition through the second connecting column, connecting plate and spring. When the elastic partition is subjected to a force in a certain direction, it will bend elastically. When the elastic partition bends elastically, it will exert a certain force on the control button. When the control button is subjected to a certain force, the control button will turn on the warning light. When the warning light is on, the rotor bearing or thrust bearing in the turbocharger is excessively worn. The warning light reminds the staff to stop the turbocharger for maintenance in time.

[0017] 2. In this utility model, through the coordinated arrangement of a series of structures such as springs and damping pads, when friction occurs between the turbine blades and the turbine housing, and a certain force is generated between the turbine blades and the turbine housing, the coordinated arrangement of the springs and damping pads can play a buffering role, reducing the instantaneous force on the turbine blades, thereby avoiding the situation where the turbine blades are damaged due to friction between the turbine blades and the turbine housing. Attached Figure Description

[0018] The accompanying drawings, which form part of this specification, are used to provide a further understanding of this utility model. The illustrative embodiments of this utility model and their descriptions are used to explain this utility model and do not constitute an improper limitation of this utility model.

[0019] Figure 1 This is a schematic diagram of the overall three-dimensional structure of this utility model. Figure 1 .

[0020] Figure 2 This is a schematic diagram of the overall three-dimensional structure of this utility model. Figure 2 .

[0021] Figure 3 This is a cross-sectional view of the present invention.

[0022] Figure 4 This is a utility model Figure 3 A magnified schematic diagram of the structure at point A in the diagram.

[0023] Figure 5 This is a schematic diagram of the wear detection mechanism of this utility model.

[0024] Figure 6 This is a cross-sectional view of the wear detection component of this utility model.

[0025] In the picture:

[0026] 100. Turbine housing; 110. Annular mounting slot;

[0027] 200. Turbine blades;

[0028] 300. Warning lights;

[0029] 400. Wear detection mechanism;

[0030] 410. Wear detection component; 411. Control button; 412. First connecting post; 4121. Limiting groove; 4122. Cylindrical mounting slot; 413. Elastic partition; 414. Spring; 415. Damping pad; 416. Connecting plate; 4161. Limiting block; 417. Second connecting post; 418. Arc plate. Detailed Implementation

[0031] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0032] It should be noted that the following detailed description is exemplary and intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains.

[0033] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of exemplary embodiments according to the invention. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0034] like Figure 1-6 As shown, a device for detecting wear and damage in a turbocharger includes a turbine housing 100, a turbine blade 200 disposed inside the turbine housing 100, a warning light 300 disposed on the outer circumferential wall of the turbine housing 100 and arranged in a ring array, and an annular mounting slot 110 opened on the inner circumferential wall of the turbine housing 100, a wear detection mechanism 400 disposed inside the annular mounting slot 110, and the wear detection mechanism 400 is composed of eighteen wear detection components 410 arranged in a ring array. The wear detection components 410 are used to detect whether friction occurs between the turbine housing 100 and the turbine blade 200.

[0035] The wear detection assembly 410 is provided with a first connecting post 412. A cylindrical mounting slot 4122 is opened at the center of one end of the first connecting post 412. An elastic partition 413 and a connecting plate 416 are provided inside the cylindrical mounting slot 4122. The elastic partition 413 is located on one side of the connecting plate 416, and the elastic partition 413 and the connecting plate 416 are connected by a spring 414. One side surface of the connecting plate 416 is connected to the arc plate 418 through a second connecting post 417. A control button 411 is provided on the end wall of the cylindrical mounting slot 4122.

[0036] The elastic partition 413 is fixedly connected to the first connecting post 412. The outer circumferential wall of the connecting plate 416 and the inner circumferential wall of the cylindrical mounting slot 4122 are in clearance fit. Because the outer circumferential wall of the connecting plate 416 and the inner circumferential wall of the cylindrical mounting slot 4122 are in clearance fit, the movement of the connecting plate 416 can be limited and guided.

[0037] The outer wall of the arc plate 418 and the wall of the annular mounting slot 110 are in clearance fit. Because the outer wall of the arc plate 418 and the wall of the annular mounting slot 110 are in clearance fit, the movement of the arc plate 418 can be limited and guided.

[0038] Limiting blocks 4161 are installed on the circumferential outer wall of the connecting plate 416. There are four limiting blocks 4161, and the four limiting blocks 4161 are arranged in a ring array. The other end of the limiting block 4161 is installed in the limiting groove 4121. A damping pad 415 is provided on one side inner wall of the limiting groove 4121. The damping pad 415 can play a damping role and prevent the spring 414 from being in a rebound state for a long time.

[0039] The outer wall of the limiting block 4161 and one side of the outer wall of the damping pad 415 are in an overfitting fit, while the outer wall of the limiting block 4161 and the groove wall of the limiting groove 4121 are in a clearance fit. Because the outer wall of the limiting block 4161 and the groove wall of the limiting groove 4121 are in a clearance fit, the movement of the connecting plate 416 can be further limited and guided.

[0040] The limiting groove 4121 is formed on the circumferential inner wall of the cylindrical mounting slot 4122. There are four limiting grooves 4121, and the four limiting grooves 4121 are arranged in a ring array.

[0041] The inner wall of the arc plate 418 and the circumferential outer wall of the turbine blade 200 are in clearance fit.

[0042] Operator: During use, when friction occurs between the turbine blades 200 and the turbine housing 100, the turbine blades 200 exert a certain force on the arc-shaped plate 418. When the arc-shaped plate 418 is subjected to a certain force, it transmits the force to the elastic partition 413 through the second connecting post 417, the connecting plate 416, and the spring 414. When the elastic partition 413 is subjected to a force in a certain direction, it will elastically bend. When the elastic partition 413 elastically bends, it will exert a certain force on the control button 411. When the control button 411 is subjected to a certain force, the warning light 300 will be turned on. When indicator light 300 illuminates, it indicates excessive wear in the rotor bearing or thrust bearing within the turbocharger. The indicator light 300 alerts staff to promptly shut down and maintain the turbocharger. When friction occurs between the turbine blades 200 and the turbine housing 100, and a certain force is generated between them, the spring 414, damping pad 415, and other structures work together to buffer the impact, reducing the instantaneous force on the turbine blades 200. This prevents damage to the turbine blades 200 caused by friction between them and the turbine housing 100.

[0043] The above description is merely a preferred embodiment of this utility model and is not intended to limit the invention. For those skilled in the art, various modifications and variations can be made to this invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this invention should be included within the protection scope of this invention.

Claims

1. A device for detecting wear and damage in turbochargers, comprising a turbine housing (100), characterized in that: Turbine blades (200) are provided inside the turbine housing (100). Warning lights (300) are provided on the outer circumferential wall of the turbine housing (100) and are arranged in a ring array. A ring-shaped mounting slot (110) is provided on the inner circumferential wall of the turbine housing (100). A wear detection mechanism (400) is provided inside the ring-shaped mounting slot (110) and is composed of a ring array of eighteen wear detection components (410). The wear detection assembly (410) is provided with a first connecting post (412). A cylindrical mounting slot (4122) is provided at the center of one end of the first connecting post (412). An elastic partition (413) and a connecting plate (416) are provided inside the cylindrical mounting slot (4122). The elastic partition (413) is located on one side of the connecting plate (416), and the elastic partition (413) and the connecting plate (416) are connected by a spring (414). One side surface of the connecting plate (416) is connected to the arc plate (418) through a second connecting post (417). A control button (411) is provided on the end wall of the cylindrical mounting slot (4122).

2. The device for detecting wear and damage in turbochargers according to claim 1, characterized in that: The elastic partition (413) is fixedly connected to the first connecting column (412), and the outer circumferential wall of the connecting plate (416) is clearance-fitted with the inner circumferential wall of the cylindrical mounting slot (4122).

3. The device for detecting wear and damage in turbochargers according to claim 1, characterized in that: The outer wall of the arc plate (418) and the wall of the annular mounting slot (110) are in clearance fit.

4. The device for detecting wear and damage in turbochargers according to claim 1, characterized in that: Limiting blocks (4161) are installed on the circumferential outer wall of the connecting plate (416). There are four limiting blocks (4161), and the four limiting blocks (4161) are arranged in a ring array. The other end of the limiting block (4161) is installed in the limiting groove (4121). A damping pad (415) is provided on one side inner wall of the limiting groove (4121).

5. The device for detecting wear and damage in turbochargers according to claim 4, characterized in that: The outer wall of the limiting block (4161) and one side of the outer wall of the damping pad (415) are in an overfit, while the outer wall of the limiting block (4161) and the groove wall of the limiting groove (4121) are in a clearance fit.

6. The device for detecting wear and damage in turbochargers according to claim 4, characterized in that: The limiting groove (4121) is formed on the circumferential inner wall of the cylindrical mounting slot (4122). There are four limiting grooves (4121), and the four limiting grooves (4121) are arranged in a ring array.

7. The device for detecting wear and damage in turbochargers according to claim 1, characterized in that: The inner wall of the arc-shaped plate (418) and the circumferential outer wall of a region of the turbine blade (200) are in clearance fit.

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