Liquid rocket engine turbine pump bearing axial clearance measuring device

Abstract

The utility model relates to a liquid rocket engine turbopump bearing axial clearance measuring device, which comprises a cylindrical shell, a gland, a pressure loading device, a pressure loading piece and a dynamometer, a step ring groove matched with a bearing to be measured is arranged at the upper part of the inner wall of the shell, a bearing outer ring of the bearing to be measured is embedded and supported at the groove bottom of the step ring groove, and the pressure loading device is arranged on the shell. The gland is detachably installed at the upper end of the shell, the dynamometer is arranged at the bottom in the shell, the pressure loading piece penetrates through an inner ring of a bearing to be tested, the bottom of the pressure loading piece makes contact with the dynamometer, the upper end of the pressure loading piece is provided with a force loading part attached to the upper end of the inner ring of the bearing to be tested, and the pressure loading device is installed on the gland and connected with the upper end of the pressure loading piece. And the gland is used for applying downward pressure to the pressure loading piece and is provided with a vertically through measuring hole. The device has the advantages of being simple and reasonable in structural design, reliable in work, low in operation labor intensity and capable of enabling the measurement of the axial clearance of the bearing to be more accurate and convenient.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and in particular to a device for measuring the axial clearance of a liquid rocket engine turbopump bearing. Background Technology

[0002] The turbopump is a high-speed rotating component in a liquid rocket engine, and its operating condition and reliability directly affect the safety and stability of the engine. Bearings, as crucial components of rotating machinery, support the rotor and ensure its safe and stable operation. Bearing clearance is a critical parameter of rolling bearings, directly impacting their performance and lifespan. Unlike ordinary civilian rotating machinery, the axial and radial clearances within a liquid rocket engine turbopump require strict control, with allowable tolerances typically as low as 0.01 mm. Axial clearance is affected by adjustments in the turbopump's operating conditions, often resulting in axial movement due to variations in these conditions. Therefore, measuring the axial clearance of rolling bearings under different axial loading conditions to ensure long-term stable rotor operation is of great significance for improving the safety and reliability of liquid rocket engines.

[0003] Currently, the following two methods are mainly used in the domestic civilian sector for measuring the axial clearance of rolling bearings:

[0004] 1) Applying load to the bearing and measuring displacement through a small pressure handle has the disadvantage that the outer diameter of the bearing being measured is small and the applied load does not meet the axial pressure requirements of the turbine pump bearing.

[0005] 2) Applying load and measuring displacement by driving a cylinder with an external power source has the disadvantage of a large measuring device, high installation and equipment costs, and the need for additional energy.

[0006] Therefore, currently, the axial clearance measurement of rolling bearings in domestically used liquid rocket engine turbopumps mainly relies on applying weights to achieve the axial pressure required for the rolling bearing's operating condition. This method has two main drawbacks: ① Since the axial pressure on the turbopump rolling bearings is between 1000-6000N, measuring the bearing's axial clearance requires manual handling of weights weighing 100-600kg, resulting in high workload and low efficiency; ② For liquid rocket engines with greater thrust, the required axial bearing pressure is higher, and existing civilian bearing axial clearance measurement devices do not meet the requirements for the turbopump bearing's operating condition.

[0007] Therefore, it is necessary to develop a device for measuring the axial clearance of a liquid rocket engine turbopump bearing to overcome the aforementioned technical problems. Utility Model Content

[0008] The technical problem to be solved by this utility model is to provide a device for measuring the axial clearance of a liquid rocket engine turbopump bearing, which effectively overcomes the defects of the prior art.

[0009] The technical solution of this utility model to solve the above-mentioned technical problems is as follows:

[0010] A liquid rocket engine turbopump bearing axial clearance measuring device includes a cylindrical housing, a pressure cap, a pressure loading device, a pressure loading component, and a force gauge. The upper part of the inner wall of the housing has a stepped annular groove adapted to the bearing under test. The outer ring of the bearing under test is fitted and supported at the bottom of the stepped annular groove. The pressure cap is detachably mounted on the upper end of the housing. The force gauge is located at the bottom of the housing. The pressure loading component passes through the inner ring of the bearing under test, and its bottom contacts the force gauge. The upper end of the pressure loading component has a force loading portion that fits against the upper end of the inner ring of the bearing under test. The pressure loading device is mounted on the pressure cap and connected to the upper end of the pressure loading component, used to apply downward pressure to the pressure loading component. The pressure cap has a through-hole.

[0011] Based on the above technical solution, the present invention can be further improved as follows.

[0012] Furthermore, the aforementioned housing includes a cylindrical body and a support base. A connecting ring is provided on the lower outer periphery of the cylindrical body. The connecting ring is bolted to the support base, and the force measuring device is placed on the upper end of the support base.

[0013] Furthermore, an annular boss is provided on the upper part of the outer periphery of the aforementioned cover, the annular boss is pressed against the upper end of the aforementioned housing, and is connected to the upper end of the aforementioned housing by bolts.

[0014] Furthermore, the aforementioned pressure loading member is a cylindrical component adapted to the aforementioned bearing under test, and the upper outer periphery of the aforementioned pressure loading member is provided with an annular force loading portion.

[0015] Furthermore, the aforementioned force measuring device is a pressure sensor.

[0016] Furthermore, the upper middle part of the aforementioned force gauge is provided with a protruding columnar contact portion, and the lower middle part of the aforementioned pressure loading member is provided with a positioning hole adapted to the aforementioned contact portion, and the aforementioned contact portion is embedded in the aforementioned positioning hole.

[0017] Furthermore, the aforementioned pressure loading device includes a tightening bolt, and the middle part of the aforementioned gland is provided with a threaded hole adapted to the aforementioned tightening bolt. The lower end of the aforementioned tightening bolt passes through the aforementioned threaded hole and is screwed into each other. The lower end of the aforementioned tightening bolt contacts the upper end of the aforementioned pressure loading component.

[0018] Furthermore, the upper end of the aforementioned tightening bolt is provided with a square head to facilitate the application of torque.

[0019] Furthermore, the aforementioned pressure loading device also includes a torque wrench, which is used to engage with the aforementioned square head and drive the aforementioned tightening bolt to screw in.

[0020] Furthermore, the aforementioned measuring holes are provided in multiple manner and are distributed at intervals around the aforementioned pressure loading member, and the aforementioned measuring holes are located above the aforementioned force loading part.

[0021] The beneficial effects of this utility model are: simple and reasonable structural design, reliable operation, low labor intensity, and the ability to make the measurement of bearing axial clearance more accurate and convenient, thus improving the problem of high labor intensity during traditional measurement methods. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the axial clearance measuring device for the liquid rocket engine turbopump bearing of this utility model.

[0023] Figure 2 This is a schematic diagram of the axial clearance measuring device for the liquid rocket engine turbopump bearing of this utility model under load.

[0024] The attached diagram lists the components represented by each number as follows:

[0025] 1. Housing; 2. Gland; 3. Pressure loading device; 4. Pressure loading component; 5. Force gauge; 6. Bearing to be tested; 11. Cylinder body; 12. Support base; 21. Measuring hole; 22. Annular boss; 31. Tightening bolt; 32. Torque wrench; 41. Force loading part; 51. Contact part; 111. Stepped annular groove; 311. Square head. Detailed Implementation

[0026] The principles and features of this utility model are described below with reference to the accompanying drawings. The examples given are only for explaining this utility model and are not intended to limit the scope of this utility model.

[0027] Example

[0028] like Figure 1As shown, the liquid rocket engine turbopump bearing axial clearance measuring device of this embodiment includes a cylindrical housing 1, a pressure cap 2, a pressure loading device 3, a pressure loading component 4, and a force measuring device 5. The upper part of the inner wall of the housing 1 is provided with a stepped annular groove 111 adapted to the bearing 6 to be tested. The outer ring of the bearing 6 to be tested is fitted and supported at the bottom of the stepped annular groove 111. The pressure cap 2 is detachably mounted on the upper end of the housing 1. The force measuring device 5 is disposed at the bottom of the housing 1. The pressure loading component 4 passes through the inner ring of the bearing 6 to be tested, and its bottom is in contact with the force measuring device 5. The upper end of the pressure loading component 4 is provided with a force loading part 41 that fits against the upper end of the inner ring of the bearing 6 to be tested. The pressure loading device 3 is mounted on the pressure cap 2 and connected to the upper end of the pressure loading component 4 for applying downward pressure to the pressure loading component 4. The pressure cap 2 has a through measuring hole 21.

[0029] In the liquid rocket engine turbopump bearing axial clearance measuring device of this embodiment, the upper end face of the housing 1 is a horizontal plane, the surface of the pressure cap 2 that contacts the upper end of the housing 1 is a horizontal plane, the upper surface of the pressure cap 2 is also a horizontal plane, and the upper end face of the pressure loading member 4 is also a horizontal plane. The upper end face of the force loading part 41 is flush with the upper end face of the pressure loading member 4.

[0030] The measurement process is as follows:

[0031] When measuring the clearance of the turbine pump bearing (i.e., the bearing under test 6), the above-mentioned structure is installed, the pressure cap 2 is opened, and the force measuring device 5, the bearing under test 6, and the pressure loading component 4 are assembled in place. Simultaneously, the height (thickness) δ1 between the upper end face of the pressure cap 2 and the upper end face of the housing 1, and the thickness δ2 of the force loading part 41 of the pressure loading component 4 are recorded. At the same time, the distance height h1 between the upper end face of the outer ring of the bearing under test 6 and the upper end face of the housing 1 is measured. Then, the pressure cap 2 is installed, and the pressure loading device 3 is installed. After installation, axial pressure (i.e., vertical pressure) is applied to the pressure loading component 4 through the pressure loading device 3. Next, the distance height h2 between the upper end face of the force loading part 41 and the upper end face of the pressure cap 2 is measured through the measuring hole 21 using a height gauge. Finally, the axial clearance of the bearing under test 6 is obtained by h1 + δ1 - h2 - δ2 = δ. The overall structure is simple and reasonable, the operation is reliable, and the labor intensity of operation is low. It enables more accurate and convenient measurement of bearing axial clearance, improving the problem of high labor intensity during traditional measurement methods. At the same time, the device is simple and convenient to assemble bearings, avoiding damage to bearing components during the assembly process.

[0032] In this embodiment, the housing 1 includes a cylindrical body 11 and a support base 12. A connecting ring is provided on the lower outer periphery of the cylindrical body 11. The connecting ring is bolted to the support base 12. The force measuring device 5 is placed on the upper end of the support base 12.

[0033] In a preferred embodiment, the upper part of the outer periphery of the aforementioned pressure cover 2 is provided with an annular boss 22, which presses against the upper end of the aforementioned housing 1 and is connected to the upper end of the aforementioned housing 1 by bolts (the annular boss 22 is provided with multiple bolt holes along the circumferential direction, the bolts are installed in the bolt holes, and the lower end is connected to the corresponding screw holes on the upper end of the housing 1).

[0034] In the above implementation scheme, the annular boss 22 is convenient to be assembled with the upper end of the housing 1. The size of the main body of the cover 2 is consistent with the size of the inner cavity of the housing 1. When assembling the cover 2, the lower end is inserted, and then the annular boss 22 is assembled with the upper end of the housing 1 by bolts, which is easy to disassemble and assemble.

[0035] In a preferred embodiment, the pressure loading member 4 is a cylindrical component adapted to the bearing 6 to be tested, and the upper outer periphery of the pressure loading member 4 is provided with an annular force loading part 41.

[0036] In the above implementation scheme, the main body size (diameter) of the pressure loading member 4 is consistent with the inner diameter of the inner ring of the bearing 6 to be tested, and the cross-sectional size of the force loading part 41 is larger than the inner diameter of the inner ring of the bearing 6 to be tested, so that the force loading part 41 can press against the upper end of the inner ring of the bearing 6 to be tested (without contacting the upper end of the outer ring). In this way, when pressure is applied, it can effectively act on the inner ring of the bearing 6 to be tested, providing an effective vertical downward loading force.

[0037] In this embodiment, the force sensor 5 is a conventional pressure sensor.

[0038] More specifically, the force gauge 5 has a protruding columnar contact portion 51 at the upper center, and the pressure loading member 4 has a positioning hole at the lower center that matches the contact portion 51, with the contact portion 51 embedded in the positioning hole. The lower part of the main body of the force gauge 5 is flat, allowing it to be placed stably at the bottom of the housing 1. The contact portion 51 is located at the upper center, and the positioning hole that matches the contact portion 51 is located at the lower end of the pressure loading member 4. The two are precisely positioned and installed by the mutual limiting of the contact portion 51 and the positioning hole, ensuring that no displacement occurs during force loading.

[0039] In a preferred embodiment, the pressure loading device 3 includes a tightening bolt 31. The middle part of the pressure cap 2 is provided with a screw hole adapted to the tightening bolt 31. The lower end of the tightening bolt 31 passes through the screw hole and is screwed into each other. The lower end of the tightening bolt 31 contacts the upper end of the pressure loading member 4.

[0040] In the above implementation scheme, during the loading process, the tightening bolt 31 is tightened by external force. As the tightening bolt 31 is screwed downwards, the force is transmitted to the pressure loading component 4. The operation process achieves the purpose of applying axial pressure by applying torque, reducing the labor intensity of workers and improving inspection efficiency. The operation is convenient and quick, facilitating batch inspection of bearings.

[0041] In this embodiment, the upper end of the tightening bolt 31 is provided with a square head 311 for easy application of torque. It is convenient to use a tool to apply torque to the square head 311, thereby driving the tightening bolt 31 to screw in the applied pressure.

[0042] It should be noted that in this embodiment, the tightening bolt 31, the bearing to be tested 6, and the positioning hole are coaxially distributed to ensure that the force loading is on the central axis of the whole and will not deviate, so that the measurement results are more accurate and provide effective axial loading.

[0043] As a preferred implementation method, such as Figure 2 As shown, the pressure loading device 3 also includes a torque wrench 32, which is used to cooperate with the square head 311 and drive the tightening bolt 31 to screw in.

[0044] In the above implementation scheme, for liquid rocket engine turbopumps with large thrust, when a large axial pressure is applied to the bearing 6 under test, this device can ensure the stability of the bearing, allowing the tightener to read the accurate torque value from the torque wrench 32 and read the axial pressure value through the force gauge 5, thereby improving the inspection accuracy.

[0045] In this embodiment, multiple measuring holes 21 are provided and distributed at intervals around the pressure loading member 4, and the measuring holes 21 are located above the force loading part 41. Multiple sets of data can be measured from multiple measuring holes 21, reducing the error of quantity measurement. At the same time, multiple positions also facilitate measurement.

[0046] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0047] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this utility model, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0048] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0049] In this utility model, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0050] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0051] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A device for measuring the axial clearance of a liquid rocket engine turbopump bearing, characterized in that: The device includes a cylindrical housing (1), a pressure cap (2), a pressure loading device (3), a pressure loading component (4), and a force gauge (5). The upper part of the inner wall of the housing (1) is provided with a stepped annular groove (111) adapted to the bearing (6) to be tested. The outer ring of the bearing (6) to be tested is fitted and supported at the bottom of the stepped annular groove (111). The pressure cap (2) is detachably mounted on the upper end of the housing (1). The force gauge (5) is located at the bottom of the housing (1). The loading member (4) passes through the inner ring of the bearing to be tested (6) and its bottom contacts the force measuring device (5). The upper end of the pressure loading member (4) is provided with a force loading part (41) that fits against the upper end of the inner ring of the bearing to be tested (6). The pressure loading device (3) is mounted on the pressure cover (2) and connected to the upper end of the pressure loading member (4) for applying downward pressure to the pressure loading member (4). The pressure cover (2) has a measuring hole (21) that runs through the top and bottom.

2. The device for measuring the axial clearance of a liquid rocket engine turbopump bearing according to claim 1, characterized in that: The housing (1) includes a cylindrical body (11) and a support base (12). A connecting ring is provided on the lower outer periphery of the cylindrical body (11). The connecting ring is bolted to the support base (12). The force measuring device (5) is placed on the upper end of the support base (12).

3. The device for measuring the axial clearance of a liquid rocket engine turbopump bearing according to claim 1, characterized in that: The upper part of the outer periphery of the pressure cap (2) is provided with an annular boss (22), which presses against the upper end of the housing (1) and is connected to the upper end of the housing (1) by bolts.

4. The device for measuring the axial clearance of a liquid rocket engine turbopump bearing according to claim 1, characterized in that: The pressure loading member (4) is a cylindrical component adapted to the bearing (6) to be tested, and the upper outer periphery of the pressure loading member (4) is provided with an annular force loading part (41).

5. The device for measuring the axial clearance of a liquid rocket engine turbopump bearing according to claim 1, characterized in that: The force measuring device (5) is a pressure sensor.

6. The device for measuring the axial clearance of a liquid rocket engine turbopump bearing according to claim 5, characterized in that: The upper end of the force gauge (5) is provided with a protruding columnar contact part (51), and the lower end of the pressure loading member (4) is provided with a positioning hole that matches the contact part (51). The contact part (51) is embedded in the positioning hole.

7. The device for measuring the axial clearance of a liquid rocket engine turbopump bearing according to claim 1, characterized in that: The pressure loading device (3) includes a tightening bolt (31). The middle part of the pressure cap (2) is provided with a screw hole adapted to the tightening bolt (31). The lower end of the tightening bolt (31) passes through the screw hole and is screwed together. The lower end of the tightening bolt (31) contacts the upper end of the pressure loading component (4).

8. The device for measuring the axial clearance of a liquid rocket engine turbopump bearing according to claim 7, characterized in that: The upper end of the tightening bolt (31) is provided with a square head (311) to facilitate the application of torque.

9. The axial clearance measuring device for a liquid rocket engine turbopump bearing according to claim 8, characterized in that: The pressure loading device (3) further includes a torque wrench (32) for engaging with the square head (311) and driving the tightening bolt (31) to screw in.

10. A liquid rocket engine turbopump bearing axial clearance measuring device according to any one of claims 1 to 9, characterized in that: The measuring holes (21) are provided in multiple ways and are distributed at intervals around the pressure loading member (4), and the measuring holes (21) are located above the force loading part (41).

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