CN113086240A - Aeroengine installation adjusting device - Google Patents
Aeroengine installation adjusting device Download PDFInfo
- Publication number
- CN113086240A CN113086240A CN202110283578.2A CN202110283578A CN113086240A CN 113086240 A CN113086240 A CN 113086240A CN 202110283578 A CN202110283578 A CN 202110283578A CN 113086240 A CN113086240 A CN 113086240A
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- Prior art keywords
- pin shaft
- bearing pin
- locking plate
- base
- limit
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- 238000009434 installation Methods 0.000 title claims description 36
- 238000012360 testing method Methods 0.000 claims description 12
- 229910000851 Alloy steel Inorganic materials 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 4
- 230000002452 interceptive effect Effects 0.000 claims description 3
- 238000006073 displacement reaction Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 description 8
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- B64D27/40—
Abstract
The invention discloses an aeroengine mounting and adjusting device, which comprises a hand wheel, a base, a limit screw, a force bearing pin shaft, a limit locking plate, a locking bolt, a fastening screw sleeve and a spring, wherein the base is provided with a pin shaft hole along the axis direction of an engine main mounting hole, the force bearing pin shaft is arranged in the pin shaft hole, the rear end of the force bearing pin shaft is a screw thread section, the screw thread section is connected with the hand wheel through screw threads, the force bearing pin shaft is provided with a limit groove, the limit screw is screwed into the limit groove through a screw hole at the upper end of the base, the rear end of the base is provided with a limit locking plate mounting groove, the limit locking plate is arranged in the limit locking plate mounting groove of the base, the limit locking plate is clamped into a clamping groove at the front end of the hand wheel to limit the axial movement of the hand wheel along the force bearing pin shaft, the upper part of, the end face grooves of the two fastening threaded sleeves form a spring mounting section, the springs are arranged on the contact faces of the two fastening threaded sleeves, the springs are limited in the spring mounting section, and the locking bolts penetrate through the two fastening threaded sleeves and the spring and are locked through nuts.
Description
Technical Field
The invention relates to the technical field of aero-engine tests, in particular to an aero-engine installation adjusting device.
Background
Before the ground test of the aero-engine, the aero-engine needs to be installed on a test run rack, and the part of the test run rack, which is connected with an engine installation joint, has the characteristics of enough strength, adjustable size and position, simple structure and the like, so that the safety of the aero-engine in the installation test process is ensured. The mounting joints of a plurality of engines are in a joint bearing structure, a fixed mounting seat is generally designed on a test run rack and matched with a pin shaft with a corresponding size to support the engine, the structural sizes of the mounting seat and the pin shaft are fixed at the beginning of design, and the test run rack cannot move any more when being mounted. This structural support has some drawbacks: a) the requirements on the overall dimension, the machining precision and the like of the mounting seat and the pin shaft are high, and once the dimension of one part is deviated, the engine cannot be mounted and fixed. If the connection part of the engine mounting joint needs to be fine-adjusted, the position of the whole bracket needs to be adjusted and positioned again. b) When the pin shaft is connected with the upper hole type part of the engine mounting section, the distance in the axial direction can be adjusted only by increasing or decreasing the gaskets, and the process is complicated and low in efficiency. At present, no special literature data is introduced and referred to for the fixing and adjusting device of the aeroengine mounting joint, and the research in the field is blank at home.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to provide an installation and adjustment device capable of replacing a hole type installation section type aero-engine, overcomes the defect of complex installation and adjustment process in the prior art, and well achieves the purpose that the installation and adjustment process of the aero-engine can be rapidly completed on the premise of ensuring the safety and reliability in the installation and test process of the aero-engine.
The technical scheme of the invention is as follows:
an aeroengine mounting and adjusting device comprises a hand wheel 1, a base 2, a limit screw 3, a bearing pin shaft 4, a limit locking plate 5, a locking bolt 8, a fastening screw sleeve 9 and a spring 10, wherein the base 1 is provided with a pin shaft hole along the axis direction of an engine main mounting hole, the bearing pin shaft 4 is arranged in the pin shaft hole, the rear end of the bearing pin shaft 4 is a thread section, the thread section is connected with the hand wheel (1) through threads, the bearing pin shaft 4 is provided with a limit groove 11, the limit screw 3 is screwed into the limit groove 11 through a screw hole at the upper end of the base 1 and used for limiting the axial rotation of the bearing pin shaft 4, the rear end of the base 2 is provided with a limit locking plate mounting groove, the limit locking plate 5 is arranged in the limit locking plate mounting groove of the base 2, and the limit locking plate 5 is clamped into a clamping groove at the front end of the hand wheel 1, restriction hand wheel 1 is along 4 axial displacement of load round pin axle, 2 upper portions of base open and to have spacing swivel nut mounting hole, fastening swivel nut 9 be two, just two fastening swivel nuts 9 relative install in spacing swivel nut mounting hole, two fastening swivel nut 9's terminal surface have an end face groove, two end face grooves form the spring mounting section, spring 10 set up on two fastening swivel nut 9's contact surface, and spring 10 is restricted the spring mounting section in, locking bolt 8 pass inside two fastening swivel nuts 9 and spring 10 to lock through the nut.
Further, spacing locking plate 5 be door-shaped structure, one side of spacing locking plate 5 is provided with the installation auricle, the opposite side has a locating hole, pass the locating hole through set screw 6 and fix spacing locking plate 5 on base 2, and spacing locking plate 5 can follow the through-hole that set screw 6 rotation passed the installation auricle through bolt 7, restriction spacing locking plate 5 is along 4 axial rotations of load round pin axle, the door-shaped frame card of spacing locking plate 5 is in the draw-in groove of hand wheel.
Furthermore, a conical section is arranged at the front end of the bearing pin shaft 4, and the conical section can prevent the bearing pin shaft 4 from interfering with other parts on the engine.
Further, the conical section front end be provided with the installation section, the installation section is cylindrical, the installation section is used for being connected with the engine mount joint.
Furthermore, four connecting holes are formed in the base 2, and the base 2 is connected with the test bed support through the four connecting holes.
Furthermore, the bearing pin shaft 4 is in clearance fit with the pin shaft hole of the base 2, the fit precision is within 0.05mm, and the bearing pin shaft 4 and the central axis of the engine mounting section can be ensured to be coaxial.
Furthermore, the outer cylindrical surface of the rear end of the hand wheel 1 is provided with reticular patterns, so that the hand wheel 4 can be prevented from slipping when being rotated.
Furthermore, the parallelism between the central axis of the pin shaft hole and the ground of the base 1 is within 0.05mm, so that the bearing pin shaft 4 and the central axis of the engine mounting section can be ensured to be coaxial.
Furthermore, the bottoms of the contact surfaces of the two fastening screw sleeves 9 are provided with symmetrical arc surfaces which are matched with the outer surface of the bearing pin shaft
Further, the hand wheel 1, the base 2, the limit screw 3, the bearing pin shaft 4, the limit locking plate 5, the locking bolt 8, the fastening screw sleeve 9 and the spring 10 are all made of alloy steel materials, and the alloy steel rigidity is high.
The invention has the beneficial effects that:
the invention provides an aeroengine mounting and adjusting device, which can completely replace the original fixed mounting bracket, the strength and the reliability of the aeroengine mounting and adjusting device meet the requirements of aeroengine mounting and testing, secondly, the position of a bearing shaft pin is quickly adjusted on the premise of not changing the position of a main bracket, the mounting and adjusting process is quickly completed, and the working efficiency is improved.
Drawings
FIG. 1 is a front view of the structure of the present invention;
FIG. 2 is a side view of the structure of the present invention;
FIG. 3 is a cross-sectional view along AA of FIG. 1;
wherein: 1. the hand wheel, 2, the base, 3, the stop screw, 4, the load-bearing pin axle, 5, the limit locking plate, 6, the set screw, 7, the bolt, 8, the locking bolt, 9, the fastening swivel nut, 10, the spring, 11, the spacing groove.
Detailed Description
The following detailed description of the embodiments of the present invention, such as the shapes, configurations, mutual positions and connection relationships of the components, the functions and operating principles of the components, the manufacturing processes and the operation and use methods thereof, will be further described in detail with reference to the accompanying drawings, so as to help those skilled in the art to more completely, accurately and deeply understand the concept and technical solutions of the present invention:
as shown in fig. 1, an aeroengine mounting and adjusting device comprises a hand wheel 1, a base 2, a limit screw 3, a force bearing pin shaft 4, a limit locking plate 5, a fixing screw 6, a bolt 7, a locking bolt 8, a fastening screw sleeve 9, a spring 10 and a limit groove 11;
the base comprises a base body and a bottom mounting surface, a plurality of connecting holes are formed in the bottom mounting surface, during use, the base is fixed to a test bed support through the connecting holes of the bottom mounting surface, the base body is located above the bottom mounting surface, a through pin shaft hole along the axis direction of a main mounting hole of an engine is formed in the base body and used for mounting a bearing pin shaft 4 and a hand wheel, the pin shaft hole in the base body is divided into two hole sections with different diameters, the hole section with the small diameter is used for mounting the bearing pin shaft 4, one end with the large diameter is used for mounting the hand wheel, the top of the base body is further provided with a bulge, and a limiting screw sleeve mounting hole is formed in the bulge and used. The parallelism between the central axis of the pin shaft hole and the ground of the base 1 is within 0.05mm, so that the coaxiality of the bearing pin shaft 4 and the central axis of the engine mounting section can be ensured.
As shown in fig. 1, the bearing pin shaft comprises a middle shaft body, the rear end of the shaft body is provided with a thread section, the outer surface of the thread section is provided with an external thread, the front end of the shaft body is a conical section, the front end of the conical section is an installation section, the conical section can prevent the bearing pin shaft 4 from interfering with other parts on the engine, the installation section is cylindrical, the installation section is used for being connected with an engine installation section, the shaft body is arranged in a hole section with a small hole diameter of a pin shaft hole and is in clearance fit with the hole section, the fit precision is within 0.05mm, the pin shaft 4 can be properly adjusted, the bearing pin shaft 4 is coaxial with the central axis of the engine installation section, and the thread section is arranged in the hole section with a large.
The pin shaft body is provided with a limiting groove, the limiting screw 3 is screwed into the limiting groove 11 through a screw hole in the upper end of the base 1 and used for limiting axial rotation of the bearing pin shaft 4, the limiting screw 3 is in clearance fit with the limiting groove, the limiting screw 3 can be guaranteed to be smoothly inserted into the limiting groove 11 and can be limited from axially rotating the bearing pin shaft 4, the limiting groove 11 can be opened in a plurality, and therefore matching of a plurality of limiting screws can be achieved.
The hand wheel 1 comprises a wheel disc and a connecting section, the connecting section is of a hollow structure, an internal thread is arranged on the inner wall surface of the connecting section, as shown in figure 1, the connecting section is arranged in a hole section with a large hole diameter of a pin hole and is in threaded connection with a thread section of a bearing pin shaft 4, the outer diameter of the connecting section is larger than the hole section with a small hole diameter of the pin hole, the hand wheel 1 can not completely enter the pin hole, the outer surface of the connecting section is also provided with a circle of clamping groove, the rear end of the base 2 is provided with a limiting locking plate mounting groove, the position of the limiting locking plate 5 mounting groove corresponds to the clamping groove, the limiting locking plate 5 is arranged in the limiting locking plate mounting groove of the base 2, the limiting locking plate 5 is clamped into the clamping groove at the front end of the hand wheel 1, the hand wheel 1 is limited from axially moving along the bearing pin shaft, meanwhile, the weight reduction of the hand wheel can be realized, the outer surface of the wheel disc is provided with reticular patterns, and the hand wheel 4 can be prevented from slipping when rotated, so that the operation is facilitated.
As shown in fig. 2, limiting locking plate 5 is door-shaped structure, one side of limiting locking plate 5 door-shaped structure is provided with the installation auricle, the opposite side has a locating hole, pass the locating hole through set screw 6 and fix limiting locking plate 5 on the limiting locking plate mounting groove of base 2, and limiting locking plate 5 can be followed set screw 6 and rotated, when installing limiting locking plate 5, articulate limiting locking plate 5 one side on base 2 through set screw 6 earlier, the other end is rotatory to the limiting locking plate mounting groove of base in, and limiting locking plate card is gone into in the draw-in groove of load round pin axle 4, rethread bolt 7 passes the through-hole of installation auricle, limiting locking plate 5 is along load round pin axle 4 axial rotation, limiting hand wheel 1's door-shaped frame card is in hand wheel 1's draw-in groove, limiting hand wheel 1.
As shown in fig. 3, the base 2 has two fixing screw sleeve mounting holes formed inside the protrusions, the number of the fastening screw sleeves 9 is two, and the two fastening screw sleeves 9 are oppositely arranged in the limiting screw sleeve mounting holes, the two fastening screw sleeves 9 are in clearance fit with the limiting screw sleeve mounting holes, so that the fastening screw sleeves 9 are convenient to install and disassemble, the end surfaces of the two fastening screw sleeves 9 are provided with end surface grooves, the end surface grooves are communicated with the through holes of the fastening screw sleeves 9, the width of the end surface grooves is larger than that of the through holes of the fastening screw sleeves 9, the two end surface grooves form spring mounting sections, the spring 10 is arranged on the contact surface of the two fastening screw sleeves 9, the outer diameter of the spring is larger than the aperture of the through hole of the fastening screw sleeve 9, so that the spring 10 is confined in the spring mounting section, the locking bolt 8 passes through the two fastening nuts 9 and the inside of the spring 10, and the two fastening screw sleeves and the spring are tightly pressed in the limiting screw sleeve mounting hole through nut locking.
When the locking bolt 8 is unlocked, the fastening screw sleeve 9 and the spring 10 cannot limit the movement of the bearing pin shaft 4 along the axis, the hand wheel 1 is rotated at the moment, the hand wheel 1 and the bearing pin shaft 4 can generate axial movement due to the fact that thread pairs exist, and meanwhile, the hand wheel 1 is limited by the limiting locking plate 5 and cannot move, so that the bearing pin shaft 4 can generate movement along the axis. Therefore, the force bearing pin shaft 4 can be adjusted by rotating the hand wheel 1.
Further, as shown in fig. 3, the bottom of the contact surface of the two fastening screw sleeves 9 is provided with a symmetrical arc surface, the arc surface is matched with the outer cylindrical surface of the bearing pin shaft 4, after the fastening screw sleeves 9 are installed, the arc surface can be attached to the outer cylindrical surface of the bearing pin shaft 4, and the fastening screw sleeves 9 are placed to interfere with the bearing pin shaft 4.
In addition, the hand wheel 1, the base 2, the limit screw 3, the bearing pin shaft 4, the limit locking plate 5, the locking bolt 8, the fastening screw sleeve 9 and the spring 10 are all made of alloy steel materials, and the alloy steel materials are high in rigidity and can bear large load and are not easy to damage.
The using method of the invention comprises the following steps: when the aero-engine is installed, the force bearing pin shaft 4 can be adjusted by loosening the locking bolt 8 and then rotating the hand wheel 1, so that the force bearing pin shaft 4 can penetrate into the position of an installation section of the aero-engine, the installation process can be completed after the locking bolt 8 is locked after the position is adjusted, if the width between two main installation sections of the aero-engine is larger than the span between the force bearing shafts 4, the bolt 7 is taken down, the locking bolt 8 and the limiting screw 3 are loosened, the limiting locking plate 5 is opened, the hand wheel 1 and the force bearing pin shaft 4 can be taken out at the moment, the hand wheel 1, the force bearing pin shaft 4 and each limiting part are installed again after the aero-engine falls into a proper position, the force bearing pin shaft 4 can be adjusted by rotating the hand wheel 1 again, so that the force bearing pin shaft 4 penetrates into the position of the.
The invention has been described above with reference to the accompanying drawings, it is obvious that the invention is not limited to the specific implementation in the above-described manner, and it is within the scope of the invention to apply the inventive concept and solution to other applications without substantial modification.
Claims (10)
1. The utility model provides an aeroengine installation adjusting device which characterized in that: comprises a hand wheel (1), a base (2), a limit screw (3), a bearing pin shaft (4), a limit locking plate (5), a locking bolt (8), a fastening screw sleeve (9) and a spring (10), wherein the base (1) is provided with a pin shaft hole along the axis direction of an engine main mounting hole, the bearing pin shaft (4) is arranged in the pin shaft hole, the rear end of the bearing pin shaft (4) is a thread section, the thread section is connected with the hand wheel (1) through threads, the bearing pin shaft (4) is provided with a limit groove (11), the limit screw (3) is screwed into the limit groove (11) through a screw hole at the upper end of the base (1) and is used for limiting the axial rotation of the bearing pin shaft (4), the rear end of the base (2) is provided with a limit locking plate, the limit locking plate (5) is arranged in the limit locking plate mounting groove of the base (2), just spacing locking plate (5) card go into the draw-in groove of hand wheel (1) front end in, restriction hand wheel (1) are along load round pin axle (4) axial displacement, base (2) upper portion open and to have spacing swivel nut mounting hole, fastening swivel nut (9) be two, just two fastening swivel nuts (9) relative install in spacing swivel nut mounting hole, the terminal surface of two fastening swivel nuts (9) has the terminal surface groove, two terminal surface grooves form spring mounting section, spring (10) set up on the contact surface of two fastening swivel nuts (9), and spring (10) are restricted the spring mounting section in, locking bolt (8) pass inside two fastening swivel nuts (9) and spring (10) to lock through the nut.
2. An aircraft engine installation adjustment device according to claim 1, characterised in that: spacing locking plate (5) be door-shaped structure, one side of spacing locking plate (5) is provided with the installation auricle, the opposite side has a locating hole, pass the locating hole through set screw (6) and fix spacing locking plate (5) on base (2), and spacing locking plate (5) can be followed set screw (6) and rotated, pass the through-hole of installation auricle through bolt (7), limit spacing locking plate (5) along load round pin axle (4) axial rotation, the door-shaped frame card of spacing locking plate (5) is in the draw-in groove of hand wheel.
3. An aircraft engine installation adjustment device according to claim 1, characterised in that: the front end of the bearing pin shaft (4) is provided with a conical section which can prevent the bearing pin shaft (4) from interfering with other parts on the engine.
4. An aircraft engine installation adjustment device according to claim 3, characterised in that: the mounting section is cylindrical and is used for being connected with an engine mounting joint.
5. An aircraft engine installation adjustment device according to claim 1, characterised in that: the base (2) is provided with four connecting holes, and the base (2) is connected with the test bed bracket through the four connecting holes.
6. An aircraft engine installation adjustment device according to claim 1, characterised in that: the bearing pin shaft (4) is in clearance fit with the pin shaft hole of the base (2), the fit precision is within 0.05mm, and the bearing pin shaft (4) and the central axis of the engine mounting section can be ensured to be coaxial.
7. An aircraft engine installation adjustment device according to claim 1, characterised in that: the outer cylindrical surface of the rear end of the hand wheel (1) is provided with netted patterns, and the hand wheel (4) can be prevented from slipping when being rotated.
8. An aircraft engine installation adjustment device according to claim 1, characterised in that: the parallelism between the central axis of the pin shaft hole and the ground of the base (1) is within 0.05mm, so that the bearing pin shaft (4) and the central axis of the engine mounting section are coaxial.
9. An aircraft engine installation adjustment device according to claim 1, characterised in that: the bottom of the contact surface of the two fastening screw sleeves (9) is provided with symmetrical arc surfaces which are matched with the outer surface of the bearing pin shaft (4).
10. An aircraft engine installation adjustment device according to claim 1, characterised in that: the hand wheel (1), the base (2), the limiting screw (3), the bearing pin shaft (4), the limiting locking plate (5), the locking bolt (8), the fastening screw sleeve (9) and the spring (10) are all made of alloy steel materials, and the alloy steel rigidity is high.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110283578.2A CN113086240A (en) | 2021-03-16 | 2021-03-16 | Aeroengine installation adjusting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110283578.2A CN113086240A (en) | 2021-03-16 | 2021-03-16 | Aeroengine installation adjusting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113086240A true CN113086240A (en) | 2021-07-09 |
Family
ID=76668253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110283578.2A Pending CN113086240A (en) | 2021-03-16 | 2021-03-16 | Aeroengine installation adjusting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113086240A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3596410A (en) * | 1969-02-17 | 1971-08-03 | Litton Industries Inc | Machine tool with retractable combined chordal gage and lateral locator |
| US4087075A (en) * | 1976-04-22 | 1978-05-02 | Iwa Nechanicky | Valve assembly |
| CN102294664A (en) * | 2011-06-30 | 2011-12-28 | 西北工业大学 | Clamp for inner support sleeve |
| CN203712610U (en) * | 2014-01-15 | 2014-07-16 | 哈尔滨东安发动机（集团）有限公司 | Shaft sleeve installation tool |
| CN107538425A (en) * | 2017-09-18 | 2018-01-05 | 贵州凯阳航空发动机有限公司 | Engine movable ground oil-sealing arrangement |
| CN107584461A (en) * | 2017-09-18 | 2018-01-16 | 贵州凯阳航空发动机有限公司 | Engines ground oil-sealing arrangement |
| EP3619080A1 (en) * | 2018-04-20 | 2020-03-11 | Autel Intelligent Technology Corp., Ltd. | Automobile calibration device |
| CN210499927U (en) * | 2019-08-29 | 2020-05-12 | 昆山藤乔电子有限公司 | Valve rod detection clamping device |
| CN111376185A (en) * | 2018-12-28 | 2020-07-07 | 杭州巨星科技股份有限公司 | Adjustable torque clamp |
-
2021
- 2021-03-16 CN CN202110283578.2A patent/CN113086240A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3596410A (en) * | 1969-02-17 | 1971-08-03 | Litton Industries Inc | Machine tool with retractable combined chordal gage and lateral locator |
| US4087075A (en) * | 1976-04-22 | 1978-05-02 | Iwa Nechanicky | Valve assembly |
| CN102294664A (en) * | 2011-06-30 | 2011-12-28 | 西北工业大学 | Clamp for inner support sleeve |
| CN203712610U (en) * | 2014-01-15 | 2014-07-16 | 哈尔滨东安发动机（集团）有限公司 | Shaft sleeve installation tool |
| CN107538425A (en) * | 2017-09-18 | 2018-01-05 | 贵州凯阳航空发动机有限公司 | Engine movable ground oil-sealing arrangement |
| CN107584461A (en) * | 2017-09-18 | 2018-01-16 | 贵州凯阳航空发动机有限公司 | Engines ground oil-sealing arrangement |
| EP3619080A1 (en) * | 2018-04-20 | 2020-03-11 | Autel Intelligent Technology Corp., Ltd. | Automobile calibration device |
| CN111376185A (en) * | 2018-12-28 | 2020-07-07 | 杭州巨星科技股份有限公司 | Adjustable torque clamp |
| CN210499927U (en) * | 2019-08-29 | 2020-05-12 | 昆山藤乔电子有限公司 | Valve rod detection clamping device |
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