CN220304822U - Aeroengine steady state performance test fixture - Google Patents
Aeroengine steady state performance test fixture Download PDFInfo
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- CN220304822U CN220304822U CN202321381918.6U CN202321381918U CN220304822U CN 220304822 U CN220304822 U CN 220304822U CN 202321381918 U CN202321381918 U CN 202321381918U CN 220304822 U CN220304822 U CN 220304822U
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- fixedly connected
- turbofan
- state performance
- steady state
- turntable
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- 238000011056 performance test Methods 0.000 title claims abstract description 7
- 238000012360 testing method Methods 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims description 4
- 230000001788 irregular Effects 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 description 5
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 230000003746 surface roughness Effects 0.000 description 3
- 230000008021 deposition Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 210000004243 sweat Anatomy 0.000 description 1
Abstract
The utility model belongs to the technical field of aero-engines, in particular to an aero-engine steady state performance test fixture, which comprises a workbench, a guide post and a top plate; the top of the workbench is fixedly connected with a guide post; a top plate is fixedly connected to the top of the guide post; the bottom of the top plate is fixedly connected with a guide rod; the bottom of the guide rod is fixedly connected with a curtain; a motor is fixedly connected to the bottom of the workbench; when the steady state performance of the turbofan reaches the standard, the laser line emitted by the laser pen rotates around the curtain in a circle, so that the line presents a complete circle shape, when the steady state performance of the turbofan is unbalanced, the laser line emitted by the laser pen is in a shaking shape, so that the line projected on the surface of the curtain by the laser pen presents an irregular shape, and when encountering the turbofan, a worker needs to be prompted to overhaul and maintain, and further the testing efficiency of the turbofan is improved.
Description
Technical Field
The utility model relates to the technical field of aero-engines, in particular to a steady-state performance testing tool for an aero-engine.
Background
The aeroengine is a highly complex and precise thermodynamic machine, is mainly used as a power source for airplane flight, and can be specifically divided into a piston engine, a turbofan engine and a turboshaft engine.
The structure of the turbojet engine consists of an air inlet channel, a gas compressor, a combustion chamber, a turbine and a tail nozzle, wherein an afterburner is arranged between the turbine and the tail nozzle of the fighter, and the turbojet engine still belongs to one of heat engines, so that the working principle of the heat engine is required to be followed: energy is input at high pressure and released at low pressure.
In the prior art, in the long-time use process of an aeroengine, due to various factors such as natural wear, scale deposit, fatigue, corrosion and the like, the blade tip clearance of a rotating part of the engine is increased, the surface roughness of the blade is increased, and the steady-state performance of the engine blade is deviated, so that the steady-state performance test tool for the aeroengine is provided for the problems.
Disclosure of Invention
In order to overcome the defects of the prior art and solve the problems in the background art, the utility model provides an aeroengine steady-state performance test fixture.
The technical scheme adopted for solving the technical problems is as follows: the utility model relates to an aeroengine steady-state performance testing tool which comprises a workbench, guide posts and a top plate; the top of the workbench is fixedly connected with a guide post; a top plate is fixedly connected to the top of the guide post; the bottom of the top plate is fixedly connected with a guide rod; the bottom of the guide rod is fixedly connected with a curtain; a motor is fixedly connected to the bottom of the workbench; the output end of the motor is fixedly connected with a turntable; a fixed unit is arranged in the turntable; the top of the turntable is provided with a turbofan through a fixing unit; the surface mounting of turbofan has the laser pen, and is located the bottom of curtain.
Preferably, the fixing unit includes a clamping groove; a clamping groove is formed in the turntable; a clamping block is connected in the clamping groove in a sliding manner; the end part of the clamping block is provided with a guide groove; the inside wall of guide slot is articulated through the torsional spring has the fixed plate.
Preferably, a locking groove is formed in the clamping block; a cavity is formed in the turntable; the inner side wall of the cavity is connected with a locking block in a sliding way; the side end of the locking block is fixedly connected with a first spring, and the first spring is connected to the inner side wall of the cavity in a sliding manner; the bottom of the clamping block is fixedly connected with a second spring, and the other end of the second spring is fixedly connected to the inner side wall of the clamping groove.
Preferably, a pull rod is fixedly connected to the side end of the locking block, and a pull handle is fixedly connected to the other end of the pull rod; the pull rod is connected with the cavity and the inside of the turntable in a sliding way.
Preferably, the bottom of the workbench is fixedly connected with supporting legs and provided with a plurality of supporting legs; the end of the locking piece is semi-arc-shaped.
The utility model has the advantages that:
1. according to the utility model, the turbofan is placed on the surface of the turntable and fixed through the fixing unit, and then the motor is started to drive the turntable to rotate, so that the turntable drives the turbofan to rotate, and as the laser pen is arranged on the surface of the turbofan, when the steady state performance of the turbofan reaches the standard, the laser line emitted by the laser pen rotates in a circle around the curtain, so that the line presents a complete circle shape, when the steady state performance of the turbofan is unbalanced, the laser line emitted by the laser pen presents a shaking shape, so that the line projected on the surface of the curtain by the laser pen presents an irregular shape, and when the turbofan is encountered, a worker needs to be prompted to carry out overhaul and maintenance, and the testing efficiency of the turbofan is further improved.
2. When the turbofan needs to be placed on the surface of the turntable, the fixing plate is pulled to be vertical to pull the torsion spring to generate elasticity, then the turbofan is placed on the surface of the turntable, the annular object pair Ji Kacao in the middle of the turbofan is pressed to slide towards the inside of the clamping groove, the clamping block is inserted into the inside of the clamping groove, and then the fixing plate is loosened, so that the fixing plate is reset by the elasticity generated by the torsion spring to be clamped on the surface of the turbofan, and clamping and fixing are performed.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a perspective view of a first embodiment;
FIG. 2 is a cross-sectional view of the first embodiment;
FIG. 3 is an enlarged view of FIG. 2 at A;
FIG. 4 is an enlarged view at B in FIG. 2;
fig. 5 is a schematic structural view of a wear pad according to a second embodiment.
In the figure: 1. a work table; 21. a motor; 22. a turntable; 23. a turbofan; 24. a laser pen; 25. a guide rod; 26. a curtain; 27. a guide post; 28. a top plate; 31. a clamping groove; 32. a clamping block; 33. a locking groove; 34. a guide groove; 35. a fixing plate; 36. a cavity; 37. a locking piece; 38. a first spring; 41. a pull rod; 42. a pull handle; 5. a second spring; 6. a support leg; 7. wear-resistant pad.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Example 1
Referring to fig. 1-4, an aero-engine steady-state performance testing tool comprises a workbench 1, a guide post 27 and a top plate 28; the top of the workbench 1 is fixedly connected with a guide post 27; a top plate 28 is fixedly connected to the top of the guide post 27; the bottom of the top plate 28 is fixedly connected with a guide rod 25; a curtain 26 is fixedly connected to the bottom of the guide rod 25; a motor 21 is fixedly connected to the bottom of the workbench 1; the output end of the motor 21 is fixedly connected with a turntable 22; a fixing unit is arranged inside the turntable 22; the top of the turntable 22 is provided with a turbofan 23 through a fixing unit; the surface of the turbofan 23 is provided with a laser pen 24 and is positioned at the bottom of a curtain 26; during operation, in the long-time use process of the aero-engine, due to various factors such as natural wear, scale deposition, fatigue and corrosion, the blade tip clearance of an engine rotating part is increased, the surface roughness of the blade is increased, the steady-state performance of the engine blade is caused to deviate, when the turbofan 23 is required to be detected, the turbofan 23 is placed on the surface of the turntable 22 and fixed through a fixing unit, then the motor 21 is started to drive the turntable 22 to rotate, the turntable 22 drives the turbofan 23 to rotate, and as the surface of the turbofan 23 is provided with the laser pen 24, when the steady-state performance of the turbofan 23 reaches the standard, the laser line emitted by the laser pen 24 rotates in a circle around the curtain 26, so that the line is in a complete circle shape, and when the steady-state performance of the turbofan 23 is unbalanced, the laser line emitted by the laser pen 24 is in a shaking shape, so that the line projected on the surface of the curtain 26 is in an irregular shape, when the turbofan 23 is encountered, a worker is required to be prompted to carry out overhaul and maintenance, and further the test efficiency of the turbofan 23 is improved.
The fixing unit comprises a clamping groove 31; a clamping groove 31 is formed in the turntable 22; a clamping block 32 is connected inside the clamping groove 31 in a sliding manner; the end part of the clamping block 32 is provided with a guide groove 34; the inner side wall of the guide groove 34 is hinged with a fixing plate 35 through a torsion spring; during operation, when the turbofan 23 needs to be placed on the surface of the turntable 22, the fixing plate 35 is pulled to be vertical to pull the torsion spring to generate elasticity, then the turbofan 23 is placed on the surface of the turntable 22, the ring pair Ji Kacao in the middle of the turbofan 23 is pressed to slide towards the inside of the clamping groove 31, the clamping block 32 is inserted into the inside of the clamping groove 31, then the fixing plate 35 is loosened, the fixing plate 35 is reset by the elasticity generated by the torsion spring, and then the fixing plate is clamped on the surface of the turbofan 23 to be clamped and fixed.
A locking groove 33 is formed in the clamping block 32; a cavity 36 is formed in the turntable 22; the inner side wall of the cavity 36 is connected with a locking block 37 in a sliding way; the side end of the locking block 37 is fixedly connected with a first spring 38, and the first spring 38 is connected on the inner side wall of the cavity 36 in a sliding manner; the bottom of the clamping block 32 is fixedly connected with a second spring 5, and the other end of the second spring 5 is fixedly connected on the inner side wall of the clamping groove 31; when the locking device works, but when the clamping block 32 slides downwards, the second spring 5 is extruded to generate elasticity, the locking block 37 is extruded, the locking block 37 is stretched to the inside of the cavity 36 by force to extrude the first spring 38 to generate elasticity, when the locking groove 33 is aligned with the cavity 36, the first spring 38 generates elasticity to push the locking block 37 to be inserted into the inside of the locking groove 33 for clamping and fixing, the clamping block 32 is fixed in the clamping groove 31, then the fixing plate 35 tightly extrudes the end part of the turbofan 23 for clamping and fixing, and the problem that slipping occurs due to the influence of centrifugal force when the turntable 22 rotates is avoided.
A pull rod 41 is fixedly connected to the side end of the locking piece 37, and a pull handle 42 is fixedly connected to the other end of the pull rod 41; the pull rod 41 is slidably connected to the cavity 36 and the inside of the turntable 22; when the turbofan 23 finishes detection, the pull rod 41 is driven to slide towards the side end by pulling the pull handle 42, so that the pull rod 41 drives the locking piece 37 to stretch into the cavity 36, then the second spring 5 generates elasticity to push the clamping block 32 to slide upwards, the clamping block 32 drives the fixing plate 35 to be separated from the turbofan 23, and then the fixing plate 35 is vertically swung, so that a worker can conveniently take out the turbofan 23 for maintenance.
The bottom of the workbench 1 is fixedly connected with supporting legs 6 and provided with a plurality of supporting legs; the end part of the locking block 37 is semi-arc; in operation, the overall stability of the table 1 is improved by mounting the legs 6 at the bottom of the table 1.
Example two
Referring to fig. 5, in a first comparative example, as another embodiment of the present utility model, the end of the pull handle 42 is fixedly connected with the wear pad 7; during operation, through installing wear pad 7 at the tip of pull handle 42, improve the antiskid and the protective effect of pull handle 42, avoid the staff when pulling pull handle 42 because the hand sweat problem, lead to the problem of slipping to appear between staff's hand and the pull handle 42, cause the hand to appear injured problem.
Working principle: in the long-time use process of the aeroengine, due to various factors such as natural wear, scale deposition, fatigue, corrosion and the like, the blade tip clearance of an engine rotating part is increased, the surface roughness of a blade is increased, the steady state performance of the engine blade is caused to deviate, when the turbofan 23 is required to be detected, the turbofan 23 is placed on the surface of the turntable 22 and fixed through a fixing unit, then the motor 21 is started to drive the turntable 22 to rotate, the turntable 22 drives the turbofan 23 to rotate, and as the surface of the turbofan 23 is provided with the laser pen 24, when the steady state performance of the turbofan 23 reaches the standard, the laser line emitted by the laser pen 24 rotates in a circle around the curtain 26, so that the line is in a complete circle shape, and when the steady state performance of the turbofan 23 is unbalanced, the laser line emitted by the laser pen 24 is in a shaking shape, so that the line projected on the surface of the curtain 26 by the laser pen 24 is in an irregular shape, and when the turbofan 23 is met, a worker is required to be prompted to carry out overhaul and maintenance, and further the test efficiency of the turbofan 23 is improved; when the turbofan 23 needs to be placed on the surface of the turntable 22, the fixing plate 35 is pulled to be vertical to pull the torsion spring to generate elasticity, then the turbofan 23 is placed on the surface of the turntable 22, so that a ring pair Ji Kacao in the middle of the turbofan 23 is pressed, the clamping block 32 is pressed to slide towards the inside of the clamping groove 31, the clamping block 32 is inserted into the inside of the clamping groove 31, then the fixing plate 35 is loosened, the fixing plate 35 is reset by the elasticity generated by the torsion spring, and is clamped on the surface of the turbofan 23 to be clamped and fixed; when the clamping block 32 slides downwards, the second spring 5 is extruded to generate elastic force, the locking block 37 is extruded to enable the locking block 37 to be stretched to the inside of the cavity 36 and extrude the first spring 38 to generate elastic force, when the locking groove 33 is aligned with the cavity 36, the first spring 38 generates elastic force to push the locking block 37 to be inserted into the inside of the locking groove 33 for clamping and fixing, the clamping block 32 is fixed in the clamping groove 31, then the fixing plate 35 tightly extrudes the end part of the turbofan 23 for clamping and fixing, and the problem that slipping occurs due to the influence of centrifugal force when the turntable 22 rotates is avoided; when the turbofan 23 is detected, the pull rod 41 is driven to slide towards the side end by pulling the pull handle 42, so that the pull rod 41 drives the locking piece 37 to stretch into the cavity 36, then the second spring 5 generates elasticity to push the clamping block 32 to slide upwards, so that the clamping block 32 drives the fixing plate 35 to be separated from the turbofan 23, and then the fixing plate 35 is swung to be vertical, thereby being convenient for a worker to take out the turbofan 23 for maintenance; by mounting the legs 6 at the bottom of the table 1, the overall stability of the table 1 is improved.
In the description of the present specification, the descriptions of the terms "one embodiment," "example," "specific example," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present utility model. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing has shown and described the basic principles, principal features and advantages of the utility model. It will be understood by those skilled in the art that the present utility model is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications may be made without departing from the spirit and scope of the utility model, which is defined in the appended claims.
Claims (6)
1. The steady-state performance testing tool for the aero-engine comprises a workbench (1), a guide post (27) and a top plate (28); the top of the workbench (1) is fixedly connected with a guide post (27); a top plate (28) is fixedly connected to the top of the guide post (27); the method is characterized in that: the bottom of the top plate (28) is fixedly connected with a guide rod (25); a curtain (26) is fixedly connected to the bottom of the guide rod (25); a motor (21) is fixedly connected to the bottom of the workbench (1); the output end of the motor (21) is fixedly connected with a rotary table (22); a fixed unit is arranged in the turntable (22); the top of the turntable (22) is provided with a turbofan (23) through a fixing unit; the surface of the turbofan (23) is provided with a laser pen (24) and is positioned at the bottom of the curtain (26).
2. The aircraft engine steady state performance test fixture of claim 1, wherein: the fixing unit comprises a clamping groove (31); a clamping groove (31) is formed in the rotary table (22); a clamping block (32) is connected in the clamping groove (31) in a sliding manner; the end part of the clamping block (32) is provided with a guide groove (34); the inner side wall of the guide groove (34) is hinged with a fixing plate (35) through a torsion spring.
3. The aeroengine steady state performance testing tool according to claim 2, wherein: a locking groove (33) is formed in the clamping block (32); a cavity (36) is formed in the turntable (22); the inner side wall of the cavity (36) is connected with a locking block (37) in a sliding way; the side end of the locking piece (37) is fixedly connected with a first spring (38), and the first spring (38) is connected to the inner side wall of the cavity (36) in a sliding mode.
4. An aircraft engine steady state performance test fixture according to claim 3, wherein: the bottom of the clamping block (32) is fixedly connected with a second spring (5), and the other end of the second spring (5) is fixedly connected to the inner side wall of the clamping groove (31).
5. The aeroengine steady state performance testing tool according to claim 4, wherein: a pull rod (41) is fixedly connected to the side end of the locking block (37), and a pull handle (42) is fixedly connected to the other end of the pull rod (41); the pull rod (41) is slidably connected inside the cavity (36) and the turntable (22).
6. The aeroengine steady state performance testing tool according to claim 5, wherein: the bottom of the workbench (1) is fixedly connected with supporting legs (6) and provided with a plurality of supporting legs; the end of the locking piece (37) is semi-arc-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321381918.6U CN220304822U (en) | 2023-06-01 | 2023-06-01 | Aeroengine steady state performance test fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321381918.6U CN220304822U (en) | 2023-06-01 | 2023-06-01 | Aeroengine steady state performance test fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220304822U true CN220304822U (en) | 2024-01-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321381918.6U Active CN220304822U (en) | 2023-06-01 | 2023-06-01 | Aeroengine steady state performance test fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220304822U (en) |
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2023
- 2023-06-01 CN CN202321381918.6U patent/CN220304822U/en active Active
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