CN220322938U - Aeroengine blade strength detection device - Google Patents
Aeroengine blade strength detection device Download PDFInfo
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- CN220322938U CN220322938U CN202323308821.5U CN202323308821U CN220322938U CN 220322938 U CN220322938 U CN 220322938U CN 202323308821 U CN202323308821 U CN 202323308821U CN 220322938 U CN220322938 U CN 220322938U
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- 238000001514 detection method Methods 0.000 title claims abstract description 42
- 230000007246 mechanism Effects 0.000 claims abstract description 14
- 230000000149 penetrating effect Effects 0.000 claims 1
- 230000006978 adaptation Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005012 migration Effects 0.000 description 1
- 238000013508 migration Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses an aero-engine blade strength detection device, and relates to the technical field of aero-engines. Including the base platform, be fixed with the arch platform on the base platform, be provided with detection mechanism on the arch platform, the standing groove has been seted up at base platform middle part, and the standing groove top is fixed with places the platform, is provided with the clamping assembly in the standing groove, and the clamping assembly is including setting up the first screw rod of lower part position in the standing groove, and first screw rod level transversely sets up, and first screw rod both ends all rotate the cover and are equipped with first riser, and first riser is fixed mutually with the standing groove tank bottom. According to the utility model, through the arrangement of the detection mechanism and the clamping assembly, the clamping assembly clamps and positions the blades to a certain extent from multiple directions during detection operation, the positions of the blades on the placing table are kept fixed, and the detection mechanism is controlled to perform detection operation, so that the condition that the blades are easy to displace is avoided, and the detection use of the device is ensured to a certain extent.
Description
Technical Field
The utility model relates to the technical field of aero-engines, in particular to an aero-engine blade strength detection device.
Background
An aeroengine is a highly complex and precise thermodynamic machine, and an aeroengine blade is an indispensable part for an aeroengine, so that it is particularly important for the detection of the aeroengine blade.
The prior device for detecting the strength of the blade of the aeroengine (authorized bulletin number: CN 216847269U) has the following defects: according to the device, the laser irradiation lamp in the mounting groove is turned on, the motor is started, the position of the pressing plate is regulated, the laser irradiation lamp irradiates all parts of the engine blade, the effect of detecting all parts of the engine blade is achieved, and the working efficiency is effectively improved.
Disclosure of Invention
The utility model aims to provide an aeroengine blade strength detection device which is used for solving the problems in the background technology.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides an aeroengine blade intensity detection device, including the base platform, be fixed with the arch platform on the base platform, be provided with detection mechanism on the arch platform, the standing groove has been seted up at the base platform middle part, the standing groove top is fixed with the standing platform, be provided with the clamping assembly in the standing groove, the clamping assembly is including setting up the first screw rod of lower part position in the standing groove, first screw rod level transversely sets up, first screw rod both ends all rotate the cover and are equipped with first riser, first riser is fixed mutually with the standing groove tank bottom, fixed cover is equipped with first turbine on the first screw rod, symmetrical cover is equipped with first grip block on the first screw rod, first screw rod top is provided with the second screw rod, the second screw rod level is vertical to be set up, the cover is equipped with the second riser all rotated at second screw rod both ends, the second riser is fixed mutually with the standing groove tank bottom, symmetrical cover is equipped with the second grip block on the second screw rod, fixed cover is equipped with the second turbine on the second screw rod.
Preferably, one side of the first turbine and one side of the second turbine are engaged with a worm, the worm is vertically arranged, the worm is rotationally inserted into the bottom of the placing groove, the top end of the worm is connected with a micro motor, and the micro motor is arranged on the bottom surface of the placing table.
Preferably, the first clamping plates symmetrically arranged on the first screw are internally provided with thread grooves which are matched with the external threads of the first screw and have the same and opposite directions, and the second clamping plates symmetrically arranged on the second screw are internally provided with thread grooves which are matched with the external threads of the second screw and have the opposite and same directions.
Preferably, the first clamping plate and the second clamping plate penetrate through and are arranged on the placing table, and a limiting hole matched with the first clamping plate and the second clamping plate is formed in the placing table and used for limiting movement of the first clamping plate and the second clamping plate.
Preferably, the detection mechanism comprises a moving block horizontally and transversely arranged on a transverse table of the arch-shaped table in a sliding mode, one side of the moving block is connected with an electric telescopic rod for driving the moving block to horizontally move, an arch-shaped plate is fixed on the bottom surface of the moving block, and the transverse plate of the arch-shaped plate is horizontally and vertically arranged.
Preferably, a screw rod is inserted between the two vertical plates of the arch plate in a rotating way, one end of the screw rod is connected with a rotating motor, a sliding block is arranged on the screw rod in an adapting way, through grooves matched with the sliding block are formed in the arch plate, a plurality of hydraulic rods are arranged on the bottom surface of the sliding block at equal intervals, and a detection pressing plate is arranged at the bottom end of the hydraulic rod.
Compared with the prior art, the utility model has the beneficial effects that:
this aeroengine blade intensity detection device, through the setting of detection mechanism and clamping assembly, when detecting the operation, the clamping assembly carries out certain centre gripping location to the blade from a plurality of directions, keeps the blade to place the fixed in position of bench, control detection mechanism detect the operation can to avoided the condition that the blade easily takes place the displacement, guaranteed the detection of device to a certain extent and used.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a first cross-sectional view of the present utility model;
FIG. 3 is a second cross-sectional view of the present utility model;
fig. 4 is a schematic perspective view of the base table and the clamping assembly of the present utility model.
In the figure: 1. a base table; 2. a placement table; 201. a first screw; 202. a first turbine; 203. a first clamping plate; 204. a second screw; 205. a second turbine; 206. a second clamping plate; 207. a worm; 208. a limiting hole; 3. an arch table; 301. a moving block; 302. an electric telescopic rod; 303. a arch plate; 304. a screw rod; 305. a sliding block; 306. a hydraulic rod; 307. and detecting the pressing plate.
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.
In the process of detecting the aeroengine blade, the intensity detection device is needed, the device provided by the utility model is specially used for clamping blades with different specifications and sizes, so that the follow-up detection operation is convenient, and in the process of using the device, the device is needed to carry out preparation work such as checking in advance, so that the normal operation of the device is ensured.
As shown in fig. 1 to 4, the present utility model provides a technical solution: the utility model provides an aeroengine blade intensity detection device, including base platform 1, be fixed with arch platform 3 on the base platform 1, be provided with detection mechanism on the arch platform 3, the standing groove has been seted up at base platform 1 middle part, the standing groove top is fixed with places platform 2, be provided with clamping assembly in the standing groove, clamping assembly is including setting up the first screw 201 of lower part position in the standing groove, first screw 201 level transversely sets up, first screw 201 both ends all rotate the cover and are equipped with first riser, first riser is fixed mutually with the standing groove tank bottom, fixed cover is equipped with first turbine 202 on the first screw 201, the symmetry cover is equipped with first grip block 203 on the first screw 201, first screw 201 top is provided with second screw 204, second screw 204 level vertically sets up, second screw 204 both ends all rotate the cover and are equipped with the second riser, the second riser is fixed mutually with the standing groove tank bottom, the symmetry cover is equipped with second turbine 205 on the second screw 204, wherein, base platform 1 four corners is fixed with the supporting leg for supporting the device.
In the embodiment, one side of the first turbine 202 and one side of the second turbine 205 are engaged with a worm 207, the worm 207 is vertically arranged, the worm 207 is rotationally inserted into the bottom of the placing groove, the top end of the worm 207 is connected with a micro motor, the micro motor is installed on the bottom surface of the placing table 2, thread grooves which are matched with the external threads of the first screw 201 and have the same and opposite directions are formed in the first clamping plate 203 which is symmetrically arranged on the first screw 201, thread grooves which are matched with the external threads of the second screw 204 and have the opposite and same directions are formed in the second clamping plate 206 which is symmetrically arranged on the second screw 204, the first clamping plate 203 and the second clamping plate 206 penetrate through the placing table 2, a limiting hole 208 which is matched with the first clamping plate 203 and the second clamping plate 206 is formed in the placing table 2 and used for limiting the movement of the first clamping plate 203 and the second clamping plate 206, wherein the micro motor has a self-locking function, and the micro motor is driven to drive the first clamping plate 203 and the second clamping plate 206 to be respectively close to each other or far away from each other when being started.
In the embodiment, detection mechanism includes horizontal sliding setting up the movable block 301 on the horizontal platform of arch platform 3, movable block 301 one side is connected with electric telescopic handle 302, be provided with vertical piece on the arch platform 3, electric telescopic handle 302 one end is connected with vertical piece, be used for driving movable block 301 and carry out horizontal migration, the movable block 301 bottom surface is fixed with arch plate 303, the horizontal vertical setting of diaphragm level of arch plate 303, it is equipped with spiral shell stick 304 to rotate between the two risers of arch plate 303, spiral shell stick 304 one end is connected with the rotating electrical machines, the adaptation is equipped with slider 305 on the spiral shell stick 304, the logical groove with slider 305 looks adaptation has been seted up on the arch plate 303, slider 305 bottom surface equidistance is provided with a plurality of hydraulic levers 306, the hydraulic lever 306 bottom is provided with detection clamp plate 307, through the setting of detection mechanism and clamping assembly, during the detection operation, the clamping assembly carries out certain centre gripping location to the blade from a plurality of directions, keep the blade fixed in the position of placing bench 2, the detection operation can be carried out to control detection mechanism, thereby the condition that the blade is easy to take place the displacement, the detection of the device has been guaranteed to a certain extent, wherein the bottom surface of the device is used for detecting, the blade is provided with the optical transmitter 305, the hydraulic transmitter is used for detecting, the intensity is used for detecting to the clamp plate 307.
Working principle: when the device is used, the blade to be detected is placed on the placing table 2, the micro motor is controlled to start, the micro motor drives the worm 207 to rotate, so that the worm 207 synchronously drives the first turbine 202 and the second turbine 205 to rotate, the first turbine 202 rotates to enable the first screw 201 to rotate, the first clamping plates 203 are close to each other for operation, the second turbine 205 rotates to enable the second screw 204 to rotate, the second clamping plates 206 are close to each other for operation, the first clamping plates 203 and the second clamping plates 206 clamp and fix the blade, the detection mechanism is controlled to start, and detection operation is carried out.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made hereto without departing from the spirit and scope of the utility model as defined by the appended embodiments and equivalents thereof.
Claims (6)
1. The utility model provides an aeroengine blade intensity detection device, includes base platform (1), its characterized in that: be fixed with arch platform (3) on base platform (1), be provided with detection mechanism on arch platform (3), standing groove has been seted up at base platform (1) middle part, the standing groove top is fixed with places platform (2), be provided with clamping assembly in the standing groove, clamping assembly is including setting up first screw rod (201) of lower part position in the standing groove, first screw rod (201) level transversely sets up, first screw rod (201) both ends all rotate the cover and are equipped with first riser, first riser is fixed with the standing groove tank bottom mutually, fixed cover is equipped with first turbine (202) on first screw rod (201), symmetrical cover is equipped with first grip block (203) on first screw rod (201), first screw rod (201) top is provided with second screw rod (204), second screw rod (204) level vertical setting, second screw rod (204) both ends all rotate the cover and are equipped with the second riser, second riser and standing groove tank bottom is fixed, the symmetry cover is equipped with second grip block (206) on second screw rod (204) is equipped with second turbine (205).
2. An aircraft engine blade strength detection device according to claim 1, wherein: one side of the first turbine (202) and one side of the second turbine (205) are engaged with a worm (207), the worm (207) is vertically arranged, the worm (207) is rotationally inserted into the bottom of the placing groove, the top end of the worm (207) is connected with a micro motor, and the micro motor is arranged on the bottom surface of the placing table (2).
3. An aircraft engine blade strength detection device according to claim 1, wherein: the first clamping plates (203) symmetrically arranged on the first screw (201) are internally provided with thread grooves which are matched with the external threads of the first screw (201) and have the same and opposite directions, and the second clamping plates (206) symmetrically arranged on the second screw (204) are internally provided with thread grooves which are matched with the external threads of the second screw (204) and have the opposite and same directions.
4. An aircraft engine blade strength detection device according to claim 1, wherein: the first clamping plate (203) and the second clamping plate (206) are arranged on the placing table (2) in a penetrating mode, and limiting holes (208) matched with the first clamping plate (203) and the second clamping plate (206) are formed in the placing table (2) and used for limiting movement of the first clamping plate (203) and the second clamping plate (206).
5. An aircraft engine blade strength detection device according to claim 1, wherein: the detection mechanism comprises a moving block (301) horizontally and transversely arranged on a transverse platform of the arch-shaped platform (3) in a sliding mode, one side of the moving block (301) is connected with an electric telescopic rod (302) for driving the moving block (301) to horizontally move, an arch-shaped plate (303) is fixed on the bottom surface of the moving block (301), and the transverse plate of the arch-shaped plate (303) is horizontally and vertically arranged.
6. The aircraft engine blade strength detection device according to claim 5, wherein: screw rods (304) are inserted between two vertical plates of the arch-shaped plate (303) in a rotating mode, one ends of the screw rods (304) are connected with rotating motors, sliding blocks (305) are arranged on the screw rods (304) in an adapting mode, through grooves matched with the sliding blocks (305) are formed in the arch-shaped plate (303), a plurality of hydraulic rods (306) are arranged on the bottom surface of the sliding blocks (305) at equal intervals, and detection pressing plates (307) are arranged at the bottom ends of the hydraulic rods (306).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323308821.5U CN220322938U (en) | 2023-12-06 | 2023-12-06 | Aeroengine blade strength detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323308821.5U CN220322938U (en) | 2023-12-06 | 2023-12-06 | Aeroengine blade strength detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220322938U true CN220322938U (en) | 2024-01-09 |
Family
ID=89416651
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323308821.5U Active CN220322938U (en) | 2023-12-06 | 2023-12-06 | Aeroengine blade strength detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220322938U (en) |
-
2023
- 2023-12-06 CN CN202323308821.5U patent/CN220322938U/en active Active
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