CN215296706U - Sampling device for mechanical property sample of blade tenon of aero-engine - Google Patents
Sampling device for mechanical property sample of blade tenon of aero-engine Download PDFInfo
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- CN215296706U CN215296706U CN202121406138.3U CN202121406138U CN215296706U CN 215296706 U CN215296706 U CN 215296706U CN 202121406138 U CN202121406138 U CN 202121406138U CN 215296706 U CN215296706 U CN 215296706U
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- blade tenon
- shaft sleeve
- outer shaft
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Abstract
The utility model relates to the field of machining and special machining of aero-engine material performance samples, in particular to a sampling device for aero-engine blade tenon mechanical performance samples; comprises an outer shaft sleeve (3), a rotary chuck (2), a locking butterfly bolt (1) and a fastening screw (7); the utility model adopts the profiling design according to the blade groove of the device for sampling the mechanical property sample of the blade tenon, realizes the close fit with the blade tenon, ensures the stability of the sample size precision in the sampling process, and completes the sample processing of all the blade tenons of the compressor engine by adjusting the rotation angle of the rotary chuck and the outer shaft sleeve; the utility model discloses simplify operation process, saved traditional anchor clamps assemble time, improved the machining efficiency of aeroengine blade tenon at mechanical properties sample, simultaneously, reduced traditional isolated plant's consumptive material purchase, saved scientific research manufacturing cost.
Description
Technical Field
The utility model relates to an aeroengine material performance sample machining and special type processing field especially relate to a sampling device for aeroengine blade tenon mechanical properties sample.
Background
The compressor blade is the most centralized key core part in the aero-engine, and is tightly assembled and connected with a mortise on a compressor disc through a tenon, more than sixteen thousand revolutions per minute are needed, more than six hundred working blades are provided, the stage pressurization and the stage temperature rise are needed, the harsh requirements of high speed, high temperature, high pressure, high load and high reliability are met, and various subjects such as theories, aerodynamics, materials, special processes and the like are needed to be integrated. Before a certain type of engine is put into operation for formal pilot run, important mechanical property test data in materials science need to be developed, the stability and the reliability of the mechanical property test data of the blade tenon are the basis for accumulating the data of the mechanical property test research curve of the engine, and the processing efficiency and the quality of a sample are important guarantees of the data reliability. Because the aero-engine is designed with weight requirements, the aero-engine is produced by integral precision castings, the machining allowance is extremely small, when an aero-engine blade tenon mechanical property sample with extremely complicated part shape is sampled, the machining allowance is extremely small, clamping and machining are extremely difficult, the working efficiency is low, the sample sampling qualification rate is low, and the requirement for sampling the blade tenon mechanical property samples in a large batch cannot be met.
Disclosure of Invention
The utility model aims to solve the above problem, the utility model discloses a universal device that is used for aeroengine blade tenon mechanical properties sample to take a sample, under this utility model device's effect, can quick clamping, accurate alignment part shape comparatively complicated aeroengine blade tenon mechanical properties sample's sample processing to obtain higher work efficiency and qualification rate.
The purpose of the utility model is realized through the following technical scheme: a sampling device for mechanical property samples of blade tenons of aero-engines comprises an outer shaft sleeve, a rotary chuck, a locking butterfly bolt and a fastening screw; the outer shaft sleeve is provided with a through hole on the upper end face, the rotary chuck is of a stepped shaft structure, the upper end of the rotary chuck is arranged in the through hole of the outer shaft sleeve, the lower end of the rotary chuck is provided with a positioning clamping groove, one side of the positioning clamping groove is provided with an elastic clamping piece, the elastic clamping piece and the rotary chuck are of an integrated structure, the outer shaft sleeve and the rotary chuck are fastened by the fastening screw, and the blade tenon is fixed in the positioning clamping groove by the locking butterfly bolt through the elastic clamping piece.
The elastic clamping piece is one part of the rotary chuck and comprises a thin wall part and a thick wall part, the length of the thick wall part is the same as that of the positioning clamping groove, the length of the thin wall part is greater than 1/2 of the length of the thick wall part, U-shaped grooves are formed in two sides of the thin wall part, and the width of each U-shaped groove is greater than or equal to 2 mm. (the thin wall part is beneficial to adjusting the width of the positioning clamping groove, and the thick wall part is beneficial to clamping the side surface of the blade tenon in a uniform stress manner.)
The positioning clamping groove is a stepped groove, and the shape of the positioning clamping groove is consistent with that of the blade tenon.
The stepped hole of the rotary chuck is in transition fit with the excircle of the outer shaft sleeve and can rotate around the outer shaft sleeve.
Two clamping reference plane surfaces parallel to the vice jaw are arranged on two sides of the outer shaft sleeve.
The circumference of the lower end of the outer shaft sleeve is provided with a positioning scale mark a, the upper end surface of the rotary chuck is provided with a positioning scale mark b, and the positioning scale mark a and the positioning scale mark b are used for adjusting the positioning of the rotary chuck and the outer shaft sleeve.
The length of the upper end of the rotary chuck is not higher than the upper surface of the outer shaft sleeve.
The utility model has the advantages of it is following:
(1) the utility model discloses device blade draw-in groove according to sample of blade tenon mechanical properties sample adopts the profile modeling design, has realized closely cooperating with the blade tenon, has guaranteed sample size precision's in the sample process stability, the utility model relates to a make simple, the device that the structure is good, once only drops into, permanent use.
(2) The utility model discloses application scope is wide, through the rotation angle of the rotatory chuck of adjustment and outer axle sleeve to the sample processingequipment of all blade tenons of compressor engine is accomplished in accurate quick location.
(3) The utility model discloses simplify operation process, saved traditional anchor clamps assemble time, improved the machining efficiency of aeroengine blade tenon at mechanical properties sample, simultaneously, reduced traditional isolated plant's consumptive material purchase, saved scientific research manufacturing cost.
Drawings
Fig. 1 is a schematic structural diagram of the present invention;
FIG. 2 is a schematic view of the blade clamping of the present invention;
FIG. 3 is a schematic view of a blade clamping slot of the present invention;
in the figure: the method comprises the following steps of 1-locking a butterfly bolt, 2-rotating a chuck, 3-an outer shaft sleeve, 4-a vice clamping reference plane, 5-an exhaust hole, 6-a positioning scale line, 7-a fastening screw, 8-an elastic clamping sheet and 9-a positioning clamping groove.
Detailed Description
The following description is further made for the structural principle and the working principle of the present invention with reference to the accompanying drawings, but the scope of protection of the present invention is not limited to the embodiments.
As shown in fig. 1 to 3, a sampling device for mechanical property samples of blade tenons of aero-engines comprises an outer shaft sleeve 3, a rotary chuck 2, a locking butterfly bolt 1 and a fastening screw 7; through-hole 5 is established to 3 up end of outer axle sleeve, rotary chuck 2 is the step axle structure, and in the through-hole 5 of outer axle sleeve 3 was packed into to the upper end, the lower extreme was equipped with positioning groove 9, positioning groove 9 be the ladder groove, the shape is unanimous with the blade tenon shape.
An elastic clamping piece 8 is arranged on one side of the positioning clamping groove 9, the elastic clamping piece 8 and the rotary chuck 2 are of an integral structure, the outer shaft sleeve 3 and the rotary chuck 2 are fastened by the fastening screw 7, and the blade tenon is fixed in the positioning clamping groove 9 by the locking butterfly bolt 1 through clamping the elastic clamping piece 8; the stepped hole of the rotary chuck 2 is in transition fit with the excircle of the outer shaft sleeve 3 and can rotate around the outer shaft sleeve 3; two clamping reference plane surfaces 4 parallel to the vice jaw are arranged on two sides of the outer shaft sleeve 3; the circumferential surface of the lower end of the outer shaft sleeve 3 is provided with a positioning scale mark a6, the upper end surface of the rotary chuck 2 is provided with a positioning scale mark b10, and the positioning scale mark a6 and the positioning scale mark b10 are used for adjusting the positioning of the rotary chuck 2 and the outer shaft sleeve 3; the length of the upper end of the rotary chuck 2 is not higher than the upper surface of the outer shaft sleeve 3.
The elastic clamping piece 8 is one part of the rotary chuck 2 and comprises a thin wall part and a thick wall part, the length of the thick wall part is the same as that of the positioning clamping groove 9, the length of the thin wall part is greater than 1/2 of the length of the thick wall part, U-shaped grooves are formed in two sides of the thin wall part, and the width of each U-shaped groove is greater than or equal to 2 mm. The thin wall part is beneficial to adjusting the width of the positioning clamping groove 9, and the thick wall part is beneficial to uniformly stressing and clamping the side surface of the blade tenon.
The working process of the utility model is as follows: handle according to corresponding order the utility model discloses a device that is used for aeroengine tenon mechanical properties sample to take a sample, the combination assembles together, 2 transition fit of rotatory chuck in outer axle sleeve 3, find accurate rotatory chuck 2 and the corresponding scale mark 6 locking screw 7 in the 3 outsides of outer axle sleeve, 3 clamping of outer axle sleeve on the parallel jaw vice, make spark-erosion wire cutting machine bed molybdenum filament parallel with 9 both sides limits of quick constant head tank, it pushes away positioning channel 9 positions to put into the blade tenon, 8 tight blade tenons of tight cushion of rotatory locking spiral bolt 1 extrusion clamp are fixed with it. The device is clamped on a parallel jaw vice, and can be quickly positioned according to the corresponding position of the device, so that the operation process is simplified, the assembly time of the traditional clamp is saved, long-time waiting is not needed, the processing utilization rate of the wire cut electric discharge machine is effectively improved, and the sampling time of cutting mechanical property samples by the blade tenon of the aero-engine is shortened. The processing efficiency of sampling the mechanical property sample of the blade tenon of the aero-engine is improved, and the time period of the mechanical property test data of the blade tenon of the aero-engine is obviously shortened.
The above description is only for the preferred embodiments of the present invention, and is not intended to limit the present invention in any way. The person skilled in the art can, without departing from the scope of the invention, utilize the above-mentioned technical content to make numerous possible variations and modifications to the patented technical solution of the invention, or to modify equivalent embodiments with equivalent variations. Therefore, any modification, equivalent change and modification made by the above implementation according to the technology of the present invention all belong to the protection scope of the present invention.
Claims (7)
1. The utility model provides a sampling device that is used for mechanical properties sample of aeroengine blade tenon which characterized in that: comprises an outer shaft sleeve (3), a rotary chuck (2), a locking butterfly bolt (1) and a fastening screw (7); through-hole (5) are established to outer axle sleeve (3) up end, rotatory chuck (2) are step axle structure, and in through-hole (5) of outer axle sleeve (3) were packed into to the upper end, the lower extreme was equipped with positioning groove (9), and positioning groove (9) one side is equipped with elasticity and presss from both sides tight piece (8), and elasticity presss from both sides tight piece (8) and rotatory chuck (2) structure as an organic whole, fastening screw (7) fasten outer axle sleeve (3) and rotatory chuck (2), locking butterfly bolt (1) is fixed the blade tenon in positioning groove (9) through pressing from both sides tight elasticity and pressing from both sides tight piece (8).
2. The sampling device for the mechanical property sample of the blade tenon of the aeroengine according to claim 1, wherein: the elastic clamping piece (8) is one part of the rotary chuck (2) and comprises a thin wall part and a thick wall part, the length of the thick wall part is the same as that of the positioning clamping groove (9), the length of the thin wall part is greater than 1/2 of the length of the thick wall part, two sides of the thin wall part are U-shaped grooves, and the width of each U-shaped groove is greater than or equal to 2 mm.
3. The sampling device for the mechanical property sample of the blade tenon of the aeroengine according to claim 1, wherein: the positioning clamping groove (9) is a stepped groove, and the shape of the positioning clamping groove is consistent with that of the blade tenon.
4. The sampling device for the mechanical property sample of the blade tenon of the aeroengine according to claim 1, wherein: the stepped hole of the rotary chuck (2) is in transition fit with the excircle of the outer shaft sleeve (3) and can rotate around the outer shaft sleeve (3).
5. The sampling device for the mechanical property sample of the blade tenon of the aeroengine according to claim 1, wherein: two clamping reference plane surfaces (4) parallel to the vice jaw are arranged on two sides of the outer shaft sleeve (3).
6. The sampling device for the mechanical property sample of the blade tenon of the aeroengine according to claim 1, wherein: the circumferential surface of the lower end of the outer shaft sleeve (3) is provided with positioning scale marks a (6), and the upper end surface of the rotary chuck (2) is provided with positioning scale marks b (10).
7. The sampling device for the mechanical property sample of the blade tenon of the aeroengine according to claim 1, wherein: the length of the upper end of the rotary chuck (2) is not higher than the upper surface of the outer shaft sleeve (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121406138.3U CN215296706U (en) | 2021-06-23 | 2021-06-23 | Sampling device for mechanical property sample of blade tenon of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121406138.3U CN215296706U (en) | 2021-06-23 | 2021-06-23 | Sampling device for mechanical property sample of blade tenon of aero-engine |
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| Publication Number | Publication Date |
|---|---|
| CN215296706U true CN215296706U (en) | 2021-12-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121406138.3U Active CN215296706U (en) | 2021-06-23 | 2021-06-23 | Sampling device for mechanical property sample of blade tenon of aero-engine |
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| CN (1) | CN215296706U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114670134A (en) * | 2022-04-18 | 2022-06-28 | 中国航发沈阳发动机研究所 | Aeroengine turbine guide blade sampling clamp |
-
2021
- 2021-06-23 CN CN202121406138.3U patent/CN215296706U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114670134A (en) * | 2022-04-18 | 2022-06-28 | 中国航发沈阳发动机研究所 | Aeroengine turbine guide blade sampling clamp |
| CN114670134B (en) * | 2022-04-18 | 2023-06-02 | 中国航发沈阳发动机研究所 | Aeroengine turbine guide vane sampling clamp |
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