CN210464286U - Detection tool for detecting blade shape of aero-engine blade - Google Patents
Detection tool for detecting blade shape of aero-engine blade Download PDFInfo
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- CN210464286U CN210464286U CN201921896168.XU CN201921896168U CN210464286U CN 210464286 U CN210464286 U CN 210464286U CN 201921896168 U CN201921896168 U CN 201921896168U CN 210464286 U CN210464286 U CN 210464286U
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Abstract
The utility model discloses a detect frock for aeroengine blade leaf shape detects, fixed standard plate, blade locating piece and standard plate locating piece are fixed mounting respectively on the bottom plate, the blade locating piece is located the position that is close to its one end on the bottom plate, two at least fixed standard plates are located the first side on the bottom plate, two at least standard plate locating pieces are located the second side on the bottom plate, two at least activity standard plate movable mounting are in the second side on the bottom plate and through the standard plate locating piece location of one-to-one, the standard shape and the size that correspond the position on fixed standard plate and the activity standard plate one-to-one and the space between the two are regional and the aeroengine blade are unanimous completely. The utility model discloses can detect the accurate location of aeroengine blade, again can quick assembly disassembly, have that investment cost is low, easy operation, commonality are good, detect the characteristics that the precision is high, the practicality is strong, and the practicality is extremely strong, and the facilitate promotion is used.
Description
Technical Field
The utility model relates to an aviation part detects the frock, especially relates to a detect frock that is used for aeroengine blade leaf shape to detect.
Background
Various aero-engine blades are typical free-form surface parts, and due to the characteristics of complex blade shape structure design, high machining precision and the like, the blades cannot be machined by traditional equipment during manufacturing, and four-axis equipment, five-axis equipment and other equipment are required to be used for machining with various tools.
The machining is only one difficulty in manufacturing the blade, and the other difficulty is whether the machined geometric dimension and geometric tolerance meet the design verification scheme.
Because the blade shape structure of the blade of the aircraft engine is complex, the traditional detection equipment cannot complete detection, the most adopted scheme at present is to use three coordinates matched with a special blade detection module and an auxiliary detection clamp for detection, and an automatic scanning measuring head is adopted for scanning and then is compared with a theoretical model, so that a detection result is obtained. However, the prior preparation work of the traditional detection method is complex and long in time consumption, the equipment investment is direct and huge in cost, the requirement on the level of a three-coordinate detector is extremely high, an operator cannot perform self-detection in time, and the small processing enterprises with low production capacity cannot bear the relevant time and capital cost.
For example, the following steps are carried out: such a part is shown as a turbine blade for an aircraft engine. The performance of the engine is highly dependent on the design and level of manufacture of the blade profile. An aircraft engine blade is a typical free-form part whose curve shape, manufacturing accuracy and quality directly determine the magnitude of the propulsion efficiency and safety of the engine.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a detection frock that is used for aeroengine blade leaf shape to detect specially in order to solve above-mentioned problem.
The utility model discloses a following technical scheme realizes above-mentioned purpose:
a detection tool for detecting blade shape of an aircraft engine blade comprises a transverse bottom plate, a vertical fixed standard plate, a blade positioning block, a standard plate positioning block and a vertical movable standard plate, the fixed standard plates, the blade positioning blocks and the standard plate positioning blocks are respectively fixedly arranged on the bottom plate, one or more blade positioning blocks are positioned on the bottom plate near one end of the bottom plate and are used for positioning one end of the blade of the aircraft engine, at least two fixed standard plates are positioned on a first side of the bottom plate and are arranged in parallel, at least two standard plate positioning blocks are positioned on a second side of the bottom plate opposite to the first side of the bottom plate and are arranged in parallel, at least two movable standard plates are movably arranged on the second side of the bottom plate and are positioned through the standard plate positioning blocks which are in one-to-one correspondence, the shapes and the sizes of the surfaces of the sides, close to each other, of the fixed standard plate and the movable standard plate meet the following requirements: the fixed standard plate and the movable standard plate are in one-to-one correspondence, and the gap area between the fixed standard plate and the movable standard plate is completely consistent with the standard shape and size of the corresponding position on the aero-engine blade.
Preferably, in order to meet the detection requirement and reduce the cost, the two blade positioning blocks are provided, the surfaces of the two blade positioning blocks, which are in contact with one end of the aircraft engine blade, are completely consistent with the standard shapes and sizes of the corresponding positions on the aircraft engine blade, and the number of the fixed standard plates, the number of the standard plate positioning blocks and the number of the movable standard plates are three.
Furthermore, in order to facilitate the rapid assembly and disassembly of the movable standard plate, the lower end of the movable standard plate is provided with an L-shaped notch matched with the corresponding position of the bottom plate.
The beneficial effects of the utility model reside in that:
the utility model discloses based on the design theory of carrying out standardized detection to the important position cross-section outline of aeroengine blade, utilize bottom plate, fixed standard plate, blade locating piece, standard plate locating piece and activity standard plate to form can be to the accurate location detection of aeroengine blade, can quick assembly disassembly's quick detection structure again, have investment cost low, easy operation, the commonality is good, detect the characteristics that the precision is high, the practicality is strong, convenient to popularize and apply; in actual use, whether the blade shape of the aero-engine blade is qualified or not can be detected only by placing the aero-engine blade to be detected on the bottom plate and accurately positioning the aero-engine blade, and then testing whether the clearance between the aero-engine blade and the fixed standard plate or the movable standard plate can be placed by using the feeler gauge in the standard error thickness. Through verification, the detection result of the detection tool is identical with the three-coordinate detection result, and the practicability is strong.
Drawings
FIG. 1 is a schematic view of the three-dimensional structure of the detection tool for detecting the blade profile of the blade of the aircraft engine according to the present invention after the movable standard block is removed;
FIG. 2 is a schematic perspective view of the detection tool for detecting blade profile of an aircraft engine according to the present invention;
fig. 3 is a three-dimensional structure schematic diagram when being used for the detection frock that aeroengine blade leaf shape detected.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings:
as shown in the figures 1 and 2, the detection tool for detecting the blade profile of the blade of the aircraft engine comprises a transverse bottom plate 2, a vertical fixed standard plate, a blade positioning block, a standard plate positioning block and a vertical movable standard plate, wherein the fixed standard plate is fixedly arranged on the bottom plate 2 respectively, the fixed standard plate comprises a first fixed standard plate 5, a second fixed standard plate 7 and a third fixed standard plate 9, the blade positioning block comprises a first blade positioning block 1 and a second blade positioning block 4, the standard plate positioning block comprises a first standard plate positioning block 3, a second standard plate positioning block 6 and a third standard plate positioning block 8, the movable standard plate comprises a first movable standard plate 10, a second movable standard plate 11 and a third movable standard plate 12, and the first blade positioning block 1 and the second blade positioning block 4 are positioned on the bottom plate 2 and are close to one end of the first blade positioning block and are used for aligning the aircraft engine One end of an engine blade (see an aircraft engine blade 13 in fig. 3) is positioned, the surfaces of a first blade positioning block 1 and a second blade positioning block 4, which are contacted with one end of the aircraft engine blade (see the aircraft engine blade 13 in fig. 3), are completely consistent with the standard shapes and sizes of corresponding positions on the aircraft engine blade (see the aircraft engine blade 13 in fig. 3), a first fixed standard plate 5, a second fixed standard plate 7 and a third fixed standard plate 9 are positioned on a first side of a base plate 2 and are arranged in parallel, a first standard plate positioning block 3, a second standard plate positioning block 6 and a third standard plate positioning block 8 are positioned on a second side of the base plate 2, which is opposite to the first side, and are arranged in parallel, a first movable standard plate 10, a second movable standard plate 11 and a third movable standard plate 12 are movably arranged on the second side of the base plate 2 and respectively pass through the first standard plate positioning blocks 3, which are in one-to, The second standard plate positioning block 6 and the third standard plate positioning block 8 are positioned, and the shapes and the sizes of the surfaces of the sides, close to each other, of the fixed standard plate and the movable standard plate meet the following requirements: the first fixed standard plate 5, the second fixed standard plate 7 and the third fixed standard plate 9 correspond to the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12 one by one, and the gap area between the first fixed standard plate and the third movable standard plate is completely consistent with the standard shape and size of the corresponding position on the aero-engine blade (see the aero-engine blade 13 of fig. 3), and the lower ends of the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12 are respectively provided with an 'L' -shaped notch matched with the corresponding position on the bottom plate 2, so that the rapid installation is facilitated. It should be noted that the number of the positioning blocks and the standard blocks may be more, and is determined according to actual needs.
In order to realize accurate detection, when the tool is processed, the position sizes of the first blade positioning block 1, the second blade positioning block 4, the first fixed standard plate 5, the second fixed standard plate 7 and the third fixed standard plate 9 need to be accurately controlled, and the dimensional tolerance among the first blade positioning block, the second blade positioning block, the first fixed standard plate 5, the second fixed standard plate 7 and the third fixed standard plate 9 is controlled within +/-0.01 mm, so that the measured section and the theoretical section on the tool can be ensured to be at the same position; the second blade positioning block 4 is used for limiting the arrangement position and the angle of the aero-engine blade 13, so that during machining, the inclined plane angle of the second blade positioning block 4 needs to be controlled within +/-1', and meanwhile, the inner arc line positions and the radian of the first fixed standard plate 5, the second fixed standard plate 7 and the third fixed standard plate 9 need to be accurately calculated and controlled; for three fixed standard blocks and three movable standard blocks, the following control needs to be carried out during processing: the contour of the contact surface with a product must accord with a theoretical contour, the thickness of a standard block is 5mm, the tolerance must be controlled within +/-0.01 mm, the contour tip part of the standard block is 0.4mm, chamfers on the left side and the right side must be symmetrical, the error is controlled within +/-0.02 mm, the contour conformity must be detected by three coordinates before the contour tip part of the standard block is processed, and the processing and detecting sequence cannot be reversed.
As shown in fig. 1 to 3, in use, first, the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12 are taken down, the aero-engine blade 13 to be detected is placed on the base plate 2, and is primarily positioned by the base plate 2, the first blade positioning block 1, the second blade positioning block 4, the first fixed standard plate 5, the second fixed standard plate 7, the third fixed standard plate 9, the first standard plate positioning block 3, the second standard plate positioning block 6 and the third standard plate positioning block 8, so that the aero-engine blade 13 is as close as possible to the first blade positioning block 1, the second blade positioning block 4, the first fixed standard plate 5, the second fixed standard plate 7 and the third fixed standard plate 9; then, correspondingly placing the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12 beside the first standard plate positioning block 3, the second standard plate positioning block 6 and the third standard plate positioning block 8 respectively and pushing the first movable standard plate, the second movable standard plate and the third movable standard plate tightly to enable the L-shaped notches to abut against corresponding positions of the bottom plate 2, and at the moment, completing the installation of the aero-engine blade 13, as shown in FIG. 3; sequentially using feelers with different thicknesses of 0.01mm, 0.02mm … and the like to detect gaps between each standard block and the aero-engine blade 13, wherein if the feeler with the thickness of 0.01mm can be plugged into the gap and the feeler with the thickness of 0.02mm cannot be plugged into the gap, the shape error is 0.01mm, and by analogy, the contour difference between the actual shape and the designed shape of the product can be detected, so that the actual leaf-shaped section of the aero-engine blade 13 is easily compared with the leaf-shaped section of the designed standard section, the difference value is visually measured, and the rapid detection is completed; in the detection process, the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12 can be pressed by hands to maintain the stable state, and another limit structure can be designed, which can be easily realized by adopting the conventional technology, for example, mounting grooves are arranged on the bottom plate 2 at the positions corresponding to the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12, the lower ends of the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12 are respectively arranged in the corresponding mounting grooves, clamping strips are arranged on the first standard plate positioning block 3, the second standard plate positioning block 6 and the third standard plate positioning block 8, and the clamping strips are used for clamping the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12 after being mounted in place so as to prevent the first movable standard plate 10, the second movable standard plate 11 and the third movable standard plate 12 from moving outwards, namely, the continuous positioning function of each movable standard plate is realized.
The above-mentioned embodiment is only the preferred embodiment of the present invention, and is not to the limitation of the technical solution of the present invention, as long as the technical solution can be realized on the basis of the above-mentioned embodiment without creative work, all should be regarded as falling into the protection scope of the right of the present invention.
Claims (3)
1. The utility model provides a detect frock for aeroengine blade leaf shape detects which characterized in that: comprises a transverse bottom plate, a vertical fixed standard plate, a blade positioning block, a standard plate positioning block and a vertical movable standard plate, the fixed standard plates, the blade positioning blocks and the standard plate positioning blocks are respectively fixedly arranged on the bottom plate, one or more blade positioning blocks are positioned on the bottom plate near one end of the bottom plate and are used for positioning one end of the blade of the aircraft engine, at least two fixed standard plates are positioned on a first side of the bottom plate and are arranged in parallel, at least two standard plate positioning blocks are positioned on a second side of the bottom plate opposite to the first side of the bottom plate and are arranged in parallel, at least two movable standard plates are movably arranged on the second side of the bottom plate and are positioned through the standard plate positioning blocks which are in one-to-one correspondence, the shapes and the sizes of the surfaces of the sides, close to each other, of the fixed standard plate and the movable standard plate meet the following requirements: the fixed standard plate and the movable standard plate are in one-to-one correspondence, and the gap area between the fixed standard plate and the movable standard plate is completely consistent with the standard shape and size of the corresponding position on the aero-engine blade.
2. The detection tool for detecting the blade profile of the aero-engine blade according to claim 1, wherein: the two blade positioning blocks are completely consistent with the standard shapes and sizes of the corresponding positions on the aero-engine blade on the surfaces, contacted with one end of the aero-engine blade, of the two blade positioning blocks, and the number of the fixed standard plates, the number of the standard plate positioning blocks and the number of the movable standard plates are three.
3. The detection tool for detecting the blade profile of the aero-engine blade according to claim 1 or 2, wherein: the lower end of the movable standard plate is provided with an L-shaped notch matched with the corresponding position of the bottom plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921896168.XU CN210464286U (en) | 2019-11-06 | 2019-11-06 | Detection tool for detecting blade shape of aero-engine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921896168.XU CN210464286U (en) | 2019-11-06 | 2019-11-06 | Detection tool for detecting blade shape of aero-engine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210464286U true CN210464286U (en) | 2020-05-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921896168.XU Active CN210464286U (en) | 2019-11-06 | 2019-11-06 | Detection tool for detecting blade shape of aero-engine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210464286U (en) |
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2019
- 2019-11-06 CN CN201921896168.XU patent/CN210464286U/en active Active
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