CN217251680U - Accurate correcting device for aero-engine blade - Google Patents
Accurate correcting device for aero-engine blade Download PDFInfo
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- CN217251680U CN217251680U CN202123187071.1U CN202123187071U CN217251680U CN 217251680 U CN217251680 U CN 217251680U CN 202123187071 U CN202123187071 U CN 202123187071U CN 217251680 U CN217251680 U CN 217251680U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model discloses a precise shape correcting device for an aircraft engine blade, which comprises a base, a blade fixing mechanism, a sliding shooting mechanism and a rotary distance measuring mechanism, wherein the blade fixing mechanism, the sliding shooting mechanism and the rotary distance measuring mechanism are positioned on the upper surface of the base; the middle part of the short edge at one side of the base is provided with a slot parallel to the long edge, the rotary distance measuring mechanism is positioned at the tail end of the slot, and the blade fixing mechanism and the sliding shooting mechanism are positioned at the same side of the slot; the rotary distance measuring mechanism comprises a base fixedly arranged on the upper surface of the base, a first spring plate is arranged on the side wall of the base opposite to one side of the slot, and a second spring plate is arranged on one side wall of the base parallel to the slot. The utility model discloses an aeroengine blade is with accurate school shape device structural design is reasonable, and easy operation can detect the radius of rotation size under the different positions department of blade rotation or the rotation state, through contrasting the purpose that realizes the accurate school shape of blade with the standard value, cooperates the position that shooting mechanism accuracy judgement blade defect position that slides, and the practicality is higher.
Description
Technical Field
The utility model relates to an aeroengine blade calibration technical field specifically is to relate to an aeroengine blade is with accurate school shape device.
Background
Aircraft engine blades are important components of the turbine section of a gas turbine engine, and the blades rotating at high speed are responsible for drawing high-temperature and high-pressure airflow into the combustor to maintain the operation of the engine. The importance of the aero-engine blade under the extreme severe conditions of high temperature and high complex stress is obvious that the inlet temperature of the advanced aero-engine can reach 1380 ℃, the thrust can reach 226KN, the aero-engine blade bears the action of aerodynamic force and centrifugal force, the tensile stress borne by the blade part reaches 140MPa, the tensile stress borne by the blade root part can reach 560MPa, the performance of the aero-engine is directly determined by the blade casting process of the future aero-engine, and the method is also an obvious mark of the national aero-industry level.
In order to ensure stable and long-term operation in extreme environments of high temperature and high pressure, turbine blades are often forged from high temperature alloys and are cooled in different ways, such as internal air flow cooling, boundary layer cooling, or thermal barrier coatings protecting the blades, to ensure operational reliability. In steam and gas turbine engines, metal fatigue of the blades is the leading cause of engine failure. Strong vibration or resonance can cause metal fatigue. Engineers often use friction dampers to reduce the damage these factors cause to the blades. In the production process of the blade, the precise shaping of the blade becomes one of the main contents of detection.
Patent CN113084445A discloses a blade profile correction adjusting mechanism of an aircraft engine, which comprises a clamping component for clamping a blade and a profile correction adjusting driving mechanism for promoting the clamping component to perform adjusting movement; the clamping assembly comprises two clamping blocks which are respectively clamped on the leaf back and the leaf basin of the blade, and the two clamping blocks are fixedly connected through a detachable structure; the correction adjusting driving mechanism comprises a linear driving mechanism for driving the clamping assembly to perform linear movement and a rotary driving mechanism for driving the clamping assembly to perform rotary swing. The shape correcting adjusting mechanism can correct all detection sections of the blade body of the blade in multiple dimensions, and is favorable for improving the qualification rate and the size uniformity of products. It lacks a real-time sizing view of the blade.
SUMMERY OF THE UTILITY MODEL
To the problem that exists, the utility model provides an aeroengine blade is with accurate school shape device.
The technical scheme of the utility model is that:
a precise shape correction device for an aircraft engine blade comprises a base, a blade fixing mechanism, a sliding shooting mechanism and a rotating distance measuring mechanism, wherein the blade fixing mechanism, the sliding shooting mechanism and the rotating distance measuring mechanism are positioned on the upper surface of the base;
the middle part of the short edge at one side of the base is provided with a slot parallel to the long edge, the rotary distance measuring mechanism is positioned at the tail end of the slot, and the blade fixing mechanism and the sliding shooting mechanism are positioned at the same side of the slot;
the blade fixing mechanism comprises a fixed seat fixedly arranged on the upper surface of the base, a first rotating motor fixedly arranged on the upper surface of the fixed seat and a second rotating motor arranged at the output end of the first rotating motor;
the sliding shooting mechanism comprises a sliding plate arranged on the upper surface of the base in a sliding mode, a lifting rod fixedly arranged on one end, far away from the open groove, of the upper surface of the sliding plate, a lifting block connected with the lifting rod in a sliding mode, and a 3D camera fixedly connected with the lifting block;
the rotary distance measuring mechanism comprises a base fixedly arranged on the upper surface of the base, a first spring plate is arranged on the side wall of one side of the groove opposite to the base, and a second spring plate is arranged on one side wall of the base, which is parallel to the groove.
Furthermore, an air speed measuring instrument is arranged on one side of the upper surface of the base, which is opposite to the blade fixing mechanism and the sliding shooting mechanism. The wind speed measuring device is used for measuring the wind speed generated by the high-speed rotation of the blade so as to judge the qualification degree of the blade.
Furthermore, the output end of the second rotating motor is provided with an embedded groove for fixing the root of the blade. The blade root fixing device is used for firmly fixing the blade root.
Further, the first spring plate back through a set of spring pole with pedestal connection, the base top is equipped with electronic distance meter, the second spring plate back is connected through the connecting rod that a set of spring pole and base lateral wall were equipped with, the terminal top of connecting rod also is equipped with electronic distance meter, the second spring plate be located with blade fixed establishment and the relative one side of slip shooting mechanism. The size of the rotation radius of the blade can be detected through the first spring plate, and the size of the rotation radius of the blade during rotation can be detected through the second spring plate, so that the sizes of different rotation radii can be detected, and the sizes of different rotation radii can be compared with a standard value to achieve the purpose of shape correction.
Furthermore, a group of first sliding grooves perpendicular to the groove and a group of second sliding grooves parallel to the groove are formed in the position, corresponding to the sliding plate, of the upper surface of the base, a first sliding block in sliding connection with the first sliding grooves is arranged at one end, close to the groove, of the bottom of the sliding plate, and a second sliding block in sliding connection with the first sliding grooves and the second sliding grooves is arranged at one end, far away from the groove, of the bottom of the sliding plate. The position change of the sliding shooting mechanism can be realized through the two groups of sliding grooves, so that the blade fixing mechanism is matched to complete the all-dimensional dead-angle-free shooting detection of the blade.
Furthermore, the length of the first sliding block is 3/4-4/5 of the width of the groove, and when the first sliding block slides to the other side of the groove, the position of the second sliding block corresponds to the position of the second sliding groove. And seamless butt joint between the two groups of sliding blocks and the two groups of sliding grooves is ensured.
Furthermore, a locking knob is arranged on the back of the lifting block, a threaded rod arranged at the center of the locking knob is in threaded connection with a threaded groove formed in the back of the lifting block, and the threaded rod penetrates through the threaded groove and then is abutted to the lifting rod. The fixation between the lifting block and the lifting rod is strengthened.
The beneficial effects of the utility model are that:
(1) the utility model discloses an aeroengine blade is with accurate school shape device structural design is reasonable, and easy operation can detect the radius of rotation size under the different positions department of blade rotation or the rotation state, through contrasting the purpose that realizes the accurate school shape of blade with the standard value, cooperates the position that shooting mechanism accuracy judgement blade defect position that slides, and the practicality is higher.
(2) The utility model discloses an aeroengine blade is with accurate school shape device can realize the high-speed rotation and the rotation of blade to characteristics such as blade wind speed detect, realized blade comprehensive properties's detection in accurate school shape, thereby can realize the all-round no dead angle shooting detection that the blade was accomplished to the position change cooperation blade fixed establishment that slides shooting mechanism through two sets of spouts.
Drawings
Fig. 1 is a schematic front view of the overall structure of the present invention;
FIG. 2 is a schematic side view of the present invention;
fig. 3 is a schematic structural view of the sliding shooting mechanism of the present invention;
fig. 4 is a schematic structural view of the sliding plate according to the present invention after sliding.
The system comprises a base 1, a slot 11, an anemometer 12, a first sliding chute 13, a second sliding chute 14, a blade fixing mechanism 2, a first rotating motor 21, a second rotating motor 22, a fixed seat 23, a fixed groove 24, a caulking groove 3, a sliding shooting mechanism 31, a sliding plate 32, a lifting rod 33, a lifting block 34, a 3D camera 35, a first sliding block 36, a second sliding block 36, a locking knob 37, a threaded rod 38, a threaded groove 39, a rotary distance measuring mechanism 4, a first spring plate 41, a second spring plate 42, a base 43, a spring rod 44, an electronic distance measuring instrument 45 and a connecting rod 46.
Detailed Description
Example 1
As shown in fig. 1, the precise sizing device for the blade of the aircraft engine comprises a base 1, a blade fixing mechanism 2, a sliding shooting mechanism 3 and a rotating distance measuring mechanism 4, wherein the blade fixing mechanism 2, the sliding shooting mechanism 3 and the rotating distance measuring mechanism 4 are positioned on the upper surface of the base 1;
as shown in fig. 2, a slot 11 parallel to the long side is formed in the middle of the short side on one side of the base 1, the rotary distance measuring mechanism 4 is located at the end of the slot 11, the blade fixing mechanism 2 and the sliding shooting mechanism 3 are located on the same side of the slot 11, an air speed measuring instrument 12 is arranged on the upper surface of the base 1 on the side opposite to the blade fixing mechanism 2 and the sliding shooting mechanism 3, and the air speed measuring instrument 12 is a commercially available Kanomax high-precision air speed and air gauge;
as shown in fig. 1, the blade fixing mechanism 2 includes a fixing base 23 fixedly disposed on the upper surface of the base 1, a first rotating motor 21 fixedly disposed on the upper surface of the fixing base 23, a second rotating motor 22 disposed at the output end of the first rotating motor 21, an output end of the second rotating motor 22 is provided with an insertion slot 24 for fixing the root of the blade, and the first rotating motor 21 and the second rotating motor 22 are both commercially available BLDC brushless motors which are adjusted in structure and shape to fit the size of the blade fixing mechanism 2;
as shown in fig. 3 and 4, the sliding shooting mechanism 3 includes a sliding plate 31 slidably disposed on the upper surface of the base 1, a lifting rod 32 fixedly disposed on an end of the upper surface of the sliding plate 31 far away from the open slot 11, a lifting block 33 slidably connected to the lifting rod 32, and a 3D camera 34 fixedly connected to the lifting block 33, wherein a set of first sliding slots 13 perpendicular to the open slot 11 and a set of second sliding slots 14 parallel to the open slot 11 are disposed on the upper surface of the base 1 at positions corresponding to the sliding plate 31, a first sliding block 35 slidably connected to the first sliding slots 13 is disposed on an end of the bottom of the sliding plate 31 near the open slot 11, a second sliding block 36 slidably connected to both the first sliding slots 13 and the second sliding slots 14 is disposed on an end of the bottom of the sliding plate 31 far away from the open slot 11, the first sliding block 35 has a length 3/4 corresponding to the width of the open slot 11, the second sliding block 36 corresponds to the position of the second sliding slots 14 when the first sliding block 35 slides to the other side of the open slot 11, a locking knob 37 is arranged on the back of the lifting block 33, a threaded rod 38 arranged in the center of the locking knob 37 is in threaded connection with a threaded groove 39 arranged on the back of the lifting block 33, and the threaded rod 38 penetrates through the threaded groove 39 and then abuts against the lifting rod 32;
as shown in fig. 2, the rotary distance measuring mechanism 4 includes a base 43 fixedly disposed on the upper surface of the base 1, a first spring plate 41 is disposed on a side wall of the base 43 opposite to the side of the slot 11, a second spring plate 42 is disposed on one side wall of the base 43 parallel to the slot 11, the back of the first spring plate 41 is connected to the base 43 through a set of spring rods 44, an electronic distance measuring instrument 45 is disposed on the top of the base 43, the electronic distance measuring instrument 45 is a commercially available CMOS laser displacement sensor, the back of the second spring plate 42 is connected to a connecting rod 46 disposed on the side wall of the base 43 through a set of spring rods 44, the top of the end of the connecting rod 46 is also provided with the electronic distance measuring instrument 45, and the second spring plate 42 is disposed on a side opposite to the blade fixing mechanism 2 and the sliding camera mechanism 3.
Example 2
The present embodiment is different from embodiment 1 in that: the first slider 35 is different in length.
The length of the first slider 35 is 4/5 the width of the slot 11.
The working principle is as follows: the following is the utility model discloses an aeroengine blade is with accurate school shape device theory of operation briefly explains.
When the blade is used, firstly, the root of the blade is fixed in the caulking groove 24, the first rotating motor 21 is started to drive the second rotating motor 22 and the blade to rotate, the blade is abutted to the first spring plate 41 in the rotating process, the spring rod 44 is pushed to stretch and retract, then the rebounding distance of the first spring plate 41 is measured through the electronic distance meter 45, so that the rotating radius of the blade in the state is calculated, and the form precision of the blade is obtained by comparing the rotating radius with a standard value; after the measurement is finished, the second rotating motor 22 is started to rotate for a certain angle, the measurement is carried out again, and therefore the rotating radius of different marked positions is obtained and compared with the standard value to obtain the form precision of the blade.
When the rotation radius under rotation is measured, the second rotating motor 22 is started to drive the blades to rotate, the blades are abutted to the second spring plate 42 in the rotation process and push the spring rod 44 to stretch and retract, then the rebound distance of the second spring plate 42 is measured through the electronic distance meter 45, so that the rotation radius of the blades in the state is calculated, and the form precision of the blades is obtained by comparing the rebound distance with a standard value; after the measurement is finished, the first rotating motor 21 is started to rotate for a certain angle, the measurement is carried out again, and therefore the autorotation radiuses at different marked positions are obtained and compared with the standard values to obtain the form precision of the blade.
When the rotating wind speed is required to be measured, the first rotating motor 21 is started to drive the second rotating motor 22 and the blades to rotate at a high speed, and the rotating wind speed of the blades is measured through the wind speed measuring instrument 12 so as to judge the comprehensive performance of the blades.
When the blade needs to be observed, the sliding plate 31 is slid to enable the first sliding block 35 and the second sliding block 36 to slide towards the open slot 11 along the first sliding groove 13, when the first sliding block 35 abuts against the inner wall of the open slot 11, the sliding is stopped, at the moment, the second sliding block 36 corresponds to the second sliding groove 14, the sliding plate 31 is slid transversely to enable the second sliding block 36 to slide along the second sliding groove 14, after the sliding is stopped at a specified position, the proper shooting position is determined by adjusting the position of the lifting block 33, after the lifting block 33 stops sliding on the lifting rod 32, the locking knob 37 is rotated to enable the threaded rod 38 to move towards the lifting rod 32 along the threaded groove 39, until the tail end of the threaded rod 38 abuts against the lifting rod 32, and the lifting block 33 is prevented from sliding in the shooting process of the 3D camera 34 through pressure and friction force to affect the shooting effect.
Claims (7)
1. The precise sizing device for the blades of the aircraft engine is characterized by comprising a base (1), a blade fixing mechanism (2), a sliding shooting mechanism (3) and a rotating distance measuring mechanism (4), wherein the blade fixing mechanism, the sliding shooting mechanism and the rotating distance measuring mechanism are positioned on the upper surface of the base (1);
a groove (11) parallel to the long side is formed in the middle of the short side on one side of the base (1), the rotary distance measuring mechanism (4) is located at the tail end of the groove (11), and the blade fixing mechanism (2) and the sliding shooting mechanism (3) are located on the same side of the groove (11);
the blade fixing mechanism (2) comprises a fixed seat (23) fixedly arranged on the upper surface of the base (1), a first rotating motor (21) fixedly arranged on the upper surface of the fixed seat (23), and a second rotating motor (22) arranged at the output end of the first rotating motor (21);
the sliding shooting mechanism (3) comprises a sliding plate (31) arranged on the upper surface of the base (1) in a sliding mode, a lifting rod (32) fixedly arranged at one end, far away from the open groove (11), of the upper surface of the sliding plate (31), a lifting block (33) connected with the lifting rod (32) in a sliding mode, and a 3D camera (34) fixedly connected with the lifting block (33);
rotatory range finding mechanism (4) is including fixed setting up base (43) of base (1) upper surface, base (43) just are provided with first spring board (41) on the lateral wall of fluting (11) one side, and base (43) are parallel to and are provided with second spring board (42) on one of them lateral wall of fluting (11).
2. The precise sizing device for the aircraft engine blade is characterized in that an air speed measuring instrument (12) is arranged on one side of the upper surface of the base (1) opposite to the blade fixing mechanism (2) and the sliding shooting mechanism (3).
3. A precision sizing device for aircraft engine blades according to claim 1, characterised in that the output of the second rotating electrical machine (22) is provided with a caulking groove (24) for fixing the blade root.
4. The precise sizing device for the aircraft engine blade is characterized in that the back of the first spring plate (41) is connected with the base (43) through a group of spring rods (44), an electronic distance meter (45) is arranged at the top of the base (43), the back of the second spring plate (42) is connected with a connecting rod (46) arranged on the side wall of the base (43) through a group of spring rods (44), the top of the tail end of the connecting rod (46) is also provided with the electronic distance meter (45), and the second spring plate (42) is located on the side opposite to the blade fixing mechanism (2) and the sliding shooting mechanism (3).
5. The precise sizing device for the aircraft engine blade is characterized in that a group of first sliding grooves (13) perpendicular to the open groove (11) and a group of second sliding grooves (14) parallel to the open groove (11) are arranged on the upper surface of the base (1) at positions corresponding to the sliding plate (31), a first sliding block (35) in sliding connection with the first sliding grooves (13) is arranged at one end, close to the open groove (11), of the bottom of the sliding plate (31), and a second sliding block (36) in sliding connection with the first sliding grooves (13) and the second sliding grooves (14) is arranged at one end, far away from the open groove (11), of the bottom of the sliding plate (31).
6. The aircraft engine blade precision shape correction device as claimed in claim 5, characterized in that the length of the first sliding block (35) is 3/4-4/5 of the width of the slot (11), and the second sliding block (36) corresponds to the position of the second sliding groove (14) when the first sliding block (35) slides to the other side of the slot (11).
7. The precise sizing device for the aircraft engine blade is characterized in that a locking knob (37) is arranged on the back of the lifting block (33), a threaded rod (38) arranged at the center of the locking knob (37) is in threaded connection with a threaded groove (39) arranged on the back of the lifting block (33), and the threaded rod (38) penetrates through the threaded groove (39) and then abuts against the lifting rod (32).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123187071.1U CN217251680U (en) | 2021-12-17 | 2021-12-17 | Accurate correcting device for aero-engine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123187071.1U CN217251680U (en) | 2021-12-17 | 2021-12-17 | Accurate correcting device for aero-engine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217251680U true CN217251680U (en) | 2022-08-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123187071.1U Active CN217251680U (en) | 2021-12-17 | 2021-12-17 | Accurate correcting device for aero-engine blade |
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| Country | Link |
|---|---|
| CN (1) | CN217251680U (en) |
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2021
- 2021-12-17 CN CN202123187071.1U patent/CN217251680U/en active Active
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