Electronic testing fixture for high-pressure turbine first-order blade shock absorber part

Abstract

The invention discloses a high-pressure turbine first-order blade shock absorber part electronic testing fixture which comprises a base, a first positioning seat is fixedly connected to the base, a measuring module fixing seat is fixedly connected to the top of the first positioning seat, and a second positioning seat and a third positioning seat are fixedly connected to the top of the first positioning seat. A PLC is fixedly connected to the top of the base, a pressure regulating valve is fixedly connected to the top of the base, a starting switch is installed on the side wall of the base, a to-be-detected part is placed on the top of the first positioning seat, and a first limiting part and a second limiting part are installed on the top of the base. The first limiting part and the second limiting part abut against the to-be-detected part. According to the electronic testing fixture, the size of the high-pressure turbine first-order blade shock absorber can be rapidly detected, the detection time is shortened, and the detection difficulty is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of electronic inspection tools, and particularly to an electronic inspection tool for high-pressure turbine first-stage blade shock absorber parts. Background Art

[0002] Since the parts of the high-pressure turbine first-stage blade shock absorber need to contact other components in the turbine engine, its dimensional requirements are very strict. Usually, 100% inspection of its important dimensions is required to ensure good performance during use.

[0003] The important area of the high-pressure turbine first-stage blade shock absorber is a curved surface. Conventional inspection tools cannot achieve rapid measurement. Using equipment such as coordinate measuring machines and optical scanners, the measurement time is long, the cost of measurement equipment is high, the skill level requirements for operators are high, and it is not very suitable for mass production. Therefore, we designed an electronic inspection tool for high-pressure turbine first-stage blade shock absorber parts to solve the above problems. Summary of the Invention

[0004] The purpose of the present invention is to solve the deficiencies in the prior art, and an electronic inspection tool for high-pressure turbine first-stage blade shock absorber parts is proposed. This electronic inspection tool can quickly detect the dimensions of the high-pressure turbine first-stage blade shock absorber, reduce the time spent on inspection, and reduce the inspection difficulty.

[0005] To achieve the above purpose, the present invention adopts the following technical solutions: An electronic inspection tool for high-pressure turbine first-stage blade shock absorber parts, including a base, a first positioning seat fixedly connected to the base, a measurement module fixing seat fixedly connected to the top of the first positioning seat, a second positioning seat and a third positioning seat fixedly connected to the top of the first positioning seat, a PLC controller fixedly connected to the top of the base, a pressure regulating valve fixedly connected to the top of the base, a start switch installed on the side wall of the base, a part to be inspected placed on the top of the first positioning seat, a first limiting part and a second limiting part installed on the top of the first positioning seat, and the first limiting part and the second limiting part are both arranged in contact with the part to be inspected.

[0006] Preferably, a third limiting part is fixedly connected to the second positioning seat. The third limiting part includes a first third limiting part and a second third limiting part. Both the first third limiting part and the second third limiting part are fixedly connected to the outer wall of the second positioning seat, and both the first third limiting part and the second third limiting part are arranged in contact with the part to be inspected.

[0007] Preferably, a pneumatic probe is installed at the front end of the measurement module fixing seat. The pneumatic probe includes a first pneumatic probe body, a second pneumatic probe body, and a third pneumatic probe body. The first pneumatic probe body, the second pneumatic probe body, and the third pneumatic probe body are all fixedly connected to the front end of the measurement module fixing seat.

[0008] Preferably, the PLC controller is electrically connected to the pneumatic probe.

[0009] Preferably, a fourth limiting portion is fixedly connected to the front end of the third positioning seat, and the fourth limiting portion is arranged in contact with the part to be detected.

[0010] Preferably, the first limiting portion includes a first limiting part one, a first limiting part two, and a first limiting part three. The first limiting part one, the first limiting part two, and the first limiting part three have the same structure and are each composed of a fixed seat and a T-shaped screw rod. The fixed seat is arranged on the top of the first positioning seat and fixedly connected thereto, and the T-shaped screw rod penetrates through the fixed seat and is threadedly connected thereto.

[0011] Preferably, the second limiting portion includes a second limiting part one, a second limiting part two, and a second limiting part three. The second limiting part one, the second limiting part two, and the second limiting part three are all arranged on the top of the first positioning seat and fixedly connected thereto.

[0012] Preferably, four support legs are fixedly connected to the bottom of the base, and the positions of the four support legs are distributed in a rectangle.

[0013] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. This inspection tool can be used in a dedicated measurement laboratory or on-site for operation, saving site costs.

[0014] 2. It usually takes about five minutes to detect a shock absorber part using a coordinate measuring machine for this inspection tool, while this inspection tool can complete the detection within thirty seconds, resulting in a huge improvement in efficiency.

[0015] 3. This inspection tool has relatively low requirements for the professional skills of operators, and operators only need simple training to operate.

[0016] 4. The maintenance cost of this inspection tool is low.

[0017] In summary, the electronic inspection tool in the present invention can quickly detect the dimensions of the high-pressure turbine first-stage blade shock absorber, reduce the time spent on detection, and lower the detection difficulty. Description of the Drawings

[0018] Figure 1 It is the first structural schematic diagram of the electronic inspection tool for the high-pressure turbine first-stage blade shock absorber part proposed by the present invention; Figure 2 It is the second structural schematic diagram of the electronic inspection tool for the high-pressure turbine first-stage blade shock absorber part proposed by the present invention; Figure 3 It is Figure 1 The enlarged view of the structure at A in

[0019] In the figure: 1 base, 2 first positioning seat, 3 second positioning seat, 4 measuring module fixing seat, 5 part to be detected, 6 PLC controller, 7 pressure regulating valve, 8 third positioning seat, 9 start switch, 21 first limiting part, 211 first limiting part one, 212 first limiting part two, 213 first limiting part three, 22 second limiting part, 221 second limiting part one, 222 second limiting part two, 223 second limiting part three, 31 third limiting part, 311 third limiting part one, 312 third limiting part two, 41 pneumatic probe, 411 first pneumatic probe body, 412 second pneumatic probe body, 413 third pneumatic probe body, 81 fourth limiting part. Specific implementation manner

[0020] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0021] Refer to Figures 1-3 , an electronic inspection tool for a high-pressure turbine first-stage blade shock absorber part, including a base 1. Four support legs are fixedly connected to the bottom of the base 1, and the positions of the four support legs are distributed in a rectangle. A first positioning seat 2 is fixedly connected to the base 1. A measuring module fixing seat 4 is fixedly connected to the top of the first positioning seat 2. A pneumatic probe 41 is installed at the front end of the measuring module fixing seat 4. The pneumatic probe 41 includes a first pneumatic probe body 411, a second pneumatic probe body 412, and a third pneumatic probe body 413. The first pneumatic probe body 411, the second pneumatic probe body 412, and the third pneumatic probe body 413 are all fixedly connected to the front end of the measuring module fixing seat 4. Data of the part can be collected by three pneumatic probes.

[0022] A second positioning seat 3 and a third positioning seat 8 are fixedly connected to the top of the first positioning seat 2. A fourth limiting part 81 is fixedly connected to the front end of the third positioning seat 8. The fourth limiting part 81 is abutted against the part to be detected 5. A third limiting part 31 is fixedly connected to the second positioning seat 3. The third limiting part 31 includes a third limiting part one 311 and a third limiting part two 312. The third limiting part one 311 and the third limiting part two 312 are both fixedly connected to the outer wall of the second positioning seat 3. The third limiting part one 311 and the third limiting part two 312 are both abutted against the part to be detected 5, so that the part to be detected 5 can be limited to ensure the stability of the part to be detected 5 and good subsequent detection effect.

[0023] A PLC controller 6 is fixedly connected to the top of the base 1. The PLC controller 6 is electrically connected to the pneumatic probe 41. A pressure regulating valve 7 is fixedly connected to the top of the base 1. A start switch 9 is installed on the side wall of the base 1. A part to be detected 5 is placed on the top of the first positioning seat 2. The part to be detected 5 is a part of a high-pressure turbine first-stage blade shock absorber.

[0024] At the top of the first positioning seat 2, a first limiting part 21 and a second limiting part 22 are installed. Both the first limiting part 21 and the second limiting part 22 are arranged in contact with the part 5 to be detected. The first limiting part 21 includes a first first limiting part 211, a first second limiting part 212, and a first third limiting part 213. The first first limiting part 211, the first second limiting part 212, and the first third limiting part 213 have the same structure and are both composed of a fixed seat and a T-shaped screw. The fixed seat is arranged at the top of the first positioning seat 2 and is fixedly connected thereto. The T-shaped screw penetrates through the fixed seat and is threadedly connected thereto. The second limiting part 22 includes a second first limiting part 221, a second second limiting part 222, and a second third limiting part 223. The second first limiting part 221, the second second limiting part 222, and the second third limiting part 223 are all arranged at the top of the first positioning seat 2 and are fixedly connected thereto, so as to limit the part 5 to be detected and make the part 5 to be detected stable during detection.

[0025] The detection steps in the present invention are as follows: S1. First, ventilate and electrify this electronic inspection tool for the first-stage blade shock absorber part of the high-pressure turbine. S2. The staff places the part 5 to be detected on the first positioning seat 2 and confirms that it fits with the three limiting parts (the second limiting part 22, the third limiting part 31, and the fourth limiting part 81). S3. Rotate the first limiting part 21 to fix the part 5 to be detected. S4. Rotate the start switch 9 to pop out the pneumatic probe 41, which touches the part 5 to be detected, and the data is collected into the computer. S5. Rotate the start switch 9 in the reverse direction to retract the pneumatic probe 41, and the detection is completed. S6. Replace the next part and repeat the operations of S2 - S5.

[0026] The above is only the preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and should be covered by the protection scope of the present invention.

Claims

1. An electronic inspection fixture for a high-pressure turbine first-stage blade damper component, comprising a base (1), characterized in that: A first positioning seat (2) is fixedly connected to the base (1); a measuring module fixing seat (4) is fixedly connected to the top of the first positioning seat (2); a second positioning seat (3) and a third positioning seat (8) are fixedly connected to the top of the first positioning seat (2); a PLC controller (6) is fixedly connected to the top of the base (1); a pressure regulating valve (7) is fixedly connected to the top of the base (1); a start switch (9) is installed on the side wall of the base (1); a part to be detected (5) is placed on the top of the first positioning seat (2); a first limiting portion (21) and a second limiting portion (22) are installed on the top of the first positioning seat (2); the first limiting portion (21) and the second limiting portion (22) are both arranged to abut against the part to be detected (5).

2. The electronic inspection fixture for the first-stage blade damper of a high-pressure turbine according to claim 1 is characterized in that: A third limiting portion (31) is fixedly connected to the second positioning seat (3), the third limiting portion (31) comprising a third limiting portion 1 (311) and a third limiting portion 2 (312), the third limiting portion 1 (311) and the third limiting portion 2 (312) both being fixedly connected to the outer wall of the second positioning seat (3), and the third limiting portion 1 (311) and the third limiting portion 2 (312) both being arranged to abut against the part (5) to be detected.

3. The electronic inspection fixture for the first-stage blade damper of a high-pressure turbine according to claim 1 is characterized in that: A pneumatic probe pen (41) is installed at the front end of the measuring module fixing seat (4); the pneumatic probe pen (41) comprises a first pneumatic probe pen body (411), a second pneumatic probe pen body (412) and a third pneumatic probe pen body (413); the first pneumatic probe pen body (411), the second pneumatic probe pen body (412) and the third pneumatic probe pen body (413) are all fixedly connected to the front end of the measuring module fixing seat (4).

4. The electronic inspection fixture for the first-stage blade damper of a high-pressure turbine according to claim 3 is characterized in that: The PLC controller (6) is electrically connected to the pneumatic probe (41).

5. The electronic inspection fixture for the first-stage blade damper of a high-pressure turbine according to claim 1 is characterized in that: A fourth limiting portion (81) is fixedly connected to the front end of the third positioning seat (8), and the fourth limiting portion (81) is arranged to abut against the part to be detected (5).

6. The electronic inspection fixture for the first-stage blade damper of a high-pressure turbine according to claim 1 is characterized in that: The first limiting portion (21) comprises a first limiting portion one (211), a first limiting portion two (212) and a first limiting portion three (213); the first limiting portion one (211), the first limiting portion two (212) and the first limiting portion three (213) have the same structure and are composed of a fixing seat and a T-shaped screw; the fixing seat is arranged on the top of the first positioning seat (2) and is fixedly connected thereto; the T-shaped screw passes through the fixing seat and is threadedly connected thereto.

7. The electronic inspection fixture for the first-stage blade damper of a high-pressure turbine according to claim 1 is characterized in that: The second limiting portion (22) comprises a second limiting portion one (221), a second limiting portion two (222) and a second limiting portion three (223); the second limiting portion one (221), the second limiting portion two (222) and the second limiting portion three (223) are all arranged on the top of the first positioning seat (2) and fixedly connected thereto.

8. The electronic inspection fixture for the first-stage blade damper of a high-pressure turbine according to claim 1 is characterized in that: Four supporting legs are fixedly connected to the bottom of the base (1), and the positions of the four supporting legs are distributed in a rectangular shape.

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