Aero-engine blade crown dimension detection clamp

Abstract

The utility model discloses an aero-engine blade crown dimension detection clamp, which relates to the technical field of aviation detection and comprises a first supporting mechanism, a second supporting mechanism, a first positioning mechanism and a second positioning mechanism, and the first positioning mechanism and the second positioning mechanism are matched with the first supporting mechanism and the second supporting mechanism. The first supporting mechanism and the second supporting mechanism are matched with each other to be used for supporting the aero-engine blade. The first supporting mechanism comprises a supporting pin and an adjusting pin movably connected with the supporting pin. And the adjusting pin is in threaded connection with the supporting pin. According to the utility model, the technical problems of low follow-up detection precision and large error caused by infirm fixation of hot melt adhesive fixation are solved, and the technical effects that the aero-engine blade is fixed through the clamp, and the influence on the detection precision of the blade crown caused by displacement in the detection process is avoided are realized.

Description

Technical Field

[0001] This utility model relates to the field of aviation testing technology, specifically to a fixture for detecting the size of the blade crown of an aero-engine. Background Technology

[0002] Please see Figure 1 , Figure 1 This is a structural schematic diagram of an aero-engine blade. The aero-engine blade includes a blade crown 101 and a tenon 102 located on both sides. The blade crown 101 is provided with a working surface 103. When the operator inspects the blade crown size of the aero-engine blade, the operator will inspect the size between the working surfaces 103 on the blade crown to complete the conformity judgment and ensure the installation quality.

[0003] However, blade crown size detection falls under the category of detecting special characteristic parameters of blades. Due to the characteristics of blades—small size, complex shape, high geometric accuracy requirements, and large quantity—achieving accurate and rapid detection of blade crown size parameters is quite challenging. In existing technologies, blade crown size detection typically involves leveling a gauge block, fixing the blade with hot melt adhesive, and then performing coordinate measurement. However, the hot melt adhesive fixation method suffers from insecure fixation, leading to low detection accuracy and significant errors in subsequent measurements. Utility Model Content

[0004] To address the aforementioned problems, this utility model provides a fixture for detecting the crown size of aero-engine blades, comprising:

[0005] A first support mechanism, a second support mechanism, and a first positioning mechanism and a second positioning mechanism adapted to the first support mechanism and the second support mechanism;

[0006] The first support mechanism and the second support mechanism work together to support the aero-engine blades;

[0007] The first support mechanism includes a support pin and an adjusting pin movably connected to the support pin;

[0008] The adjusting pin is threadedly connected to the support pin.

[0009] In some embodiments, the second support mechanism is located on one side of the first support mechanism and includes a vertically arranged limiting pin, the limiting pin being a columnar structure, and the limiting pin abutting against one side of the blade.

[0010] In some embodiments, the first positioning mechanism is arranged perpendicular to the second support mechanism, and the first positioning mechanism includes a limiting plate, wherein the limiting plate is arranged vertically and is used for limiting after abutting against the aero-engine blade.

[0011] In some embodiments, the contact surface between the limiting plate and the aero-engine blade is a flat surface.

[0012] In some embodiments, the second positioning mechanism is located on the side of the first support mechanism away from the second support mechanism, and the second positioning mechanism is adapted to the second support mechanism;

[0013] The second positioning mechanism includes an adjusting member and a limiting pin movably connected to the adjusting member.

[0014] In some embodiments, the top of the adjusting member is an inclined plate-like structure, and its inclined portion is threadedly connected to the limiting pin. The limiting pin is inclined and is used for limiting after it abuts against the aero-engine blade.

[0015] By adopting the above technical solution, this utility model mainly has the following technical effects:

[0016] By using the first and second support mechanisms in cooperation to support the aero-engine blades, and by using the first and second positioning mechanisms to abut against the aero-engine blades and limit their position, the technical problem of unreliable fixation by hot melt adhesive, which leads to low accuracy and large errors in subsequent inspections, is solved. This achieves the technical effect of fixing the aero-engine blades with fixtures to avoid displacement during the inspection process and affecting the accuracy of blade crown inspection. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of an aero-engine blade;

[0018] Figure 2 This is a schematic diagram of the structure of a blade crown size detection fixture for aero-engines according to the present invention;

[0019] Figure 3 This is a schematic diagram of the structure of an aero-engine blade crown size detection fixture according to the present invention (from another perspective);

[0020] The meanings of the reference numerals in the attached figures are as follows:

[0021] 1. First support mechanism; 11. Support pin; 12. Adjusting pin;

[0022] 2. Second support mechanism; 21. Limit pin;

[0023] 3. First positioning mechanism; 31. Limiting plate;

[0024] 4. Second positioning mechanism; 41. Adjusting component; 42. Limit pin. Detailed Implementation

[0025] To enable those skilled in the art to better understand the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0026] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of the present invention. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0027] Please see Figures 2-3 This utility model provides a blade crown size detection fixture for aero-engines, including: a first support mechanism 1, a second support mechanism 2, and a first positioning mechanism 3 and a second positioning mechanism 4 adapted to the first support mechanism 1 and the second support mechanism 2.

[0028] In some embodiments, the first support mechanism 1 and the second support mechanism 2 are both support parts in the aero-engine blade crown size detection fixture. The first support mechanism 1 and the second support mechanism 2 cooperate with each other to support the aero-engine blade. The first positioning mechanism 3 and the second positioning mechanism 4 abut against the aero-engine blade to limit the aero-engine blade, thereby fixing the aero-engine blade on the aero-engine blade crown size detection fixture.

[0029] Furthermore, the first support mechanism 1 is a vertical support portion of the aero-engine blade. In some embodiments, the first support mechanism 1 includes a support pin 11 and an adjusting pin 12 movably connected to the support pin 11. The support pin 11 is a columnar structure and is vertically arranged. The adjusting pin 12 is located above the support pin 11 and is used to support the aero-engine blade after abutting against the bottom of the aero-engine blade.

[0030] In some more preferred embodiments, the adjusting pin 12 is threadedly connected to the support pin 11, and the height of the adjusting pin 12 can be adjusted by rotating the adjusting pin 12, thereby adapting it to the aero-engine blade during the testing process.

[0031] In some embodiments, the second support mechanism 2 is a horizontal support portion of the aero-engine blade. The second support mechanism 2 is located on one side of the first support mechanism 1. In some embodiments, the second support mechanism 2 includes a vertically arranged limiting pin 21. The limiting pin 21 is a columnar structure. By abutting the limiting pin 21 against one side of the blade, the blade is limited.

[0032] Furthermore, the first positioning mechanism 3 is arranged perpendicular to the second support mechanism 2. In some embodiments, the first positioning mechanism 3 includes a limiting plate 31, wherein the limiting plate 31 is arranged vertically and limits the aero-engine blade after abutting against it. In some more preferred embodiments, the contact surface between the limiting plate 31 and the aero-engine blade is a flat surface, so that when the operator frequently inspects the aero-engine blade, he can use the limiting plate 31 as a reference, place the aero-engine blade against the limiting plate 31 and then place it on the first support mechanism 1, and abut against the second support mechanism 2.

[0033] Furthermore, the second positioning mechanism 4 is located on the side of the first support mechanism 1 away from the second support mechanism 2. The second positioning mechanism 4 is adapted to the second support mechanism 2 and is used to limit the aero-engine blade in the horizontal direction.

[0034] In some embodiments, the second positioning mechanism 4 includes an adjusting member 41 and a limiting pin 42 movably connected to the adjusting member 41. In some embodiments, the top of the adjusting member 41 is an inclined plate-like structure, and its inclined portion is threadedly connected to the limiting pin 42. By tilting the top of the adjusting member 41, the limiting pin 42 is tilted, providing that after the inclined limiting pin 42 abuts against the aero-engine blade, on the one hand, the side of the first support mechanism 1 away from the second support mechanism 2 limits the aero-engine blade, and on the other hand, it also limits the engine blade at the top, thereby preventing the aero-engine blade from shifting during the detection process and avoiding damage to the detection accuracy of the blade crown.

[0035] Finally, it should be noted that the embodiments disclosed in this utility model are merely preferred embodiments of this utility model and are only used to illustrate the technical solutions of this utility model, not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the various embodiments of this utility model.

Claims

1. A fixture for measuring the size of the blade crown of an aero-engine, characterized in that, include: A first support mechanism, a second support mechanism, and a first positioning mechanism and a second positioning mechanism adapted to the first support mechanism and the second support mechanism; The first support mechanism and the second support mechanism work together to support the aero-engine blades; The first support mechanism includes a support pin and an adjusting pin movably connected to the support pin; The adjusting pin is threadedly connected to the support pin.

2. The blade crown size detection fixture for aero-engines according to claim 1, characterized in that, The second support mechanism is located on one side of the first support mechanism and includes a vertically arranged limiting pin. The limiting pin has a columnar structure and abuts against one side of the blade.

3. The blade crown size detection fixture for aero-engines according to claim 1, characterized in that, The first positioning mechanism is arranged perpendicular to the second support mechanism. The first positioning mechanism includes a limiting plate, wherein the limiting plate is arranged vertically and is used for limiting after abutting against the aero-engine blade.

4. The blade crown size detection fixture for aero-engines according to claim 3, characterized in that, The contact surface between the limiting plate and the aero-engine blade is a flat surface.

5. The blade crown size detection fixture for aero-engines according to claim 2, characterized in that, The second positioning mechanism is located on the side of the first support mechanism away from the second support mechanism, and the second positioning mechanism is adapted to the second support mechanism; The second positioning mechanism includes an adjusting member and a limiting pin movably connected to the adjusting member.

6. The blade crown size detection fixture for aero-engines according to claim 5, characterized in that, The top of the adjusting component is an inclined plate-like structure, and its inclined portion is threadedly connected to the limiting pin. The limiting pin is inclined and is used for limiting after it abuts against the aero-engine blade.

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