Measuring tool device for aero-engine blade channel and profile

Abstract

The invention discloses an aero-engine blade channel and profile measuring tool device. The aero-engine blade channel and profile measuring tool device is composed of a base, a channel measuring device and a profile measuring tool device. The aero-engine blade is positioned and fixed through the base, on the basis, the distance between the blade crown and the end face of the inner side channel of the margin plate is measured through the multiple measuring holes and the channel measuring pins which are arranged on the base, and the molded surface is measured through the blade back measuring sample plate and the blade basin measuring sample plate which are in special shapes. Compared with a traditional measuring system, the measuring device is simple in structure, low in cost, easy to operate, high in measuring efficiency and suitable for wide application and popularization, and the size precision is judged through direct contact between the measuring piece and the blade.

Description

Technical Field

[0001] The invention relates to an aero-engine blade machining and measuring tool, in particular to an aero-engine blade passage and profile measuring tool device. Background Art

[0002] The structure of an aircraft engine blade consists of the blade body, and the integrally formed shroud and lip plate at each end. The shroud and lip plate are used to connect and secure the blade body, and their inner sides are flat. The distance between the shroud and lip plate inner planes forms the engine's blade passage. The dorsal and basal sides of the blade body are contoured surfaces.

[0003] Aero-engine blades are typically produced through one-piece casting. However, the resulting castings often lack high surface precision, leading to inconsistent channel and profile dimensions between blades that fail to meet operational requirements. Therefore, aero-engine blade castings typically require manual polishing to achieve uniform and standard channel and profile dimensions. Prior to and during polishing, the channel and profile dimensions must be repeatedly measured to avoid excessive polishing that could cause dimensional deviations and lead to scrap.

[0004] Current aero-engine blade profile and channel measurement technologies include laser scanning, spectral confocal + three-coordinate platform, and CAD digital-analog correlation. These methods have high measurement accuracy, but have the disadvantages of high system cost, complex operation, and long time consumption, which increases the cost investment of processing companies and reduces processing efficiency.

[0005] To this end, we have developed and designed a channel and profile integrated measurement device specifically for aircraft engine blades, combining practical processing experience with theoretical foundations. Summary of the Invention

[0006] In order to solve the above technical problems, the present invention provides an aircraft engine blade passage and profile measuring device. The present invention has the characteristics of simple structure, low equipment cost, easy operation, high measurement efficiency and accuracy, reasonable design and strong practicality.

[0007] The technical solution of the present invention:

[0008] An aircraft engine blade channel and profile measuring device, consisting of a base, a channel measuring device and a profile measuring device;

[0009] The base includes a bottom plate, on the upper side of which a left channel measuring block, a blade back clamping block, and a right channel measuring block are spaced apart; a positioning pin is provided on the outer side of the left channel measuring block; a blade basin movable clamp that can move relative to the blade back clamping block is provided between the left channel measuring block and the blade back clamping block, and between the blade back clamping block and the right channel measuring block;

[0010] The channel measuring device includes three measuring holes 1 provided on the left channel measuring block, five measuring holes 2 provided on the right channel measuring block, and a movable block 1 provided on the inner side of the left channel measuring block and a movable block 2 provided on the inner side of the right channel measuring block; the outer side of the bottom of the movable block 1 is provided with a vertical limiting surface 1, and the inner side of the top is provided with three measuring holes 3; the outer side of the bottom of the movable block 2 is provided with a vertical limiting surface 2, and the inner side of the top is provided with two measuring holes 4; channel measuring pins are connected through the measuring holes 1, 2, 3 and 4;

[0011] The profile measuring device includes 5 blade back measurement templates and 5 blade basin measurement templates. The inner sides of the blade back measurement templates are respectively provided with arc-shaped concave surfaces consistent with the blade back profile of the corresponding segment, and the outer sides of the bottoms of the blade back measurement templates are provided with vertical limit surfaces three; the inner sides of the blade basin measurement templates are respectively provided with arc-shaped convex surfaces consistent with the blade basin profile of the corresponding segment, and the outer sides of the bottoms of the blade basin measurement templates are provided with vertical limit surfaces four.

[0012] This solution positions and secures aircraft engine blades using a base. Multiple measuring holes and channel measuring pins located on the base are then used to measure the distance between the blade crown and the inner channel end face of the blade rim. Specially shaped blade back and blade basin measuring templates are also used to measure the profile. Compared to traditional measurement systems, this measurement device offers a simpler structure and lower cost. Furthermore, it uses direct contact between the measuring element and the blade to determine dimensional accuracy. This makes it easy to operate and offers high measurement efficiency, making it suitable for widespread application.

[0013] Preferably, in the aforementioned aircraft engine blade channel and profile measuring device, a limiting strip is provided on each of the front and rear sides of the upper end of the base plate, and the top surface and the outer facade of the limiting strip both exceed the top surface and the outer facade of the base plate; the bottom of the movable block one, movable block two, blade back measurement template and blade basin measurement template is provided with an overhead portion extending upward, and the front end of the overhead portion extends downward to form a support leg.

[0014] This solution reduces the interference of the bottom plate plane on the measurement accuracy and improves the measurement accuracy by setting a special structure of limit strips and setting a suspended overhead part under the movable block 1, movable block 2, blade back measurement template and blade basin measurement template.

[0015] Preferably, in the aforementioned aircraft engine blade channel and profile measuring device, the blade back clamp block and the right channel measuring block are both movably connected in the sinking hole on the upper surface of the base plate, and the front and rear sides of the blade back clamp block and the right channel measuring block are fixed by top screws passing through the wall of the sinking hole.

[0016] This solution can adjust the front-to-back and up-down positions of the blade back clamp and the right channel measuring block by movably connecting the blade back clamp and the right channel measuring block to the base plate. It can generally adjust the positioning and measurement position of the measuring tool in real time, and the design is more reasonable and more practical.

[0017] Preferably, in the aforementioned aircraft engine blade channel and profile measuring device, two slide grooves are provided on the upper surface of the base plate, and the lower end of the blade basin movable clamp passes through the slide groove and is connected to the bottom of the slide groove via a rotating shaft. The side of the slide groove is threadedly connected with a fastening screw, one end of the fastening screw contacts the outer side of the blade basin movable clamp, and the other end extends to the outer side of the base plate.

[0018] The leaf basin movable clamp of this solution is adjusted in tightness by fastening screws, and has a simple structure and is easy to operate.

[0019] Preferably, in the aforementioned aircraft engine blade channel and profile measuring device, the end of the positioning pin is pointed.

[0020] The end of the positioning pin of this solution is pointed, and the contact surface with the positioning point is smaller, so it is less affected by the accuracy of the surface around the positioning point, and the positioning is more accurate and more practical.

[0021] Preferably, in the aforementioned aircraft engine blade channel and profile measuring device, the end of the channel measuring pin that contacts the aircraft engine blade is pointed.

[0022] The end of the channel measuring pin of this solution is pointed, and the contact surface with the measuring point is smaller, so it is less affected by the accuracy of the surface around the measuring point, and the measurement accuracy is higher.

[0023] Preferably, in the aforementioned aircraft engine blade channel and profile measuring device, a sinking platform is provided at one end of the channel measuring pin away from the aircraft engine blade.

[0024] Preferably, in the aforementioned aircraft engine blade channel and profile measuring device, the extension length of the sinking platform in the length direction of the channel measuring pin is 0.2-0.5 mm.

[0025] This solution sets a sinking platform at the end of the channel measuring pin, and judges the tolerance of the machined surface based on the position of the sinking platform, making channel detection faster and more efficient.

[0026] Beneficial effects of the present invention:

[0027] 1. The present invention positions and secures aircraft engine blades using a base. Multiple measuring holes and channel measuring pins located on the base are then used to measure the distance between the blade crown and the inner channel end surface of the blade rim. Specially shaped blade back and blade basin measuring templates are also used to measure the profile. Compared to traditional measurement systems, the present measuring device offers a simpler structure and lower cost. Furthermore, the device determines dimensional accuracy through direct contact between the measuring element and the blade, resulting in simple operation and high measurement efficiency, making it suitable for widespread application.

[0028] 2. The present invention provides a special structure of limit strips and provides a suspended overhead portion below the movable block 1, movable block 2, blade back measurement template and blade basin measurement template, thereby reducing the interference of the bottom plate plane on the measurement accuracy and improving the measurement accuracy.

[0029] 3. The present invention movably connects the blade back clamp and the right channel measuring block to the base plate, so that the front-to-back and up-down positions of the blade back clamp and the right channel measuring block can be adjusted. Generally, the positioning and measuring position of the measuring tool can be adjusted in real time, and the design is more reasonable and more practical.

[0030] 4. The leaf basin movable clamp of the present invention is adjusted in tightness by fastening screws, and has a simple structure and is easy to operate.

[0031] 5. The end of the positioning pin of the present invention is pointed, and the contact surface with the positioning point is smaller, so it is less affected by the accuracy of the surface around the positioning point, and the positioning is more accurate and more practical.

[0032] 6. The end of the channel measuring pin of the present invention is pointed, so the contact surface with the measuring point is smaller, and the pin is less affected by the accuracy of the surface around the measuring point, resulting in higher measurement accuracy.

[0033] 7. The present invention sets a sinking platform at the end of the channel measuring pin, and judges the tolerance of the processing surface according to the position of the sinking platform, so that the channel detection is faster and more efficient. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Attachment Figure 1 is a three-dimensional schematic diagram of the base of the present invention;

[0035] Attachment Figure 2 A top view of the base of the present invention;

[0036] Attachment Figure 3 It is a rear view of the base of the present invention;

[0037] Attachment Figure 4 It is a left side view of the base of the present invention;

[0038] Attachment Figure 5 It is a right side view of the base of the present invention;

[0039] Attachment Figure 6 It is a front view of the movable block 1 of the present invention;

[0040] Attachment Figure 7 This is the left view after the movable block 1 is placed in the base;

[0041] Attachment Figure 8 It is a front view of the movable block 2 of the present invention;

[0042] Attachment Figure 9 This is the right view after the movable block 2 is placed in the base;

[0043] Attachment Figure 10 A front view of a channel measuring pin of the present invention;

[0044] Attachment Figure 11 Schematic diagram of a channel measuring pin inserted into a measuring hole to measure the channel on the inner side of a blade crown;

[0045] Attachment Figure 12 This is a front view of the leaf back measurement sample of the present invention;

[0046] Attachment Figure 13 This is a front view of the leaf basin measurement sample of the present invention;

[0047] Attachment Figure 14 This is a schematic diagram of the structure of the blade back measurement template and the blade basin measurement template of the present invention when they are in contact with the back side and basin side of the blade body.

[0048] Explanation of the accompanying drawings: 1-base, 2-left channel measuring block, 3-blade back clamping block, 4-right channel measuring block, 5-positioning pin, 6-measuring hole one, 7-measuring hole two, 8-blade basin movable clamp, 9-limiting plate, 10-movable block one, 11-measuring hole three, 12-movable block two, 13-measuring hole four, 14-channel measuring pin, 15-sinking platform, 16-blade back measuring template, 17-arc-shaped concave surface, 18-limiting surface three, 19-blade basin measuring template, 20-arc-shaped convex surface, 21-limiting surface four, 22-limiting surface one, 23-limiting surface two, 24-sinking hole, 25-top screw, 26-fastening screw, 27-slide groove, 28-rotating shaft, 29-overhead part, 30-support leg, 31-blade body, 32-blade crown. DETAILED DESCRIPTION

[0049] The present invention will be further described below with reference to the examples, but they are not intended to limit the present invention.

[0050] Embodiments of the present invention

[0051] An aircraft engine blade channel and profile measuring device, as shown in the attached Figure 1-14 As shown, it consists of a base, a channel measuring device and a surface measuring device;

[0052] The base includes a rectangular bottom plate 1, and a left channel measuring block 2, a leaf back clamping block 3 and a right channel measuring block 4 are spaced apart on the upper side of the bottom plate 1; a positioning pin 5 is provided on the outer side of the left channel measuring block 2, wherein the distance between the distal end of the left channel measuring block 2 and the tip of the positioning pin 5 is 28.163±0.01mm, the distance between the proximal end of the leaf back clamping block 3 and the tip of the positioning pin 5 is 56.103±0.01mm, the distance between the distal end of the leaf back clamping block 3 and the tip of the positioning pin 5 is 84.043±0.01mm, the distance between the limit point at the proximal end of the right channel measuring block 4 and the tip of the positioning pin 5 is 111.983±0.01mm, and the distance between the distal end of the right channel measuring block 4 and the tip of the positioning pin 5 is 139.932±0.01mm; a leaf basin movable clamp 8 that can move back and forth relative to the leaf back clamping block 3 is provided between the left channel measuring block 2 and the leaf back clamping block 3, and between the leaf back clamping block 3 and the right channel measuring block 4;

[0053] The channel measuring device includes three measuring holes 1 (6) provided on the left channel measuring block 2, five measuring holes 2 (7) provided on the right channel measuring block 4, and a movable block 10 provided on the inner side of the left channel measuring block 2 and a movable block 2 (12) provided on the inner side of the right channel measuring block 4; the outer side of the bottom of the movable block 10 is provided with a vertical limiting surface 1 (22), and the inner side of the top is provided with three measuring holes 3 (11); the outer side of the bottom of the movable block 2 (12) is provided with a vertical limiting surface 2 (23), and the inner side of the top is provided with two measuring holes 4 (13); a channel measuring pin 14 is connected through the measuring holes 1 (6), 2 (7), 3 (11), and 4 (13); wherein the inner diameters of the measuring holes 1 (6), 2 (7), 3 (11), and 4 (13) are consistent, and the channel measuring pin 14 can be inserted into the measuring holes without shaking;

[0054] The profile measuring device includes 5 blade back measurement templates 16 and 5 blade basin measurement templates 19. The inner sides of the blade back measurement templates 16 are respectively provided with arc-shaped concave surfaces 17 consistent with the blade back profile of the corresponding section, and the outer sides of the bottoms of the blade back measurement templates 16 are provided with vertical limit surfaces 3 18; the inner sides of the blade basin measurement templates 19 are respectively provided with arc-shaped convex surfaces 20 consistent with the blade basin profile of the corresponding section, and the outer sides of the bottoms of the blade basin measurement templates 19 are provided with vertical limit surfaces 4 21; the shapes and curvatures of the arc-shaped concave surfaces 17 and the arc-shaped convex surfaces 20 on the 5 blade back measurement templates 16 and the blade basin measurement template 19 are not consistent, and are designed according to the changes in the profile of the blade body 31 in the length direction and the morphology on both sides of the blade body 31 of the fixed measurement section.

[0055] When performing actual measurement in this embodiment, the steps are as follows:

[0056] Base fixing:

[0057] S1. First, flip the leaf basin movable clamp 8 outward to the maximum distance;

[0058] S2. Place the aircraft engine blade 1 between the blade basin movable clamp 8 and the blade back clamp 3, with the inner surface of the blade crown 32 on its left side contacting the end of the positioning pin 5 to form the first positioning point, the lower side of the left end of the blade 31 is placed on the step of the left channel measuring block 2 and moved back to form the second positioning point, the back of the middle part of the blade 31 is pressed against the blade back clamp 3 to form the third positioning point, the lower side of the right end of the blade 31 is placed on the step of the right channel measuring block 4 and moved back to form the fourth positioning point, then adjust the blade basin movable clamp 8 to contact the blade basin side of the blade 31, and clamp the blade 31 to form the fifth and sixth positioning points respectively, and fix and position the aircraft engine blade through the above 6 positioning points.

[0059] Channel measurement:

[0060] S1. Insert the channel measuring pin 14 from the inner side of the left channel measuring block 2 to the outer side into the measuring hole 6, so that the end of the channel measuring pin 14 contacts the inner side of the leaf crown 32. Figure 11 As shown, the tolerance of the inner surface of the blade crown 32 is judged by the scale reserved on the channel measuring pin 14. If the scale at the right end of the measuring pin 14 completely enters the measuring hole 6, it means that the inner surface of the blade crown 32 at the channel measuring point is over-polished, which may cause the part to be scrapped; if the scale at the left end of the channel measuring pin 14 still does not enter the measuring hole 6, it means that the inner surface of the blade crown 32 at the channel measuring point is not polished enough, and it should be re-polished after making a record; according to the above method, Figure 7 The channel points on the inner side of the leaf crown 32 corresponding to the three channel measurement points V4, V5 and V6 on the left channel measurement block 2 are measured;

[0061] S2. After measuring V4, V5 and V6, insert the movable block 10 from the front side of the bottom plate 1 and press it on the bottom plate 1. The limit surface 22 is tightly fitted with the side of the bottom plate 1. The side of the movable block 10 is in close contact with the inner side of the left channel measurement block 2. Then, according to the method of S1, insert the channel measurement pin 14 into the measurement hole 3 11 and measure the adjacent Figure 7 The channel points at the corresponding positions of the three channel measurement points V1, V2 and V3 shown in FIG;

[0062] S3. According to the method in S1, the channel measuring pins 14 are sequentially inserted from the inner side of the right channel measuring block 4 into the measuring hole 2 7, so that their ends contact the inner side of the edge plate at the other end of the aircraft engine blade. The structure of the edge plate is similar to that of the blade crown 32, not shown in the drawings. Its inner side is flat, but the difference is that it is located at the opposite ends of the blade body 31 from the blade crown 32. After the above operations, Figure 9 The five channel measurement points V7, V8, V9, V12 and V13 shown are measured at the inner side channel points of the edge plate at the corresponding positions;

[0063] S4. Finally, according to the method of S2, insert the movable block 2 12 from the front side of the bottom plate 1 and press it on the bottom plate 1. The limit surface 23 is tightly fitted with the side of the bottom plate 1. The side of the movable block 2 12 is in close contact with the inner side of the right channel measurement block 4. Then insert the channel measurement pin 14 into the measurement hole 4 13 and measure the adjacent Figure 9 The channel points corresponding to the two channel measurement points V10 and V11 shown in;

[0064] S5. When the tolerances of the channel points corresponding to the aforementioned 12 measurement points V1-V12 are all within the error range, it indicates that the channel size of the aircraft engine blade meets the requirements.

[0065] Surface measurement:

[0066] S1. Figure 2 As shown by the lines A1-A1, A2-A2, A3-A3, A4-A4 and A5-A5 in FIG, when measuring the profile, the five blade basin measurement templates 19 and the blade back measurement templates 16 are placed on the lines A1-A1, A2-A2, A3-A3, A4-A4 and A5-A5 respectively, and the blade basin measurement templates 19 and blade back measurement templates 16 of the corresponding sections are numbered in advance;

[0067] S2. When measuring the blade back profile, first insert the blade back measurement template 16 corresponding to A1-A1 from the rear side of the base plate 1 and place it on the base plate 1. Its side surface is in close contact with the outer side of the right channel measurement block 4, and the limit surface 3 18 is in close contact with the side surface of the base plate 1, as shown in the attached figure. Figure 13 As shown, at this time, use light to illuminate the contact surface between the arc-shaped concave surface 17 and the back side of the blade body 31 from one side of the blade back measurement template 16, and then observe the light transmission width of the contact surface from the other side. If the light transmission width is smaller than the light transmission width of the standard part profile, continue polishing until it meets the use requirements. If the light transmission width is larger than the light transmission width of the standard part profile, the blade may be scrapped.

[0068] S3 according to the method of S2, select A2-A2, A3-A3, A4-A4 and A5-A5 corresponding segments of the blade back measurement template 16 to measure the back surface of the blade 1 segment;

[0069] S4. According to the method of S2, select the blade basin measurement template 19 of the corresponding section to measure the surface of the blade basin side.

[0070] Further implementation examples are attached Figure 1-14As shown, a limiting strip 9 is provided on each of the front and rear sides of the upper end of the base plate 1. The top and outer surfaces of the limiting strip 9 both extend beyond the top and outer surfaces of the base plate 1. The bottoms of the movable block 10, movable block 2, blade back measurement template 16, and blade basin measurement template 19 are provided with an upwardly extending overhead portion 29. The front ends of the overhead portion 29 extend downward to form support legs 30. The support height of the support legs 30 is sufficient to keep the movable block 10, movable block 2, blade back measurement template 16, and blade basin measurement template 19 horizontal and not tilted. This reduces the contact area between the bottom and inner sides of the movable block 10, movable block 2, blade back measurement template 16, and blade basin measurement template 19 and the upper and side surfaces of the base plate 1, thereby reducing errors caused by uneven surfaces of the base plate 1.

[0071] Further implementation examples are attached Figure 1-14 As shown, the blade back clamping block 3 and the right channel measuring block 4 are both movably connected to a countersunk hole 24 on the upper surface of the base plate 1. The blade back clamping block 3 and the right channel measuring block 4 are secured at their front and rear ends by screws 25 extending through the walls of the countersunk hole 24. If the size of the aircraft engine blade changes, the screws 25 can be unscrewed to adjust the vertical and front-to-back positions of the blade back clamping block 3 and the right channel measuring block 4 in the countersunk hole 24. Once properly adjusted, the screws 25 can be tightened to secure them.

[0072] Further implementation examples are attached Figure 1-14 As shown, the upper surface of the base plate 1 is provided with two chutes 27. The lower end of the blade basin movable clamp 8 passes through the chutes 27 and is connected to the bottom of the chutes 27 via a rotating shaft 28. A fastening screw 26 is threadedly connected to the side of the chutes 27. One end of the fastening screw 26 contacts the outer side of the blade basin movable clamp 8, and the other end extends to the outer side of the base plate 1. The chutes 27 are through holes that pass through the base plate 1 from top to bottom. In order to reduce the overall weight of the base plate 1, the lower part of the base plate 1 is hollowed out. When the blade basin movable clamp 8 needs to be opened, the fastening screw 26 is rotated to move it away from the blade basin movable clamp 8. At this time, the blade basin movable clamp 8 loses its force and tilts backward, thereby completing the opening action. After the aircraft engine blade is placed, the fastening screw 26 is rotated in the opposite direction, pushing the blade basin movable clamp 8 toward the blade body 31 until the blade body 31 is completely compressed.

[0073] Further implementation examples are attached Figure 1-14 As shown, the end of the positioning pin 5 is pointed, specifically, is dome-shaped.

[0074] Further implementation examples are attached Figure 1-14 As shown, the end of the channel measuring pin 14 that contacts the aircraft engine blade is pointed, specifically, in the shape of a dome.

[0075] Further implementation examples are attached Figure 1-14As shown, a recessed platform 15 is provided at the end of the channel measurement pin 14 away from the aircraft engine blade. Preferably, the recessed platform 15 extends 0.2-0.5 mm along the length of the channel measurement pin 14. The maximum error range for the channel measurement point is 0.2-0.5 mm, i.e., ±0.25 mm. If the recessed platform 15 enters the measurement hole but not completely, the surface channel measurement point meets the requirements. If the recessed platform 15 does not enter the measurement hole at all, the surface requires further polishing. If the recessed platform 15 fully enters the measurement hole but its top still does not contact the channel measurement point, it indicates over-polishing.

[0076] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, can make equivalent replacements or changes based on the technical solutions and inventive concepts of the present invention, which should be covered by the scope of protection of the present invention.

Claims

1. An aircraft engine blade passage and profile measuring device, characterized by: It consists of a base, a channel measuring device and a surface measuring device; The base comprises a bottom plate (1), and a left channel measuring block (2), a leaf back clamping block (3), and a right channel measuring block (4) are provided on the upper side of the bottom plate (1); a positioning pin (5) is provided on the outer side of the left channel measuring block (2); and a leaf basin movable clamp (8) that can move relative to the leaf back clamping block (3) is provided between the left channel measuring block (2) and the leaf back clamping block (3), and between the leaf back clamping block (3) and the right channel measuring block (4); The channel measuring device comprises three measuring holes (1) (6) provided on the left channel measuring block (2), five measuring holes (2) (7) provided on the right channel measuring block (4), and a movable block (10) (10) provided on the inner side of the left channel measuring block (2) and a movable block (12) (12) provided on the inner side of the right channel measuring block (4); the outer side of the bottom of the movable block (10) is provided with a vertical limiting surface (22), and the inner side of the top is provided with three measuring holes (3) (11); the outer side of the bottom of the movable block (12) is provided with a vertical limiting surface (23), and the inner side of the top is provided with two measuring holes (4) (13); the measuring holes (1) (6), the measuring holes (7), the measuring holes (3) (11) and the measuring holes (4) (13) are connected with channel measuring pins (14); The profile measuring device comprises five blade back measuring templates (16) and five blade basin measuring templates (19), wherein the inner sides of the blade back measuring templates (16) are respectively provided with arc-shaped concave surfaces (17) consistent with the blade back profile of the corresponding section, and the outer sides of the bottoms of the blade back measuring templates (16) are respectively provided with vertical limiting surfaces (3) (18); the inner sides of the blade basin measuring templates (19) are respectively provided with arc-shaped convex surfaces (20) consistent with the blade basin profile of the corresponding section, and the outer sides of the bottoms of the blade basin measuring templates (19) are respectively provided with vertical limiting surfaces (4) (21).

2. The aircraft engine blade passage and profile measuring device according to claim 1, characterized in that: A limiting plate (9) is provided on each of the front and rear sides of the upper end of the base plate (1), and the top surface and the outer facade of the limiting plate (9) are higher than the top surface and the outer facade of the base plate (1); the bottoms of the movable block 1 (10), the movable block 2 (12), the blade back measurement template (16) and the blade basin measurement template (19) are provided with an overhead portion (29) extending upward, and the front end of the overhead portion (29) extends downward to form a support leg (30).

3. The aircraft engine blade passage and profile measuring device according to claim 1, characterized in that: The blade back clamping block (3) and the right channel measuring block (4) are both movably connected in a sinking hole (24) on the upper surface of the bottom plate (1), and the front and rear sides of the blade back clamping block (3) and the right channel measuring block (4) are fixed by top screws (25) passing through the wall of the sinking hole (24).

4. The aircraft engine blade passage and profile measuring device according to claim 1, characterized in that: Two slide grooves (27) are provided on the upper surface of the base plate (1), and the lower end of the leaf basin movable clamp (8) passes through the slide groove (27) and is connected to the bottom of the slide groove (27) via a rotating shaft (28). The side of the slide groove (27) is threadedly connected with a fastening screw (26), one end of the fastening screw (26) contacts the outer side of the leaf basin movable clamp (8), and the other end extends to the outer side of the base plate (1).

5. The aircraft engine blade passage and profile measuring device according to claim 1, characterized in that: The end of the positioning nail (5) is pointed.

6. The aircraft engine blade passage and profile measuring device according to claim 1, characterized in that: One end of the channel measuring pin (14) that contacts the aeroengine blade is pointed.

7. The aircraft engine blade passage and profile measuring device according to claim 1, characterized in that: The end of the channel measuring pin (14) away from the aircraft engine blade is provided with a sinking platform (15).

8. The aircraft engine blade passage and profile measuring device according to claim 7, characterized in that: The extension length of the sinking platform (15) in the length direction of the channel measuring pin (14) is 0.2-0.5 mm.

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