Angle detection device for chord angle of turbine blade of aero-engine

Abstract

The utility model discloses an angle detection device for a chord angle of a turbine blade of an aero-engine, and belongs to the technical field of manufacturing of turbine blades of aero-engines. The device comprises a base, and the base is provided with a blade mounting part used for mounting the turbine blade of the aero-engine; the angle detection assembly comprises a vertical supporting plate and a rotation detection piece, the rotation detection piece comprises a stopping plate and an angle positioning pin, one end of the stopping plate is provided with a stopping straight edge, and the stopping straight edge is used for stopping the blade front edge and the blade rear edge of the aero-engine turbine blade; and the angle mark is provided with angle scales, and when the stop plate rotates, the angle positioning needle can point to the angle scales. According to the method, the blade chord angles of the blade front edge and the blade rear edge of the detection section of the aero-engine turbine blade can be detected, detection of the detection section of the aero-engine turbine blade is achieved, and evaluation of the quality of the aero-engine turbine blade is facilitated.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine turbine blade manufacturing technology, and in particular to an angle detection device for the chord angle of aero-engine turbine blades. Background Technology

[0002] Turbine blades are core components of aircraft engines. Operating in extremely complex environments with ultra-high temperatures and pressures, turbine blades endure complex mechanical stresses during aircraft start-up, shutdown, and changes in flight attitude. The performance of the turbine blades directly determines the engine's thrust, fuel consumption, and lifespan. The turbine blade body exhibits a three-dimensional spatial twist along its height, with significant differences in cross-sectional shape at different radii. This allows airflow to conform to the blade profile, reducing energy loss. During turbine blade production, the blade chord angle is a commonly used key testing parameter; whether the chord angle meets the specified range directly affects engine performance.

[0003] Currently, the chord angle of turbine blades is typically measured using a coordinate measuring machine (CMM). CMMs can precisely inspect the geometric dimensions, shape, and positional tolerances of turbine blades, and their high precision and automation make them a core tool for modern industrial quality control. However, CMMs are expensive, requiring significant investment in production costs, and are difficult to maintain, making them unsuitable for all companies. Furthermore, CMMs have strict requirements for ambient temperature and humidity, making them suitable for batch inspections of blades. In actual production, sending large quantities of blades to CMMs for chord angle inspection is inefficient and consumes excessive time and effort. Therefore, there is an urgent need for a device that facilitates rapid on-site inspection of the chord angle of aero-engine turbine blades. Summary of the Invention

[0004] The purpose of this invention is to overcome at least one deficiency of the prior art and provide an angle detection device for the chord angle of aero-engine turbine blades, which is beneficial for quickly detecting the chord angle of aero-engine turbine blades on the production site.

[0005] The technical solution of this utility model to solve the above-mentioned technical problems is as follows:

[0006] An angle detection device for the chord angle of aero-engine turbine blades according to this application includes:

[0007] A base, wherein the base is provided with a blade mounting part for suspending and mounting an aero-engine turbine blade, the blade mounting part protruding upward relative to the upper side of the base, and when the aero-engine turbine blade is mounted on the blade mounting part, the aero-engine turbine blade is suspended relative to the upper side of the base.

[0008] An angle detection assembly includes a vertical support plate and a rotation detection component. The vertical support plate is positioned opposite the leading and trailing edges of the aero-engine turbine blade fixed to the blade mounting portion. A concave curved surface is formed between the leading and trailing edges of the blade. The vertical support plate extends vertically upward to form an extension portion, which has a connecting arm facing the aero-engine turbine blade. The rotation detection component is rotatably mounted on a first side of the connecting arm. The rotation detection component includes a stop plate and an angle positioning pin. The stop plate has a stop edge at one end facing the concave curved surface of the blade, which is used to stop the leading and trailing edges of the aero-engine turbine blade. The end of the stop plate away from the concave curved surface of the blade is connected to the angle positioning pin.

[0009] An angle marker is provided on the extension and is located on the same side as the rotation detection element. The angle marker has an angle scale. When the stop straight edge rotates against the leading edge and trailing edge of the aero-engine turbine blade, the angle positioning pin can point to the angle scale on the angle marker.

[0010] The beneficial effects of this utility model are as follows: In this embodiment, the base is provided with a blade mounting part, on which the turbine blades of the aero-engine can be mounted. The rotating detection component includes a stop plate with a stop straight edge for stopping the leading and trailing edges of the aero-engine turbine blades. This facilitates using the stop straight edge as the blade chord line passing through the current detection section and tangent to the leading and trailing edges of the blades. Furthermore, it facilitates measuring the angle of the stop straight edge to measure the chord angle of the current detection section. Thus, the stop straight edge of the stop plate can be stopped against the detection section of the leading and trailing edges of the aero-engine turbine blades, causing the stop plate to rotate and driving the angle positioning needle to rotate. With the angled positioning pin rotated to point to the corresponding angle scale, the measurement personnel can obtain the blade chord angle of the current inspection section of the aero-engine turbine blade based on the position of the rotating angle positioning pin on the corresponding angle scale. Furthermore, the angle detection device for the chord angle of aero-engine turbine blades in this embodiment can be used to sequentially detect the blade chord angle of the leading edge and trailing edge of different inspection sections of the aero-engine turbine blade, thereby obtaining the blade chord angle of different inspection sections of the aero-engine turbine blade. This enables the inspection of the inspection section of the aero-engine turbine blade, which is beneficial for evaluating the quality of the aero-engine turbine blade.

[0011] In addition, based on the above technical solution, the present invention can be further improved as follows, and can also have the following additional technical features.

[0012] According to one embodiment of the present invention, the angle detection component further includes:

[0013] A horizontal positioning reference plate, wherein the first end of the horizontal positioning reference plate is connected to the lower side of the vertical support plate, the second end of the horizontal positioning reference plate extends toward one side of the concave curved surface of the blade to form an extended support end, and the extended support end passes through the clearance channel formed between the lower end of the aero-engine turbine blade and the upper side of the base, and the lower side of the horizontal positioning reference plate is provided with a horizontal positioning reference surface.

[0014] In this embodiment, the lower side of the horizontal positioning reference plate is provided with a horizontal positioning reference surface, which makes it easy to place the horizontal positioning reference surface horizontally against the upper side of the base. Thus, the lower side of the horizontal positioning reference plate can be used as an angle reference surface on the angle mark, or as an angle reference surface for the chord line tangent to the leading edge and trailing edge of the blade. This is beneficial for obtaining the blade chord angle of different test sections of the aero-engine turbine blade, thereby facilitating accurate detection of the test section of the aero-engine turbine blade.

[0015] According to one embodiment of the present invention, the angle detection device for the chord angle of aero-engine turbine blades further includes:

[0016] A horizontal reference rail is installed on the upper side of the base and located on the first side of the aero-engine turbine blade fixed to the blade mounting part, and the horizontal reference rail is set parallel to the blade length direction of the aero-engine turbine blade fixed to the blade mounting part.

[0017] The second horizontal reference rail is installed on the upper side of the base and located on the second side of the aero-engine turbine blade fixed on the blade mounting part. The second horizontal reference rail is set parallel to the first horizontal reference rail, and the upper sides of the first horizontal reference rail and the second horizontal reference rail are set coplanarly to form a horizontal placement reference surface.

[0018] In this embodiment, the upper sides of horizontal reference rail one and horizontal reference rail two are coplanar to form a horizontal placement reference surface. This facilitates the horizontal positioning reference surface to be placed horizontally against the horizontal placement reference surface, making the horizontal positioning reference surface horizontal. Thus, the lower side of the horizontal positioning reference plate can be used as an angle reference surface on the angle mark, or as an angle reference surface for the chord lines tangent to the leading and trailing edges of the blade. This is beneficial for obtaining the blade chord angle of different detection sections of the aero-engine turbine blade, thereby facilitating accurate detection of the detection sections of the aero-engine turbine blade.

[0019] According to one embodiment of the present invention, a first protrusion is provided on the lower side of the first end of the horizontal positioning reference plate, and the lower side of the first protrusion forms a first positioning reference surface; a second protrusion is provided on the lower side of the second end of the horizontal positioning reference plate, and the lower side of the second protrusion forms a second positioning reference surface; the first positioning reference surface and the second positioning reference surface are coplanar to form the horizontal positioning reference surface.

[0020] In this embodiment, by providing a first protrusion and a second protrusion, an avoidance groove can be formed between the first protrusion and the second protrusion, reducing the area of ​​the horizontal positioning reference surface. When the horizontal positioning reference plate is placed on the upper side of the base, only the first positioning reference surface and the second positioning reference surface are in contact with the upper side of the base. Therefore, it is only necessary to ensure the machining accuracy of the first positioning reference surface and the second positioning reference surface, and there is no need to perform fine machining on the bottom surface of the horizontal positioning reference plate, reducing the amount of machining required for fine machining and lowering the machining cost.

[0021] According to one embodiment of the present invention, the first side of the angle positioning pin is disposed away from the first side of the connecting arm, the second side of the angle positioning pin is disposed close to the first side of the connecting arm, the second side of the stop plate and the second side of the angle positioning pin are both disposed in contact with the first side of the connecting arm, and the first side of the stop plate and the first side of the angle positioning pin are both coplanar with the first side of the horizontal positioning reference plate.

[0022] In this embodiment, the second side of the stop plate and the second side of the angle positioning pin are both fitted to the first side of the connecting arm, which facilitates the stop plate and the angle positioning pin to rotate against the first side of the connecting arm when rotating, thereby improving the rotation accuracy and thus improving the angle detection accuracy of the chord angle of the turbine blade of the aero-engine; furthermore, the first side of the stop plate and the first side of the angle positioning pin are both coplanar with the first side of the horizontal positioning reference plate, avoiding interference between the stop plate and the angle positioning pin and other components located outside the first side of the horizontal positioning reference plate when rotating.

[0023] According to one embodiment of the present invention, the angle detection device for the chord angle of aero-engine turbine blades further includes:

[0024] The locating pins are provided in multiple pairs. The multiple pairs of locating pins are installed at intervals on the base along the length direction of the aero-engine turbine blade fixed on the blade mounting part. The two locating pins arranged in pairs are located on both sides of the aero-engine turbine blade in a direction perpendicular to the aero-engine turbine blade. The locating pins are provided with a vertical locating plane that fits against the first side of the horizontal locating reference plate.

[0025] In this embodiment, by installing multiple pairs of positioning pins at intervals on the base, the chord angle of multiple selected detection sections on the blade of the aero-engine turbine can be detected. The vertical positioning plane is in contact with the first side of the horizontal positioning reference plate, which improves the contact accuracy and facilitates more precise selection of the detection sections of the aero-engine turbine blade, thereby improving the accuracy of the chord angle detection.

[0026] According to one embodiment of the present invention, the blade mounting portion includes:

[0027] A tenon support block is installed on the upper side of the base and protrudes upward. The tenon support block is provided with a tenon limiting support part for the turbine blade of the aero-engine.

[0028] The blade crown support block is mounted on the upper side of the base and protrudes upward, opposite to the tenon support block. The blade crown support block is provided with the blade crown limiting support part of the aero-engine turbine blade. The tenon limiting support part and the blade crown limiting support part can be used to fix the aero-engine turbine blade and make the aero-engine turbine blade suspended relative to the upper side of the base.

[0029] The blade mounting section in this embodiment includes a tenon support block and a blade crown support block. The tenon limiting support block and the blade crown limiting support block suspend and fix the upper side of the aero-engine turbine blade relative to the base. This ensures that when the aero-engine turbine blade is stopped by the stop plate on the angle detection component, the aero-engine turbine blade will not deviate. This is beneficial for the angle detection component to detect the chord angle of the aero-engine turbine blade and improve the accuracy of the chord angle detection.

[0030] According to one embodiment of the present invention, the blade mounting portion further includes:

[0031] A blade locking assembly is movably connected to the base and positioned opposite the concave curved surface of the blade. The blade locking assembly has a locking position and an unlocking position relative to the concave curved surface of the blade. When the blade locking assembly is in the locking position, it locks the aero-engine turbine blade fixed to the blade mounting portion. When the blade locking assembly is in the unlocking position, it releases the locking of the aero-engine turbine blade fixed to the blade mounting portion.

[0032] In this embodiment, a blade locking assembly is movably connected to the base. When the blade locking assembly is in the locked position, it can work together with the tenon support block and the blade crown support block to further lock and fix the aero-engine turbine blade. When detecting the chord angle of the aero-engine turbine blade, it avoids displacement of the turbine blade that may cause measurement errors. This is beneficial for the angle detection assembly to detect the chord angle of the aero-engine turbine blade and improves the accuracy of the chord angle detection.

[0033] According to one embodiment of the present invention, the angle detection device for the chord angle of aero-engine turbine blades further includes:

[0034] The blade crown limiting block is installed on the upper side of the base near the blade crown support block and protrudes upward to form an extended limiting part. The extended limiting part is arranged opposite to the leading edge and trailing edge of the aero-engine turbine blade fixed on the blade mounting part. The extended limiting part is provided with multiple pin holes, and the opening direction of the multiple pin holes is the same as the length direction of the blade body.

[0035] Multiple movable limit pins are provided and are installed in the pin holes in a one-to-one correspondence. The side of the movable limit pin facing the blade crown can stop and limit the blade crown.

[0036] In this embodiment, an extended limiting portion on the blade crown limiting block on the base is used to stop and limit the side of the aero-engine turbine blade away from the leading and trailing edges of the blade. When the chord angle of the aero-engine turbine blade is measured, and the stopping plate abuts against the leading and trailing edges of the blade, the extended limiting portion can block the aero-engine turbine blade, preventing it from moving towards the side away from the leading and trailing edges. Furthermore, one end of the movable limiting pin is installed in the pin hole, and the other end stops and limits the crown portion of the aero-engine turbine blade. The extended limiting portion and the movable limiting pin can jointly limit the crown portion of the aero-engine turbine blade, improving the installation accuracy of the aero-engine turbine blade. This facilitates the angle detection component in detecting the chord angle of the aero-engine turbine blade, improving the accuracy of the chord angle detection.

[0037] According to one embodiment of the present invention, the extended limiting portion is provided with a blade side stop straight edge on one side of the leading edge and trailing edge of the aero-engine turbine blade fixed on the blade mounting portion, and the blade side stop straight edge can stop against the back side of the leading edge and trailing edge of the aero-engine turbine blade fixed on the blade mounting portion.

[0038] In this embodiment, by providing a blade side stop straight edge on the extended limiting part, the blade side stop straight edge can limit the aero-engine turbine blade in the lateral direction when installing the aero-engine turbine blade, which is beneficial to the installation accuracy of the aero-engine turbine blade, thereby facilitating more accurate detection of the chord angle of the aero-engine turbine blade. Furthermore, when installing the aero-engine turbine blade, only the blade side stop straight edge and the aero-engine turbine blade stop are required, so it is only necessary to ensure the machining accuracy of the blade side stop straight edge, without the need to perform finishing on other parts of the extended limiting part, reducing the amount of finishing work and lowering the machining cost.

[0039] According to one embodiment of the present invention, the stop plate has an inclined clearance surface at its second end along the length direction of the horizontal positioning reference plate. The inclined clearance surface is inclined from the second side of the stop plate to the first side of the stop plate, and the inclined clearance surface and the first side of the stop plate define the stop straight edge.

[0040] In this embodiment, the inclined clearance surface and the first side surface of the stop plate define the stop edge. The stop edge has a small area. When the stop edge abuts against the leading edge and trailing edge of the aero-engine turbine blade, only the stop edge abuts against the leading edge and trailing edge of the aero-engine turbine blade. Therefore, it is only necessary to ensure the machining accuracy of the stop edge, and there is no need to perform finishing on other parts of the stop plate, reducing the amount of finishing work and lowering the machining cost. Furthermore, when the stop edge abuts against the aero-engine turbine blade, it helps to reduce the contact area between the stop edge and the leading edge and trailing edge of the aero-engine turbine blade, thereby helping to reduce the detection error of the chord angle of the aero-engine turbine blade and improve the detection accuracy of the chord angle. Attached Figure Description

[0041] To more clearly illustrate the technical solutions in this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0042] Figure 1 This is a schematic diagram of the structure of the angle detection device for the chord angle of aero-engine turbine blades according to an embodiment of the present invention;

[0043] Figure 2 for Figure 1 The front view after straightening;

[0044] Figure 3 for Figure 2 The left view;

[0045] Figure 4 for Figure 2 Top view;

[0046] Figure 5 This is a schematic diagram of the angle detection component in an embodiment of the present invention;

[0047] Figure 6 for Figure 5 The right view;

[0048] Figure 7 This is a schematic diagram of the rotation detection element in an embodiment of the present utility model;

[0049] Figure 8 This is a schematic diagram showing that the chord of a detection section obtained by cutting along the width direction of the turbine blade of an aero-engine in an embodiment of this application is tangent to the leading edge and trailing edge of the blade. Detailed Implementation

[0050] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0051] To better understand the above-mentioned objectives, features, and advantages of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0052] Many specific details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Therefore, the scope of protection of the present invention is not limited to the specific embodiments disclosed below.

[0053] This application provides an angle detection device for the chord angle of turbine blades in aero-engines, such as... Figures 1 to 8 As shown, it includes:

[0054] The base 1 is provided with a blade mounting part for suspending the turbine blade of the aero-engine. The blade mounting part protrudes upward relative to the upper side of the base 1. When the turbine blade 3 of the aero-engine is mounted on the blade mounting part, the turbine blade 3 of the aero-engine is suspended relative to the upper side of the base 1.

[0055] Angle detection component 2 includes a vertical support plate 21 and a rotation detection component. The vertical support plate 21 is positioned directly opposite the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3, which is fixed to the blade mounting section. A concave curved surface of the blade body 32 is formed between the leading edge 321 and the trailing edge 322. The vertical support plate 21 extends vertically upward to form an extension, and a connecting arm 22 is provided on the extension facing the aero-engine turbine blade 3. The rotation detection component is rotatably mounted on the first side of the connecting arm 22. The rotation detection component includes a stop plate 23 and an angle positioning pin 24. The stop plate 23 has a stop straight edge 231 at one end facing the concave curved surface of the blade body 32, which is used to stop the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3. The end of the stop plate 23 away from the concave curved surface of the blade body 32 is connected to the angle positioning pin 24.

[0056] Angle mark 27 is provided on the extension and is located on the same side as the rotation detection element. Angle mark 27 is provided with angle scale. When the stop straight edge 231 rotates by stopping the leading edge 321 and trailing edge 322 of the turbine blade 3 of the aircraft engine, the angle positioning pin 24 can point to the angle scale on angle mark 27.

[0057] In this embodiment, as Figures 1 to 8As shown, the base 1 in this embodiment is provided with a blade mounting part, on which the aero-engine turbine blade 3 can be mounted. The rotating detection component includes a stop plate 23 with a stop straight edge 231 for stopping the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3. This is beneficial because the stop straight edge 231 is used as a chord line 34 passing through the current detection section and tangent to the leading edge 321 and trailing edge 322 of the blade. This facilitates the measurement of the angle of the stop straight edge 231 to measure the chord angle of the current detection section. Thus, the stop straight edge 231 of the stop plate 23 can be stopped against the detection section of the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3, causing the stop plate 23 to rotate and drive the angle. The positioning pin 24 rotates by an equal angle, and the rotated angle positioning pin 24 points to the corresponding angle scale. The measurement personnel can obtain the blade chord angle of the current detection section of the aero-engine turbine blade 3 according to the corresponding angle scale position on the angle mark 27 after the rotation of the angle positioning pin 24. Furthermore, the angle detection device for the chord angle of the aero-engine turbine blade 3 in this embodiment can be used to sequentially detect the blade chord angle of the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3 at different detection sections to obtain the blade chord angle of the aero-engine turbine blade 3 at different detection sections, thereby realizing the detection of the detection section of the aero-engine turbine blade 3, which is beneficial for the quality evaluation of the aero-engine turbine blade 3.

[0058] In this embodiment, as Figures 1 to 4 As shown, the base 1 in this embodiment has a rectangular plate structure. The lower side of the base 1 is provided with a mounting groove with an open lower side. The left side plate of the base 1 is provided with a handheld port 191 communicating with the mounting groove, and the right side plate of the base 1 is provided with a handheld port 192 communicating with the mounting cavity. The handheld port 191 and the handheld port 192 are arranged opposite each other. The upper side of the base 1 is provided with a mounting positioning reference pin 18 for mounting and positioning the blade mounting part.

[0059] Furthermore, such as Figures 1 to 8As shown, in this embodiment, the rotation detection component has a T-shaped structure and is detachably mounted on the first side of the connecting arm 22. The connecting arm 22 is provided with a rotation pin hole 221. The horizontal edge of the rotation detection component is machined to form a stop straight edge 231. The rotation detection component is rotatably mounted on the vertical edge, with the rotation center close to the middle position of the stop straight edge 231. A connecting hole 242 is provided at the rotation center. Rotation is achieved by the rotation connecting pin 212 cooperating with the rotation pin hole 221 and the connecting hole 242. The width of the stop straight edge 231 on the stop plate 23 can be in the range of 0.1mm-0.55mm. The angle positioning pin 24 has a long plate-like structure. The end of the pin 24 away from the stop plate 23 extends away from the stop plate 23 to form an indicator tip 241. The indicator tip 241 can point to the angle scale on the angle mark 27. By providing the indicator tip 241 on the angle positioning pin 24, when the stop straight edge 231 of the stop plate 23 is stopped against the cross section to be tested of the leading edge 321 and trailing edge 322 of the turbine blade 3 of the aero-engine, the stop plate 23 rotates and drives the angle positioning pin 24 to rotate by an equal angle. After rotation, the angle positioning pin 24 points to the corresponding angle scale. The indicator tip 241 can point to the precise angle scale, which makes it easy for the staff to read the angle currently pointed to by the indicator tip 241.

[0060] Furthermore, such as Figures 1 to 4 As shown, the turbine blade 3 of the aero-engine in this embodiment includes a tenon 31, a blade crown 33 and a blade body 32, with the blade body 32 connected between the tenon 31 and the blade crown 33.

[0061] One embodiment of this utility model is as follows: Figures 1 to 6 As shown, the angle detection component 2 also includes:

[0062] The horizontal positioning reference plate 25 has its first end connected to the lower side of the vertical support plate 21, and its second end extends toward the side of the concave curved surface of the blade 32 to form an extended support end. The extended support end passes through the clearance channel formed between the lower end of the aero-engine turbine blade 3 and the upper side of the base 1. The lower side of the horizontal positioning reference plate 25 is provided with a horizontal positioning reference surface.

[0063] In this embodiment, as Figures 1 to 6As shown, in this embodiment, the lower side of the horizontal positioning reference plate 25 is provided with a horizontal positioning reference surface, which makes it easy to place the horizontal positioning reference surface horizontally against the upper side of the base 1. Thus, the lower side of the horizontal positioning reference plate 25 can be used as the angle reference surface on the angle mark 27, or as the angle reference surface of the chord line tangent to the leading edge 321 and trailing edge 322 of the blade. This is beneficial for obtaining the blade chord angle of different detection sections of the aero-engine turbine blade 3, thereby facilitating accurate detection of the detection section of the aero-engine turbine blade 3.

[0064] Furthermore, such as Figures 1 to 6 As shown, the vertical support plate 21 is vertically connected to one side of the upper side of the horizontal positioning reference plate 25. The upper side of the horizontal positioning reference plate 25 and the side of the vertical support plate 21 facing the rotation detection member form a rotation avoidance groove 26, and the rotation detection member can rotate within the rotation avoidance groove 26.

[0065] One embodiment of this utility model is as follows: Figures 1 to 4 As shown, the angle detection device for the chord angle of aero-engine turbine blades also includes:

[0066] The horizontal reference rail 10 is installed on the side of the base 1 and located on the first side of the aero-engine turbine blade 3 fixed on the blade mounting part. The horizontal reference rail 10 is set parallel to the length direction of the blade body 32 of the aero-engine turbine blade 3 fixed on the blade mounting part.

[0067] Horizontal reference rail 2 11 is installed on the upper side of the base 1 and located on the second side of the aero-engine turbine blade 3 fixed on the blade mounting part. Horizontal reference rail 2 11 is set parallel to horizontal reference rail 10. The upper sides of horizontal reference rail 10 and horizontal reference rail 2 11 are set coplanarly to form a horizontal placement reference surface.

[0068] In this embodiment, as Figures 1 to 6 As shown, in this embodiment, the upper side of the horizontal reference rail 10 and the upper side of the horizontal reference rail 11 are coplanar to form a horizontal placement reference surface, which facilitates the horizontal positioning reference surface to be placed horizontally against the horizontal placement reference surface, making the horizontal positioning reference surface horizontal. Thus, the lower side of the horizontal positioning reference plate 25 can be used as the angle reference surface on the angle mark 27, and the lower side of the horizontal positioning reference plate 25 can also be used as the angle reference surface of the chord line tangent to the leading edge 321 and the trailing edge 322 of the blade. This is beneficial for obtaining the blade chord angle of different detection sections of the aero-engine turbine blade 3, thereby facilitating the accurate detection of the detection section of the aero-engine turbine blade 3.

[0069] One embodiment of this utility model is as follows: Figures 1 to 6As shown, a first protrusion 251 is provided on the lower side of the first end of the horizontal positioning reference plate 25, and the lower side of the first protrusion 251 forms a first positioning reference surface; a second protrusion 252 is provided on the lower side of the second end of the horizontal positioning reference plate 25, and the lower side of the second protrusion 252 forms a second positioning reference surface. The first positioning reference surface and the second positioning reference surface are coplanar to form a horizontal positioning reference surface.

[0070] In this embodiment, as Figures 1 to 6 As shown, in this embodiment, by providing a first protrusion 251 and a second protrusion 252, an avoidance groove can be formed between the first protrusion 251 and the second protrusion 252, reducing the area of ​​the horizontal positioning reference surface. When the horizontal positioning reference plate 25 is placed on the upper side of the base 1, only the first positioning reference surface and the second positioning reference surface are in contact with the upper side of the base 1. Therefore, it is only necessary to ensure the machining accuracy of the first positioning reference surface and the second positioning reference surface, and there is no need to perform fine machining on the bottom surface of the horizontal positioning reference plate 25, reducing the amount of machining required for fine machining and lowering the machining cost.

[0071] One embodiment of this utility model is as follows: Figures 1 to 6 As shown, the first side of the angle positioning pin 24 is set away from the first side of the connecting arm 22, the second side of the angle positioning pin 24 is set close to the first side of the connecting arm 22, the second side of the stop plate 23 and the second side of the angle positioning pin 24 are both set in contact with the first side of the connecting arm 22, and the first side of the stop plate 23 and the first side of the angle positioning pin 24 are both set on the same plane as the first side of the horizontal positioning reference plate 25.

[0072] In this embodiment, as Figures 1 to 6 As shown, in this embodiment, the second side of the stop plate 23 and the second side of the angle positioning pin 24 are both fitted to the first side of the connecting arm 22, which facilitates the stop plate 23 and the angle positioning pin 24 to rotate against the first side of the connecting arm 22 when rotating, thereby improving the rotation accuracy and thus improving the angle detection accuracy of the chord angle of the turbine blade 3 of the aero-engine; furthermore, the first side of the stop plate 23 and the first side of the angle positioning pin 24 are both coplanar with the first side of the horizontal positioning reference plate 25, avoiding interference between the stop plate 23 and the angle positioning pin 24 and other components located outside the first side of the horizontal positioning reference plate 25 when rotating.

[0073] One embodiment of this utility model is as follows: Figures 1 to 6 As shown, the angle detection device for the chord angle of aero-engine turbine blades also includes:

[0074] The positioning pins 16 are provided in multiple pairs. The multiple pairs of positioning pins 16 are installed on the base 1 at intervals along the length direction of the aero-engine turbine blade 3 fixed on the blade mounting part. The two positioning pins 16 arranged in pairs are located on both sides of the aero-engine turbine blade 3 in a direction perpendicular to the aero-engine turbine blade 3. The positioning pins 16 are provided with a vertical positioning plane 161 that fits against the first side of the horizontal positioning reference plate 25.

[0075] In this embodiment, as Figures 1 to 6 As shown, in this embodiment, by installing multiple pairs of positioning pins 16 at intervals on the base 1, the chord angle of multiple selected detection sections on the blade body 32 of the aero-engine turbine blade 3 can be detected. The vertical positioning plane 161 is in contact with the first side of the horizontal positioning reference plate 25, which improves the contact accuracy and facilitates more accurate selection of the detection section of the aero-engine turbine blade 3, thereby improving the accuracy of the chord angle detection.

[0076] In this embodiment, as Figures 1 to 8 As shown, six pairs of locating pins 16 are installed at intervals on the base 1. The vertical locating planes 161 on the same pair of locating pins 16 that are in contact with the first side of the horizontal locating reference plate 25 are coplanar. The aero-engine turbine blade 3 has six sections to be inspected. Each section to be inspected on the aero-engine turbine blade 3 corresponds one-to-one with the vertical locating planes 161 on each pair of locating pins 16. Multiple inspection sections of the standard turbine blade correspond one-to-one with multiple inspection sections at the position of the aero-engine turbine blade 3. Multiple inspection sections are selected at intervals along the extension direction of the blade body of the standard turbine blade. For example, in a certain model of standard turbine blade, the blade body extends from the standard turbine blade... Starting from the blade crown position, six test sections, L1-L6, are selected sequentially. The distance from section L1 to the blade crown end face is 14.00 mm, the distance from section L1 to section L2 is 19.20 mm, the distance from section L2 to section L3 is 24.50 mm, the distance from section L3 to section L4 is 26.50 mm, the distance from section L4 to section L5 is 28.30 mm, and the distance from section L5 to section L6 is 29.00 mm. If section L1 is the first test section, then section L1 is used as the current test section. Any one of the standard turbine blade sections L2-L6 can be regarded as the next test section.

[0077] In this embodiment, as Figures 1 to 8As shown, taking section L1 as an example, if the standard chord angle of section L1 of a standard turbine blade is 35.6°, and the allowable error range is ±1.0°, when the chord angle of section L1 of the aero-engine turbine blade 3 is greater than or equal to 34.6° and less than or equal to 36.6°, then section L1 of the aero-engine turbine blade 3 is judged to have a qualified chord angle; while when the chord angle of section L1 is less than 34.6° or greater than 36.6°, then section L1 of the aero-engine turbine blade 3 is judged to have an unqualified chord angle. Furthermore, based on the obtained chord angle error, the chord angle of the currently inspected section can be sequentially determined to be qualified, and other calculation or judgment methods can also be used.

[0078] Furthermore, such as Figure 8 As shown, in this embodiment, the angle formed between the chord 34 of the detection section and the X-axis is taken as the chord angle of the detection section. The chord angle of the detection section can also be selected as a reference axis as needed.

[0079] It should be noted that the multiple detection sections of the blade body 32 of the turbine blade 3 can be set according to the measurement and detection needs of the turbine blade 3, the spacing between two adjacent detection sections can also be set according to the measurement and detection needs of the turbine blade 3, and the number of detection sections can also be adjusted according to the measurement and detection needs of the turbine blade 3.

[0080] In this embodiment, as Figures 1 to 8 As shown, the angle detection device for the chord angle of aero-engine turbine blades in this embodiment is used to measure and detect multiple test sections of a standard turbine blade to obtain the standard measured chord angle of the multiple test sections of the standard turbine blade. Then, the angle detection device for the chord angle of aero-engine turbine blades in this embodiment is used to measure and detect multiple test sections of aero-engine turbine blade 3. The obtained chord angles of the multiple test sections of aero-engine turbine blade 3 are compared with the standard measured chord angles of the corresponding multiple test sections of the standard turbine blade. The same angle detection device for the chord angle of aero-engine turbine blades can be used again for measurement and detection, which helps to offset the influence of the error caused by the accuracy of the angle detection device for the chord angle of aero-engine turbine blades itself.

[0081] One embodiment of this utility model is as follows: Figures 1 to 4 As shown, the blade mounting section includes:

[0082] The tenon support block 12 is installed on the upper side of the base 1 and protrudes upward. The tenon support block 12 is provided with a tenon limiting support part 121 for the turbine blade 3 of the aircraft engine.

[0083] The blade crown support block 13 is installed on the upper side of the base 1 opposite to the tenon support block 12 and protrudes upward. The blade crown support block 13 is provided with a blade crown limiting support for the aero-engine turbine blade 3. The tenon limiting support 121 and the blade crown limiting support can be used to fix the aero-engine turbine blade 3 and make the aero-engine turbine blade 3 suspended relative to the upper side of the base 1.

[0084] In this embodiment, as Figures 1 to 4 As shown, the blade mounting part in this embodiment includes a tenon support block 12 and a blade crown support block 13. The tenon limiting support part 121 and the blade crown limiting support part 13 suspend and fix the aero-engine turbine blade 3 relative to the upper side of the base 1. This makes it easy for the aero-engine turbine blade 3 to not deviate when the stop plate 23 on the angle detection component 2 stops it. This is beneficial for the angle detection component 2 to detect the chord angle of the aero-engine turbine blade 3 and improve the accuracy of the chord angle detection.

[0085] In this embodiment, as Figures 1 to 4 As shown, in this embodiment, the left end of the upper side of the base 1 and the tenon support block 12 are connected and fixed by screws. The tenon 31 of the aero-engine turbine blade 3 is horizontally supported by the tenon support protrusion 122 on the tenon support block 12. The tenon support protrusion 122 can also limit the tenon 31. The rear part of the tenon support block 12 is provided with a tenon limiting support part 121. The tenon 31 of the aero-engine turbine blade 3 is positioned by the tenon limiting support part 121. Furthermore, the right end of the upper side of the base 1 and the blade crown support block 13 are connected and fixed by screws. The blade crown 33 of the aero-engine turbine blade 3 is horizontally supported by the blade crown support protrusion 131 on the blade crown support block 13. The blade crown support protrusion 131 can also limit the blade crown 33. The blade crown support block 13 and the tenon support block 12 are arranged opposite each other.

[0086] One embodiment of this utility model is as follows: Figures 1 to 4 As shown, the blade mounting section also includes:

[0087] The blade locking assembly is movably connected to the base 1 and is positioned opposite the recessed curved surface of the blade 32. The blade locking assembly has a locking position and an unlocking position relative to the recessed curved surface of the blade 32. When the blade locking assembly is in the locking position, it can lock the aero-engine turbine blade 3 fixed on the blade mounting part; when the blade locking assembly is in the unlocking position, it releases the locking of the aero-engine turbine blade 3 fixed on the blade mounting part.

[0088] In this embodiment, as Figures 1 to 4As shown, in this embodiment, a blade locking assembly is movably connected to the base 1. When the blade locking assembly is in the locked position, it can work together with the tenon support block 12 and the blade crown support block 13 to further lock and fix the aero-engine turbine blade 3. When detecting the chord angle of the aero-engine turbine blade 3, it avoids displacement of the blade body 32 of the aero-engine turbine blade 3, which would cause measurement errors. This is beneficial for the angle detection assembly 2 to detect the chord angle of the aero-engine turbine blade 3 and improve the accuracy of the chord angle detection.

[0089] In this embodiment, as Figures 1 to 4 As shown, in order to limit the front side of the blade body 32 of the aero-engine turbine blade 3, a blade locking assembly is installed on the base 1. The blade locking assembly is used to limit the front side of the blade body 32 of the aero-engine turbine blade 3. The blade locking assembly includes a locking stop arm 15, a thrust control knob 151, and a tension spring 152. The locking stop arm 15 is approximately L-shaped and includes a vertical plate and a stop portion. The stop portion is used to abut against the recessed front sidewall of the blade body 32. The recessed front sidewall of body 32 has an arc-shaped stop. The upper side of the base 1 has a locking member movable passage 17 at the front end. The locking member movable passage 17 is vertically opened and communicates with the mounting groove. The vertical plate of the locking stop swing arm 15 passes through the locking member movable passage 17. The lower end of the vertical plate of the locking stop swing arm 15 is hinged to the lower end of the base 1 and located in the mounting groove. The front side of the vertical plate of the locking stop swing arm 15 is also connected to one end of the tension spring 152. The other end of the tension spring 152 is connected to the front sidewall of the mounting groove.

[0090] Furthermore, such as Figures 1 to 4As shown, in this embodiment, the locking stop arm 15 is adjusted in position by the thrust control knob 151, so that the locking stop arm 15 stops or releases from the blade body 32 of the aero-engine turbine blade 3. Specifically, a threaded through hole is provided on the front side wall of the base 1. The thrust control knob 151 includes a thrust threaded rod and a control knob. The thrust threaded rod and the control knob are connected. The thrust threaded rod is threadedly connected to the threaded through hole provided on the front side wall of the base 1. The threaded through hole is located above the tension spring 152. The thrust threaded rod extends into the mounting groove provided on the lower side of the base 1 and stops at the front side of the vertical plate of the locking stop arm 15. Furthermore, when the thrust control knob 151 is turned, the thrust thread of the thrust control knob 151 is engaged. The rod is rotated backward, and the thrust threaded rod pushes the locking stop arm 15 backward, causing it to swing backward within the movable opening 17 of the locking member. This causes the stop portion of the locking stop arm 15 to abut against the recessed front sidewall of the aero-engine turbine blade 3. Thus, in this embodiment, the aero-engine turbine blade 3 is jointly fixed by the tenon support block 12, the blade crown support block 13, and the locking stop arm 15. In addition, when it is necessary to remove the aero-engine turbine blade 3, the thrust control knob 151 is turned in the opposite direction, causing the thrust threaded rod of the thrust control knob 151 to rotate forward. Under the tension of the tension spring 152, the thrust threaded rod swings forward within the movable clearance opening and releases the pushing action on the locking stop arm 15, thereby releasing the fixation of the aero-engine turbine blade 3.

[0091] It should be noted that the structure of the base 1 in this embodiment can be varied, and the way the turbine blade 3 of the aero-engine placed on the base 1 can also be varied. This makes it easy to achieve the goal of stopping the straight edge 231 of the stop plate 23 against the leading edge 321 and trailing edge 322 of the detection section of the turbine blade 3, so as to sequentially measure and detect multiple detection sections of the turbine blade 3 and obtain the chord angle of multiple detection sections of the turbine blade 3.

[0092] One embodiment of this utility model is as follows: Figures 1 to 4 As shown, the angle detection device for the chord angle of aero-engine turbine blades also includes:

[0093] The blade crown limiting block 14 is mounted on the upper side of the base 1 near the blade crown support block 13 and protrudes upward to form an extended limiting part 141. The extended limiting part 141 is set opposite to the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3 fixed on the blade mounting part. The extended limiting part 141 is provided with a plurality of pin holes 143, and the opening direction of the plurality of pin holes 143 is the same as the length direction of the blade body 32.

[0094] Multiple movable limit pins 142 are provided and are installed in the pin holes 143 in a one-to-one correspondence. The movable limit pins 142 on the side facing the blade crown 33 can stop and limit the blade crown 33.

[0095] In this embodiment, as Figures 1 to 4 As shown, in this embodiment, the extended limiting portion 141 on the blade crown limiting block 14 on the base 1 stops and limits the side of the aero-engine turbine blade 3 away from the leading edge 321 and trailing edge 322. When the chord angle of the aero-engine turbine blade 3 is measured, and when the stop plate 23 abuts against the leading edge 321 and trailing edge 322, the extended limiting portion 141 can block the aero-engine turbine blade 3, preventing the aero-engine turbine blade 3 from facing away from the leading edge 321 and trailing edge 322. The trailing edge 322 of the blade moves to one side; furthermore, one end of the movable limiting pin 142 is installed in the pin hole 143, and the other end stops and limits the crown 33 part of the aero-engine turbine blade 3. The extended limiting part 141 and the movable limiting pin 142 can jointly limit the crown 33 part of the aero-engine turbine blade 3, improve the installation accuracy of the aero-engine turbine blade 3, thereby facilitating the angle detection component 2 to detect the chord angle of the aero-engine turbine blade 3 and improve the chord angle detection accuracy.

[0096] In this embodiment, as Figures 1 to 4 As shown, in this embodiment, the leaf crown limiting block 14 is installed on the right end of the upper side of the base 1 by bolts. The leaf crown limiting block 14 is located on the left side of the leaf crown support block 13, and the rear side of the right end of the leaf body 32 is stopped and limited by the leaf crown limiting block 14.

[0097] One embodiment of this utility model is as follows: Figures 1 to 4 As shown, the extended limiting part 141 has a blade side stop straight edge 144 on one side of the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3 fixed on the blade mounting part. The blade side stop straight edge 144 can stop against the back of the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3 fixed on the blade mounting part.

[0098] In this embodiment, as Figures 1 to 4As shown, in this embodiment, by providing a blade side stop straight edge 144 on the extended limiting part 141, when installing the aero-engine turbine blade 3, the blade side stop straight edge 144 can limit the aero-engine turbine blade 3 in the lateral direction, which is beneficial to the installation accuracy of the aero-engine turbine blade 3, thereby facilitating more accurate detection of the chord angle of the aero-engine turbine blade 3; furthermore, when installing the aero-engine turbine blade 3, only the blade side stop straight edge 144 and the aero-engine turbine blade stop are needed, so that only the machining accuracy of the blade side stop straight edge 144 needs to be ensured, and other parts on the extended limiting part 141 do not need to be precision machined, reducing the amount of precision machining and lowering the machining cost.

[0099] One embodiment of this utility model is as follows: Figures 1 to 7 As shown, the stop plate 23 has an inclined clearance surface at its second end along the length direction of the horizontal positioning reference plate 25. The inclined clearance surface is inclined from the second side of the stop plate 23 to the first side of the stop plate 23, and a stop straight edge 231 is defined between the inclined clearance surface and the first side of the stop plate 23.

[0100] In this embodiment, as Figures 1 to 7 As shown, in this embodiment, a stop edge 231 is formed between the inclined clearance surface and the first side surface of the stop plate 23. The stop edge 231 has a small area. When the stop edge 231 abuts against the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3, only the stop edge 231 abuts against the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3. Therefore, it is only necessary to ensure the machining accuracy of the stop edge 231, and there is no need to perform finishing on other parts of the stop plate 23, thereby reducing the amount of finishing work and reducing the machining cost. Furthermore, when the stop edge 231 abuts against the aero-engine turbine blade 3, it is beneficial to reduce the contact area between the stop edge 231 and the leading edge 321 and trailing edge 322 of the aero-engine turbine blade 3, thereby reducing the detection error of the chord angle of the aero-engine turbine blade 3 and improving the detection accuracy of the chord angle.

[0101] In addition to the technical solutions disclosed in this embodiment, other structures of the aero-engine turbine blades in this utility model and their working principles can be referred to conventional technical solutions in this technical field. However, these conventional technical solutions are not the focus of this utility model, and will not be described in detail here.

[0102] In this utility model, the term "multiple" refers to two or more unless otherwise explicitly defined. The terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; "linking" can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0103] In the description of this utility model, it should be understood that the terms "upper", "lower", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or unit referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0104] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0105] The above are merely preferred embodiments of this application and are not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. An angle detection device for the chord angle of aero-engine turbine blades, characterized in that, include: A base, wherein the base is provided with a blade mounting part for suspending and mounting an aero-engine turbine blade, the blade mounting part protruding upward relative to the upper side of the base, and when the aero-engine turbine blade is mounted on the blade mounting part, the aero-engine turbine blade is suspended relative to the upper side of the base. An angle detection assembly includes a vertical support plate and a rotation detection component. The vertical support plate is positioned opposite the leading and trailing edges of the aero-engine turbine blade fixed to the blade mounting portion. A concave curved surface is formed between the leading and trailing edges of the blade. The vertical support plate extends vertically upward to form an extension portion, which has a connecting arm facing the aero-engine turbine blade. The rotation detection component is rotatably mounted on a first side of the connecting arm. The rotation detection component includes a stop plate and an angle positioning pin. The stop plate has a stop edge at one end facing the concave curved surface of the blade, which is used to stop the leading and trailing edges of the aero-engine turbine blade. The end of the stop plate away from the concave curved surface of the blade is connected to the angle positioning pin. An angle marker is provided on the extension and is located on the same side as the rotation detection element. The angle marker has an angle scale. When the stop straight edge rotates against the leading edge and trailing edge of the aero-engine turbine blade, the angle positioning pin can point to the angle scale on the angle marker.

2. The angle detection device for the chord angle of aero-engine turbine blades according to claim 1, characterized in that, The angle detection component also includes: A horizontal positioning reference plate, wherein the first end of the horizontal positioning reference plate is connected to the lower side of the vertical support plate, the second end of the horizontal positioning reference plate extends toward one side of the concave curved surface of the blade to form an extended support end, and the extended support end passes through the clearance channel formed between the lower end of the aero-engine turbine blade and the upper side of the base, and the lower side of the horizontal positioning reference plate is provided with a horizontal positioning reference surface.

3. The angle detection device for the chord angle of aero-engine turbine blades according to claim 2, characterized in that, Also includes: A horizontal reference rail is installed on the upper side of the base and located on the first side of the aero-engine turbine blade fixed to the blade mounting part, and the horizontal reference rail is set parallel to the blade length direction of the aero-engine turbine blade fixed to the blade mounting part. The second horizontal reference rail is installed on the upper side of the base and located on the second side of the aero-engine turbine blade fixed on the blade mounting part. The second horizontal reference rail is set parallel to the first horizontal reference rail, and the upper sides of the first horizontal reference rail and the second horizontal reference rail are set coplanarly to form a horizontal placement reference surface.

4. The angle detection device for the chord angle of aero-engine turbine blades according to claim 2, characterized in that, The horizontal positioning reference plate has a first protrusion on the lower side of the first end, and the lower side of the first protrusion forms a first positioning reference surface; the horizontal positioning reference plate has a second protrusion on the lower side of the second end, and the lower side of the second protrusion forms a second positioning reference surface. The first positioning reference surface and the second positioning reference surface are coplanar to form the horizontal positioning reference surface.

5. The angle detection device for the chord angle of aero-engine turbine blades according to claim 2, characterized in that, The first side of the angle positioning pin is disposed away from the first side of the connecting arm, the second side of the angle positioning pin is disposed close to the first side of the connecting arm, the second side of the stop plate and the second side of the angle positioning pin are both disposed in contact with the first side of the connecting arm, and the first side of the stop plate and the first side of the angle positioning pin are both coplanar with the first side of the horizontal positioning reference plate.

6. The angle detection device for the chord angle of aero-engine turbine blades according to claim 5, characterized in that, Also includes: The locating pins are provided in multiple pairs. The multiple pairs of locating pins are installed at intervals on the base along the length direction of the aero-engine turbine blade fixed on the blade mounting part. The two locating pins arranged in pairs are located on both sides of the aero-engine turbine blade in a direction perpendicular to the aero-engine turbine blade. The locating pins are provided with a vertical locating plane that fits against the first side of the horizontal locating reference plate.

7. The angle detection device for the chord angle of aero-engine turbine blades according to any one of claims 1 to 6, characterized in that, The blade mounting portion includes: A tenon support block is installed on the upper side of the base and protrudes upward. The tenon support block is provided with a tenon limiting support part for the turbine blade of the aero-engine. The blade crown support block is mounted on the upper side of the base and protrudes upward, opposite to the tenon support block. The blade crown support block is provided with the blade crown limiting support part of the aero-engine turbine blade. The tenon limiting support part and the blade crown limiting support part can be used to fix the aero-engine turbine blade and make the aero-engine turbine blade suspended relative to the upper side of the base.

8. The angle detection device for the chord angle of aero-engine turbine blades according to claim 7, characterized in that, The blade mounting section further includes: A blade locking assembly is movably connected to the base and positioned opposite the concave curved surface of the blade. The blade locking assembly has a locking position and an unlocking position relative to the concave curved surface of the blade. When the blade locking assembly is in the locking position, it locks the aero-engine turbine blade fixed to the blade mounting portion. When the blade locking assembly is in the unlocking position, it releases the locking of the aero-engine turbine blade fixed to the blade mounting portion.

9. The angle detection device for the chord angle of aero-engine turbine blades according to claim 7, characterized in that, Also includes: The blade crown limiting block is installed on the upper side of the base near the blade crown support block and protrudes upward to form an extended limiting part. The extended limiting part is arranged opposite to the leading edge and trailing edge of the aero-engine turbine blade fixed on the blade mounting part. The extended limiting part is provided with multiple pin holes, and the opening direction of the multiple pin holes is the same as the length direction of the blade body. Multiple movable limit pins are provided and are installed in the pin holes in a one-to-one correspondence. The side of the movable limit pin facing the blade crown can stop and limit the blade crown.

10. The angle detection device for the chord angle of aero-engine turbine blades according to claim 9, characterized in that, The extended limiting part has a blade side stop edge on one side of the leading edge and trailing edge of the aero-engine turbine blade fixed on the blade mounting part. The blade side stop edge can stop against the back of the leading edge and trailing edge of the aero-engine turbine blade fixed on the blade mounting part.

11. The angle detection device for the chord angle of aero-engine turbine blades according to any one of claims 2 to 6, characterized in that, The stop plate has an inclined clearance surface at its second end along the length of the horizontal positioning reference plate. The inclined clearance surface is inclined from the second side of the stop plate to the first side of the stop plate, and the inclined clearance surface and the first side of the stop plate define the stop straight edge.

Images