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

Abstract

The utility model discloses an angle detection assembly for a chord angle of an aero-engine turbine blade, and belongs to the technical field of aero-engine turbine blade manufacturing. The device comprises a horizontal positioning reference plate; the vertical supporting plate is vertically connected to the horizontal positioning datum plate, and a connecting arm is arranged on the vertical supporting plate; the rotating detection piece is rotationally installed on the connecting arm, the rotating detection piece comprises a stopping plate and an angle positioning pin, and stopping straight edges used for stopping the blade front edge and the blade rear edge of the aero-engine turbine blade are formed on the stopping plate; and the angle positioning needle can point to angle scales arranged on the angle mark. When the angle detection assembly in the embodiment is used for detecting the chord angle of the turbine blade of the aero-engine, when the stop plate rotates and drives the angle positioning needle to rotate by the same angle, the angle positioning needle after rotation can point to the corresponding angle scale position, and the chord angle of the turbine blade of the aero-engine can be detected. And obtaining the blade chord line angle of the current detection cross section of the aero-engine turbine blade.

Description

TECHNICAL FIELD

[0001] The utility model relates to aero -engine turbine blade processing and manufacturing technical field especially relates to a kind of angle detection assembly for aero -engine turbine blade chord line angle. BACKGROUND

[0002] Aero -engine turbine blade is the core component in aero -engine, to improve turbine efficiency, blade surface is usually designed into twisted variable cross-section surface, so that airflow flows smoothly between blade, reduces energy loss.The blade profile of aero -engine turbine blade is the space surface that is stacked according to certain stacking rule by basic element airfoil, and the manufacturing quality of blade directly affects the performance of the entire engine;Among them, the chord line angle of multiple sections on aero -engine turbine blade is one of important factors influencing the performance of engine, and the chord line angle of multiple sections on aero -engine turbine blade is an important index whether aero -engine turbine blade is qualified, therefore, detecting the chord line angle of multiple sections on aero -engine turbine blade is one of important qualification detection items of aero -engine turbine blade.

[0003] At present, in order to realize the chord line angle measurement of multiple sections on aero -engine turbine blade, the prior art usually uses three -coordinate measuring machine to measure aero -engine turbine blade;Further, three -coordinate measuring machine is a high-precision precision measurement test equipment integrating light, electricity and computer;However, three -coordinate measuring device is expensive, and the equipment has high maintenance cost in use process;In addition, three -coordinate measuring device has strict requirements on site temperature and humidity, is suitable for batch detection of blade, and in actual production, a large number of produced blades are sent to three -coordinate measuring device for blade chord line angle detection, and the working efficiency is low, and excessive time and energy are consumed in detection process. Therefore, a detection assembly for quickly detecting the angle of chord line angle of aero -engine turbine blade in production site is required. SUMMARY

[0004] The utility model aims at overcoming at least one of the above prior art, and provides a kind of detection assembly for detecting the angle of chord line angle of aero -engine turbine blade.

[0005] The technical scheme for solving the above technical problems of the utility model is as follows:

[0006] According to the angle detection assembly for the chord line angle of aero -engine turbine blade provided in the present application, comprising:

[0007] Horizontal positioning reference plate, the lower side of the horizontal positioning reference plate is provided with horizontal positioning reference surface, and the horizontal positioning reference plate is in long strip structure;

[0008] A vertical support plate is vertically connected to the first end of the horizontal positioning reference plate in the length direction, and the vertical support plate extends upward to form an extension, and a connecting arm is arranged on the extension towards the second end of the horizontal positioning reference plate in the length direction, and the connecting arm protrudes relative to the extension in the length direction of the horizontal positioning reference plate;

[0009] A rotation detection piece is rotatably installed on the first side of the connecting arm, and the rotation detection piece comprises a stop plate and an angle positioning needle, the first end of the stop plate in the length direction of the horizontal positioning reference plate is arranged close to and connected to the angle positioning needle, and the second end of the stop plate in the length direction of the horizontal positioning reference plate extends away from the angle positioning needle to form a stop straight edge for stopping the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine;

[0010] An angle mark is arranged on the extension and on the same side as the rotation detection piece, and the angle mark is provided with an angle scale, and when the stop straight edge stops the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine and rotates, the angle positioning needle can point to the angle scale on the angle mark.

[0011] The beneficial effects of the utility model are that the rotation detection piece in the embodiment is rotatably installed on the vertical support plate, the rotation detection piece comprises a stop plate and an angle positioning needle, when the angle detection assembly in the embodiment is used to detect the chordal angle of the turbine blade of the aero-engine, the stop straight edge arranged on the stop plate can stop on the blade leading edge and the blade trailing edge of the detection section of the turbine blade, the straight line stop straight edge can be used as the blade chord that passes through the current detection section and is tangent to the blade leading edge and the blade trailing edge, so that the stop straight edge of the stop plate can stop on the detection section of the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine, the stop plate rotates and drives the angle positioning needle to rotate by an equal angle, the angle positioning needle after rotation points to the corresponding angle scale, the measurement staff can obtain the chordal angle of the current detection section of the turbine blade of the aero-engine according to the corresponding angle scale position of the angle mark pointed to by the angle positioning needle after rotation, further, the lower side of the horizontal positioning reference plate is provided with a horizontal positioning reference surface, the lower side of the horizontal positioning reference plate can be used as the angle reference surface on the angle mark, or the lower side of the horizontal positioning reference plate can be used as the angle reference surface of the chord tangent to the blade leading edge and the blade trailing edge, which is beneficial to obtain the chordal angle of the detection section of the turbine blade of the aero-engine, and further facilitates the accurate detection of the detection section of the turbine blade of the aero-engine.

[0012] In addition, on the basis of the above technical solutions, the utility model can also be improved as follows, and can have the following additional technical features.

[0013] According to one embodiment of the utility model, the first side of the stop plate is arranged away from the first side of the connecting arm, the second side of the stop plate is arranged close to the first side of the connecting arm, and the first side of the horizontal positioning reference plate is coplanarly arranged with the first side of the stop plate.

[0014] The second side of the stop plate in the embodiment is arranged in close contact with the first side of the connecting arm, facilitating rotation of the stop plate in close contact with the first side of the connecting arm, improving rotation accuracy, and further improving the angle detection accuracy of the chord line angle of the turbine blade of the aero-engine.

[0015] According to one embodiment of the utility model, the first side of the angle positioning needle is arranged away from the first side of the connecting arm, the second side of the angle positioning needle is arranged close to the first side of the connecting arm, and the second side of the stop plate and the second side of the angle positioning needle are both arranged in close contact with the first side of the connecting arm.

[0016] The second side of the angle positioning needle in the embodiment is arranged in close contact with the first side of the connecting arm, facilitating rotation of the angle positioning needle in close contact with the first side of the connecting arm, improving rotation accuracy, and further improving the angle detection accuracy of the chord line angle of the turbine blade of the aero-engine.

[0017] According to one embodiment of the utility model, the lower side of the first end of the horizontal positioning reference plate is provided with a first protrusion, the lower side of the first protrusion forms a first positioning reference surface, the lower side of the second end of the horizontal positioning reference plate is provided with a second protrusion, the lower side of the second protrusion forms a second positioning reference surface, and the first positioning reference surface and the second positioning reference surface are coplanar to form the horizontal positioning reference surface.

[0018] In the embodiment, the first protrusion and the second protrusion are arranged, an avoiding groove can be formed between the first protrusion and the second protrusion, the area of the horizontal positioning reference surface is reduced, 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, so that only the machining accuracy of the first positioning reference surface and the second positioning reference surface needs to be ensured, the bottom surface of the horizontal positioning reference plate does not need to be finely machined, the machining amount of fine machining is reduced, and the machining cost is reduced.

[0019] According to one embodiment of the utility model, the stop plate is provided with an inclined avoiding surface at the second end in the length direction of the horizontal positioning base plate, the inclined avoiding surface is inclined from the second side surface of the stop plate to the first side surface of the stop plate, and the stop straight edge is defined between the inclined avoiding surface and the first side surface of the stop plate.

[0020] The inclined avoiding surface in the embodiment and the first side surface of the stop plate define the stop straight edge, the area of the stop straight edge is small, when the stop straight edge is stopped at the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine, only the stop straight edge is stopped at the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine, so that only the machining precision of the stop straight edge needs to be ensured, other parts on the stop plate do not need to be finished, the machining amount of finishing is reduced, and the machining cost is reduced; further, when the stop straight edge stops the turbine blade of the aero-engine, the contact area of the stop straight edge and the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine is reduced, so that the detection error of the chord angle of the turbine blade of the aero-engine is reduced, and the chord angle detection precision is improved.

[0021] According to one embodiment of the utility model, the angle positioning needle is a long plate structure, one end of the angle positioning needle away from the stop plate extends to form a indicating needle tip away from the stop plate, and the indicating needle tip can point to the angle scale on the angle mark.

[0022] In the embodiment, when the stop straight edge of the stop plate is stopped on the to-be-detected section surface of the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine, the stop plate is rotated and drives the angle positioning needle to rotate by an equal angle, the angle positioning needle after rotation points to the corresponding angle scale, the indicating needle tip can point to the accurate angle scale, and the staff can read the angle pointed to by the indicating needle tip.

[0023] According to one embodiment of the utility model, the rotation detection piece is detachably installed on the first side surface of the connecting arm.

[0024] The rotation detection piece in the embodiment is detachably installed on the first side surface of the connecting arm, the rotation detection piece is convenient to disassemble and assemble, and the rotation detection piece is convenient to maintain and replace.

[0025] According to one embodiment of the utility model, the rotation detection piece is a T-shaped structure.

[0026] The rotating detection piece in the embodiment has a T-shaped structure, is simple in structure, and is beneficial to processing a stop straight edge on the horizontal side of the rotating detection piece, rotatingly installing the vertical side of the rotating detection piece, and facilitating the rotating detection piece to rotate when the stop straight edge is stopped on the to-be-detected section of the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine.

[0027] According to one embodiment of the present application, the width of the stop straight edge ranges from 0.1 mm to 0.55 mm.

[0028] The width of the stop straight edge in the embodiment ranges from 0.1 mm to 0.55 mm. When the stop straight edge is stopped on the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine, only the stop straight edge is stopped on the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine, which is beneficial to reducing the contact area between the stop straight edge and the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine, reducing the error caused by the contact between the stop straight edge and the blade leading edge and the blade trailing edge of the turbine blade of the aero-engine, and improving the accuracy of angle measurement.

[0029] According to one embodiment of the present application, the vertical support plate is vertically connected to one side of the upper side of the horizontal positioning reference plate, and a rotating avoidance groove is defined between the upper side of the horizontal positioning reference plate and the side of the vertical support plate opposite to the rotating detection piece, and the rotating detection piece can rotate in the rotating avoidance groove.

[0030] The rotating avoidance groove defined between the vertical support plate and the upper side of the horizontal positioning reference plate in the embodiment can rotate in the rotating avoidance groove during the rotation of the rotating detection piece, avoids interference between the rotating detection piece and other components on the outer side of the horizontal positioning reference plate, and ensures the accuracy of detection of the rotating detection piece. BRIEF DESCRIPTION OF DRAWINGS

[0031] In order to more clearly illustrate the technical solutions in the present application, the following will briefly introduce the drawings needed in the embodiment description. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative effort.

[0032] Figure 1 FIG. 1 is a schematic view of an angle detection assembly for chord line angle of turbine blade of aero-engine in the embodiment of the present application;

[0033] Figure 2 FIG. 2 is a right view of the angle detection assembly for chord line angle of turbine blade of aero-engine in the embodiment of the present application; Figure 1

[0034] Figure 3 ​A structure schematic view of the rotation detection piece in the embodiment of the present application;

[0035] Figure 4 A schematic view of a chord line of a detection section obtained by cutting along the width direction of the blade body of the turbine blade of the aero-engine in the embodiment of the present application is tangent to the leading edge and the trailing edge of the blade;

[0036] Figure 5 A structure schematic view of the angle detection assembly for the chord line angle of the turbine blade of the aero-engine in the embodiment of the present application abutting on the base. DETAILED DESCRIPTION

[0037] In order to make the purpose, technical scheme and advantages of the present application more clear, the following will further describe the embodiments of the present application in detail with reference to the drawings.

[0038] In order to make the purpose, technical scheme and advantages of the present application more clear, the following will further describe the embodiments of the present application in detail with reference to the drawings.

[0039] In the following description, a lot of specific details are set forth in order to give a thorough understanding of the present application, but the present application can also be implemented in other ways different from those described herein, therefore, the protection scope of the present application is not limited by the specific embodiments disclosed below.

[0040] The angle detection assembly for the chord line angle of the turbine blade of the aero-engine provided by the present application comprises: Figures 1 to 4 As shown in the figure, comprising:

[0041] A horizontal positioning reference plate 25, the lower side of the horizontal positioning reference plate 25 is provided with a horizontal positioning reference surface, and the horizontal positioning reference plate 25 is in a long strip structure;

[0042] A vertical support plate 21 vertically connected to the first end of the horizontal positioning reference plate 25 in the length direction, the vertical support plate 21 vertically extends to form an extension, the extension is provided with a connecting arm 22 towards the second end of the horizontal positioning reference plate 25 in the length direction, and the connecting arm 22 is protruded relative to the extension in the length direction of the horizontal positioning reference plate 25;

[0043] The rotation detection piece is rotationally installed on the first side of the connecting arm 22, and the rotation detection piece comprises a stop plate 23 and an angle positioning needle 24, the first end of the stop plate 23 along the length direction of the horizontal positioning reference plate 25 is arranged close to and connected with the angle positioning needle 24, and the second end of the stop plate 23 along the length direction of the horizontal positioning reference plate 25 extends away from the angle positioning needle 24 to form a stop straight edge 231 for stopping the blade leading edge 321 and the blade trailing edge 322 of the aero-engine turbine blade 3;

[0044] The angle mark 27 is arranged on the extension part and on the same side as the rotation detection piece, the angle mark 27 is provided with an angle scale, and when the stop straight edge 231 stops the blade leading edge 321 and the blade trailing edge 322 of the aero-engine turbine blade 3 and rotates, the angle positioning needle 24 can point to the angle scale on the angle mark 27.

[0045] In the embodiment, as shown in Figures 1 to 4 the rotation detection piece is rotationally installed on the vertical support plate 21, and the rotation detection piece comprises a stop plate 23 and an angle positioning needle 24, when the chord angle of the aero-engine turbine blade is detected by using the angle detection assembly, the stop straight edge 231 arranged on the stop plate 23 can stop on the blade leading edge 321 and the blade trailing edge 322 of the detection section of the aero-engine turbine blade, so that the straight stop straight edge 231 can be used as the chord line 34 of the turbine blade blade body 32 passing through the current detection section and tangent to the blade leading edge 321 and the blade trailing edge 322, so that the stop straight edge 231 of the stop plate 23 can stop on the detection section of the blade leading edge 321 and the blade trailing edge 322 of the aero-engine turbine blade 3, so that the stop plate 23 rotates and drives the angle positioning needle 24 to rotate by an equal angle, the rotated angle positioning needle 24 points to the corresponding angle scale, and the measurement worker can obtain the chord angle of the current detection section of the aero-engine turbine blade 3 according to the position of the rotated angle positioning needle 24 pointing to the corresponding angle scale on the angle mark 27; further, the lower side of the horizontal positioning reference plate 25 is provided with a horizontal positioning reference surface, the lower side of the horizontal positioning reference plate 25 can be used as the angle reference surface on the angle mark 27, or the lower side of the horizontal positioning reference plate 25 can be used as the angle reference surface of the chord line tangent to the blade leading edge 321 and the blade trailing edge 322, so as to obtain the chord angle of the different detection sections of the aero-engine turbine blade 3, and then facilitate accurate detection of the detection section of the aero-engine turbine blade 3.

[0046] In one embodiment of the utility model, as shown in Figure 1 and Figure 2As shown, the first side of the stop plate 23 is arranged away from the first side of the connecting arm 22, and the second side of the stop plate 23 is arranged close to the first side of the connecting arm 22, and the first side of the horizontal positioning reference plate 25 is arranged coplanar with the first side of the stop plate 23.

[0047] In the embodiment, as shown in Figure 1 and Figure 2 the second side of the stop plate 23 in the embodiment is arranged in abutment with the first side of the connecting arm 22, facilitating the stop plate 23 to rotate in abutment with the first side of the connecting arm 22 during rotation, improving the rotation accuracy, and further improving the angle detection accuracy of the chordal angle of the turbine blade of the aero-engine.

[0048] In the embodiment, as shown in Figure 1 and Figure 2 the first side of the angle positioning needle 24 is arranged away from the first side of the connecting arm 22, and the second side of the angle positioning needle 24 is arranged close to the first side of the connecting arm 22, and the second side of the stop plate 23 and the second side of the angle positioning needle 24 are both arranged in abutment with the first side of the connecting arm 22.

[0049] In the embodiment, as shown in Figure 1 and Figure 2 the second side of the angle positioning needle 24 in the embodiment is arranged in abutment with the first side of the connecting arm 22, facilitating the angle positioning needle 24 to rotate in abutment with the first side of the connecting arm 22 during rotation, improving the rotation accuracy, and further improving the angle detection accuracy of the chordal angle of the turbine blade of the aero-engine.

[0050] In the embodiment, as shown in Figure 1 and Figure 2 the first end of the horizontal positioning reference plate 25 is provided with a first protrusion 251, and the lower side of the first protrusion 251 forms a first positioning reference surface; the second end of the horizontal positioning reference plate 25 is provided with a second protrusion 252, and the lower side of the second protrusion 252 forms a second positioning reference surface, and the first positioning reference surface and the second positioning reference surface are coplanar to form a horizontal positioning reference surface.

[0051] In the embodiment, as shown in Figure 1 and Figure 2As shown, in the embodiment, the first protrusion 251 and the second protrusion 252 are arranged, and the avoiding recess is formed between the first protrusion 251 and the second protrusion 252, so as to reduce 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, so that the machining precision of the first positioning reference surface and the second positioning reference surface needs to be ensured, and the bottom surface of the horizontal positioning reference plate 25 does not need to be finely machined, thereby reducing the machining amount and the machining cost.

[0052] In the embodiment, as shown in Figure 5 When the first protrusion 251 and the second protrusion 252 are abutted against the upper side of the base 1, and the first positioning reference surface and the second positioning reference surface are in contact with the upper side of the base 1, the horizontal positioning reference plate 25 can be based on the upper side of the base 1 as the angle reference. Further, in order to facilitate the detection of the chord angle of the aero-engine turbine blade, the aero-engine turbine blade 3 can be fixedly installed on the upper side of the base 1 and suspended relative to the upper side of the base 1, and the chord angle of the aero-engine turbine blade fixedly installed on the upper side of the base 1 is detected by using the angle detection assembly in the embodiment.

[0053] In the embodiment, as shown in Figure 5 The horizontal reference rail one 10 is installed on the front side of the base 1, is installed on the upper side of the base 1 and located at the first side of the aero-engine turbine blade 3 fixedly installed on the blade mounting portion, and is arranged parallel to the length direction of the blade body 32 of the aero-engine turbine blade 3 fixedly installed on the blade mounting portion; the horizontal reference rail two 11 is installed on the rear side of the base 1, is installed on the upper side of the base 1 and located at the second side of the aero-engine turbine blade 3 fixedly installed on the blade mounting portion, and is arranged parallel to the horizontal reference rail one 10. The upper sides of the horizontal reference rail one 10 and the horizontal reference rail two 11 are arranged in the same plane to form the horizontal placement 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 horizontal placement reference surface formed by the upper sides of the horizontal reference rail one 10 and the horizontal reference rail two 11 arranged in the same plane.

[0054] In the embodiment, as shown in Figure 5As shown, a tenon support block 12 is installed on the left side of the base 1. 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 aero-engine. A blade crown support block 13 is installed on the right side of the base 1. 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 part for the turbine blade 3 of the aero-engine. The tenon limiting support part 121 and the blade crown limiting support part can be used to fix the turbine blade 3 of the aero-engine and make the turbine blade 3 of the aero-engine suspended relative to the upper side of the base 1.

[0055] In this embodiment, as Figure 5 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 on the tenon support block 12. The tenon support protrusion 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.

[0056] In this embodiment, as Figure 5 As shown, in this embodiment, the base 1 is also equipped with a crown limiting block 14, which is installed on the upper side of the base 1 near the crown support block 13 and protrudes upward to form an extended limiting part. The extended limiting part can limit the crown 33.

[0057] In this embodiment, as Figure 5 As shown, in this embodiment, a blade locking assembly is movably connected to the base 1. The blade locking assembly is movably connected to the base 1 and is positioned directly opposite the concave curved surface of the blade 32. The blade locking assembly has a locking position and an unlocking position relative to the concave 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.

[0058] In this embodiment, as Figure 5As 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.

[0059] In this embodiment, as Figure 5 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. 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 part used to stop against the recessed front side wall of the blade 32 is arc-shaped. The front end of the upper side of the base 1 is provided with a locking member movable passage. The locking member movable passage is vertically opened and communicates with the mounting groove. The vertical plate of the locking stop arm 15 passes through the locking member movable passage. The lower end of the vertical plate of the locking stop 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 arm 15 is also connected to one end of the tension spring. The other end of the tension spring is connected to the front side wall of the mounting groove.

[0060] Furthermore, such as Figure 5As 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 turbine blade 3 of the aero-engine. 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. The thrust threaded rod extends into the mounting groove provided on the lower side of the base 1 and stops against 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 threaded rod is screwed backward, and the thrust threaded rod pushes the locking stop arm 15 backward, causing it to swing backward within the movable opening 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, 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.

[0061] In this embodiment, as Figure 5 As shown, in this embodiment, the base 1 is provided with multiple pairs of positioning pins 16 on the front and rear sides. 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 the direction perpendicular to the aero-engine turbine blade 3. The positioning pin 16 is provided with a vertical positioning plane 161 that fits against the first side of the horizontal positioning reference plate 25.

[0062] In this embodiment, as Figure 5 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.

[0063] Furthermore, such as Figure 5As shown, the base 1 in this embodiment can have various structures, and the way the turbine blade 3 of the aero-engine placed on the base 1 can also be varied. This facilitates the measurement and testing of multiple detection sections of the aero-engine turbine blade 3 by having the stop plate 23's straight edge 231 abut against the blade's leading edge 321 and trailing edge 322 of the detection section of the aero-engine turbine blade 3, thereby obtaining the chord angle of the multiple detection sections of the aero-engine turbine blade 3.

[0064] Furthermore, such as Figure 4 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.

[0065] It should be noted that the multiple inspection sections of the blade body 32 of the aero-engine turbine blade can be set according to the inspection requirements of the aero-engine turbine blade, the spacing between two adjacent inspection sections can also be set according to the inspection requirements of the aero-engine turbine blade, and the number of inspection sections can also be adjusted according to the inspection requirements of the aero-engine turbine blade.

[0066] Furthermore, the angle detection component for the chord angle of aero-engine turbine blades in this embodiment can also have other usage methods to facilitate the detection of the chord angle of aero-engine turbine blades; it should be noted that the structure of the base 1 in this embodiment can also have various forms, which will not be elaborated here.

[0067] One embodiment of this utility model is as follows: Figures 1 to 3 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.

[0068] In this embodiment, as Figures 1 to 3As 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 and improving the detection accuracy of the chord angle.

[0069] One embodiment of this utility model is as follows: Figures 1 to 3 As shown, the angle positioning pin 24 is a long plate-shaped structure. The end of the angle positioning pin 24 away from the stop plate 23 extends away from the stop plate 23 to form an indicator pin tip 241. The indicator pin tip 241 can point to the angle scale on the angle mark 27.

[0070] In this embodiment, as Figures 1 to 3 As shown, in this embodiment, an indicator needle tip 241 is provided on the angle positioning needle 24. When the stop 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 needle 24 to rotate by an equal angle. After rotation, the angle positioning needle 24 points to the corresponding angle scale, and the indicator needle tip 241 can point to the precise angle scale, which makes it convenient for the staff to read the angle currently pointed to by the indicator needle tip 241.

[0071] One embodiment of this utility model is as follows: Figures 1 to 3 As shown, the rotation detection element is detachably mounted on the first side of the connecting arm 22.

[0072] In this embodiment, as Figures 1 to 3 As shown, in this embodiment, the rotation detection component is detachably mounted on the first side of the connecting arm 22, which facilitates the disassembly and assembly of the rotation detection component and is beneficial for its maintenance and replacement.

[0073] One embodiment of this utility model is as follows: Figures 1 to 3 As shown, the rotation detection component has a T-shaped structure.

[0074] In this embodiment, as Figures 1 to 3As shown, the rotation detection component in this embodiment has a T-shaped structure, which is simple and facilitates the formation of a stop edge 231 on the horizontal side of the rotation detection component. The vertical side of the rotation detection component is rotated and installed, with the rotation center close to the middle position of the stop edge 231. This facilitates the rotation of the rotation detection component when the stop edge 231 is abutted against the cross section to be tested on the leading edge 321 and trailing edge 322 of the turbine blade 3 of the aero-engine.

[0075] Furthermore, such as Figures 1 to 3 As shown, the connecting arm 22 is provided with a rotating pin hole, and the horizontal edge of the rotating detection component is machined to form a stop straight edge 231. The rotating detection component is rotatably installed 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 installation is achieved by the rotating connecting pin 212 cooperating with the rotating pin hole and the connecting hole 242.

[0076] One embodiment of this utility model is as follows: Figure 3 As shown, the width of the stop straight edge 231 ranges from 0.1mm to 0.55mm.

[0077] In this embodiment, as Figure 3 As shown, in this embodiment, the width of the stop edge 231 is set to be between 0.1mm and 0.55mm. When the stop edge 231 is abutted against the leading edge 321 and trailing edge 322 of the turbine blade 3 of the aero-engine, only the stop edge 231 abuts against the leading edge 321 and trailing edge 322 of the turbine blade 3. This helps to reduce the contact area between the stop edge 231 and the leading edge 321 and trailing edge 322 of the turbine blade detection section, thereby reducing the error caused by the contact between the stop edge 231 and the leading edge 321 and trailing edge 322 of the turbine blade detection section and improving the accuracy of angle measurement.

[0078] One embodiment of this utility model is as follows: Figure 1 and Figure 2 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.

[0079] In this embodiment, as Figure 1 and Figure 2 As shown, in this embodiment, a rotation avoidance groove 26 is defined between the vertical support plate 21 and the upper side of the horizontal positioning reference plate 25. During rotation, the rotation detection component can rotate within the rotation avoidance groove 26, avoiding interference between the rotation detection component and other components on the outer side of the horizontal positioning reference plate 25, thus ensuring the accuracy of the rotation detection component.

[0080] 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.

[0081] 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.

[0082] 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.

[0083] 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.

[0084] 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 component for the chord angle of aero-engine turbine blades, characterized in that, include: A horizontal positioning reference plate, wherein the lower side of the horizontal positioning reference plate is provided with a horizontal positioning reference surface, and the horizontal positioning reference plate has a long strip structure; A vertical support plate is vertically connected to the first end of the horizontal positioning reference plate along its length. The vertical support plate extends vertically upward to form an extension. A connecting arm is provided on the second end of the extension facing the length of the horizontal positioning reference plate. The connecting arm protrudes relative to the extension along the length of the horizontal positioning reference plate. A rotation detection component is rotatably mounted on the first side of the connecting arm. The rotation detection component includes a stop plate and an angle positioning pin. The stop plate is located near the angle positioning pin at a first end along the length direction of the horizontal positioning reference plate and is connected to the angle positioning pin. The stop plate extends away from the angle positioning pin at a second end along the length direction of the horizontal positioning reference plate to form a stop straight edge for stopping the leading edge and trailing edge of the turbine blade of the aero-engine. 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 turbine blade of the aero-engine, the angle positioning pin can point to the angle scale on the angle marker.

2. The angle detection component for the chord angle of aero-engine turbine blades according to claim 1, characterized in that, The first side of the stop plate is disposed away from the first side of the connecting arm, the second side of the stop plate is disposed close to the first side of the connecting arm, and the first side of the horizontal positioning reference plate is disposed on the same plane as the first side of the stop plate.

3. The angle detection component 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, and 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.

4. The angle detection assembly for the chord angle of aero-engine turbine blades according to claim 1, 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 assembly for the chord angle of aero-engine turbine blades according to any one of claims 1 to 4, 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.

6. The angle detection assembly for the chord angle of aero-engine turbine blades according to any one of claims 1 to 4, characterized in that, The angle positioning pin is a long plate-shaped structure. The end of the angle positioning pin away from the stop plate extends away from the stop plate to form an indicator tip. The indicator tip can point to the angle scale on the angle mark.

7. The angle detection assembly for the chord angle of aero-engine turbine blades according to any one of claims 1 to 4, characterized in that, The rotation detection element is detachably mounted on the first side of the connecting arm.

8. The angle detection assembly for the chord angle of aero-engine turbine blades according to any one of claims 1 to 4, characterized in that, The rotation detection element has a T-shaped structure.

9. The angle detection assembly for the chord angle of aero-engine turbine blades according to any one of claims 1 to 4, characterized in that, The width of the stop edge ranges from 0.1mm to 0.55mm.

10. The angle detection assembly for the chord angle of aero-engine turbine blades according to any one of claims 1 to 4, characterized in that, The vertical support plate is vertically connected to one side of the upper side of the horizontal positioning reference plate. A rotation avoidance groove is defined between the upper side of the horizontal positioning reference plate and the side of the vertical support plate facing the rotation detection member. The rotation detection member can rotate within the rotation avoidance groove.

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