A device for repairing torsional deformation of a high-pressure rectification vane blade of an aero-engine

Abstract

The application provides a device for repairing torsional deformation of a high-pressure rectification vane blade of an aero-engine, belonging to the field of aero-engine manufacturing, comprising a base, a support placed on the base, a rotating shaft mechanism installed on the support and used for realizing torsional correction of the blade along a stacking axis, a blade tenon clamping mechanism connected with the rotating shaft mechanism and used for clamping a tenon of the blade, a blade pan fixing mechanism fixed on the base and used for pressing a blade pan profile, and a blade back fixing mechanism used for pressing a blade back profile. The device realizes repairing of a torsional angle of an unqualified high-pressure rectification vane blade relative to the tenon in a manufacturing process, so that the blade returns to a qualified range, and the unqualified rectification vane is saved.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine manufacturing, and specifically relates to a device for repairing torsional deformation of high-pressure rectifier blades in aero-engines. Background Technology

[0002] High-pressure rectifier blades are a crucial component of aero-engine compressors. Their primary function is to decelerate and diffuse the airflow accelerated by the upstream rotor blades, further increasing air pressure and providing a suitable flow direction for the next stage rotor. Early materials primarily used stainless steel, but modern engines, to reduce weight and improve performance, often employ titanium alloys and heat-resistant nickel-based alloys. The manufacturing process for high-pressure rectifier blades typically employs cold rolling and milling techniques. During the manufacturing and repair of high-pressure rectifier blades, because the blade body is usually a thin-walled, easily deformable structure, when deformation occurs and the blade no longer meets the design requirements, it needs to be corrected and repaired. Correction is generally divided into cold correction and hot correction. Cold correction involves applying external force to bring the blade body dimensions back to the acceptable range, such as using a press to mechanically correct the blade.

[0003] Due to the unique shape and structure of the high-pressure rectifier blades, the tooling table of ordinary presses cannot meet the requirements for clamping the blades, nor can it meet the requirements for twisting angles. Summary of the Invention

[0004] The purpose of this invention is to solve the problem that the tooling table of ordinary presses in the prior art cannot meet the requirements for clamping blades and thus cannot perform torsion angle correction, and to provide a device that can repair the torsion angle of high-pressure rectifier blades.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a device for repairing torsional deformation of high-pressure rectifier blades of aero-engines, comprising a base, a support placed on the base, a rotating shaft mechanism mounted on the support for realizing torsional correction of the blade along the stacking axis, a blade tenon clamping mechanism connected to the rotating shaft mechanism for clamping the tenon of the blade, a blade basin fixing mechanism fixed on the base for pressing the blade basin profile, and a blade back fixing mechanism for pressing the blade back profile.

[0006] The device for repairing torsional deformation of high-pressure rectifier blades of aero engines provided by the present invention also has the following technical features: the rotating shaft mechanism includes a rotating shaft, a transition support plate that contacts the blade tenon clamping mechanism, and a rotating support plate for connecting the transition support plate to a support. The transition support plate is located between the rotating support plate and the blade tenon clamping mechanism.

[0007] The device for repairing torsional deformation of high-pressure rectifier blades of aero engines provided by the present invention also has the following technical features: the rotating shaft mechanism further includes locking pins and locking screws for fixing and locking the rotating shaft mechanism.

[0008] The device for repairing torsional deformation of high-pressure rectifier blades for aero-engines provided by the present invention also has the following technical feature: the blade tenon clamping mechanism is an eccentric cam locking mechanism, which locks / loosens the blade tenon by operating the rotation of the eccentric shaft in both directions.

[0009] The device for repairing torsional deformation of high-pressure rectifier blades for aero-engines provided by the present invention also has the following technical features: the blade tenon clamping mechanism includes an eccentric shaft and two locking pressure plates for clamping the blade tenon.

[0010] The device for repairing torsional deformation of high-pressure rectifier blades for aero-engines provided by the present invention also has the following technical feature: the pressure blocks of the locking plate, the blade basin fixing mechanism, and the blade back fixing mechanism are replaceable.

[0011] The device for repairing torsional deformation of high-pressure rectifier blades of aero engines provided by the present invention also has the following technical feature: the rotating support plate is provided with tightening screws on both sides, and the tightening screws push the rotating support plate to rotate, thereby driving the blade tenon clamping mechanism to rotate along the rotating axis.

[0012] The device for repairing torsional deformation of high-pressure rectifier blades of aero engines provided by the present invention also has the following technical features: the transition support plate and the rotating support plate are connected by screws, and the transition support plate and the blade tenon clamping mechanism are connected by pins.

[0013] The device for repairing torsional deformation of high-pressure rectifier blades of aero engines provided by the present invention also has the following technical feature: the device further includes lifting eye bolts for hoisting.

[0014] The device for repairing torsional deformation of high-pressure rectifier blades of aero engines provided by the present invention also has the following technical feature: the support is provided with an angle mark for determining the rotation angle of the rotating shaft mechanism.

[0015] Beneficial effects: The device provided in this application for repairing torsional deformation of high-pressure rectifier blades for aero-engines enables the repair of the torsional angle of the blade relative to the tenon in the manufacturing process of defective high-pressure rectifier blades, bringing it back to the acceptable range and saving the defective rectifier blades. The repair device precisely controls the specific value of the torsional tenon angle, i.e., the torsional range, through angle markings on the clamping and rotating mechanism, avoiding complete damage to the blade to the point of scrapping due to excessive torsional angle, and accumulates the torsional angle value of the repaired blade, providing accurate digitalization for the repair work.

[0016] This repair device can adapt to blades of different shapes and sizes by changing the shape of the locking plate and the blade-shaped pressure block in the blade tenon clamping mechanism, while keeping the rest of the device completely unchanged. This greatly saves the processing cost of parts and is very suitable for the characteristics of current products with small batches, multiple varieties, and rapid upgrades. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a front view of the repair device provided in an embodiment of the present invention; Figure 2 This is a top view of the repair device provided in an embodiment of the present invention; Figure 3 for Figure 1 A cross-sectional view of the AA plane; Figure 4 for Figure 2 A sectional view of the C-plane; Figure 5 This is an isometric view of the repair device provided in the embodiment of the present invention. Wherein, 1: base; 2: support; 3: rotating shaft mechanism; 4: locking pin; 5: rotating support plate; 6: transition support plate; 7: blade tenon clamping mechanism; 8: blade basin fixing mechanism; 9: blade back fixing mechanism; 10: locking screw; 11: screw; 12: tightening screw; 13: pin; 14: eye bolt. Detailed Implementation

[0019] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. However, it should be noted that these embodiments are not intended to limit the present invention. Equivalent changes or substitutions in function, method, or structure made by those skilled in the art based on these embodiments are all within the protection scope of the present invention.

[0020] In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", 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 the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the invention.

[0021] Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0022] The terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art will understand the specific meaning of these terms in this invention based on the specific circumstances.

[0023] like Figure 1-5 As shown, this embodiment of the invention provides a device for repairing torsional deformation of a high-pressure rectifier blade of an aero-engine, including a base 1, a support 2 placed on the base 1, a rotating shaft mechanism 3 installed on the support 2 for realizing torsional correction of the blade along the stacking axis, a blade tenon clamping mechanism 7 connected to the rotating shaft mechanism 3 for clamping the tenon of the blade, a blade basin fixing mechanism 8 fixed on the base 1 for pressing the blade basin profile, and a blade back fixing mechanism 9 for pressing the blade back profile.

[0024] In some embodiments, the rotating shaft mechanism 3 includes a rotating shaft, a transition support plate 6 that contacts the blade tenon clamping mechanism 7, and a rotating support plate 5 for connecting the transition support plate 6 to the support 2. The transition support plate 6 is located between the rotating support plate 5 and the blade tenon clamping mechanism 7.

[0025] In some embodiments, the rotating shaft mechanism 3 further includes a locking pin 4 and a locking screw 10 for fixing and locking the rotating shaft mechanism 3.

[0026] In some embodiments, the blade tenon clamping mechanism 7 is an eccentric cam locking mechanism, which locks / unlocks the blade tenon by rotating the eccentric shaft in both directions.

[0027] In some embodiments, the blade tenon clamping mechanism 7 includes an eccentric shaft and two locking plates for clamping the blade tenon.

[0028] In some embodiments, the locking plate, the leaf basin fixing mechanism 8, and the leaf back fixing mechanism 9 can be replaced.

[0029] In some embodiments, the rotating support plate 5 is provided with tightening screws 12 on both sides. The tightening screws 12 push the rotating support plate 5 to rotate, thereby driving the blade tenon clamping mechanism 7 to rotate along the rotating axis.

[0030] In some embodiments, the transition support plate 6 and the rotating support plate 5 are connected by screws 11, and the transition support plate 6 and the blade tenon clamping mechanism 7 are connected by pins 13.

[0031] In some embodiments, the device further includes eye bolts 14 for lifting.

[0032] In some embodiments, the support 2 is also provided with an angle mark for determining the rotation angle of the rotating shaft mechanism.

[0033] The method of using any of the aforementioned repair devices during the repair process is as follows: 1. First, insert the locking pin 4 to fix the rotating shaft mechanism 3. Loosen the eccentric shaft in the blade tenon clamping mechanism 7, place the blade tenon between the two locking pressure plates, and make the lower end face of the blade tenon contact the limiting pin. Then tighten the eccentric shaft to operate the two locking pressure plates to clamp the blade tenon.

[0034] 2. By manipulating the tightening screws in the blade basin fixing mechanism 8 and the blade back fixing mechanism 9, the front blade basin and blade back profile pressing block are pushed to press the blade body, thereby completely restraining the blade.

[0035] 3. Pull out the locking pin 4, and push the rotating support plate 5 by manipulating the tightening screw 12, thereby driving the blade tenon clamping mechanism 7 to rotate along the rotating shaft mechanism 3. Since the blade body is fixed and cannot move by the blade basin fixing mechanism 8 and the blade back fixing mechanism 9, rotating the tenon can achieve the angle deformation of the tenon relative to the blade body, thereby achieving the angle repair of the blade body.

[0036] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention. The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the protection scope of the present invention.

Claims

1. A device for repairing torsional deformation of high-pressure rectifier blades in aero-engines, characterized in that, It includes a base, a support placed on the base, a rotating shaft mechanism installed on the support for realizing the torsional correction of the blade along the stacking axis, a blade tenon clamping mechanism connected to the rotating shaft mechanism for clamping the tenon of the blade, a blade basin fixing mechanism fixed on the base for pressing the blade basin profile, and a blade back fixing mechanism for pressing the blade back profile.

2. The device for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 1, characterized in that, The rotating shaft mechanism includes a rotating shaft, a transition support plate that contacts the blade tenon clamping mechanism, and a rotating support plate for connecting the transition support plate to the support. The transition support plate is located between the rotating support plate and the blade tenon clamping mechanism.

3. The device for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 2, characterized in that, The rotating shaft mechanism also includes locking pins and locking screws for fixing and locking the rotating shaft mechanism.

4. The device for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 1, characterized in that, The blade tenon clamping mechanism is an eccentric cam locking mechanism, which locks / unlocks the blade tenon by rotating the eccentric shaft in both directions.

5. The device for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 4, characterized in that, The blade tenon clamping mechanism includes an eccentric shaft and two locking plates for clamping the blade tenon.

6. The apparatus for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 5, characterized in that, The locking plate, the leaf basin fixing mechanism, and the leaf back fixing mechanism's pressure blocks are replaceable.

7. The device for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 2, characterized in that, The rotating support plate is provided with tightening screws on both sides. The tightening screws push the rotating support plate to rotate, thereby driving the blade tenon clamping mechanism to rotate along the rotating axis.

8. The device for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 2, characterized in that, The transition support plate and the rotating support plate are connected by screws, and the transition support plate and the blade tenon clamping mechanism are connected by pins.

9. The apparatus for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 1, characterized in that, The device also includes eye bolts for lifting.

10. The apparatus for repairing torsional deformation of high-pressure rectifier blades in aero-engines according to claim 1, characterized in that, The support is also provided with an angle mark for determining the rotation angle of the rotating shaft mechanism.

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