A vibration reduction ring for an aeroengine stator blade

Abstract

The application belongs to the field of aero-engine design, and particularly relates to a vibration reduction ring for a stator blade of an aero-engine, which comprises a stator blade, an outer edge plate installed on the outer edge of the stator blade, an inner edge plate installed on the inner edge of the stator blade, and a connection between the outer edge plate and a casing through a threaded fastener; the front edge of the stator blade and the corresponding position of the corresponding casing and the rear edge and the corresponding position of the corresponding casing are both provided with a part A, the side wall of the inner edge plate is flat; an inner ring is arranged in the casing and coaxial with the casing, the outer wall surface of the inner ring is provided with a mounting hole, the mounting hole is connected with the side wall of the inner edge plate in a matched mode, a vibration reduction ring is arranged between the side wall and the contact surface of the mounting hole, the material of the vibration reduction ring comprises polyetherimide, polyether ether ketone or polyphenyl plastic, the vibration reduction ring can be self-positioned, the vibration reduction ring does not need to be positioned by the inner ring and the boss of the stator blade, the structure of the stator blade and the inner ring is simplified, and the processing cost and the weight of the parts are reduced.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aero-engine design, and particularly relates to a vibration-reducing ring for a stator blade of an aero-engine. BACKGROUND

[0002] The assembly form of the stator blade of the aero-engine is that the outer edge plate is fixed with the outer ring casing, and the inner edge plate is inserted with the inner ring. The vibration-reducing ring for the stator blade realizes the insertion and fixation of the inner edge plate of the blade with the inner ring, avoids the cantilever structure of the blade, improves the rigidity of the blade and reduces the deformation of the blade, and simultaneously solves the damage problem of the blade and the inner ring casing caused by the micro-motion wear of the inner edge plate of the blade and the inner ring.

[0003] The existing stator blade non-fixed end is only assembled with a cylindrical bushing. The cylindrical bushing cannot be fixed and needs to be positioned by the blade or the inner ring, and is only matched with the stator blade with a cylindrical shaft at the inner end, and the use condition is single. SUMMARY

[0004] In order to solve the above problems, the application provides a vibration-reducing ring for a stator blade of an aero-engine, which comprises:

[0005] The stator blade is provided with an outer edge plate at the outer edge thereof and an inner edge plate at the inner edge thereof, and the outer edge plate is connected with the casing through a threaded fastener; the leading edge of the stator blade is provided with a part A at the corresponding position of the casing and the trailing edge is provided with a part A at the corresponding position of the casing; and the side wall of the inner edge plate is flat.

[0006] The inner ring is arranged in the casing and coaxial with the casing, and the outer wall surface of the inner ring is provided with a mounting hole which is connected with the side wall of the inner edge plate; a vibration-reducing ring is arranged between the side wall and the contact surface of the mounting hole, and the material of the vibration-reducing ring comprises polyetherimide, polyether ether ketone or polyphenyl ether.

[0007] Preferably, the edge of the side wall is provided with a first stepped surface, the edge of the hole of the mounting hole is provided with a second stepped surface, the first stepped surface is connected with the second stepped surface, and the freedom degree of the stator blade in the radial direction of the inner ring is limited.

[0008] Preferably, the mounting hole is a through hole, the hole of the mounting hole close to the stator blade is provided with a stepped surface, the vibration-reducing ring is provided with a vertical wall between the side wall and the side wall surface of the mounting hole, and a flange perpendicular to the vertical wall, and the flange is overlapped with the stepped surface.

[0009] Preferably, the end of the vertical wall away from the flange is provided with a lug, the lug and the flange form a mounting groove therebetween, and the width of the mounting groove is equal to the length of the mounting hole, so that the wall surface of the mounting hole is immersed in the mounting groove.

[0010] Preferably, the height of the lug is 0.5-1.5 mm.

[0011] Preferably, the wall thickness of the vertical wall is 0.6-1.5 mm.

[0012] Preferably, the damping ring is formed by injection molding.

[0013] The present application has the following advantages:

[0014] 1. The inner wall surface of the damping ring is not limited by shape and size, and can be the same as the shape of the inner edge plate of the stator blade, thereby reducing the design limitations of the inner edge plate of the stator blade.

[0015] 2. The damping ring can be self-positioned, and does not need an inner ring and a stator blade boss to position the damping ring, thereby simplifying the structure of the stator blade and the inner ring, reducing the processing cost and the weight of the parts.

[0016] 3. The inner end of the stator blade does not need to be designed with a damping ring positioning boss, the stator blade can be inserted into the inner ring first and then rotated to move out, thereby avoiding interference with the part A in front of the blade during disassembly, and the part A can not be disassembled during disassembly, improving the assembly of the stator blade, reducing the disassembly workload, and improving the work efficiency. If the part A is a casing base or cannot be disassembled, this structure can realize the assembly of the blade under the whole ring casing, thereby avoiding the split casing structure and reducing the part and assembly workload. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a schematic diagram of the damping ring for the stator blade of the aircraft engine according to a preferred embodiment of the present application;

[0018] Figure 2 is Figure 1 the B-B direction schematic diagram of the damping ring of the embodiment shown;

[0019] Figure 3 is Figure 2 the sectional view along the C-C direction of the schematic diagram shown. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme of the present application will be described in more detail below in combination with the drawings in the embodiments of the present application. In the drawings, the same or similar reference signs represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all of the embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as limiting the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below in combination with the drawings.

[0021] As Figures 1-3 shown in the figure, the vibration damper ring for the aero-engine stator blade comprises:

[0022] The stator blade 1 is provided with an outer edge plate 12 at the outer edge thereof and an inner edge plate 11 at the inner edge thereof, and the outer edge plate 12 is connected to the casing 3 through threaded fasteners; the stator blade 1 is provided with a part A at the corresponding position of the front edge and the corresponding position of the rear edge of the casing 3, and the side wall of the inner edge plate 11 is flat;

[0023] The inner ring 2 is placed in the casing 3 and coaxial with the casing 3, and the outer wall surface of the inner ring 2 is provided with mounting holes which are connected to the side wall of the inner edge plate 11; the vibration damper ring 4 is mounted between the side wall and the side wall surface of the mounting hole, the vibration damper ring 4 is made of non-metallic material and has a thin wall structure, the vibration damper ring 4 has a vertical wall between the side wall and the side wall surface of the mounting hole, the inner wall surface of the vertical wall is flush with the outer wall surface, the inner wall surface of the vibration damper ring 4 is not limited in shape and size, and can be the same as the shape of the inner edge plate 11 of the stator blade, such as quadrilateral, polygonal and irregular shape, and can be matched with the inner edge plate 11 of the stator blade in a small gap according to the use requirement; the outer wall surface of the vibration damper ring 4 is not limited in shape and size, and can be the same as the shape of the mounting groove of the inner ring 2, such as quadrilateral, polygonal and irregular shape, and can be matched with the mounting groove of the inner ring in a small gap. The outer end surface of the vibration damper ring is a flow path surface, and the size is designed according to the size of the flow path; the inner end surface of the vibration damper ring 4 is flush with the end surface of the mounting groove of the inner ring.

[0024] The material of the vibration damper ring 4 includes polyetherimide, polyether ether ketone or polyphenylsiloxane.

[0025] Preferably, the edge of the side wall has a first step surface, the edge of the hole of the mounting hole has a second step surface, the first step surface is connected to the second step surface, and the freedom degree of the stator blade 1 in the radial direction of the inner ring 2 is limited.

[0026] Preferably, the mounting hole is a through hole, the hole of the mounting hole close to the stator blade 1 has a step surface, the vibration damper ring 4 has a vertical wall between the side wall and the side wall surface of the mounting hole, and a flange perpendicular to the vertical wall, and the flange overlaps the step surface.

[0027] Preferably, the end of the vertical wall away from the flange has a lug protrusion, and the lug protrusion and the flange form a mounting groove therebetween, and the width of the mounting groove is equal to the length of the mounting hole, so that the wall surface of the mounting hole is immersed in the mounting groove.

[0028] Preferably, the vibration damper ring 4 and the inner ring are designed as an equal-wall-thickness flat section at the matching position of the inlet and outlet of the vibration damper ring 4 and the inner ring, so as to facilitate the disassembly and assembly of the vibration damper ring 4; and the vibration damper ring 4 and the inner ring are designed as a lug structure at the circumferential matching position, the lug protrusion is 0.5-1.5 mm, the small protrusion of the vibration damper ring 4 is easy to fall off, the large protrusion of the vibration damper ring 4 is difficult to assemble, and is easy to be damaged during assembly and disassembly.

[0029] Preferably, the wall thickness of the vertical wall is 0.6-1.5 mm, which is easy to damage when the wall thickness is small and difficult to assemble when the wall thickness is large.

[0030] Preferably, the damping ring 4 is formed by injection molding, which is also called press molding or compression molding. The operation is to put the powdered, granular or fibrous plastic into the mold cavity at the molding temperature, then close the mold and pressurize to make it form and solidify. The molding of the damping ring 4 in the application can be used for thermosetting plastic, thermoplastic and rubber material.

[0031] The advantages of the application are:

[0032] 1. The inner wall surface of the damping ring is not limited by shape and size, and can realize the same shape as the inner edge plate of the stator blade, reducing the design limitations of the inner edge plate of the stator blade.

[0033] 2. The damping ring can be self-positioned without the need for an inner ring and a stator blade boss to position the damping ring, simplifying the structure of the stator blade and the inner ring, reducing the processing cost and the weight of the parts.

[0034] 3. The inner end of the stator blade does not need to be designed with a damping ring positioning boss. When the stator blade is disassembled, it can be inserted into the inner ring first, then rotated and removed, avoiding interference with the blade front part A during disassembly. The part A can not be disassembled during disassembly, improving the assembly of the stator blade, reducing the disassembly workload and improving work efficiency. If part A is a casing base or cannot be disassembled, this structure can realize the assembly of the blade under the whole ring casing, avoiding the split casing structure and reducing the parts and assembly workload.

[0035] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto. Any changes or replacements within the technical scope disclosed in the application can be easily thought of by those skilled in the art, which should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A vibration damper ring for a stator blade of an aeroengine, characterized in that The application relates to a stator blade (1) and an inner ring (2) for a gas turbine, and belongs to the technical field of gas turbines. The outer edge of the stator blade (1) is provided with an outer edge plate (12), the inner edge of the stator blade (1) is provided with an inner edge plate (11), the outer edge plate (12) is connected with a casing (3) through a threaded fastener; the front edge of the stator blade (1) is provided with a part A at a position corresponding to the casing (3), and the rear edge is provided with a part A at a position corresponding to the casing (3); the side wall of the inner edge plate (11) is flat; The inner ring (2) is arranged in the casing (3) and coaxial with the casing (3), the outer wall surface of the inner ring (2) is provided with a mounting hole, the mounting hole is connected with the side wall of the inner edge plate (11) in a matched mode; a damping ring (4) is arranged between the side wall and the contact surface of the mounting hole, the material of the damping ring (4) comprises polyetherimide, polyether ether ketone or polyphenyl plastic; The edge of the side wall is provided with a first step surface, the edge of the hole of the mounting hole is provided with a second step surface, the first step surface is connected with the second step surface in a matched mode, and the freedom degree of the stator blade (1) along the radial direction of the inner ring (2) is limited; The mounting hole is a through hole, the hole of the mounting hole close to the stator blade (1) is provided with a step surface, the damping ring (4) is provided with a vertical wall between the side wall and the side wall surface of the mounting hole and a turn-up edge perpendicular to the vertical wall, and the turn-up edge is overlapped with the step surface The end of the vertical wall away from the turn-up edge is provided with a lug, the lug and the turn-up edge form a mounting groove, the width of the mounting groove is equal to the length of the mounting hole, and the wall surface of the mounting hole is immersed in the mounting groove.

2. The vibration ring for a turbine stator vane of a gas turbine engine of claim 1, wherein, The protruding height of the lug is 0.5-1.5 mm.

3. The vibration ring for a turbine stator vane of a gas turbine engine of claim 1, wherein, The wall thickness of the vertical wall is 0.6-1.5 mm.

4. The vibration ring for a turbine stator vane of a gas turbine engine of claim 1, wherein, The damping ring (4) is formed through injection molding.

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