Integral type vibration reduction damper for parallel crown blades of engine and assembling method of integral type vibration reduction damper

Abstract

The invention discloses an integral type vibration reduction damper for parallel crown blades of an engine and an assembling method of the integral type vibration reduction damper, the integral type vibration reduction damper comprises an integral ring type flange, the integral ring type flange is provided with a positioning part, and the positioning part is suitable for being connected with a blade crown of each parallel crown blade; a notch is formed in the whole ring type flange; the multiple damping fins are arranged on the whole-ring type blocking edge at intervals, the damping fins penetrate through the space between blade bodies of every two adjacent parallel crown blades and are located on the radial inner sides of blade crowns of the parallel crown blades, and the radial outer side faces of the damping fins are friction faces; and the friction surfaces of the damping fins are attached to the radial inner side surfaces of the blade crowns of the two adjacent parallel crown blades and block a gap between the blade crowns of the two adjacent parallel crown blades. According to the invention, the excitation load of the blade crown can be reduced through friction acting, the gas leakage between the blades can be reduced, and the blade can be simply assembled in an engine rotor assembly and has very high safety.

Description

Technical Field

[0001] The present invention relates to the field of aero-engines, and particularly to an integral vibration damping device for parallel-crowned blades of an engine and an assembly method thereof. Background Art

[0002] In an aero-engine, blades are one of the key components. The existing crowned blades made of superalloys are often designed in a serrated shape, and by designing a pre-twist angle, adjacent blade crowns are pressed against each other, and the friction between the blade crowns is used to reduce the damage of the exciting load to the blades. However, in recent years, the materials science has developed a variety of new high-temperature materials for manufacturing aero-engine blades, such as titanium aluminide alloys, niobium silicide-based alloys, ceramic matrix composites, and so on. These materials have the advantages of high temperature resistance, corrosion resistance, low density, etc., but are usually brittle. If used to manufacture crowned blades, they are not suitable for designing a pre-twist structure. Therefore, the crowns made of these new high-temperature materials usually adopt a parallel structure, and the friction between the parallel crowns cannot be directly used to reduce the exciting load.

[0003] The existing vibration damping devices for engine rotors are usually designed in a structure where each blade corresponds to a vibration damping device. This solution usually requires designing a firm assembly structure or a sealed chamber to connect the blades and the movable vibration damping devices together. Therefore, the vibration damping devices are usually installed below the rim of the rotor blades to reduce the stress at the blade roots. If it is necessary to reduce the stress at the tips of the blades with a long blade body, a serrated crown is designed to use the friction damping between the crowns. If a split vibration damping device is used between the parallel crowns, there are two risks: First, the vibration damping device is in the gas flow path. If a single vibration damping device becomes loose during the high-speed rotation of the rotor, it will hit the parts downstream of the flow path at a high speed, causing unpredictable damage to the engine; Second, the assembly process is difficult. Whether the blades and the rotor disc are assembled first or the blades and the vibration damping devices are assembled first, it is difficult to install the vibration damping devices one by one. If the rotor needs to be disassembled and inspected frequently, the assembly work is very cumbersome. Summary of the Invention

[0004] In view of this, the present invention provides an integral vibration damping device for parallel-crowned blades of an engine and an assembly method thereof to solve the problems that the existing vibration damping devices for engine rotors are prone to become loose during the high-speed rotation of the rotor and are difficult to install and disassemble.

[0005] In a first aspect, the present invention provides an integral vibration damping device for parallel-crowned blades of an engine, including:

[0006] An integral ring-shaped rib, on which a positioning portion is provided, and the positioning portion is adapted to be connected to the crowns of the parallel-crowned blades; a notch is provided on the integral ring-shaped rib;

[0007] A plurality of damping plates are arranged at intervals on the integral ring-shaped rib. The damping plates pass through between the blade bodies of two adjacent parallel shroud blades and are located radially inside the shrouds of the parallel shroud blades. The radially outer side surface of the damping plate is a friction surface, and the friction surface of the damping plate is attached to the radially inner side surfaces of the shrouds of two adjacent parallel shroud blades and seals the gap between the shrouds of two adjacent parallel shroud blades.

[0008] The beneficial effects of the integral vibration damping device for the parallel shroud blades of the above engine are as follows:

[0009] The integral ring-shaped rib and the damping plates adopt an integrated design. All the damping plates are connected into a whole through the integral ring-shaped rib, and there are axial and radial limiting relationships between the integral ring-shaped rib and the shroud, which can simplify the assembly process and reduce the risk of part detachment, avoiding the risk of single loosening of the traditional split-type vibration damping device. The damping is located radially inside the shroud, and the integral structure and the shroud form a circular constraint. Even when rotating at high speed, the damping plates will not break away alone and impact the flow passage, ensuring the safe operation of the engine.

[0010] Notches are provided on the integral ring-shaped rib, which can ensure that when the rotor rotates and works, the friction surface of the damping plate is displaced under the action of the centrifugal load of the whole vibration damping device, fits on the surface of the shroud, and frictionally does work when the blade is excited, consuming the excitation load of the blade and effectively suppressing the vibration stress of the blade body.

[0011] The friction surface of the damping plate is installed between two adjacent shrouds, which can seal the gas in the flow passage, reduce the leakage of the gas, and reduce the energy loss.

[0012] The radially outer side surface (friction surface) of the damping plate automatically fits the radially inner side surface of the shroud under the action of centrifugal force. The frictional contact is stable and does not rely on the pre-twisting performance of the blade material. A frictional interface is directly constructed between the parallel shroud blades, which is applicable to brittle material blades and expands the application of new high-temperature materials in aeroengines.

[0013] The integral vibration damping device is connected to all the shrouds through the positioning part of the integral ring-shaped rib, and there is no need to install split-type damping devices on the blades one by one, greatly reducing the assembly complexity. It is especially suitable for the maintenance scenario of the engine rotor that needs to be frequently disassembled and inspected.

[0014] In an optional embodiment, the positioning part is a hook groove provided on the axially rear side surface of the integral ring-shaped rib, and the hook groove is adapted to be connected to the leading edge of the shroud of the parallel shroud blade.

[0015] The beneficial effects of the above technical solution are as follows: The cooperation between the hook groove and the leading edge of the shroud is achieved by plugging. During installation, the integral ring-shaped baffle only needs to be axially pushed into the leading edge of the shroud to achieve automatic clamping. All shrouds are synchronously fixed through the hook grooves of the same integral ring-shaped baffle, avoiding the cumbersome process of installing traditional split dampers one by one.

[0016] In an alternative embodiment, the damping piece is integrally provided on the axially rear side surface of the integral ring-shaped baffle, and the damping piece is located radially inside the hook groove.

[0017] In an alternative embodiment, a baffle is integrally provided on the rear side of the damping piece extending from the shroud of the parallel shroud blade, and the damping piece and the baffle cooperate with each other to position the trailing edge of the shroud of the parallel shroud blade.

[0018] The beneficial effects of the above technical solution are as follows: The integrated design of the damping piece and the baffle forms a shroud positioning module of "front hook and rear baffle". During installation, only the damping piece needs to be axially pushed into the hook groove, and then the baffle is bent to complete the front and rear limit positions without additional adjustment or fastening, and the installation is very convenient. During maintenance, the baffle is straightened, and the integral vibration damping damper can be directly separated from the parallel shroud blade, and the disassembly is very convenient.

[0019] In an alternative embodiment, there is a clearance fit between the damping piece and the shroud of the parallel shroud blade.

[0020] The beneficial effects of the above technical solution are as follows: After the baffle is bent, a certain amount of movement is ensured for the damping piece when assembling the bent baffle, so that the damping piece is loosely assembled with the shroud, and the damping piece is closely attached to the shroud to ensure the relative movement between the shroud during vibration and the vibration damping damper, thereby generating friction.

[0021] In an alternative embodiment, the edge profile of the damping piece is a parallel straight line or a structure that fits the profile of the blade body.

[0022] In an alternative embodiment, the integral ring-shaped baffle is circular.

[0023] In a second aspect, the present invention provides an assembly method for an integral vibration damping damper of an engine parallel shroud blade, including the following steps:

[0024] S1. Insert the blade body of the parallel shroud blade axially between two adjacent damping pieces, and assemble the shroud of the parallel shroud blade onto the positioning portion of the integral ring-shaped baffle;

[0025] S2. Assemble all the parallel shroud blades in the manner of step S1, so that after the assembly, each damping piece fits against the radially inner side surface of the shroud of the parallel shroud blade, and seals the gap between the shrouds of two adjacent parallel shroud blades;

[0026] S3. Assemble the tenons of all parallel shrouded blades into the mortises of the rotor disk.

[0027] In an alternative embodiment, in step S1, insert the leading edge of the shroud of the parallel shrouded blade into the hook groove of the integral retaining edge to position the leading edge of the shroud of the parallel shrouded blade.

[0028] After performing step S3, bend the baffle plate at the rear side of each damping piece so that the damping piece and the baffle plate cooperate with each other to position the trailing edge of the shroud of the parallel shrouded blade.

[0029] In an alternative embodiment, when bending the baffle plate at the rear side of each damping piece, allow the damping piece to have a certain amount of movement.

[0030] In summary, the technical solution of the present invention has the following advantages:

[0031] 1. The integral vibration damping damper of the present invention will not fall off separately, reducing the risk of the damping piece falling in the flow passage.

[0032] 2. The integral retaining edge with a hook groove of the present invention connects multiple damping pieces into one body, greatly simplifying the assembly process.

[0033] 3. The integral retaining edge with a hook groove of the present invention has a notch, ensuring that the friction surface of the damping piece is displaced under the action of the centrifugal load of the entire vibration damping damper during the rotation of the rotor, fits on the surface of the shroud, and performs frictional work during blade excitation.

[0034] 4. The friction surface of the damper of the present invention is installed between two adjacent shrouds, which can seal the gas in the flow passage and reduce the gas leakage. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0036] Figure 1 Schematic diagram of the structure of a shrouded blade made of existing superalloy designed with a serrated shape;

[0037] Figure 2 Schematic diagram of the structure of a shrouded blade made of existing superalloy designed with a parallel shroud;

[0038] Figure 3 Schematic diagram of the structure of the integral vibration damping damper for the engine parallel shrouded blade provided by the present invention;

[0039] Figure 4 Side view of the integral vibration damping device for the parallel crown blades of the engine provided by the present invention;

[0040] Figure 5 Schematic structural diagram of the integral vibration damping device for the parallel crown blades of the engine provided by the present invention during assembly;

[0041] Figure 6 Side view of the baffle in the integral vibration damping device for the parallel crown blades of the engine provided by the present invention before bending;

[0042] Figure 7 Side view of the baffle in the integral vibration damping device for the parallel crown blades of the engine provided by the present invention after bending;

[0043] Figure 8 Schematic structural diagram of the integral vibration damping device for the parallel crown blades of the engine provided by the present invention when the edge contour of the damping sheet is set as parallel straight lines;

[0044] Figure 9 Schematic structural diagram of the integral vibration damping device for the parallel crown blades of the engine provided by the present invention when the damping sheet is designed to fit the blade body contour.

[0045] Explanation of reference numerals:

[0046] 1, integral ring-shaped rib; 11, hook groove; 2, damping sheet; 21, friction surface; 3, baffle; 4, notch; 6, parallel crown blade; 61, blade body; 62, blade crown; 621, leading edge of blade crown; 622, trailing edge of blade crown; 63, tenon; 7, rotor disk. Detailed implementation manners

[0047] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some but not all of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present invention.

[0048] In an aeroengine, the blade is one of the key components. As Figure 1 shown, referring to the Chinese invention patent with the authorization announcement number CN101372895B, the existing crowned blades made of superalloy are often designed as serrated, and by designing the pre-twist angle of the blade body, the adjacent blade crowns are pressed against each other during the rotor working state, and the friction between the blade crowns is used to reduce the damage of the excitation load to the blade.

[0049] New high-temperature materials such as titanium aluminide alloys, niobium silicide-based alloys, ceramic matrix composites, etc. cannot withstand large pre-torsion loads. Therefore, when used to manufacture shrouded blades, it is not suitable to design the shroud as a serrated shape. It can only be designed as a parallel shroud, as Figure 2 shown. This design state itself does not have a friction damping structure. A new damping structure needs to be designed for the shroud to reduce the exciting load.

[0050] When the engine rotor rotates at high speed, intense vibrations will occur due to the unsteady turbulent flow of the gas. For different engine structures, at different natural frequencies, the vibration load will surge, causing damage to the rotor blades. For this harmful phenomenon, generally, dynamic damping is designed on the blades to generate frictional loads through centrifugal force to reduce the stress of the blades.

[0051] Existing engine rotor damping dampers are usually designed with a one-to-one correspondence structure between the blades and the damping dampers. This solution usually requires designing a firm assembly structure or a sealed chamber to connect the blades and the movable damping dampers together. Therefore, the damping dampers are usually installed below the rim of the rotor blade to reduce the stress at the blade root. If it is necessary to reduce the stress at the tip of a blade with a long blade body, a serrated shroud is designed to utilize friction damping between the shrouds. There are risks when using split damping dampers between parallel shrouds: First, the damping dampers are in the gas flow path. If a single damping damper becomes loose during high-speed rotation of the rotor, it will hit the parts downstream of the flow path at high speed, causing unpredictable damage to the engine; Second, the assembly process is difficult. Whether the blades and the rotor disc are assembled first or the blades and the damping dampers are assembled first, it is difficult to install the damping dampers one by one. If the rotor often needs to be disassembled and inspected, the assembly work is very cumbersome.

[0052] Based on this, the present invention provides an integral damping damper for engine parallel crown blades, which can not only reduce the exciting load of the shroud through frictional work, but also reduce the gas leakage between the blades, can be simply assembled into the engine rotor assembly, and has high safety. The present invention improves the integral damping damper applicable to parallel crown blades in two aspects:

[0053] First, enhance the safety of the integral damping damper of the parallel crown blades and reduce the risk of the damping pieces falling in the flow path;

[0054] Second, simplify the assembly process of the integral damping damper of the parallel crown blades and improve the process efficiency of rotor assembly and disassembly.

[0055] Combined with Figures 3 to 9 shown, according to an embodiment of the present invention, in the first aspect, an integral damping damper for engine parallel crown blades is provided, including an integral ring-shaped rib 1 and damping pieces 2.

[0056] Among them, the engine parallel crown blade includes a blade body 61, a blade crown 62, and a blade root. The blade body 61 is the main part of the blade, and its shape and curved surface design play a key role in the aerodynamic performance of the engine. Through precise aerodynamic design, the blade body can guide the air flow to flow smoothly, improving the efficiency and performance of the engine. The blade crown 62 is a parallel crown, located at the top of the blade, and its characteristic is that the shape of the crown part remains parallel within a certain range. The design of the parallel crown can enhance the rigidity and stability of the blade, reduce the vibration and deformation of the blade during high-speed rotation, thereby improving the reliability and service life of the blade. The blade root is used to fix the blade on the rotor disk of the engine, and a tenon 63 is provided on the blade root.

[0057] The integral ring-shaped rib 1 is provided with a positioning portion, and the positioning portion is adapted to be connected to the blade crowns of the parallel crown blades to axially and radially fix the integral ring-shaped rib 1 on the blade crowns, having an axial and radial limiting relationship with the blade crowns.

[0058] A plurality of damping sheets 2 are provided and are respectively arranged at intervals on the integral ring-shaped rib 1. The damping sheets 2 pass through between the blade bodies 61 of two adjacent parallel crown blades and are located radially inside the blade crowns 62 of the parallel crown blades, and are assembled on two adjacent blade crowns. The radially outer side surface of the damping sheet 2 is a friction surface 21, and the friction surface 21 of the damping sheet 2 is attached to the radially inner side surfaces of the blade crowns 62 of two adjacent parallel crown blades and seals the gap between the blade crowns 62 of two adjacent parallel crown blades.

[0059] For the above integral vibration damping device of the engine parallel crown blade, the integral ring-shaped rib 1 and the damping sheets 2 adopt an integrated design. All the damping sheets 2 are connected into a whole through the integral ring-shaped rib, and the integral ring-shaped rib 1 has an axial and radial limiting relationship with the blade crowns, which can simplify the assembly process and reduce the risk of part detachment, avoiding the risk of single loosening of the traditional split vibration damping device. The damping sheets 2 are located radially inside the blade crowns, and the integral structure forms a ring-shaped constraint with the blade crowns. Even during high-speed rotation, the damping sheets 2 will not separate alone and impact the flow channel, ensuring the safe operation of the engine.

[0060] The integral ring-shaped rib 1 is provided with a notch 4, which can ensure that when the rotor rotates and works, the friction surface of the damping sheet is displaced under the action of the centrifugal load of the entire vibration damping device, adheres to the surface of the blade crown, and frictionally does work during blade excitation, consuming the excitation load of the blade and effectively suppressing the vibration stress of the blade body.

[0061] The friction surface of the damping sheet 2 is installed between two adjacent blade crowns, which can seal the gas in the flow channel, reduce the leakage amount of the gas, and reduce the energy loss.

[0062] The radially outer side surface (friction surface) of the damping piece 2 automatically fits against the radially inner side surface of the blade crown under the action of centrifugal force. The frictional contact is stable and does not rely on the pre-twisting performance of the blade material. A frictional interface is directly constructed between the parallel-crown blades, which is applicable to brittle material blades and expands the application of new high-temperature materials in aeroengines.

[0063] The integral vibration damping damper is connected to all blade crowns through the positioning part of the integral ring-shaped rib. There is no need to install split dampers on the blades one by one, which greatly reduces the assembly complexity. It is especially suitable for the maintenance scenario of engine rotors that need to be frequently disassembled and inspected.

[0064] In some embodiments, the positioning part is a hook groove 11 provided on the axially rear side surface of the integral ring-shaped rib 1. The hook groove 11 is adapted to be connected to the leading edge 621 of the blade crown of the parallel-crown blade. In this embodiment, the cooperation between the hook groove 11 and the leading edge 621 of the blade crown adopts an insertion method. During installation, only the integral ring-shaped rib needs to be pushed axially into the leading edge of the blade crown to achieve automatic clamping. All blade crowns are synchronously fixed through the hook grooves of the same integral ring-shaped rib, avoiding the cumbersome process of installing split dampers one by one in the traditional way.

[0065] The geometric shape of the hook groove is set as an inverted hook type. The hook groove is an open mechanical connection structure, allowing the integral ring-shaped rib and the blade crown to have a small amount of free deformation when thermal expansion occurs at high temperature, avoiding the problem of thermal stress concentration that may be caused by welding or bolt connection.

[0066] It should be noted that in this embodiment, the radially outer side refers to the direction along the radius pointing outside the circumference, the radially inner side refers to the direction along the radius pointing inside the circumference, and the axially rear side refers to the side along the axis pointing backward.

[0067] In some embodiments, the side view of a single damping piece of this part is as Figure 4 shown. The damping piece 2 is integrally provided on the axially rear side surface of the integral ring-shaped rib 1. The damping piece 2 is located radially inside the hook groove 11. After the leading edge 621 of the blade crown of the parallel-crown blade is positioned in the hook groove 11, the blade crown of the parallel-crown blade is located radially outside the damping piece. When the rotor rotates, the centrifugal force pushes the damping piece to fit against the radially inner side surface of the blade crown outward, ensuring that the friction surface 21 always presses tightly against the blade crown, and the contact pressure can be adapted without pre-tightening force.

[0068] In some embodiments, the rear side of the damping sheet 2 extends from the shroud of the parallel shrouded blades and is integrally provided with a baffle 3. The damping sheet 2 and the baffle 3 cooperate with each other to position the trailing edge 622 of the shroud of the parallel shrouded blades. The baffle 3 is a straight baffle. After the integral retaining edge 1 with a hook groove of the vibration damping damper fits with the leading edges of the shrouds of all the blades, the baffle 3 is bent. The baffle 3 and the damping sheet 2 cooperate to form axial and radial limits for the trailing edge 622 of the shroud, and form front and rear clamping with the hook groove 11 of the leading edge 621 of the shroud, so as to form front and rear limits between the damping sheet 2 and the parallel shrouded blades. The positioning of the baffle 3 for the trailing edge of the shroud keeps the friction surface 21 of the damping sheet in uniform pre-tightening with the radially inner side of the shroud all the time, avoiding local detachment or uneven pressure of the friction surface caused by the swing of the trailing edge of the shroud.

[0069] The integrated design of the damping sheet 2 and the baffle forms a shroud positioning module of "front hook and rear baffle". During installation, only the damping sheet 2 needs to be axially pushed into the hook groove, and then the baffle 3 is bent to complete the front and rear limits, without additional adjustment or fastening. During maintenance, the baffle 3 is straightened, and the integral vibration damping damper can be directly separated from the parallel shrouded blades.

[0070] In some embodiments, there is a clearance fit between the damping sheet 2 and the shroud of the parallel shrouded blades. More specifically, after the baffle 3 is bent, a certain amount of movement is ensured for the damping sheet when assembling the bent baffle 3, so that the damping sheet is loosely assembled with the shroud, and the damping sheet is closely attached to the shroud, ensuring the relative movement between the shroud during vibration and the vibration damping damper, and thus generating friction.

[0071] In some embodiments, the edge contour of the friction surface of the damping sheet 2 is designed to fit the edge contour of the blade body and cannot block the assembly.

[0072] As Figure 8 shown, the edge contour of the damping sheet 2 can be set as parallel straight lines.

[0073] As an alternative embodiment, as Figure 9 shown, the damping sheet 2 is designed into a structure that fits the blade body contour. This can reduce the kinetic energy loss of the gas in the flow channel. The specific structural design of the damping sheet 2 can be carried out in combination with the gas dynamics design. As long as the blade body can penetrate into the gap between two adjacent damping sheets 2, the assembly requirements can be met.

[0074] In some embodiments, the integral retaining edge 1 is circular and can be directly positioned at the periphery of each parallel shrouded blade of the engine rotor.

[0075] According to an embodiment of the present invention, in a second aspect, there is provided an engine rotor assembly, including parallel shrouded blades 6, a rotor disc 7, and the above-mentioned integral vibration damping damper. The parallel shrouded blades 6 and the rotor disc 7 are connected by mortise and tenon joints, and the integral vibration damping damper is positioned on the parallel shrouded blades 6.

[0076] According to an embodiment of the present invention, in a third aspect, there is provided an assembly method for an integral vibration damping device of an engine parallel crown blade, including the following steps:

[0077] S1. Insert the blade body 61 of the parallel crown blade 6 axially between two adjacent damping plates 2, and assemble the blade crown 62 of the parallel crown blade 6 onto the positioning portion of the integral ring-shaped edge 1. More specifically, insert the leading edge 621 of the blade crown of the parallel crown blade into the hook groove 11 of the integral ring-shaped edge 1 to position the leading edge 621 of the blade crown of the parallel crown blade.

[0078] S2. Assemble all the parallel crown blades 6 in the manner of step S1, so that after the assembly is completed, each damping plate 2 fits against the radially inner side surface of the blade crown 62 of the parallel crown blade, and seal the gap between the blade crowns 62 of two adjacent parallel crown blades 6.

[0079] S3. Assemble the tenons of all the parallel crown blades 6 into the tenon grooves of the rotor disk 7.

[0080] After performing step S3, bend the baffle 3 behind each damping plate 2 so that the damping plate 2 and the baffle 3 cooperate with each other to position the trailing edge 622 of the blade crown of the parallel crown blade. When bending the baffle 3 behind each damping plate 2, make the damping plate 2 have a certain amount of movement so that the damping plate 2 is loosely assembled with the trailing edge 622 of the blade crown.

[0081] The bending position of the integral vibration damping device is as Figure 7 shown. The state after the integral vibration damping device and the parallel crown blade are assembled is as Figure 8 shown.

[0082] According to the working temperature requirement of the engine rotor, the manufacturing material of the integral vibration damping device designed by the present invention should be an alloy suitable for this working temperature. Moreover, its ultimate strength and yield strength should both meet the results of the rotor stress calculation.

[0083] During the operation of the engine, the integral vibration damping device is subjected to centrifugal force, and the friction surface of the damping plate 2 will closely adhere to the inner surface of the flow channel of the blade crown. Therefore, the shape design of the friction surface of the damping plate should be carried out in combination with gas dynamic calculation to minimize the influence of the damping plate on the gas flow.

[0084] After the integral vibration damping device designed by the present invention is assembled and installed on the engine parallel crown blade, it can not only reduce the excitation load of the blade crown by friction work, but also reduce the gas leakage between the parallel crown blades. Moreover, it is a single part, enhancing the safety of the integral vibration damping device of the parallel crown blade and reducing the risk of the damping plate falling in the flow channel; the assembly process is simple, improving the assembly and disassembly work efficiency.

[0085] Through simulation modeling and trial fitting, the vibration damping damper of the present invention can be assembled on the parallel shroud blades of the engine, and theoretically can reduce the exciting load of the shroud.

[0086] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations fall within the scope defined by the appended claims.

Claims

1. An integral vibration damping damper for an engine parallel crown blade, characterized in that, Comprising: An integral ring-shaped rib (1), on which a positioning portion is provided, and the positioning portion is adapted to be connected to the crowns of the parallel shroud blades; A notch (4) is provided on the integral ring-shaped rib (1); A plurality of damping sheets (2), which are arranged at intervals on the integral ring-shaped rib (1), the damping sheets (2) pass through between the blade bodies (61) of two adjacent parallel shroud blades and are located radially inside the crowns (62) of the parallel shroud blades, the radially outer side surface of the damping sheet (2) is a friction surface (21), and the friction surface (21) of the damping sheet (2) is attached to the radially inner side surfaces of the crowns (62) of two adjacent parallel shroud blades and seals the gap between the crowns (62) of two adjacent parallel shroud blades; 2. The integral vibration damping damper for the engine parallel crown blade according to claim 1, characterized in that The positioning portion is a hook groove (11) provided on the axially rear side surface of the integral ring-shaped rib (1), and the hook groove (11) is adapted to be connected to the leading edge (621) of the crown of the parallel shroud blade; 3. The integral vibration damping damper of the engine parallel crown blade according to claim 2, characterized in that, The damping sheet (2) is integrally provided on the axially rear side surface of the integral ring-shaped rib (1), and the damping sheet (2) is located radially inside the hook groove (11); 4. The integral vibration damping damper for the engine parallel crown blade according to claim 3, characterized in that, A baffle (3) is integrally provided on the rear side of the damping sheet (2) extending from the crown of the parallel shroud blade, and the damping sheet (2) and the baffle (3) cooperate with each other to position the trailing edge (622) of the crown of the parallel shroud blade; 5. The integral vibration damping damper for the engine parallel crown blade according to any one of claims 1-4, characterized in that, The damping sheet (2) has a clearance fit with the crown of the parallel shroud blade; 6. The integral vibration damping damper of the engine parallel crown blade according to any one of claims 1-4, characterized in that, The edge profile of the damping sheet (2) is a parallel straight line or a structure conforming to the blade body profile; 7. The integral vibration damping damper of the engine parallel crown blade according to any one of claims 1-4, characterized in that, The integral ring-shaped rib (1) is circular; 8. An assembly method for an integral vibration damping damper of an engine parallel crown blade, characterized in that, Comprising the following steps: S1. Insert the blade body (61) of the parallel shroud blade (6) axially between two adjacent damping sheets (2), and assemble the crown (62) of the parallel shroud blade (6) to the positioning portion of the integral ring-shaped rib (1); S2. Assemble all the parallel shroud blades (6) in the manner of step S1 in sequence, so that after the assembly, each damping sheet (2) is attached to the radially inner side surface of the crown (62) of the parallel shroud blade (6) and seals the gap between the crowns (62) of two adjacent parallel shroud blades (6); S3. Assemble the tenons of all the parallel shroud blades (6) into the tenon grooves of the rotor disk (7); 9. The assembly method of the integral vibration damping damper for the engine parallel crown blade according to claim 8, characterized in that, In step S1, insert the leading edge (621) of the crown of the parallel shroud blade into the hook groove (11) of the integral ring-shaped rib (1) to position the leading edge (621) of the crown of the parallel shroud blade; After performing step S3, bend the baffle (3) at the rear side of each damping sheet (2) so that the damping sheet (2) and the baffle (3) cooperate with each other to position the trailing edge (622) of the crown of the parallel shroud blade; 10. The assembly method of the integral vibration damping damper of the engine parallel crown blade according to claim 9, characterized in that, When bending the baffle (3) at the rear side of each damping sheet (2), make the damping sheet (2) have a play.

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