An aircraft engine turbine disk rotor balance connection device

Abstract

This application belongs to the technical field of aero-engine turbine disk rotor balance, and specifically relates to a balance connection device for an aero-engine turbine disk rotor, including: a positioning seat, which is connected to the drum connection edge on the turbine disk rotor; a support ring, one side of which has an annular support protrusion, and the outer edge has an annular connection edge; the annular support protrusion abuts against the positioning seat; the annular connection edge is connected to the positioning seat; a plurality of positioning blocks, which are connected to the other side of the support ring, are distributed along the circumferential direction of the support ring, and extend into the center of the turbine disk rotor; when an external force acting on the center part of the support ring and directed away from the positioning seat is applied, each positioning block can be outwardly opened and abutted against the center of the turbine disk rotor; when the external force acting on the center part of the support ring and directed away from the positioning seat disappears, each positioning block contracts inwardly and separates from the center of the turbine disk rotor.

Description

Technical Field

[0001] This application belongs to the technical field of aero-engine turbine disk rotor balancing, and particularly relates to a balancing connection device for an aero-engine turbine disk rotor. Background Art

[0002] Before an aero-engine turbine disk rotor is installed, it needs to be balanced. When balancing the turbine disk rotor, a balancing connection device is connected to a balancing machine, and the balancing machine is used for driving to collect and adjust the unbalance of the turbine disk rotor.

[0003] The balancing connection device is connected between the turbine disk rotor and the balancing machine, and it is necessary to radially position the center of the turbine disk rotor and be able to transmit torque circumferentially to the turbine disk rotor. Using the current balancing connection device to balance the turbine disk rotor has the following defects:

[0004] 1) The machining tolerances of the centers of different turbine disk rotors are relatively large, up to 0.2 mm. When radially positioning them, it is easy to have situations of large interference or large clearance fits. When there is a large interference amount, it is not convenient for assembly and disassembly, and it will cause damage to the center of the turbine disk rotor. When there is a large clearance amount, it will introduce uncertain errors to the balance of the turbine disk rotor, affecting the balance effect of the turbine disk rotor;

[0005] 2) During the balancing process of the turbine disk rotor, it is easy for the turbine disk rotor to come off, resulting in damage to the turbine disk rotor.

[0006] In view of the existence of the above technical defects, this application is proposed.

[0007] It should be noted that the disclosure of the above background art content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background art should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0008] The purpose of this application is to provide a balancing connection device for an aero-engine turbine disk to overcome or mitigate at least one aspect of the known technical defects.

[0009] The technical solution of this application is:

[0010] A balancing connection device for an aero-engine turbine disk rotor, comprising:

[0011] A positioning seat, which is connected to the drum connection edge on the turbine disk rotor;

[0012] A support ring, having an annular support protrusion on one side and an annular connection edge on the outer edge; the annular support protrusion abuts against the positioning seat; the annular connection edge is connected to the positioning seat;

[0013] A plurality of positioning blocks, connected to the other side of the support ring, distributed circumferentially along the support ring, and extending into the center of the turbine disk rotor;

[0014] When an external force acting on the center part of the support ring in the direction away from the positioning seat is applied, each positioning block can be opened outward and abutted against the center of the turbine disk rotor;

[0015] When the external force acting on the center part of the support ring in the direction away from the positioning seat disappears, each positioning block contracts inward and separates from the center of the turbine disk rotor.

[0016] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, between the positioning seat and the drum connection edge on the turbine disk rotor, they are connected by an anti-rotation pin.

[0017] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, between the annular connection edge and the positioning seat, they are connected by bolts.

[0018] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, each positioning block only has an arc-shaped surface;

[0019] When each positioning block opens outward, each arc-shaped surface abuts against the center of the turbine disk rotor;

[0020] When each positioning block contracts inward, each arc-shaped surface separates from the center of the turbine disk rotor.

[0021] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, it further includes:

[0022] A sleeve, having a perforation at its closed end, its open end extends into the support ring, and the outer wall of this end has an annular convex edge; the annular convex edge extends between the positioning seat and the support ring;

[0023] A screw, one end of which passes through the perforation and is screwed to the positioning seat, and the outer wall of the part extending into the sleeve has an annular convex fin;

[0024] When the screw is screwed outward from the positioning seat, the annular convex fin will abut against the inside of the closed end of the sleeve, so that the center part of the support ring receives an external force in the direction away from the positioning seat;

[0025] When the screw is screwed inward into the positioning seat, the annular convex fin will separate from the inside of the closed end of the sleeve, so that the external force acting on the center part of the support ring in the direction away from the positioning seat disappears.

[0026] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, the positioning seat has a positioning protrusion, and the positioning protrusion extends into the sleeve;

[0027] One end of the screw passing through the perforation is screwed on the positioning protrusion.

[0028] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, it further includes:

[0029] A gland, which is connected to the positioning seat by bolts and presses on the side of the turbine disk rotor core part facing away from the positioning seat.

[0030] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, the closed end of the sleeve has a through hole;

[0031] The bolts connecting the positioning seat and the gland pass through the through hole.

[0032] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, the bolts connecting the positioning seat and the gland are screwed on the positioning protrusion.

[0033] According to at least one embodiment of the present application, in the above-mentioned aero-engine turbine disk rotor balance connection device, the side of the gland facing the turbine disk rotor has a positioning groove, and its side wall has a through hole; the through hole communicates with the positioning groove;

[0034] The closed end of the sleeve extends into the positioning groove;

[0035] One end of the screw facing away from the positioning seat extends out from the through hole. Description of the Drawings

[0036] Figure 1 is a schematic diagram of the aero-engine turbine disk rotor balance connection device provided by the embodiment of the present application;

[0037] Figure 2 is a partial cross-sectional view of the support ring and the positioning block provided by the embodiment of the present application;

[0038] Figure 3 is a three-dimensional view of the support ring and the positioning block provided by the embodiment of the present application;

[0039] Figure 4 is a schematic diagram of the sleeve provided by the embodiment of the present application;

[0040] Figure 5 is a schematic diagram of the screw provided by the embodiment of the present application;

[0041] Wherein:

[0042] 1 - Positioning seat; 2 - Turbine disk rotor; 3 - Support ring; 4 - Positioning block; 5 - Sleeve; 6 - Screw; 7 - gland.

[0043] To better illustrate this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation of this patent. Detailed implementation manners

[0044] To make the technical solutions and their advantages of this application clearer, the technical solutions of this application will be further described clearly and completely below with reference to the drawings. It can be understood that the specific embodiments described here are only some embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0045] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the technical field to which this application belongs. The words indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to indicate the relative directions or position relationships, rather than implying that the device or component must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative position relationship may also change accordingly. Therefore, it cannot be construed as a limitation of this application. The terms "first", "second", "third", and similar terms used in the description of this application are only for descriptive purposes to distinguish different components and cannot be construed as indicating or implying relative importance. The words "a", "an", or "the" and similar terms used in the description of this application should not be construed as an absolute limitation of the quantity, but should be understood as having at least one. The terms "including" or "comprising" and similar terms used in the description of this application are intended to cover the elements or items appearing before this word and the elements or items listed after this word and their equivalents, without excluding other elements or items.

[0046] In addition, it should be noted that, unless otherwise clearly specified and defined, the similar terms such as "installed", "connected", and "linked" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can also be the communication inside two components. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0047] The following further elaborates on this application with reference to the attached Figures 1-5 drawings.

[0048] An aero-engine turbine disk rotor balance connection device includes:

[0049] A positioning seat 1, connected to the drum connection edge on the turbine disk rotor 2;

[0050] A support ring 3, having an annular support protrusion on one side and an annular connection edge on the outer edge; the annular support protrusion abuts against the positioning seat 1; the annular connection edge is connected to the positioning seat 1;

[0051] A plurality of positioning blocks 4, connected to the other side of the support ring 3, distributed circumferentially along the support ring 3, and extending into the center of the turbine disk rotor 2;

[0052] When an external force acting on the center of the support ring 3 is directed away from the positioning seat 1, each positioning block 4 can be caused to open outward and abut against the inside of the center of the turbine disk rotor 2;

[0053] When the external force acting on the center of the support ring 3 and directed away from the positioning seat 1 disappears, each positioning block 4 contracts inward and separates from the center of the turbine disk rotor 2.

[0054] For the aero-engine turbine disk rotor balance connection device disclosed in the above embodiments, those skilled in the art can understand that the design positions the positioning blocks 4 circumferentially connected to the side of the support ring 3 facing away from the positioning seat 1. The side of the support ring 3 facing the positioning seat 1 abuts against the positioning seat 1 through the annular support protrusion, and the outer edge is connected to the positioning seat 1 through the annular connection edge. When an external force acting on the center of the support ring 3 is directed away from the positioning seat 1, under the constraint of the annular connection edge and the support of the annular support protrusion, the support ring 3 bulges outward away from the positioning seat 1, causing each positioning block 4 to turn outward and open outward. When the external force acting on the center of the support ring 3 and directed away from the positioning seat 1 disappears, the support ring 3 will naturally recover, causing each positioning block 4 to turn inward and contract inward.

[0055] Using the aero-engine turbine disk rotor balance connection device disclosed in the above embodiments to balance the turbine disk rotor, the following steps can be referred to:

[0056] The positioning seat 1 is connected to the drum connection edge of the turbine disc rotor 2. At this time, no external force is applied to the center of the support ring 3 that is opposite to the positioning seat 1. Each positioning block 4 shrinks inwards and has a small radial dimension. Each positioning block 4 can easily extend into the center of the turbine disc rotor 2, thereby avoiding damage to the turbine disc rotor 2.

[0057] An external force is applied to the center of the support ring 3 in a direction away from the positioning seat 1, so that each positioning block 4 is opened outward, the radial dimension becomes larger, and the positioning block 4 is adaptively pressed against the center of the turbine disc rotor 2, thereby achieving effective radial positioning of the center of the turbine disc rotor 2, and avoiding the situation of large interference or large clearance with the center of the turbine disc rotor 2;

[0058] The rotating shaft of the balancing machine is connected to the positioning seat 1 to drive the turbine disc rotor 2 to rotate, and the unbalance amount of the turbine disc rotor 2 is collected and adjusted;

[0059] After the unbalance adjustment of the turbine disk rotor 2 is completed, the application of external force to the center of the support ring 3 facing away from the positioning seat 1 can be cancelled, so that each positioning block 4 shrinks inward, the radial dimension is reduced, and it is separated from the center of the turbine disk rotor 2. When the positioning seat 1 is separated from the drum connecting edge of the turbine disk rotor 2, it can be easily detached from the center of the turbine disk rotor 2, so as to avoid damage to the turbine disk rotor 2.

[0060] In some optional embodiments, in the above-mentioned aircraft engine turbine disk rotor balancing connection device, the positioning seat 1 is connected to the drum connecting edge on the turbine disk rotor 2 through an anti-rotation pin to ensure reliable torque transmission with the turbine disk rotor 2.

[0061] In some optional embodiments, in the above-mentioned aircraft engine turbine disk rotor balancing connection device, the annular connecting edge and the positioning seat 1 are connected by bolts.

[0062] In some optional embodiments, in the above-mentioned aircraft engine turbine disk rotor balancing connection device, each positioning block 4 has only an arc surface;

[0063] When each positioning block 4 is opened outward, each arc-shaped surface abuts against the disc center of the turbine disc rotor 2, thereby avoiding the generation of large local stress;

[0064] When each positioning block 4 contracts inwardly, each arc-shaped surface is separated from the disc center of the turbine disc rotor 2 .

[0065] In some optional embodiments, the above-mentioned aircraft engine turbine disk rotor balancing connection device further includes:

[0066] The sleeve 5 has a through hole at its closed end and an open end extending into the support ring 3. The outer wall of the sleeve 5 has an annular convex edge; the annular convex edge extends between the positioning seat 1 and the support ring 3.

[0067] A screw rod 6, one end of which passes through a perforation and is screwed to a positioning seat 1, and the outer wall of the part of the screw rod extending into a sleeve 5 has an annular convex fin;

[0068] When the screw rod 6 is screwed outward from the positioning seat 1, the annular convex fin will abut against the inside of the closed end of the sleeve 5, so that the central part of the support ring 3 is subjected to an external force away from the positioning seat 1;

[0069] When the screw rod 6 is screwed inward into the positioning seat 1, the annular convex fin will be separated from the inside of the closed end of the sleeve 5, so that the external force on the central part of the support ring 3 away from the positioning seat 1 disappears.

[0070] For the aero-engine turbine disk rotor balance connection device disclosed in the above embodiment, those skilled in the art can understand that by screwing the screw rod 6 away from the positioning seat 1, it is convenient to manipulate each positioning block to open outward and contract inward.

[0071] In some alternative embodiments, in the above aero-engine turbine disk rotor balance connection device, the positioning seat 1 has a positioning protrusion, and the positioning protrusion extends into the sleeve 5;

[0072] One end of the screw rod 6 passing through the perforation is screwed to the positioning protrusion.

[0073] In some alternative embodiments, in the above aero-engine turbine disk rotor balance connection device, it further includes:

[0074] A gland 7, which is connected to the positioning seat 1 by bolts and presses against the side of the center of the turbine disk rotor 2 away from the positioning seat 1 to prevent the turbine disk rotor 1 from coming off during the balance process of the turbine disk rotor.

[0075] In some alternative embodiments, in the above aero-engine turbine disk rotor balance connection device, the closed end of the sleeve 5 has a through hole;

[0076] The bolts connecting the positioning seat 1 and the gland 7 pass through the through hole.

[0077] In some alternative embodiments, in the above aero-engine turbine disk rotor balance connection device, the bolts connecting the positioning seat 1 and the gland 7 are screwed to the positioning protrusion.

[0078] In some alternative embodiments, in the above aero-engine turbine disk rotor balance connection device, the side of the gland 7 facing the turbine disk rotor 2 has a positioning groove, and its side wall has a through hole; the through hole communicates with the positioning groove;

[0079] The closed end of the sleeve 5 extends into the positioning groove;

[0080] One end of the screw rod 6 away from the positioning seat 1 extends out from the through hole for convenient manipulation.

[0081] In some alternative embodiments, in the above-described aeroengine turbine disk rotor balancing connection device, the support ring 3 and its support protrusions have a plurality of cracks, dividing the support ring 3 and its support protrusions into a plurality of fan-shaped blocks, and each fan-shaped block is correspondingly connected to a positioning block 4.

[0082] The various embodiments in the specification are described in a progressive manner. The key point of each embodiment is the difference from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other.

[0083] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.

Claims

1. An aeroengine turbine disk rotor balance connection device, characterized in that Comprising: A positioning seat (1), connected to the drum connection edge on the turbine disk rotor (2); A support ring (3), having an annular support protrusion on one side and an annular connection edge on the outer edge; the annular support protrusion abuts against the positioning seat (1); the annular connection edge is connected to the positioning seat (1); A plurality of positioning blocks (4), connected to the other side of the support ring (3), distributed circumferentially along the support ring (3) and extending into the center of the turbine disk rotor (2); When an external force acting on the center of the support ring (3) is directed away from the positioning seat (1), it can cause each of the positioning blocks (4) to open outward and abut against the center of the turbine disk rotor (2); When the external force acting on the center of the support ring (3) and directed away from the positioning seat (1) disappears, each of the positioning blocks (4) contracts inward and separates from the center of the turbine disk rotor (2); Each of the positioning blocks (4) only has an arc-shaped surface; When each of the positioning blocks (4) opens outward, each of the arc-shaped surfaces abuts against the center of the turbine disk rotor (2); When each of the positioning blocks (4) contracts inward, each of the arc-shaped surfaces separates from the center of the turbine disk rotor (2); The aeroengine turbine disk rotor balance connection device further comprises: A sleeve (5), having a perforation at its closed end, and its open end extending into the support ring (3), with an annular convex edge on the outer wall of this end; the annular convex edge extends between the positioning seat (1) and the support ring (3); A screw (6), one end of which passes through the perforation and is screwed to the positioning seat (1), and having an annular convex fin on the outer wall of the part extending into the sleeve (5); When the screw (6) is screwed outward from the positioning seat (1), the annular convex fin will abut against the inside of the closed end of the sleeve (5), causing an external force acting on the center of the support ring (3) to be directed away from the positioning seat (1); When the screw (6) is screwed inward into the positioning seat (1), the annular convex fin will separate from the inside of the closed end of the sleeve (5), causing the external force acting on the center of the support ring (3) and directed away from the positioning seat (1) to disappear; The positioning seat (1) has a positioning protrusion, and the positioning protrusion extends into the sleeve (5); One end of the screw (6) passing through the perforation is screwed to the positioning protrusion; The aeroengine turbine disk rotor balance connection device further comprises: A gland (7), connected to the positioning seat (1) by bolts and pressing against the side of the center of the turbine disk rotor (2) that is away from the positioning seat (1).

2. The aeroengine turbine disk rotor balance connection device according to claim 1, characterized in that Between the positioning seat (1) and the drum connection edge on the turbine disk rotor (2), they are connected by an anti-rotation pin.

3. The aeroengine turbine disk rotor balance connection device according to claim 1, characterized in that Between the annular connection edge and the positioning seat (1), they are connected by bolts.

4. The aeroengine turbine disk rotor balance connection device according to claim 1, characterized in that The closed end of the sleeve (5) has a through-hole; The bolts connecting the positioning seat (1) and the gland (7) pass through the through-hole.

5. The aeroengine turbine disk rotor balance connection device according to claim 1, characterized in that The bolts connecting the positioning seat (1) and the gland (7) are screwed to the positioning protrusion.

6. The aeroengine turbine disk rotor balance connection device according to claim 1, characterized in that The side of the gland (7) facing the turbine disk rotor (2) has a positioning groove, and its side wall has a through-hole; the through-hole communicates with the positioning groove; The closed end of the sleeve (5) extends into the positioning groove; One end of the screw rod (6) facing away from the positioning seat (1) extends out of the through hole.

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