A device and method for detecting assembly of a rotor structure of an intermediate pressure compressor of an aeroengine

Abstract

The application belongs to the technical field of rotor structure assembly of aero-engine intermediate pressure compressor, and particularly relates to a rotor structure assembly detection device and method of aero-engine intermediate pressure compressor. The device is designed to block the front and back of the rotor structure disc cavity by using a disc core sealing plate and a disc cavity sealing plate, form a closed space, connect the inflation nozzle on the disc cavity sealing plate to a high-pressure gas source through a pipeline, inflate the rotor structure disc cavity, simulate the pulling force generated by the aerodynamic axial force, judge whether the rotor structure assembly is qualified by the change of the concentricity of the rotor structure before and after inflation and pressure relief, and reassemble in the unqualified case, so as to ensure the overall performance of the aero-engine during operation.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of rotor structure assembly of aero-engine intermediate compressor, and particularly relates to a rotor structure assembly detection device and method of aero-engine intermediate compressor. BACKGROUND

[0002] The aero-engine compressor rotor mainly comprises multiple rotor disks, rotor blades are arranged on each rotor disk, the rotor disks are connected through drum connecting edges by bolts, in order to ensure the reliability and stability of the connection, sufficient pre-tightening force needs to be applied on each bolt, and the interference fit is designed between the joints in order to ensure good centering and prevent unbalanced force.

[0003] In practice, it is difficult to ensure the consistency of the pre-tightening force of each bolt on the rotor structure of the aero-engine intermediate compressor, and the interference fit between the joints is not uniform in the axial direction. When the aero-engine is working, the high-speed rotation of the compressor rotor, the aerodynamic axial force generated by the flow channel, and the pressure difference between the inside and outside of the disc cavity generate a pulling force that tends to separate on each rotor disk. The uneven pre-tightening force between each bolt and the uneven friction force generated by the interference fit between the joints are redistributed, which further leads to non-uniform deformation at the connection of the rotor disk, changes the concentricity of the rotor structure greatly, increases the unbalance of the compressor, generates severe vibration, and affects the overall performance of the aero-engine.

[0004] The present application is proposed in view of the above technical defects.

[0005] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The purpose of the present application is to provide a rotor structure assembly detection device and method of aero-engine intermediate compressor to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is:

[0008] In one aspect, a rotor structure assembly detection device of aero-engine intermediate compressor is provided, wherein the rotor structure comprises:

[0009] The first-stage rotor disk is formed with a front-side drum on the front side, the front-side drum gradually shrinks in the radial direction towards the front to form a front journal, and the rear side of the first-stage rotor disk is formed with a rear-side drum, the rear end of the rear-side drum has an inward annular connecting edge;

[0010] a second stage rotor disk, disposed behind the first stage rotor disk;

[0011] a third stage rotor disk, disposed behind the second stage rotor disk, a front side drum is formed on the front side of the third stage rotor disk, the front end of the front side drum has an inward annular connecting edge, the two inward annular connecting edges are fastened on the two sides of the second stage rotor disk by bolts, and the second stage rotor disk is in interference fit with the second stage rotor disk through the stopper; a rear side drum is formed on the rear side of the third stage rotor disk, the rear end of the rear side drum has an outward annular connecting edge;

[0012] The rotor structure assembly detection device of the intermediate pressure compressor of the aircraft engine described above further comprises:

[0013] Two disc core sealing plates are bolted and fastened on the two sides of the first stage rotor disk to block the disc core part of the first stage rotor disk;

[0014] A disc cavity sealing plate is bolted on the outward annular connecting edge to block the rear end of the rear side drum on the third stage rotor disk, and has an inflation hole thereon;

[0015] An inflation nozzle is connected to the disc cavity sealing plate and communicates with the inflation hole.

[0016] According to at least one embodiment of the present application, in the rotor structure assembly detection device of the intermediate pressure compressor of the aircraft engine described above, the two disc core sealing plates and the disc core of the first stage rotor disk are positioned by the stopper.

[0017] According to at least one embodiment of the present application, in the rotor structure assembly detection device of the intermediate pressure compressor of the aircraft engine described above, the two disc core sealing plates and the first stage rotor disk are sealed by a non-metallic material.

[0018] According to at least one embodiment of the present application, in the rotor structure assembly detection device of the intermediate pressure compressor of the aircraft engine described above, the disc core sealing plate on the rear side of the first stage rotor disk is a two-half butt joint structure.

[0019] According to at least one embodiment of the present application, the rotor structure assembly detection device of the intermediate pressure compressor of the aircraft engine described above further comprises:

[0020] A turntable has a stepped protrusion extending into the front journal to position the rotor structure.

[0021] In another aspect, a rotor structure assembly detection method for an intermediate pressure compressor of an aircraft engine is provided, comprising:

[0022] Two disc core sealing plates are bolted and fastened on the two sides of the first stage rotor disk to block the disc core part of the first stage rotor disk;

[0023] The disc cavity sealing plate is bolted to the outward annular connecting edge to seal the rear end of the rear side drum on the third stage rotor wheel disc;

[0024] The inflation nozzle is connected to the disc cavity sealing plate and communicates with the inflation hole on the disc cavity sealing plate;

[0025] The front journal is clamped to the stepped protrusion on the rotary table for positioning;

[0026] The concentricity of the rotor structure is measured and referred to as the original concentricity A;

[0027] The inflation nozzle and the high-pressure gas source are connected by a pipeline to inflate the disc cavity of the rotor structure, so that the pressure reaches a predetermined value;

[0028] The concentricity of the rotor structure is measured and referred to as the inflation concentricity B;

[0029] The pressure in the disc cavity of the rotor structure is unloaded;

[0030] The concentricity of the rotor structure is measured and referred to as the unloading concentricity C;

[0031] If B-A or C-A is greater than the corresponding deformation limit value, the rotor structure is reassembled.

[0032] According to at least one embodiment of the present application, in the rotor structure assembly detection method of the intermediate pressure compressor of the aero-engine described above, the concentricity of the rotor structure is characterized by the angle between the axis of the bolt connecting the disc cavity sealing plate and the outward annular connecting edge and the axis of the front journal.

[0033] The present application has at least the following beneficial technical effects:

[0034] The present application provides a rotor structure assembly detection device and method for an intermediate pressure compressor of an aero-engine, which utilizes a disc core sealing plate and a disc cavity sealing plate to seal the front and rear of the disc cavity of the rotor structure, forming a closed space. An inflation nozzle connected to the disc cavity sealing plate is connected to a high-pressure gas source through a pipeline to inflate the disc cavity of the rotor structure, simulating the pulling force generated by the aerodynamic axial force. By measuring the change in the concentricity of the rotor structure before and after inflation and unloading, it is determined whether the rotor structure assembly is qualified. In the case of unqualified, the assembly is reassembled, thereby ensuring the overall performance of the aero-engine during operation. BRIEF DESCRIPTION OF DRAWINGS

[0035] Figure 1 is a schematic diagram of the rotor structure assembly detection device for an intermediate pressure compressor of an aero-engine provided by the present application;

[0036] Among them:

[0037] 1 - first stage rotor wheel disk; 2 - second stage rotor wheel disk; 3 - third stage rotor wheel disk; 4 - disk hub sealing plate; 5 - disk cavity sealing plate; 6 - turntable; 7 - air charging nozzle; 8 - pipeline; 9 - high pressure gas source.

[0038] In order to better illustrate the present embodiment, some components in the drawings can be omitted, enlarged or reduced, and do not represent the actual size of the product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0039] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described in detail below in combination with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0040] In addition, unless otherwise defined, the technical terms or scientific terms used in the present application description should be the general meaning understood by the general technical personnel in the field to which the present application belongs. The words indicating the relative direction or position relationship, such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the present application description, are only used to indicate the relative direction or position relationship, and not to imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and the relative position relationship may also change accordingly when the absolute position of the described object changes, therefore, it cannot be understood as a limitation of the present application. The "first", "second", "third" and similar terms used in the present application description are only for the purpose of description, to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and similar terms used in the present application description should not be understood as an absolute limitation on the quantity, but should be understood as the existence of at least one. The "include" or "contain" and similar terms used in the present application description mean that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and do not exclude other elements or objects.

[0041] In addition, it needs to be explained that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and similar words used in the description of the application should be understood broadly, for example, the connection can be fixed connection, or detachable connection, or integrally connected; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal communication of two elements, and those skilled in the art can understand the specific meaning of the application according to the specific circumstances.

[0042] The following will be described in detail in combination with the accompanying drawings Figure 1 The application is further described in detail.

[0043] In one aspect, a rotor structure assembly detection device for a middle pressure compressor of an aero-engine is provided, wherein the rotor structure comprises:

[0044] The first-stage rotor disc 1 is formed with a front drum on the front side, the radial dimension of which gradually contracts forward to form a front journal; and a rear drum is formed on the rear side of the first-stage rotor disc 1, the rear end of which has an inward annular connecting edge;

[0045] The second-stage rotor disc 2 is arranged behind the first-stage rotor disc 1;

[0046] The third-stage rotor disc 3 is arranged behind the second-stage rotor disc 2, and is formed with a front drum on the front side, the front end of which has an inward annular connecting edge; the two inward annular connecting edges are fastened on the two sides of the second-stage rotor disc 2 by bolts, and are in interference fit with the second-stage rotor disc 2 by a stopper; and a rear drum is formed on the rear side of the third-stage rotor disc 3, the rear end of which has an outward annular connecting edge;

[0047] The rotor structure assembly detection device for the middle pressure compressor of the aero-engine described above further comprises:

[0048] Two disc core sealing plates 4 are fastened on the two sides of the first-stage rotor disc 1 by bolts to block the disc core part of the first-stage rotor disc 1, and the bolts can avoid the first-stage rotor disc 1 to cause damage to the first-stage rotor disc 1;

[0049] A disc cavity sealing plate 5 is connected on the outward annular connecting edge by bolts to block the rear end of the rear drum of the third-stage rotor disc 3, and has an inflation hole thereon, and the bolt connection can use the existing bolt hole on the outward annular connecting edge;

[0050] An inflation nozzle 7 is connected on the disc cavity sealing plate 5 and communicates with the inflation hole.

[0051] The rotor structure assembly detection device for the middle pressure compressor of the aero-engine disclosed in the above embodiment can connect the inflation nozzle 7 to a high-pressure gas source through a pipeline in specific application, and the high-pressure gas source can be connected to the inflation hole through the inflation nozzle 7 to inflate the disc cavity sealing plate 5 and the third-stage rotor disc 3, so that the interference fit between the two can be checked.

[0052] For the above-mentioned embodiment of the aero-engine intermediate pressure compressor rotor structure assembly detection device, those skilled in the art can understand that the design utilizes the disc core sealing plate 4 and the disc cavity sealing plate 5 to block the front and rear of the disc cavity of the rotor structure disc, thereby forming a closed space. When applied, the inflation nozzle 7 connected to the disc cavity sealing plate 5 can be connected to the high-pressure gas source 9 through the pipeline 8 to inflate the disc cavity of the rotor structure, simulate the pulling force generated by the aerodynamic axial force, and judge whether the assembly of the rotor structure is qualified by the change of the concentricity of the rotor structure before and after inflation and pressure relief. In the case of unqualified, reassemble to ensure the overall performance of the aero-engine during operation.

[0053] In some optional embodiments of the above-mentioned aero-engine intermediate pressure compressor rotor structure assembly detection device, the two disc core sealing plates 4 are positioned between the disc core of the first-stage rotor disc 1 by using a stop.

[0054] In some optional embodiments of the above-mentioned aero-engine intermediate pressure compressor rotor structure assembly detection device, the two disc core sealing plates 4 are sealed between the first-stage rotor disc 1 by using a non-metallic material.

[0055] In some optional embodiments of the above-mentioned aero-engine intermediate pressure compressor rotor structure assembly detection device, the disc core sealing plate 4 located at the rear side of the first-stage rotor disc 1 is a two-half butt joint structure, which can bypass the disc core part of the second-stage rotor disc 2 and the third-stage rotor disc 3 and be assembled to the inside of the first-stage rotor disc 2.

[0056] In some optional embodiments of the above-mentioned aero-engine intermediate pressure compressor rotor structure assembly detection device, it further comprises:

[0057] The turntable 6 has a stepped protrusion on it, which protrudes into the front journal and positions the rotor structure. The turntable 6 can also rotate the rotor structure to simulate the rotating state of the aero-engine during operation, making the rotor structure assembly detection result more accurate.

[0058] In another aspect, a method for detecting the assembly of a rotor structure of an aero-engine intermediate pressure compressor is provided, comprising:

[0059] The two disc core sealing plates 4 are bolted and fastened on both sides of the first-stage rotor disc 2 to block the disc core part of the first-stage rotor disc 1;

[0060] The disc cavity sealing plate 5 is bolted to the outward annular connecting edge to block the rear end of the rear drum on the third-stage rotor disc 3;

[0061] The inflation nozzle 7 is connected to the disc cavity sealing plate 5 and communicates with the inflation hole on the disc cavity sealing plate 5;

[0062] The front axle neck is clamped to the stepped protrusion on the rotary table 6 for positioning;

[0063] The concentricity of the rotor structure is measured, which is referred to as the original concentricity A;

[0064] The inflation nozzle 7 is connected to the high-pressure gas source 9 through the pipeline 8, and the high-pressure gas source 9 can be a high-pressure gas tank. The pressure in the rotor structure disc cavity is inflated to a predetermined value, which can be determined according to the size of the pull force generated when the aero-engine is working.

[0065] The concentricity of the rotor structure is measured, which is referred to as the original concentricity A;

[0066] The pressure in the rotor structure disc cavity is unloaded;

[0067] The concentricity of the rotor structure is measured, which is referred to as the original concentricity A;

[0068] If B-A or C-A is greater than the corresponding deformation limit value, it is judged that the rotor structure disc cavity has a large deformation before and after inflation and unloading, and the assembly of the rotor structure is unqualified, and the rotor structure needs to be reassembled or discarded.

[0069] If B-A and C-A are greater than the corresponding deformation limit value, it is judged that the rotor structure disc cavity has a small deformation before and after inflation and unloading, and the assembly of the rotor structure is qualified, and it can be balanced and then assembled into the compressor and the aero-engine to reduce the unbalance of the aero-engine during work, avoid violent vibration, and ensure the overall performance of the aero-engine during work.

[0070] In some optional embodiments, the concentricity of the rotor structure in the rotor structure assembly detection method of the compressor in the aero-engine is characterized by the angle between the axis connecting the disc cavity sealing plate 5 and the outward annular connecting edge bolt and the axis of the front axle neck.

[0071] The rotor structure assembly detection method of the compressor in the aero-engine disclosed in the above embodiments is implemented based on the rotor structure assembly detection device of the compressor in the aero-engine disclosed in the above embodiments. The description is relatively simple, and the specific related parts can be referred to the related description of the rotor structure assembly detection device of the compressor in the aero-engine. The technical effects can also be referred to the technical effects of the related parts of the rotor structure assembly detection device of the compressor in the aero-engine, which will not be described here.

[0072] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same and similar parts of each embodiment can be referred to each other.

[0073] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical schemes after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A rotor structure assembly and testing device for an aero-engine compressor, wherein, The rotor structure includes: The first stage rotor disk (1) has a front drum formed on its front side, the radial dimension of which gradually shrinks forward to form a front journal; the first stage rotor disk (1) has a rear drum formed on its rear side, the rear end of which has an inward annular connecting edge. The second-stage rotor disk (2) is located behind the first-stage rotor disk (1); The third-stage rotor disk (3) is located behind the second-stage rotor disk (2), and a front drum is formed on its front side. The front end of the front drum has an inward annular connecting edge. The inward annular connecting edge on the rear drum of the first-stage rotor disk (1) and the inward annular connecting edge on the front drum of the third-stage rotor disk (3) are fastened to both sides of the second-stage rotor disk (2) by bolts, and are in an interference fit with the second-stage rotor disk (2). A rear drum is formed on the rear side of the third-stage rotor disk (3), and the rear end of the rear drum has an outward annular connecting edge. The rotor structure assembly and testing device for the compressor in the aero-engine is characterized in that it includes: Two core sealing plates (4) are connected by bolts and fastened to both sides of the first stage rotor disk (1) to seal the core part of the first stage rotor disk (1); The cavity sealing plate (5) is bolted to the outward annular connecting edge on the rear drum of the third stage rotor disk (3), sealing the rear end of the rear drum of the third stage rotor disk (3), and has an air inlet on it; An air inlet (7) is connected to the sealing plate (5) of the disc cavity and communicates with the air inlet; The turntable (6) has a stepped protrusion that extends into the front journal to position the rotor structure. The rotor structure assembly and testing device for the compressor in the aforementioned aero-engine performs the following assembly and testing: The concentricity of the rotor structure is measured and called the original concentricity A; By connecting the air inlet (7) and the high-pressure air source (9) through the pipeline (8), air is injected into the rotor structure disk cavity to make the pressure reach the predetermined value; The concentricity of the rotor structure is measured and is called the pressurization concentricity B; The pressure inside the rotor structure disk cavity is unloaded; The concentricity of the rotor structure is measured and is called the decompression concentricity C; If BA or CA is greater than the corresponding deformation limit, the rotor structure must be reassembled. in, The concentricity of the rotor structure is characterized by the deviation angle between the axis of the connecting disc cavity sealing plate (5) and the outward annular connecting edge bolt and the axis of the front journal.

2. The rotor structure assembly and testing device for an aero-engine compressor according to claim 1, characterized in that, The two core sealing plates (4) are positioned with the core of the first stage rotor disk (1) using a stop.

3. The rotor structure assembly and testing device for an aero-engine compressor according to claim 1, characterized in that, The two disc core sealing plates (4) are sealed with non-metallic materials between themselves and the first stage rotor disc (1).

4. The rotor structure assembly and testing device for an aero-engine compressor according to claim 1, characterized in that, The disk core sealing plate (4) located behind the first-stage rotor disk (1) is a two-half docking structure.

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