An axial force balance structure for an aero-engine compressor test

Abstract

This application belongs to the technical field of axial force balance design for aero-engine compressor tests, and specifically relates to an axial force balance structure for aero-engine compressor tests. It balances the forward axial force of the compressor, and the airflow generating the pressure difference comes from the compressor. The magnitude of the generated pressure difference can vary with the compressor flow rate. By designing the sizes of the front balance disc, rear balance disc, and the apertures related to air extraction and exhaust, the generated backward thrust can match the forward axial force under various operating conditions of the compressor, avoiding being too large or too small, and having a high adaptive ability. Therefore, it can effectively ensure the smooth completion of the compressor test.

Description

Technical Field

[0001] This application belongs to the technical field of axial force balance design for aero-engine compressor tests, and particularly relates to an axial force balance structure for aero-engine compressor tests. Background Technique

[0002] In an aero-engine, as the compressor flow rate and pressure ratio gradually increase, the forward axial force in the compressor also increases. During compressor tests, if this axial force is too large, it will damage the main thrust bearing, resulting in the inability to smoothly complete the compressor test, and even cause damage and danger, scrapping the entire compressor.

[0003] Currently, during compressor tests, the following two methods are mainly used to balance the forward axial force:

[0004] 1) Connect the compressor rotor component and the test bench with a tie rod, apply a backward pulling force to the rotor component to counteract the forward axial force of the compressor. For this technical solution, the ability to balance the forward axial force of the compressor is limited by the magnitude of the axial force that the test bench can provide, and it is difficult to meet the balance requirement of the forward axial force during compressor tests. Moreover, connecting the compressor rotor component will affect the dynamic performance of the compressor rotor component, and even cause the high-order critical speed of the compressor rotor component to be close to the operating speed, leading to risks.

[0005] 2) Add a balance disk behind the compressor rotor component. Generate a backward thrust through the pressure difference between the two chambers before and after the balance disk to counteract the forward axial force of the compressor. In this technical solution, it is usually designed that the rear chamber of the balance disk is connected to the atmosphere, and the front chamber is supplied with air from the test bench. The ability to balance the forward axial force of the compressor is limited, and it is difficult to meet the balance requirement of the forward axial force during compressor tests. Moreover, the forward axial force of the compressor is related to the compressor flow rate, and the forward axial force of the compressor is different under different operating conditions, with poor adaptability.

[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 technical 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 application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0008] The purpose of this application is to provide an axial force balance structure for aero-engine compressor tests to overcome or mitigate at least one aspect of the known technical defects.

[0009] The technical solution of this application is:

[0010] An axial force balance structure for a compressor test of an aero-engine, comprising:

[0011] A front casing assembly, including an outer casing, an inner casing disposed within the outer casing, and a plurality of struts circumferentially supported between the outer casing and the inner casing; the front end of the outer casing in the front casing assembly is butt-jointed with the rear end of the compressor casing; the rear part of the inner casing in the front casing assembly extends out of the rear end of its outer casing, and has a plurality of rear high-pressure cavity air intake holes circumferentially distributed thereon;

[0012] A front balance disk, disposed within the front part of the inner casing in the front casing assembly, the outer edge of which is sealed with the inner casing in the front casing assembly through a honeycomb labyrinth seal, and the front side of which is connected to the rear end of the compressor last-stage rotor drum, and forms a front high-pressure cavity between the inner casing in the front casing assembly, the compressor last-stage rotor drum;

[0013] An intermediate casing assembly, including an outer casing, an inner ring disposed within the outer casing, and a plurality of struts circumferentially supported between the outer casing and the inner ring; the outer casing in the intermediate casing assembly is located on the outer circumference of the rear part of the inner casing in the front casing assembly, and the front end is butt-jointed with the rear end of the outer casing in the front casing assembly; the inner ring in the intermediate casing assembly is located within the rear part of the inner casing in the front casing assembly; each strut in the intermediate casing assembly penetrates through the rear part of the inner casing in the front casing assembly, and the strut has a front low-pressure cavity exhaust passage; the front low-pressure cavity exhaust passage extends to the front end of the inner ring in the intermediate casing assembly and extends to the outer casing in the intermediate casing assembly to communicate with the external environment;

[0014] A rear balance disk, disposed within the rear part of the inner casing in the front casing assembly, the outer edge of which is sealed with the inner casing in the front casing assembly through a honeycomb labyrinth seal;

[0015] An intermediate drum, located inside the inner ring in the intermediate casing assembly, sealed with the inner ring in the intermediate casing assembly through a honeycomb labyrinth seal, and both ends are connected to the rear side of the front balance disk and the front side of the rear balance disk, and form a front low-pressure cavity between the inner casing in the front casing assembly, the front balance disk, and the inner ring in the intermediate casing assembly, and form a rear high-pressure cavity between the inner casing in the front casing assembly, the inner ring in the intermediate casing assembly, and the rear balance disk; the front low-pressure cavity communicates with the front low-pressure cavity exhaust passage; the rear high-pressure cavity communicates with each rear high-pressure cavity air intake hole;

[0016] A rear casing assembly, including an outer casing, an inner casing disposed within the outer casing; the front end of the outer casing in the rear casing assembly is butt-jointed with the rear end of the outer casing in the intermediate casing assembly; the front end of the inner casing in the rear casing assembly is butt-jointed with the rear end of the inner casing in the front casing assembly;

[0017] The exhaust casing assembly includes an outer casing, an inner casing arranged in the outer casing, and a plurality of support plates circumferentially supported between the outer casing and the inner casing; the front end of the outer casing in the exhaust casing assembly is butted against the rear end of the outer casing in the rear casing assembly; the front end of the inner casing in the exhaust casing assembly is butted against the rear end of the inner casing in the rear casing assembly, and a forward annular support edge is provided in the front portion thereof;

[0018] The rear journal is arranged in the front part of the inner casing in the exhaust casing assembly, with its front end connected to the rear side of the rear balance plate, and the outer wall and the forward annular support edge are sealed by honeycomb grate teeth, forming a rear low-pressure chamber with the inner casing in the front casing assembly, the inner casing in the rear casing assembly, and the forward annular support edge;

[0019] The rear low-pressure chamber exhaust pipe runs through the outer casing and the inner casing of the exhaust casing assembly, connecting the rear low-pressure chamber and the external environment.

[0020] According to at least one embodiment of the present application, in the above-mentioned aircraft engine compressor test axial force balance structure, the rear high-pressure chamber air bleed holes and the support plate in the intermediate casing assembly are staggered in the circumferential direction.

[0021] According to at least one embodiment of the present application, in the above-mentioned aircraft engine compressor test axial force balance structure, the front part of the inner casing in the front casing assembly has an inward annular fold, and the inward annular fold and the outer edge of the front balance disk are sealed by honeycomb grate teeth.

[0022] According to at least one embodiment of the present application, in the above-mentioned aircraft engine compressor test axial force balance structure, the outer wall of the rear journal has an annular support protrusion, and the annular support protrusion and the forward annular support edge are sealed by honeycomb grate teeth.

[0023] According to at least one embodiment of the present application, the above-mentioned aircraft engine compressor test axial force balance structure further includes:

[0024] The intermediate sealing ring is sleeved on the outer periphery of the intermediate drum, is sealed with the intermediate drum through honeycomb grate teeth, and is connected to the inner ring of the intermediate casing assembly.

[0025] According to at least one embodiment of the present application, in the above-mentioned aircraft engine compressor test axial force balance structure, the outer casing of the intermediate casing assembly has a vent hole;

[0026] The aero-engine compressor test axial force balance structure further comprises:

[0027] The long plug can be connected to the outer casing of the intermediate casing assembly, pass through the vent hole, and block the rear high-pressure chamber air bleed hole;

[0028] A short plug that can be connected to the outer and middle receivers of the intermediate receiver assembly to block the vent holes.

[0029] According to at least one embodiment of the present application, in the above axial force balance structure for aeroengine compressor test, it further includes:

[0030] An exhaust pipe plug cap, which can be connected to the rear low-pressure cavity exhaust pipe to block the rear low-pressure cavity exhaust pipe.

[0031] According to at least one embodiment of the present application, in the above axial force balance structure for aeroengine compressor test, it further includes:

[0032] A front low-pressure cavity exhaust joint, which is connected to the outer casing of the intermediate casing assembly to communicate with the front low-pressure cavity exhaust passage;

[0033] An exhaust joint plug cap, which can be connected to the front low-pressure cavity exhaust joint to block the front low-pressure cavity exhaust joint.

[0034] The present application has at least the following beneficial technical effects:

[0035] Provided is an axial force balance structure for aeroengine compressor test, which balances the forward axial force of the compressor. The airflow generating the pressure difference comes from the compressor, and the magnitude of the generated pressure difference can change with the compressor flow rate. By designing the sizes of the front balance disk, rear balance disk, and the apertures related to air extraction and exhaust, the generated backward thrust can match the forward axial force in each operating state of the compressor, avoiding being too large or too small, and having a high adaptability. Thus, it can effectively ensure the smooth completion of the compressor test. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 is a schematic diagram of the axial force balance structure for aeroengine compressor test provided by the embodiment of the present application for balancing the forward axial force of the compressor;

[0037] Figure 2 is a schematic diagram of the axial force balance structure for aeroengine compressor test provided by the embodiment of the present application that does not require balancing the forward axial force of the compressor;

[0038] Figure 3 is a cross-sectional schematic diagram of the support plate in the intermediate casing assembly provided by the embodiment of the present application;

[0039] Wherein:

[0040] 1 - front casing assembly; 2 - front balance disk; 3 - compressor last-stage rotor drum; 4 - intermediate casing assembly; 5 - rear balance disk; 6 - intermediate drum; 7 - rear casing assembly; 8 - exhaust casing assembly; 9 - rear journal; 10 - rear low-pressure cavity exhaust pipe; 11 - intermediate seal ring; 12 - long plug; 13 - short plug; 14 - exhaust pipe plug cap; 15 - front low-pressure cavity exhaust joint; 16 - exhaust joint plug cap;

[0041] I - Front high - pressure chamber; II - Front low - pressure chamber; III - Rear high - pressure chamber; IV - Rear low - pressure chamber.

[0042] 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 should not be construed as a limitation to this application. Detailed implementation manners

[0043] 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 herein are only part of the 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.

[0044] 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 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 represent the relative directions or position relationships, rather than implying that the device or element 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 should not be construed as a limitation to 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 understood as indicating or implying relative importance. The terms "a", "one" or "the" and similar words used in the description of this application should not be construed as an absolute limitation on the quantity but should be understood as having at least one. The terms "including" or "comprising" and similar words used in the description of this application are intended to cover the elements or items listed after the word and their equivalents that appear before the word, without excluding other elements or items.

[0045] 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.

[0046] The following further elaborates on this application in conjunction with the Figures 1 to 3 accompanying drawings.

[0047] An axial force balance structure for an aero-engine compressor test, comprising:

[0048] A front casing assembly 1, including an outer casing, an inner casing arranged inside the outer casing, and a plurality of struts circumferentially supported between the outer casing and the inner casing, with an overall configuration similar to a turbine guide vane; the front end of the outer casing in the front casing assembly 1 is docked with the rear end of the compressor casing; the rear part of the inner casing in the front casing assembly 1 extends out of the rear end of its outer casing, and it has a plurality of rear high-pressure cavity air inlet holes circumferentially distributed thereon;

[0049] A front balance disk 2, arranged inside the front part of the inner casing in the front casing assembly 1, with its outer edge sealed with the inner casing in the front casing assembly 1 through a honeycomb labyrinth seal, and its front side connected to the rear end of the compressor last-stage rotor drum 3, forming a front high-pressure cavity I between the inner casing in the front casing assembly 1 and the compressor last-stage rotor drum 3;

[0050] An intermediate casing assembly 4, including an outer casing, an inner ring arranged inside the outer casing, and a plurality of struts circumferentially supported between the outer casing and the inner ring; the outer casing in the intermediate casing assembly 4 is located on the outer circumference of the rear part of the inner casing in the front casing assembly 1, and its front end is docked with the rear end of the outer casing in the front casing assembly 1; the inner ring in the intermediate casing assembly 4 is located inside the rear part of the inner casing in the front casing assembly 1; each strut in the intermediate casing assembly 4 penetrates through the rear part of the inner casing in the front casing assembly 1, and the strut has a front low-pressure cavity exhaust passage; the front low-pressure cavity exhaust passage extends to the front end of the inner ring in the intermediate casing assembly 4 and extends to the outer casing in the intermediate casing assembly 4, communicating with the external environment;

[0051] A rear balance disk 5, arranged inside the rear part of the inner casing in the front casing assembly 1, with its outer edge sealed with the inner casing in the front casing assembly 1 through a honeycomb labyrinth seal;

[0052] The intermediate drum 6 is located inside the inner ring of the intermediate casing assembly 4. It is sealed with the inner ring of the intermediate casing assembly 4 through a honeycomb labyrinth seal. Its two ends are connected to the rear side of the front balance disk 2 and the front side of the rear balance disk 5. It forms the front low-pressure chamber II with the inner casing of the front casing assembly 1, the front balance disk 2, and the inner ring of the intermediate casing assembly 4, and forms the rear high-pressure chamber III with the inner casing of the front casing assembly 1, the inner ring of the intermediate casing assembly 4, and the rear balance disk 5. The front low-pressure chamber II communicates with the exhaust passage of the front low-pressure chamber. The rear high-pressure chamber III communicates with the air intake holes of each rear high-pressure chamber.

[0053] The rear casing assembly 7 includes an outer casing and an inner casing arranged inside the outer casing. The front end of the outer casing of the rear casing assembly 7 is butted against the rear end of the outer casing of the intermediate casing assembly 4. The front end of the inner casing of the rear casing assembly 7 is butted against the rear end of the inner casing of the front casing assembly 1.

[0054] The exhaust casing assembly 8 includes an outer casing, an inner casing arranged inside the outer casing, and a plurality of support plates circumferentially supported between the outer casing and the inner casing. The front end of the outer casing of the exhaust casing assembly 8 is butted against the rear end of the outer casing of the rear casing assembly 7. The front end of the inner casing of the exhaust casing assembly 8 is butted against the rear end of the inner casing of the rear casing assembly 7, and it has a forward annular support edge at its front part.

[0055] The rear journal 9 is arranged inside the front part of the inner casing of the exhaust casing assembly 8. Its front end is connected to the rear side of the rear balance disk 5. It is sealed with the forward annular support edge through a honeycomb labyrinth seal. It forms the rear low-pressure chamber IV with the inner casing of the front casing assembly 1, the inner casing of the rear casing assembly 7, and the forward annular support edge.

[0056] The rear low-pressure chamber exhaust pipe 10 penetrates through the outer casing and the inner casing of the exhaust casing assembly 8 and communicates the rear low-pressure chamber IV with the external environment.

[0057] The axial force balance structure of the aero-engine compressor test disclosed in the above embodiment balances the forward axial force of the compressor as Figure 1As shown in the figure, part of the air flow flowing out of the compressor outlet can enter the front high-pressure chamber I. A small part of the air flow entering the front high-pressure chamber I will leak into the front low-pressure chamber II through the labyrinth honeycomb, and then be discharged to the external environment through the exhaust passage of the front low-pressure chamber, thereby generating a pressure difference between the front high-pressure chamber I and the front low-pressure chamber II, acting on the front balance disc 2 to generate a backward thrust, which can partially offset the forward axial force of the compressor. In addition, part of the air flow flowing out of the compressor outlet can enter the rear high-pressure chamber III through the air extraction holes in the rear high-pressure chamber. A small part of the air flow entering the rear high-pressure chamber III will leak into the rear low-pressure chamber IV through the labyrinth honeycomb, and then be discharged to the external environment through the exhaust pipe 10 of the rear low-pressure chamber, thereby generating a pressure difference between the rear high-pressure chamber III and the rear low-pressure chamber IV, acting on the rear balance disc 5 to generate a backward thrust, which can further offset the forward axial force of the compressor and ensure the smooth completion of the compressor test.

[0058] The axial force balance structure for the compressor test of the aero-engine disclosed in the above embodiment balances the forward axial force of the compressor. The air flow generating the pressure difference comes from the compressor, and the magnitude of the generated pressure difference can change with the compressor flow rate. By designing the dimensions of the front balance disc 2, the rear balance disc 5, and the relevant apertures for air extraction and exhaust, the generated backward thrust can match the forward axial force in each operating state of the compressor, avoiding being too large or too small, and having a high adaptability. Therefore, it can effectively ensure the smooth completion of the compressor test.

[0059] In some alternative embodiments, in the above axial force balance structure for the compressor test of the aero-engine, the outer casing, the inner ring, and each support plate in the intermediate casing assembly 4 are integrally formed components;

[0060] The part of the front casing assembly 1 extending from the rear end of the outer casing is disconnected from the part located inside the outer casing and is butt-jointed with each other, and a through hole for each support plate in the intermediate casing assembly 4 to penetrate is formed therebetween.

[0061] In some alternative embodiments, in the above axial force balance structure for the compressor test of the aero-engine, the air extraction holes in the rear high-pressure chamber are staggered with the support plates in the intermediate casing assembly 4 in the circumferential direction to ensure air extraction into the rear high-pressure chamber III.

[0062] In some alternative embodiments, in the above axial force balance structure for the compressor test of the aero-engine, the cross-section of the support plate in the intermediate casing assembly 4 is in the shape of a water droplet to reduce the flow resistance.

[0063] In some alternative embodiments, in the above axial force balance structure for the compressor test of the aero-engine, the front part of the inner casing in the front casing assembly 1 has an inward annular flange, and the space between the inward annular flange and the outer edge of the front balance disc 2 is sealed by a honeycomb labyrinth.

[0064] In some alternative embodiments, in the above axial force balance structure for aero-engine compressor tests, the outer wall of the rear journal 9 has an annular support protrusion, and the annular support protrusion and the forward annular support edge are sealed by a honeycomb labyrinth seal.

[0065] In some alternative embodiments, in the above axial force balance structure for aero-engine compressor tests, it further includes:

[0066] An intermediate seal ring 11, sleeved on the outer periphery of the intermediate drum 6, sealed with the intermediate drum 6 by a honeycomb labyrinth seal, and connected to the inner ring of the intermediate casing assembly 4.

[0067] In some alternative embodiments, in the above axial force balance structure for aero-engine compressor tests, the outer casing of the intermediate casing assembly 4 has a vent hole;

[0068] The above axial force balance structure for aero-engine compressor tests further includes:

[0069] A long plug 12, capable of being connected to the outer casing of the intermediate casing assembly 4, passing through the vent hole, and plugging the air inlet hole of the rear high-pressure cavity, and is used when the forward axial force balance of the compressor is not required, as Figure 2 shown;

[0070] A short plug 13, capable of being connected to the outer casing of the intermediate casing assembly 4, plugging the vent hole, and is used when the forward axial force balance of the compressor is required, as Figure 1 shown.

[0071] In some alternative embodiments, in the above axial force balance structure for aero-engine compressor tests, it further includes:

[0072] An exhaust pipe plug cap 14, capable of being connected to the rear low-pressure cavity exhaust pipe 10, plugging the rear low-pressure cavity exhaust pipe 10, and is used when the forward axial force balance of the compressor is not required, as Figure 2 shown.

[0073] In some alternative embodiments, in the above axial force balance structure for aero-engine compressor tests, it further includes:

[0074] A front low-pressure cavity exhaust joint 15, connected to the outer casing of the intermediate casing assembly 4, and communicating with the front low-pressure cavity exhaust passage;

[0075] An exhaust joint plug cap 16, capable of being connected to the front low-pressure cavity exhaust joint 15, plugging the front low-pressure cavity exhaust joint 15, and is used when the forward axial force balance of the compressor is not required, as Figure 2 shown.

[0076] In the axial force balance structure for the compressor test of the aero-engine disclosed in the above embodiments, the connection between the said components can be welding, bolt connection or threaded connection. The specific connection form to be adopted can be selected according to the specific actual situation. In order to ensure the precise positioning between the components, corresponding rabbets can be designed for positioning. In addition, part of the casing assembly can be designed as a horizontally split structure to facilitate assembly.

[0077] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same and similar parts between the various embodiments, reference can be made to each other.

[0078] So far, the technical solutions of the present application have been described in conjunction 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 fall within the protection scope of the present application.

Claims

1. An axial force balance structure for an aero-engine compressor test, characterized in that, Comprising: The front casing assembly (1) includes an outer casing, an inner casing disposed within the outer casing, and a plurality of struts circumferentially supported between the outer casing and the inner casing; the front end of the outer casing in the front casing assembly (1) is butt-jointed with the rear end of the compressor casing; the rear part of the inner casing in the front casing assembly (1) extends out of the rear end of its outer casing, and has a plurality of rear high-pressure chamber air extraction holes circumferentially distributed thereon; The front balance disk (2) is disposed within the front part of the inner casing in the front casing assembly (1), and its outer edge is sealed with the inner casing in the front casing assembly (1) through a honeycomb labyrinth seal. The front side thereof is connected to the rear end of the compressor last-stage rotor drum (3), and forms a front high-pressure chamber (I) between the inner casing in the front casing assembly (1), the compressor last-stage rotor drum (3); The intermediate casing assembly (4) includes an outer casing, an inner ring disposed within the outer casing, and a plurality of struts circumferentially supported between the outer casing and the inner ring; the outer casing in the intermediate casing assembly (4) is located on the outer periphery of the rear part of the inner casing in the front casing assembly (1), and the front end is butt-jointed with the rear end of the outer casing in the front casing assembly (1); the inner ring in the intermediate casing assembly (4) is located within the rear part of the inner casing in the front casing assembly (1); each strut in the intermediate casing assembly (4) penetrates through the rear part of the inner casing in the front casing assembly (1), and the strut has a front low-pressure chamber exhaust passage; The front low-pressure chamber exhaust passage extends to the front end of the inner ring in the intermediate casing assembly (4) and extends to the outer casing in the intermediate casing assembly (4), and communicates with the external environment; The rear balance disk (5) is disposed within the rear part of the inner casing in the front casing assembly (1), and its outer edge is sealed with the inner casing in the front casing assembly (1) through a honeycomb labyrinth seal; The intermediate drum (6) is located inside the inner ring in the intermediate casing assembly (4), and is sealed with the inner ring in the intermediate casing assembly (4) through a honeycomb labyrinth seal. The two ends are connected to the rear side of the front balance disk (2) and the front side of the rear balance disk (5), and form a front low-pressure chamber (II) between the inner casing in the front casing assembly (1), the front balance disk (2), and the inner ring in the intermediate casing assembly (4), and form a rear high-pressure chamber (III) between the inner casing in the front casing assembly (1), the inner ring in the intermediate casing assembly (4), and the rear balance disk (5); the front low-pressure chamber (II) communicates with the front low-pressure chamber exhaust passage; the rear high-pressure chamber (III) communicates with each rear high-pressure chamber air extraction hole; The rear casing assembly (7) includes an outer casing and an inner casing disposed within the outer casing; the front end of the outer casing in the rear casing assembly (7) is butt-jointed with the rear end of the outer casing in the intermediate casing assembly (4); the front end of the inner casing in the rear casing assembly (7) is butt-jointed with the rear end of the inner casing in the front casing assembly (1); The exhaust casing assembly (8) includes an outer casing, an inner casing disposed within the outer casing, and a plurality of struts circumferentially supported between the outer casing and the inner casing; the front end of the outer casing in the exhaust casing assembly (8) is butt-jointed with the rear end of the outer casing in the rear casing assembly (7); the front end of the inner casing in the exhaust casing assembly (8) is butt-jointed with the rear end of the inner casing in the rear casing assembly (7), and has a forward annular support edge at its front part; The rear journal (9) is arranged inside the front part of the inner casing in the exhaust casing assembly (8). Its front end is connected to the rear side of the rear balance disk (5). The outer wall is sealed with the forward annular support edge through a honeycomb labyrinth seal, and together with the inner casing in the front casing assembly (1), the inner casing in the rear casing assembly (7), and the forward annular support edge, it forms a rear low-pressure chamber (IV). The rear low-pressure chamber exhaust pipe (10) penetrates through the outer casing and the inner casing of the exhaust casing assembly (8) and communicates the rear low-pressure chamber (IV) with the external environment.

2. The axial force balance structure for an aero-engine compressor test according to claim 1, characterized in that The air intake holes of the rear high-pressure chamber and the struts in the intermediate casing assembly (4) are staggered in the circumferential direction.

3. The axial force balance structure for an aero-engine compressor test according to claim 1, characterized in that The front part of the inner casing in the front casing assembly (1) has an inward annular flange, and the inward annular flange is sealed with the outer edge of the front balance disk (2) through a honeycomb labyrinth seal.

4. The axial force balance structure for an aero-engine compressor test according to claim 1, characterized in that The outer wall of the rear journal (9) has an annular support protrusion, and the annular support protrusion is sealed with the forward annular support edge through a honeycomb labyrinth seal.

5. The axial force balance structure for an aero-engine compressor test according to claim 1, characterized in that It further includes: The intermediate seal ring (11) is sleeved on the outer circumference of the intermediate drum (6), sealed with the intermediate drum (6) through a honeycomb labyrinth seal, and connected to the inner ring in the intermediate casing assembly (4).

6. The axial force balance structure for an aero-engine compressor test according to claim 1, characterized in that The outer casing of the intermediate casing assembly (4) has a vent hole; The axial force balance structure for the aero-engine compressor test further includes: The long plug (12) can be connected to the outer casing of the intermediate casing assembly (4), passes through the vent hole, and plugs the air intake hole of the rear high-pressure chamber; The short plug (13) can be connected to the outer casing of the intermediate casing assembly (4) and plugs the vent hole.

7. The axial force balance structure for an aero-engine compressor test according to claim 1, characterized in that It further includes: The exhaust pipe plug cap (14) can be connected to the rear low-pressure chamber exhaust pipe (10) to plug the rear low-pressure chamber exhaust pipe (10).

8. The axial force balance structure for an aero-engine compressor test according to claim 1, characterized in that It further includes: The front low-pressure chamber exhaust joint (15) is connected to the outer casing of the intermediate casing assembly (4) and communicates with the front low-pressure chamber exhaust passage; The exhaust joint plug cap (16) can be connected to the front low-pressure chamber exhaust joint (15) to plug the front low-pressure chamber exhaust joint (15).

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