Multi-section compressor transmission structure of aero-engine

Abstract

The utility model relates to the technical field of air compressors, in particular to an aero-engine multi-section air compressor transmission structure which comprises a main shaft body, a machine shell body, a rotor assembly and a stator assembly. The turning positions of different levels of the inner wall of the aero-engine compressor shell are arranged to be of the chamfer structures, the chamfer design can reduce the resistance of airflow passing through the turning positions, the smoothness of the airflow is improved, and therefore the pneumatic flow characteristic is improved, the possibility of vortex and flow separation is reduced, and the service life of the aero-engine compressor shell is prolonged. Furthermore, the outer walls of the two sides of the rotor blade and the stator blade are designed to be of a chamfer structure, fluid can flow more smoothly along the surfaces of the blades, separation and turbulence of airflow are reduced, aerodynamic resistance is reduced, and the fluid dynamic performance is improved. Therefore, on the basis that fluid resistance is weakened and smooth passing is guaranteed, the stability of fluid flowing is effectively improved, and the risk of surge is reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of compressor, especially to aviation engine multistage compressor transmission structure. BACKGROUND

[0002] The compressor of an aero-engine is an important component of the aero-engine, and its main function is to compress the air entering the engine to increase the pressure and density of the air. This process is a key step for the aero-engine to inhale air, mix fuel and ignite to generate thrust.

[0003] Since the compressor may occur surge phenomenon under certain operating conditions (such as low flow, high pressure ratio), the performance is unstable, and the compressor may be damaged in severe cases. Therefore, a compressor transmission structure with excellent safety is needed. SUMMARY

[0004] The purpose of the aviation engine multistage compressor transmission structure proposed to solve the above problems is to improve the problem that the existing compressor may occur surge phenomenon under certain operating conditions (such as low flow, high pressure ratio), which leads to unstable performance and may damage the compressor in severe cases.

[0005] The aviation engine multistage compressor transmission structure includes a main shaft body, a casing body, a rotor assembly and a stator assembly. The main shaft body is located inside the casing body. The rotor assembly and the stator assembly are alternately distributed along the main shaft body. The rotor blades and the stator blades are both set as inclined arc blades, and the outer walls on both sides of the rotor blades and the stator blades are both provided with chamfers. The casing body is combined and adjusted according to the diameters of the rotor assembly and the stator assembly, and three groups of different size accommodating cavities are formed inside the casing body. The outer walls on both sides of the casing body at the positions of the adjacent two groups of different volume accommodating cavities are both provided with chamfers.

[0006] Preferably, the rotor assembly includes an annular support disc and rotor blades. The annular support disc is fixedly penetrated on the outer part of the shaft body of the main shaft body. The outer walls on both sides of the annular support disc are equally spaced and circumferentially provided with rotor blades.

[0007] Preferably, the stator assembly includes an auxiliary support ring, stator blades and a positioning installation ring. The inner walls on both sides of the auxiliary support ring are in close contact with the outer walls of the shaft body of the main shaft body. The outer walls on both sides of the auxiliary support ring are equally spaced and circumferentially provided with stator blades. The outer walls on both sides of the stator blades away from the auxiliary support ring are both connected with the inner walls on both sides of the positioning installation ring. The positioning installation ring is fixedly connected to the inner walls of the casing of the casing body.

[0008] Preferably, the inside of the casing body is internally mounted with three groups of rotor assemblies and stator assemblies of different sizes, which are sequentially arranged in order of size to form a low-pressure stage, a medium-pressure stage and a high-pressure stage, and the deviation ratio of the low-pressure stage, the medium-pressure stage and the high-pressure stage is a preset value, so as to form an optimal compression process.

[0009] The utility model discloses the beneficial effects are:

[0010] 1、The aero-engine multi-stage compressor transmission structure sets up the chamfer structure to the turning position of different levels in the inner wall of aero-engine compressor shell when using, and the chamfer design can reduce the resistance of airflow passing through the turning position, improve the smoothness of airflow, thereby improving the aerodynamic flow characteristics, reducing the possibility of vortex and flow separation, further through the design of setting the outer wall of both sides of rotor blade and stator blade as the chamfer structure, it is helpful to the more smooth flow of fluid along the blade surface, thereby reducing the separation and turbulence of airflow, reducing the aerodynamic resistance, improving the fluid dynamic performance, and further effectively improving the stability of fluid flow on the basis of weakening fluid resistance to ensure its smooth passage, reducing the risk of surge.

[0011] 2、The aero-engine multi-stage compressor transmission structure adds the medium-pressure stage in the middle position between the low-pressure stage and the high-pressure stage of the existing compressor when using, and the addition of the medium-pressure stage can optimize the compression ratio, thereby improving the utilization efficiency of fuel, and the engine can work in the best state during economic cruising, reducing fuel consumption, and at the same time, by reducing the working load and pressure of each stage, the wear of components can be reduced, the service life of the compressor can be prolonged, the maintenance cost can be reduced, the overall structure design is simple, and the practical effect is good. BRIEF DESCRIPTION OF DRAWINGS

[0012] Figure 1 It is the overall three-dimensional structure schematic diagram of the utility model;

[0013] Figure 2 It is the overall cross-sectional three-dimensional structure schematic diagram of the utility model;

[0014] Figure 3 It is the rotor assembly three-dimensional structure schematic diagram of the utility model;

[0015] Figure 4 It is the stator assembly three-dimensional structure schematic diagram of the utility model.

[0016] In the drawing: 1, main shaft body; 2, casing body; 3, rotor assembly; 301, annular support disc; 302, rotor blade; 4, stator assembly; 401, auxiliary support ring; 402, stator blade; 403, positioning installation ring. DETAILED DESCRIPTION

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0018] In practical implementation: such as Figures 1-4 As shown, the multi-stage compressor transmission structure of an aero-engine includes a main shaft body 1, a housing body 2, a rotor assembly 3, and a stator assembly 4: the main shaft body 1 is located inside the housing body 2;

[0019] Rotor assembly 3 and stator assembly 4 are alternately distributed along the main shaft body 1;

[0020] When air passes through, the arrangement of rotor assembly 3 here will accelerate the rotation of the air, while stator assembly 4 will slow down the air speed, thereby increasing the air pressure.

[0021] The rotor assembly 3 includes an annular support disk 301 and rotor blades 302. The annular support disk 301 is fixed to the outside of the shaft of the main shaft body 1. The rotor blades 302 are arranged in a circumferential manner on the outer side wall of the annular support disk 301 at equal intervals.

[0022] When the main shaft body 1 rotates, it will automatically drive the annular support disk 301 to rotate, which in turn drives multiple sets of rotor blades 302 to rotate synchronously. Through rotation, the kinetic energy of the airflow is converted into compression components. The rotor blades 302 generate lift through rotation, which accelerates the airflow and increases its pressure.

[0023] The stator assembly 4 includes an auxiliary support ring 401, stator blades 402, and a positioning mounting ring 403. The inner side wall of the auxiliary support ring 401 is in contact with the outer side wall of the main shaft body 1. The stator blades 402 are arranged in a circumferential manner at equal intervals on the outer side wall of the auxiliary support ring 401. The outer side wall of the stator blades 402 away from the auxiliary support ring 401 is connected to the inner side wall of the positioning mounting ring 403. The positioning mounting ring 403 is fixed to the inner wall of the housing body 2.

[0024] The positioning installation ring 403 and the auxiliary support ring 401 both serve to fix and support the stator blade 402. The function of the stator blade 402 is to guide the airflow to optimize the airflow path, reduce eddies and losses. The aerodynamic design of the stator layer helps to reduce pressure loss and ensure smooth airflow.

[0025] The inside of the casing body 2 is mounted with three groups of rotor assemblies 3 and stator assemblies 4 of different sizes, which are arranged in order of size to form a low-pressure stage, a medium-pressure stage and a high-pressure stage, and the deviation ratio of the low-pressure stage, the medium-pressure stage and the high-pressure stage is a preset value, so as to form an optimal compression process.

[0026] The rotor blades 302 and the stator blades 402 are both arranged as inclined arc-shaped blades, and the outer walls on both sides of the rotor blades 302 and the stator blades 402 are provided with chamfers; the chamfer design helps the fluid flow more smoothly along the blade surface, thereby reducing airflow separation and turbulence, reducing aerodynamic resistance and improving fluid dynamic performance.

[0027] The casing body 2 is combined and adjusted according to the diameters of the rotor assemblies 3 and the stator assemblies 4, and three groups of accommodating cavities of different sizes are formed inside the casing body 2, and the casing body 2 is provided with chamfers on the positions and side outer walls of the adjacent two groups of accommodating cavities of different sizes;

[0028] The accommodating cavities of different sizes can make the air compressor achieve better airflow distribution under different working conditions, reduce airflow resistance and improve the overall efficiency of the air compressor, and the chamfer design of the casing body 2 helps the smooth transition of airflow and reduces the vortex loss of airflow in the casing body 2, thereby improving the working performance of the air compressor.

[0029] In addition, it should be understood that although the present specification is described in terms of embodiments, not every embodiment contains only one independent technical solution, and the description of the specification is only for the sake of clarity. The skilled person should consider the specification as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that can be understood by the skilled person.

Claims

1. A multi-stage compressor drive structure for an aeroengine, characterised in that, Including main shaft body (1), casing body (2), rotor assembly (3) and stator assembly (4): the main shaft body (1) is located in the inside of casing body (2); The rotor assembly (3) and stator assembly (4) are alternately distributed along the main shaft body (1); Rotor blades (302) and stator blades (402) are both set as inclined arc blades, and the outer walls of both sides of rotor blades (302) and stator blades (402) are provided with chamfers; The casing body (2) is combined and adjusted according to the diameter size of rotor assembly (3) and stator assembly (4), and three groups of different size accommodating cavities are formed in the casing body (2), and the casing body (2) is provided with chamfers on the position and side edge outer wall of the adjacent two groups of different volume accommodating cavities.

2. The aeroengine multi-stage compressor drive structure of claim 1, wherein: The rotor assembly (3) includes an annular support disc (301) and rotor blades (302), the annular support disc (301) is fixedly penetrated on the outer wall of the shaft body of the main shaft body (1), and the side edge outer wall of the annular support disc (301) is provided with rotor blades (302) at equal intervals in a surrounding manner.

3. The aeroengine multi-stage compressor drive structure of claim 2, wherein: The stator assembly (4) includes an auxiliary support ring (401), stator blades (402) and a positioning installation ring (403), the side edge inner wall of the auxiliary support ring (401) is attached to the outer wall of the shaft body of the main shaft body (1), the side edge outer wall of the auxiliary support ring (401) is provided with stator blades (402) at equal intervals in a surrounding manner, and the side edge outer wall of the stator blades (402) away from the auxiliary support ring (401) is connected to the side edge inner wall of the positioning installation ring (403), and the positioning installation ring (403) is fixed to the inner wall of the casing of the casing body (2).

4. The aeroengine multi-stage compressor drive structure of claim 1, wherein: Three groups of different size rotor assemblies (3) and stator assemblies (4) are installed in the casing body (2), arranged and distributed in size as low pressure stage, medium pressure stage and high pressure stage in turn, and the deviation ratio of low pressure stage, medium pressure stage and high pressure stage is a preset value, so as to form the best compression process.

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