Front and rear row mixed axial diffuser of gas compressor and aero-engine with same

Abstract

The invention discloses a front-rear row mixed axial diffuser of a gas compressor and an aero-engine with the front-rear row mixed axial diffuser. The front-rear row mixed axial diffuser comprises a diffuser outer shell, a diffuser radial blade set and a diffuser axial blade set. The diffuser axial blade set comprises a plurality of front-back penetrating blades, a front-row blade set and a rear-row blade set, wherein the front-row blade set and the rear-row blade set are arranged between every two adjacent front-back penetrating blades. And the front-back penetrating blades are used for penetrating installation of a pipeline. The front-row blade set and the rear-row blade set are sequentially arranged at intervals in the axial direction of the diffuser, and the multiple front-back penetrating blades, the front-row blade set and the rear-row blade set are matched to act, so that radial air flow exhausted by the radial blade set of the diffuser extends in the axial direction to form axial air flow, and meanwhile the axial air flow is diffused and rectified. According to the diffuser, the pipeline does not directly intrude into the airflow channel, then the influence of the pipeline on the working performance of the diffuser is reduced, meanwhile, a supporting plate does not need to be designed behind the diffuser, and therefore the axial length of a gas compressor and the overall size and weight of an engine are not increased.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to a mixed axial diffuser with front and rear rows of compressor. BACKGROUND

[0002] An aero-engine generally comprises core components such as a compressor, a combustion chamber and a turbine. The engine works by the compressor rotor impeller to do work on the gas to make the gas warm and pressurized, so as to enter the combustion chamber to mix with fuel to ignite and do work on the turbine rotor. Before the gas enters the combustion chamber from the compressor, in order to make the flow field uniform and stable, a diffuser is usually designed at the outlet of the compressor to expand and straighten the gas. The diffuser is located at the outlet of the compressor and borders the combustion chamber. The region often has a fulcrum bearing arranged therein, and needs to be designed with lubrication, ventilation and air induction pipelines. In order to pursue higher aerodynamic performance, the diffuser blades of an advanced aero-engine often have a small leading edge radius and a thin blade body. The pipeline cannot directly pass through the blade body to enter the bearing cavity. If the pipeline passes through the air flow channel between the blades, it will seriously affect the aerodynamic performance of the compressor and further affect the performance of the engine. Therefore, how to arrange the pipeline through the diffuser without affecting the aerodynamic performance has become a technical difficulty.

[0003] In the prior art, there are two forms of arranging the pipeline through the diffuser: one is to directly pass through the thin blade body and invade the air flow channel, as shown in the accompanying drawings Figure 1 and Figure 2 Since the pipeline passes through the air flow channel between the blades, it will affect the aerodynamic performance of the compressor and further affect the performance of the engine. The other is to design a certain number of support plates at the rear of the diffuser, as shown in the accompanying drawings Figure 3 and Figure 4 The support plates have a relatively thick thickness to accommodate the pipeline, but increase the overall axial length of the compressor, thereby increasing the volume and weight of the engine. SUMMARY

[0004] The present application provides a mixed axial diffuser with front and rear rows of compressor and an aero-engine having the same, to solve the technical problems of the prior art that the pipeline passing through the air flow channel between the blades will affect the aerodynamic performance of the compressor and further affect the performance of the engine, and will increase the overall axial length of the compressor, thereby increasing the volume and weight of the engine.

[0005] The technical solution adopted by the present application is as follows: The application relates to a mixed axial diffuser before and after a compressor, which comprises a diffuser shell body communicated with an outlet end of the compressor, a diffuser radial blade group and a diffuser axial blade group arranged in the diffuser shell body, the diffuser radial blade group comprises a plurality of diffuser radial blades sequentially and evenly arranged along the ring direction of the diffuser shell body, and each diffuser radial blade extends along the radial direction of the diffuser; the diffuser axial blade group comprises a plurality of front and rear continuous blades sequentially and evenly arranged along the ring direction of the diffuser shell body and extending along the axial direction of the diffuser, a front blade group and a rear blade group arranged between two adjacent front and rear continuous blades; the front and rear continuous blades are used for penetratingly arranging external pipelines for introducing air or oil; the front and rear blade groups are sequentially and evenly arranged along the axial direction of the diffuser, and the plurality of front and rear continuous blades, the front blade group and the rear blade group are combined to make the radial airflow discharged by the diffuser radial blade group extend along the axial direction to form axial airflow, and meanwhile, the axial airflow is expanded, regulated and diffused.

[0006] Further, the plurality of front and rear continuous blades are evenly arranged along the ring direction of the diffuser shell body; the leading edges of the plurality of front and rear continuous blades and the leading edges of the front blade group are located at the same axial position, and the trailing edges of the plurality of front and rear continuous blades and the trailing edges of the rear blade group are also located at the same axial position.

[0007] Further, the trailing edges of the front and rear continuous blades are concave towards the leading edges to form cavities; the pipelines are arranged in the cavities.

[0008] Further, the front blade group comprises a plurality of front blades sequentially and evenly arranged along the ring direction of the diffuser shell body, the rear blade group comprises a plurality of rear blades sequentially and evenly arranged along the ring direction of the diffuser shell body, and the plurality of front blades and the plurality of rear blades are arranged one by one in the axial direction; airflow channels are formed between adjacent front blades, between adjacent rear blades, between the front and rear continuous blades and adjacent front and rear blades.

[0009] Further, the outer contour configuration of the front blades is different from that of the rear blades to adapt to the angle change and pressure change requirements of the axial airflow in the flow direction.

[0010] Further, the plurality of front blades between two adjacent front and rear continuous blades are evenly arranged along the ring direction of the diffuser shell body, and the plurality of rear blades between two adjacent front and rear continuous blades are evenly arranged along the ring direction of the diffuser shell body; the airflow channel width is the same between two adjacent front blades, between the front blade and adjacent front and rear continuous blades, between two adjacent rear blades and between the rear blade and adjacent front and rear continuous blades; the thickness of the front and rear continuous blades along the ring direction is one airflow channel width.

[0011] Further, each group of rear row blade sets further comprises at least one rear row intermediate blade arranged between two adjacent rear row blades; the at least one rear row intermediate blade is located between the two adjacent rear row blades, and an air flow channel is formed between the at least one rear row intermediate blade and the two adjacent rear row blades; or, a plurality of rear row intermediate blades are sequentially and evenly arranged along the circumferential direction of the diffuser shell body, and an air flow channel is formed between each two adjacent rear row intermediate blades or between each rear row intermediate blade and the adjacent rear row blade.

[0012] Further, the plurality of rear row intermediate blades arranged between two adjacent rear row blades are evenly arranged along the circumferential direction of the diffuser shell body; the outer profile configuration of the rear row intermediate blade is the same as that of the rear row blade.

[0013] Further, the front and rear continuous blade, the front row blade, the rear row blade and the rear row intermediate blade are respectively welded and fixed with the inner wall surface of the diffuser shell body on both sides, or are integrally formed with the diffuser shell body.

[0014] According to another aspect of the present application, an aero-engine is also provided, which has the diffuser of any one of the above.

[0015] The present application has the following advantages: The present application provides a diffuser for a compressor, which comprises a diffuser radial blade set for introducing air flow discharged from the outlet end of the compressor and making the air flow continue to flow outward in the radial direction, and a front and rear continuous blade, a front row blade set and a rear row blade set arranged sequentially and evenly in the axial direction. The front and rear continuous blade, the front row blade set and the rear row blade set jointly make the radial air flow discharged from the diffuser radial blade set flow in the axial direction to form axial air flow, expand and rectify the flowing axial air flow, so as to ensure the uniformity, stability and air flow angle of the outlet flow field of the compressor, and meet the requirements of the air flow at the inlet of the combustion chamber. The front and rear continuous blade is externally connected with pipelines for air and oil introduction and ventilation, so that the pipelines do not directly invade the air flow channel, thereby reducing the influence of the pipelines on the working performance of the diffuser, and simplifying the installation and arrangement of the pipelines. In addition, the diffuser does not need to be designed with a support plate at the rear end, so that the axial length of the compressor, the overall volume and weight of the engine are not increased, and the technical difficulties of bearing lubrication and air introduction at the interface between the compressor and the combustion chamber are solved.

[0016] In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The present application will be further described below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0017] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification. The illustrations are shown in the drawings, wherein: Figure 1 is a cross-sectional main view structural schematic diagram of the first embodiment of arranging the pipeline in the existing diffuser; Figure 2 is a top view structural schematic diagram of Figure 1 ; Figure 3 is a cross-sectional main view structural schematic diagram of the second embodiment of arranging the pipeline in the existing diffuser; Figure 4 is a top view structural schematic diagram of Figure 2 ; Figure 5 is a cross-sectional main view structural schematic diagram of the mixed axial diffuser of the front and rear rows of the compressor according to the preferred embodiment of the present application; Figure 6 is a top view structural schematic diagram of Figure 5 ;

[0018] Legend: 1, compressor; 2, diffuser outer shell; 201, air flow channel; 3, diffuser radial blade; 4, front and rear continuous blade; 401, cavity; 5, pipeline; 6, front row blade; 7, rear row blade; 8, rear row middle blade. DETAILED DESCRIPTION

[0019] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered below.

[0020] Referring to Figure 5 and Figure 6The preferred embodiment of the present application provides a mixed axial diffuser before and after the compressor, comprising: a diffuser shell 2 in communication with the outlet end of the compressor 1, and a diffuser radial blade group and a diffuser axial blade group arranged in the diffuser shell 2, the diffuser radial blade group comprises a plurality of diffuser radial blades 3 arranged in sequence along the ring direction of the diffuser shell 2, and each diffuser radial blade 3 extends along the radial direction of the diffuser. The diffuser axial blade group comprises a plurality of front and rear continuous blades 4 arranged in sequence along the ring direction of the diffuser shell 2 and extending along the axial direction of the diffuser, and a front blade group and a rear blade group arranged between adjacent two front and rear continuous blades 4. The front and rear continuous blades 4 are used for the pipeline 5 outside for air or oil to be installed. The front blade group and the rear blade group are arranged in sequence along the axial direction of the diffuser, and the plurality of front and rear continuous blades 4, the front blade group and the rear blade group cooperate to make the radial airflow discharged by the diffuser radial blade group extend along the axial direction to form an axial airflow, and at the same time, the axial airflow is diffused and rectified.

[0021] The present application provides a mixed axial diffuser before and after the compressor, which not only comprises a diffuser radial blade group for introducing the airflow discharged by the outlet end of the compressor 1 and making the airflow continue to flow outwardly in the radial direction, but also comprises front and rear continuous blades 4, a front blade group and a rear blade group arranged in sequence along the axial direction, and through the cooperation of the front and rear continuous blades 4, the front blade group and the rear blade group, not only the radial airflow discharged by the diffuser radial blade group flows along the axial direction to form an axial airflow, but also the flowing axial airflow is diffused and rectified to ensure the uniformity, stability and airflow angle of the outlet flow field of the compressor, thereby meeting the requirements of the inlet airflow of the combustion chamber. At the same time, the pipeline 5 outside for air or oil is installed through the front and rear continuous blades 4, so that the pipeline 5 does not directly invade the airflow channel, thereby reducing the influence of the pipeline 5 on the working performance of the diffuser, and making the installation and arrangement of the pipeline 5 simple, and also without the need to design a support plate at the rear of the diffuser, thereby not increasing the axial length of the compressor, the overall volume and weight of the engine, and thereby solving the technical difficulties of bearing lubrication and air induction at the interface between the compressor and the combustion chamber in the prior art.

[0022] Optionally, the plurality of front and rear continuous blades 4 are uniformly and spacedly arranged along the ring direction of the diffuser shell 2. The leading edge of the plurality of front and rear continuous blades 4 and the leading edge of the front blade group are located at the same axial position, and the trailing edge of the plurality of front and rear continuous blades 4 and the trailing edge of the rear blade group are also located at the same axial position, thereby facilitating the obtaining of a uniform gas flow field.

[0023] Optionally, as Figure 6As shown, the trailing edge of the front-rear continuous blade 4 is concave inwardly towards the direction of the leading edge to form a cavity 401. The pipeline 5 is arranged in the cavity 401. In actual design, the cavity 401 is a cavity inside the front-rear continuous blade 4, or the cavity 401 is arranged on the trailing edge of the front-rear continuous blade 4 as shown. Figure 6 As shown, the cavity 401 is bifurcated at the outer flow passage surface of the diffuser shell body, and the cavity 401 is used for installing the pipeline 5 and reducing the overall weight of the diffuser, thereby improving the working performance of the diffuser. Due to the arrangement of the front-rear continuous blade 4, the pipeline 5 only passes through the bifurcated area of the rear section of the front-rear continuous blade 4, and does not directly invade the air flow passage, thereby reducing the influence of the pipeline 5 installation on the performance of the diffuser.

[0024] Optionally, as shown, Figure 6 The front row blade group includes a plurality of front row blades 6 arranged along the ring direction of the diffuser shell body 2 and spaced apart in sequence, the rear row blade group includes a plurality of rear row blades 7 arranged along the ring direction of the diffuser shell body 2 and spaced apart in sequence, and the plurality of front row blades 6 and the plurality of rear row blades 7 are arranged one by one in the front-rear direction to make the leading edge of the rear row blade 7 receive the air flow of the trailing edge of the corresponding front row blade 6, thereby keeping the smooth and stable of the outlet flow field of the compressor, and the front row blade group and the rear row blade group are also spaced apart in the axial direction to make there be a bladeless area between the two, on the one hand, the rear row blade 7 can be designed according to the action of the front row blade 6 on the air flow, so as to better adapt to the angle and pressure requirements of the air flow output, thereby obtaining higher compressor efficiency; on the other hand, the combination of the front row blade 6 and the rear row blade 7 with relatively small blade type can obtain better weight reduction effect compared with a single larger blade, thereby improving the engine performance. The air flow passages 201 are respectively formed between adjacent front row blades 6, between adjacent rear row blades 7, and between the front-rear continuous blade 4 and adjacent front row blades 6 and adjacent rear row blades 7.

[0025] Preferably, when the front-rear continuous blade 4 is optimized by using three-dimensional software, the distance between the front-rear continuous blade 4 and the adjacent front row blade 6 and rear row blade 7 on both sides can be adjusted by adjusting the grid distance on both sides of the front-rear continuous blade 4, i.e. the blade basin and the blade back, so as to adjust the air flow passage flow and ensure the uniformity and stability of the outlet flow field of the compressor.

[0026] Preferably, the blade basin body profile of the front-rear continuous blade 4 corresponds to the blade basin profile of the front row of blades 6 and the rear row of blades 7 respectively, the blade back body profile of the front-rear continuous blade 4 corresponds to the blade back profile of the front row of blades 6 and the rear row of blades 7 respectively, and the front and rear blade profiles of the front-rear continuous blade 4 are smoothly connected without a bladeless area. In the preferred scheme, at the position with the structural requirement of arranging the internal passage pipeline, it is impossible to form a thinner blade profile at the rear row position, and the thick blade profile at the blade inlet end will greatly affect the aerodynamic performance, so the front row of blades 6 and the rear row of blades 7 cannot be combined, and therefore the front-rear continuous blade 4 occupying one width of the airflow passage is used, and the blade basin body profile and the blade back body profile of the front-rear continuous blade 4 are respectively similar to the blade basin profile and the blade back profile of the front row of blades 6 and the rear row of blades 6, thereby being beneficial to obtaining a stable and uniform aerodynamic flow field.

[0027] Preferably, the outer contour configuration of the front row of blades 6 is different from that of the rear row of blades 7 to adapt to the angle change and pressure change requirements of the axial airflow in the flow direction.

[0028] Preferably, the plurality of front row of blades 6 between the adjacent two front-rear continuous blades 4 are uniformly spaced along the ring direction of the diffuser outer shell 2, and the plurality of rear row of blades 7 between the adjacent two front-rear continuous blades 4 are uniformly spaced along the ring direction of the diffuser outer shell 2. The adjacent two front row of blades 6, the front row of blades 6 and the adjacent front-rear continuous blade 4, the adjacent two rear row of blades 7, and the rear row of blades 7 and the adjacent front-rear continuous blade 4 are each one width of the airflow passage 201. The thickness of the front-rear continuous blade 4 along the ring direction is one width of the airflow passage 201. The arrangement of the airflow passage width between the front-rear continuous blade 4, the front row of blades 6 and the rear row of blades 7 is beneficial to obtaining a more uniform flow field.

[0029] Optionally, as shown in Figure 6 each group of rear row of blades further includes at least one rear row of intermediate blade 8 arranged between the adjacent two rear row of blades 7. One rear row of intermediate blade 8 is located between the adjacent two rear row of blades 7, and the rear row of intermediate blade 8 and the adjacent rear row of blades 7 form an airflow passage 201. Alternatively, a plurality of rear row of intermediate blades 8 are sequentially and spacedly arranged along the ring direction of the diffuser outer shell 2, and the adjacent two rear row of intermediate blades 8 and the rear row of intermediate blade 8 and the adjacent rear row of blades 7 form an airflow passage 201 respectively. In this optional scheme, whether there is one rear row of intermediate blade 8 between the adjacent two rear row of blades 7 or a plurality of rear row of intermediate blades 8, the total number of the rear row of blades can be effectively increased to enhance the flow regulation effect of the diffuser on the airflow, thereby obtaining an ideal airflow deflection angle and maintaining the uniformity and stability of the outlet flow field of the compressor.

[0030] Preferably, the plurality of rear intermediate vanes 8 between two adjacent rear vanes 7 are evenly spaced along the circumferential direction of the diffuser outer casing 2. The outer profile configuration of the rear intermediate vanes 8 can be the same as or different from that of the rear vanes 7. Through aerodynamic flow field analysis by using three-dimensional software, the outer profile configuration of the rear intermediate vanes 8 can be the same as or different from that of the rear vanes 7, as long as it is beneficial to obtain a more uniform and stable flow field.

[0031] Optionally, the front and rear continuous vanes 4, the front vanes 6, the rear vanes 7 and the rear intermediate vanes 8 are respectively welded and fixed with the inner wall surfaces of the two side diffuser outer casings 2, or are integrally formed with the diffuser outer casings 2.

[0032] Optionally, the present application also provides an aero-engine with the front and rear row mixed axial diffuser of any one of the above embodiments, so that the aero-engine of the present application, through the combined action of the front and rear continuous vanes 4, the front vane group and the rear vane group, not only makes the radial airflow discharged by the radial vane group flow along the axial direction to form an axial airflow, but also expands and straightens the flowing axial airflow to ensure the uniformity, stability and airflow angle of the compressor outlet flow field, thereby meeting the requirements of the combustion chamber inlet airflow; at the same time, the front and rear continuous vanes 4 are provided with external pipelines 5 for air and oil guiding and ventilation, so that the pipelines 5 do not directly invade the airflow channel, thereby reducing the influence of the pipelines 5 on the working performance of the diffuser, and making the installation and arrangement of the pipelines 5 simple, and also eliminating the need to design a support plate at the rear of the diffuser, thereby not increasing the axial length of the compressor and the overall volume and weight of the engine, and thereby solving the technical difficulties of bearing lubrication and air guiding at the interface between the compressor and the combustion chamber in the aero-engine of the prior art.

[0033] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A hybrid axial diffuser for a compressor, characterized in that, Comprise: The diffuser shell (2) is communicated with the outlet end of the compressor (1), and the diffuser radial blade group and the diffuser axial blade group are arranged in the diffuser shell (2), the diffuser radial blade group comprises a plurality of diffuser radial blades (3) arranged along the ring direction of the diffuser shell (2) in sequence and spaced, and each diffuser radial blade (3) extends along the radial direction of the diffuser; The diffuser axial blade group comprises a plurality of front and rear continuous blades (4) arranged along the ring direction of the diffuser shell (2) in sequence and spaced, and extending along the axial direction of the diffuser, and a front row blade group and a rear row blade group arranged between adjacent two front and rear continuous blades (4); The front and rear continuous blades (4) are used for installing the external pipeline (5) for introducing air or oil; The front row blade group and the rear row blade group are arranged along the axial direction of the diffuser in sequence and spaced, and the plurality of front and rear continuous blades (4), the front row blade group and the rear row blade group cooperate to make the radial airflow discharged by the diffuser radial blade group extend along the axial direction to form an axial airflow, and simultaneously expand and rectify the axial airflow.

2. The front and rear row mixed axial diffuser of the compressor according to claim 1, characterized in that: The plurality of front and rear continuous blades (4) are uniformly and spacedly arranged along the ring direction of the diffuser shell (2); The leading edge of the plurality of front and rear continuous blades (4) and the leading edge of the front row blade group are located at the same axial position, and the trailing edge of the plurality of front and rear continuous blades (4) and the trailing edge of the rear row blade group are also located at the same axial position.

3. The front and rear row mixed axial diffuser of the compressor according to claim 1, characterized in that: The trailing edge of the front and rear continuous blade (4) is concave to form a cavity (401) towards the leading edge; The pipeline (5) is arranged in the cavity (401).

4. The front and rear row mixed axial diffuser of the compressor according to claim 1, characterized in that: The front row blade group comprises a plurality of front row blades (6) arranged along the ring direction of the diffuser shell (2) in sequence and spaced, and the rear row blade group comprises a plurality of rear row blades (7) arranged along the ring direction of the diffuser shell (2) in sequence and spaced, and the plurality of front row blades (6) and the plurality of rear row blades (7) are arranged in one-to-one correspondence along the axial direction; Adjacent front row blades (6), adjacent rear row blades (7), and the front and rear continuous blade (4) and adjacent front row blades (6) and adjacent rear row blades (7) form airflow passages (201) respectively.

5. The front and rear row mixed axial diffuser of the compressor according to claim 4, characterized in that: The outer contour configuration of the front row blade (6) is different from that of the rear row blade (7) to adapt to the angle change and pressure change requirements of the axial airflow in the flow direction.

6. The front and rear row mixed axial diffuser of the compressor according to claim 4, characterized in that: The plurality of front row blades (6) between adjacent two front and rear continuous blades (4) are uniformly and spacedly arranged along the ring direction of the diffuser shell (2), and the plurality of rear row blades (7) between adjacent two front and rear continuous blades (4) are uniformly and spacedly arranged along the ring direction of the diffuser shell (2). The width of each air flow channel (201) is equal to the width of one air flow channel (201) between two adjacent front row blades (6), between the front row blade (6) and the adjacent front-rear continuous blade (4), between two adjacent rear row blades (7), and between the rear row blade (7) and the adjacent front-rear continuous blade (4). The thickness of the front-rear continuous blade (4) along the circumferential direction is equal to the width of one air flow channel (201).

7. The mixed front-rear row axial diffuser of claim 4, wherein Each group of rear row blades further comprises at least one rear row intermediate blade (8) arranged between two adjacent rear row blades (7). The rear row intermediate blade (8) is located between two adjacent rear row blades (7), and an air flow channel (201) is formed between the rear row intermediate blade (8) and the adjacent rear row blade (7). A plurality of rear row intermediate blades (8) are arranged along the circumferential direction of the diffuser shell (2) in sequence and are spaced apart from each other, and an air flow channel (201) is formed between two adjacent rear row intermediate blades (8) and between the rear row intermediate blade (8) and the adjacent rear row blade (7).

8. The mixed front-rear row axial diffuser of claim 7, wherein The plurality of rear row intermediate blades (8) between two adjacent rear row blades (7) are uniformly spaced along the circumferential direction of the diffuser shell (2). The outer contour of the rear row intermediate blade (8) is the same as that of the rear row blade (7).

9. The mixed front-rear row axial diffuser of claim 7, wherein The front-rear continuous blade (4), the front row blade (6), the rear row blade (7), and the rear row intermediate blade (8) are respectively welded and fixed to the inner wall of the diffuser shell (2) on both sides, or are integrally formed with the diffuser shell (2).

10. An aeroengine characterised in that, The mixed front-rear row axial diffuser of any one of claims 1-9.

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