Compressor front and rear axial diffuser for mixing and aero engines.

Abstract

This invention discloses a compressor front-to-rear axial diffuser and an aero-engine incorporating the same, comprising: a diffuser housing, a diffuser radial blade assembly, and a diffuser axial blade assembly. The diffuser axial blade assembly includes multiple front-to-rear continuous blades, and a front blade assembly and a rear blade assembly disposed between adjacent front-to-rear continuous blades. The front-to-rear continuous blades are used for pipe installation. The front and rear blade assemblies are sequentially spaced along the diffuser's axial direction, and the multiple front-to-rear continuous blades, the front blade assembly, and the rear blade assembly work together to extend the radial airflow discharged from the diffuser's radial blade assembly into an axial airflow, while simultaneously diffuser and rectifying the axial airflow. This diffuser prevents pipes from directly intruding into the airflow channel, thus reducing the impact of pipes on the diffuser's performance. It also eliminates the need for a support plate behind the diffuser, thereby not increasing the compressor's axial length, the engine's overall volume, or its weight.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a compressor front-to-rear mixing axial diffuser. Furthermore, this invention also relates to an aero-engine comprising the aforementioned compressor front-to-rear mixing axial diffuser. Background Technology

[0002] Aero engines typically consist of core components such as compressors, combustion chambers, and turbines. The engine heats and pressurizes the gas by using the compressor rotor impeller to perform work on it, allowing it to mix with fuel in the combustion chamber and ignite, where it then performs work on the turbine rotor. Before the gas enters the combustion chamber from the compressor, a diffuser is usually designed at the compressor outlet to diffuse and rectify the gas, ensuring a uniform and stable flow field. The diffuser is located at the compressor outlet, at the boundary with the combustion chamber. This area often houses pivot bearings and requires the design of piping for lubrication, ventilation, and bleed air. Advanced aero engines, aiming for higher aerodynamic performance, often feature diffuser blades with small leading-edge radii and thin blades. Piping cannot directly pass through the blade body into the bearing cavity. If piping were to pass through the airflow channels between the blades, it would severely impact the compressor's aerodynamic performance, further affecting engine performance. Therefore, how to arrange piping through the diffuser without compromising aerodynamic performance has become a technical challenge.

[0003] In existing technical solutions, there are generally two forms of piping arrangement through diffusers: one is to directly pass through the thin blade and intrude into the airflow channel for arrangement, as shown in the attached figure. Figure 1 and Figure 2 As shown, since the piping passes through the airflow channels between the blades, it will affect the aerodynamic performance of the compressor, and thus further affect the engine performance; another option is to design a certain number of support plates behind the diffuser, as shown in the attached diagram. Figure 3 and Figure 4 As shown, the support plate is thick enough to accommodate the pipeline, but it will increase the overall axial length of the compressor, thereby increasing the size and weight of the engine. Summary of the Invention

[0004] This invention provides a compressor front and rear axial diffuser and an aero-engine having the same, to solve the technical problems of existing structures where the pipeline passing through the airflow channel between the blades affects the aerodynamic performance of the compressor, which in turn affects the engine performance, and increases the overall axial length of the compressor, thereby increasing the size and weight of the engine.

[0005] The technical solution adopted in this invention is as follows:

[0006] A compressor front-to-back axial diffuser includes: a diffuser housing connected to the outlet end of the compressor, and diffuser radial blade groups and diffuser axial blade groups arranged within the diffuser housing. The diffuser radial blade groups include a plurality of diffuser radial blades arranged sequentially at intervals along the circumference of the diffuser housing, and each diffuser radial blade extends radially along the diffuser. The diffuser axial blade groups include a plurality of front-to-back continuous blades arranged sequentially at intervals along the circumference of the diffuser housing and extending axially along the diffuser, and a front blade group and a rear blade group arranged between adjacent front-to-back continuous blades. The front-to-back continuous blades are used for external pipelines for priming air or oil. The front blade group and the rear blade group are arranged sequentially at intervals along the axial direction of the diffuser, and the plurality of front-to-back continuous blades, the front blade group, and the rear blade group work together to extend the radial airflow discharged from the diffuser radial blade group into an axial airflow, while simultaneously diffuser and rectifying the axial airflow.

[0007] Furthermore, multiple front-to-back continuous blades are evenly spaced along the circumferential direction of the diffuser housing; the leading edges of the multiple front-to-back continuous blades and the leading edges of the front row of blades are located in the same axial position, and the trailing edges of the multiple front-to-back continuous blades and the trailing edges of the rear row of blades are also located in the same axial position.

[0008] Furthermore, the trailing edge of the blades that run from front to back is concave inward toward its leading edge to form a cavity; the pipeline passes through the cavity.

[0009] Furthermore, the front blade group includes multiple front blades arranged sequentially at intervals along the circumference of the diffuser housing, and the rear blade group includes multiple rear blades arranged sequentially at intervals along the circumference of the diffuser housing. The multiple front blades and the multiple rear blades are arranged in a one-to-one correspondence along the axial direction. Airflow channels are formed between adjacent front blades, between adjacent rear blades, and between the front and rear connecting blades and adjacent front and rear blades.

[0010] Furthermore, the outer contour configuration of the front row of blades is different from that of the rear row of blades to adapt to the angular and pressure changes of the axial airflow in the flow direction.

[0011] Furthermore, multiple front row blades between two adjacent front-to-back continuous blades are evenly spaced along the circumference of the diffuser housing, and multiple rear row blades between two adjacent front-to-back continuous blades are evenly spaced along the circumference of the diffuser housing; the distance between two adjacent front row blades, between a front row blade and an adjacent front-to-back continuous blade, between two adjacent rear row blades, and between a rear row blade and an adjacent front-to-back continuous blade is one airflow channel width; the thickness of the front-to-back continuous blades along the circumference is one airflow channel width.

[0012] Furthermore, each set of rear blades also includes at least one rear intermediate blade disposed between two adjacent rear blades; one rear intermediate blade is located in the middle of two adjacent rear blades, and an airflow channel is formed between the rear intermediate blade and the adjacent rear blade; or, multiple rear intermediate blades are arranged sequentially at intervals along the circumference of the diffuser housing, and airflow channels are formed between two adjacent rear intermediate blades and between the rear intermediate blade and the adjacent rear blade.

[0013] Furthermore, multiple rear intermediate blades are evenly spaced along the circumferential direction of the diffuser housing between two adjacent rear blades; the outer contour configuration of the rear intermediate blades is the same as that of the rear blades.

[0014] Furthermore, the front and rear connecting blades, the front row blades, the rear row blades and the rear middle blades are respectively welded and fixed to the inner wall surface of the diffuser housing on both sides, or integrally formed with the diffuser housing.

[0015] According to another aspect of the invention, an aircraft engine is also provided, having a compressor front and rear row mixing axial diffuser as described in any of the above.

[0016] The present invention has the following beneficial effects:

[0017] This invention proposes a compressor front-to-back axial diffuser, which includes not only a diffuser radial blade assembly for introducing the airflow discharged from the compressor outlet and ensuring its continued radial outward flow, but also front and rear through blades, and a front and rear blade assembly arranged sequentially at intervals along the axial direction. Through the coordinated action of the front and rear through blades, the front and rear blade assemblies, the diffuser not only ensures the radial airflow discharged from the diffuser radial blade assembly flows axially to form an axial airflow, but also diffuses and rectifies the flowing axial airflow. To ensure the uniformity and stability of the compressor outlet flow field and the airflow angle, thereby meeting the airflow requirements at the combustion chamber inlet; at the same time, external pipelines for bleed air, bleed oil, and ventilation are installed through the front and rear through blades, so that the pipelines do not directly intrude into the airflow channel, thereby reducing the impact of the pipelines on the working performance of the diffuser and simplifying the installation and setting of the pipelines. At the same time, there is no need to design a support plate behind the diffuser, thus not increasing the axial length of the compressor, the overall volume and weight of the engine, thereby solving the technical difficulties of bearing lubrication and bleed air at the interface between the compressor and the combustion chamber in the existing technology.

[0018] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0019] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0020] Figure 1 This is a cross-sectional front view schematic diagram of an embodiment of the piping arrangement in an existing diffuser;

[0021] Figure 2 yes Figure 1 A top-view structural diagram;

[0022] Figure 3 This is a cross-sectional front view schematic diagram of an embodiment two of the existing diffuser with piping arrangement;

[0023] Figure 4 yes Figure 2 A top-view structural diagram;

[0024] Figure 5 This is a cross-sectional front view schematic diagram of the compressor front and rear axial diffuser of a preferred embodiment of the present invention;

[0025] Figure 6 yes Figure 5 A top-view structural diagram.

[0026] Legend:

[0027] 1. Air compressor;

[0028] 2. Diffuser housing; 201. Airflow channel;

[0029] 3. Diffuser radial blades;

[0030] 4. A blade that runs from front to back; 401. A cavity;

[0031] 5. Piping; 6. Front row blades; 7. Rear row blades; 8. Rear row middle blades. Detailed Implementation

[0032] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0033] Reference Figure 5 and Figure 6A preferred embodiment of the present invention provides a compressor front-to-back axial diffuser, comprising: a diffuser housing 2 communicating with the outlet end of a compressor 1, and a diffuser radial blade assembly and a diffuser axial blade assembly disposed within the diffuser housing 2. The diffuser radial blade assembly includes a plurality of diffuser radial blades 3 arranged sequentially at intervals along the circumference of the diffuser housing 2, and each diffuser radial blade 3 extends radially along the diffuser. The diffuser axial blade assembly includes a plurality of front-to-back continuous blades 4 arranged sequentially at intervals along the circumference of the diffuser housing 2 and extending axially along the diffuser, and a front blade assembly and a rear blade assembly disposed between adjacent front-to-back continuous blades 4. The front-to-back continuous blades 4 are used for external piping 5 for bleed air or bleed oil to pass through and be installed. The front and rear blade groups are arranged sequentially and alternately along the axial direction of the diffuser, and multiple blades are connected front and rear. The front and rear blade groups work together to extend the radial airflow discharged from the radial blade group of the diffuser into an axial airflow, while simultaneously diffuser and rectify the axial airflow.

[0034] This invention proposes a compressor front-to-back axial diffuser, which includes not only a diffuser radial blade assembly for introducing the airflow discharged from the compressor outlet and ensuring its continued radial outward flow, but also front-to-back through blades 4, and a front and rear blade assembly arranged sequentially at intervals along the axial direction. Through the coordinated action of the front-to-back through blades 4, the front and rear blade assemblies, the diffuser not only ensures the radial airflow discharged from the diffuser radial blade assembly flows axially to form an axial airflow, but also diffuses and rectifies the flowing axial airflow. This design ensures the uniformity and stability of the compressor outlet flow field and the airflow angle, thereby meeting the combustion chamber inlet airflow requirements. Simultaneously, external ducts 5 for bleed air, bleed oil, and ventilation are installed via the front and rear connecting blades 4. This prevents the ducts 5 from directly intruding into the airflow channel, reducing their impact on the diffuser's performance and simplifying installation and setup. Furthermore, it eliminates the need for a support plate behind the diffuser, thus not increasing the compressor's axial length, the engine's overall volume, or its weight. This addresses the technical challenges of bearing lubrication and bleed air at the compressor-combustion chamber interface in existing technologies.

[0035] Optionally, multiple front-to-back continuous blades 4 are evenly spaced along the circumferential direction of the diffuser housing 2. The leading edges of the multiple front-to-back continuous blades 4 and the leading edges of the front row of blades are located in the same axial position, and the trailing edges of the multiple front-to-back continuous blades 4 and the trailing edges of the rear row of blades are also located in the same axial position, which is beneficial to obtaining a uniform gas flow field.

[0036] Optionally, such as Figure 6As shown, the trailing edge of the front and rear connecting blades 4 is concave towards its leading edge to form a cavity 401. The pipe 5 passes through the cavity 401. In actual design, the cavity 401 is a cavity located inside the front and rear connecting blades 4, or the cavity 401 is like... Figure 6 The cavity 401 is also connected to the outer flow channel surface of the diffuser housing to form a bifurcation area. The cavity 401 is used to install the pipe 5 and also to reduce the overall weight of the diffuser, thereby improving the working performance of the diffuser. Due to the setting of the front and rear connecting blades 4, the pipe 5 only passes through the bifurcation area of ​​the rear section of the front and rear connecting blades 4, and does not directly invade the airflow channel, thereby reducing the impact of the installation of the pipe 5 on the performance of the diffuser.

[0037] Optionally, such as Figure 6 As shown, the front blade group includes multiple front blades 6 arranged sequentially and spaced apart along the circumference of the diffuser housing 2, and the rear blade group includes multiple rear blades 7 arranged sequentially and spaced apart along the circumference of the diffuser housing 2. The multiple front blades 6 and multiple rear blades 7 are arranged one-to-one in the axial direction so that the leading edge of the rear blade 7 receives the airflow from the trailing edge of the corresponding front blade 6, thereby maintaining a smooth and stable compressor outlet flow field. The front and rear blade groups are also spaced apart along the axial direction to create a bladeless zone between them. On the one hand, this allows the rear blades 7 to be designed with their airflow angle of attack according to the effect of the front blades 6 on the airflow, so as to better adapt to the angle and pressure requirements of the airflow output and thus obtain higher compressor efficiency. On the other hand, using a combination of front blades 6 and rear blades 7 with relatively small blade profiles can achieve better weight reduction to a certain extent compared to using a single larger blade, thereby improving engine performance. The airflow channels 201 are formed between the adjacent front row blades 6, the adjacent rear row blades 7, the front and rear connecting blades 4, the adjacent front row blades 6, and the adjacent rear row blades 7.

[0038] Preferably, when optimizing the design of the front and rear connected blades 4 using three-dimensional software, the flow rate of the airflow channel can be adjusted by adjusting the grid spacing on both sides of the blade head and blade back of the front and rear connected blades 4, that is, adjusting the distance between the front and rear connected blades 4 and the adjacent front row blades 6 and rear row blades 7 on both sides, so as to ensure the uniformity and stability of the compressor outlet flow field.

[0039] Preferably, the blade basin profiles of the front and rear connected blades 4 correspond to the blade basin profiles of the front blades 6 and the rear blades 7, respectively, and the blade back profiles of the front and rear connected blades 4 correspond to the blade back profiles of the front blades 6 and the rear blades 7, respectively. Furthermore, the front and rear blade profiles of the front and rear connected blades 4 are smoothly connected, with no bladeless areas. In this preferred embodiment, at locations requiring internal piping, it is impossible to form a thinner blade profile in the rear position, and a thicker blade profile at the inlet end would significantly affect aerodynamic performance. Therefore, a combination of front blades 6 and rear blades 7 cannot be used. Instead, a front and rear connected blade 4 occupying the width of one airflow channel is used. Simultaneously, the blade basin profiles and blade back profiles of the front and rear connected blades 4 are similar to the blade basin profiles and blade back profiles of the front blades 6 and the rear blades 6, respectively, thereby facilitating the acquisition of a stable and uniform aerodynamic flow field.

[0040] Preferably, the outer contour configuration of the front row blades 6 is different from that of the rear row blades 7, in order to adapt to the angular and pressure changes of the axial airflow in the flow direction.

[0041] Preferably, multiple front row blades 6 between two adjacent front-to-back connecting blades 4 are evenly spaced along the circumference of the diffuser housing 2, and multiple rear row blades 7 between two adjacent front-to-back connecting blades 4 are also evenly spaced along the circumference of the diffuser housing 2. The width of an airflow channel 201 exists between two adjacent front row blades 6, between a front row blade 6 and an adjacent front-to-back connecting blade 4, between two adjacent rear row blades 7, and between a rear row blade 7 and an adjacent front-to-back connecting blade 4. The circumferential thickness of the front-to-back connecting blades 4 is equal to the width of an airflow channel 201. This arrangement of the airflow channel widths between the front-to-back connecting blades 4, the front row blades 6, and the rear row blades 7 facilitates a more uniform flow field.

[0042] Optionally, such as Figure 6 As shown, each rear blade group also includes at least one rear intermediate blade 8 disposed between two adjacent rear blades 7. The rear intermediate blade 8 is located in the middle of two adjacent rear blades 7, and an airflow channel 201 is formed between the rear intermediate blade 8 and the adjacent rear blade 7. Alternatively, multiple rear intermediate blades 8 are arranged sequentially at intervals along the circumference of the diffuser housing 2, and airflow channels 201 are formed between adjacent rear intermediate blades 8 and between the rear intermediate blade 8 and the adjacent rear blade 7, respectively. In this optional scheme, regardless of whether there is one or multiple rear intermediate blades 8 between two adjacent rear blades 7, the total number of rear blade groups can be effectively increased, enhancing the diffuser's rectification effect on the airflow, thereby obtaining an ideal airflow steering angle and maintaining a uniform and stable compressor outlet flow field.

[0043] Preferably, multiple intermediate rear blades 8 are evenly spaced circumferentially between two adjacent rear blades 7. The outer contour configuration of the intermediate rear blades 8 can be the same as or different from that of the rear blades 7. By using three-dimensional software for aerodynamic flow field analysis, the outer contour configuration of the intermediate rear blades 8 can be the same as or different from that of the rear blades 7, as long as it is conducive to obtaining a more uniform and stable flow field.

[0044] Optionally, the front and rear connecting blades 4, the front row blades 6, the rear row blades 7 and the rear middle blades 8 are welded and fixed to the inner wall surfaces of the diffuser housing 2 on both sides, or are integrally formed with the diffuser housing 2.

[0045] Optionally, a preferred embodiment of the present invention also provides an aero-engine having a compressor front and rear axial diffuser as described above. Thus, the aero-engine of the present invention, through the combined action of the front and rear connecting blades 4, the front blade group, and the rear blade group, not only causes the radial airflow discharged from the diffuser radial blade group to flow axially to form an axial airflow, but also diffuses and rectifies the flowing axial airflow to ensure the uniformity and stability of the compressor outlet flow field and the airflow angle, thereby meeting the combustion chamber inlet airflow requirements. Simultaneously, by installing external ducts 5 for bleed air, bleed oil, and ventilation through the front and rear connecting blades 4, the ducts 5 do not directly intrude into the airflow channel, thereby reducing the impact of the ducts 5 on the diffuser's performance and simplifying the installation and setup of the ducts 5. Furthermore, it eliminates the need for a support plate behind the diffuser, thus not increasing the compressor's axial length, the overall engine volume, or its weight. This solves the technical difficulties of bearing lubrication and bleed air at the compressor-combustion chamber interface in existing aero-engines.

[0046] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A hybrid axial diffuser for a compressor, characterized in that, The application relates to a mixed axial diffuser of front and rear rows for a compressor. The mixed axial diffuser of front and rear rows for the compressor comprises an outer diffuser shell (2) communicated with an outlet end of the compressor (1), a diffuser radial blade group and a diffuser axial blade group arranged in the outer diffuser shell (2), the diffuser radial blade group comprises a plurality of diffuser radial blades (3) sequentially and evenly arranged along the ring direction of the outer 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) sequentially and evenly arranged along the ring direction of the outer diffuser shell (2) and extending along the axial direction of the diffuser, and a front blade group and a rear blade group arranged between two adjacent front and rear continuous blades (4); The front and rear continuous blades (4) are used for installing an external pipeline (5) for introducing air or oil; The front and rear continuous blades (4), the front blade group and the rear blade group are sequentially and evenly arranged along the axial direction of the diffuser, and the front and rear continuous blades (4), 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 the axial airflow is expanded and rectified; The front blade group comprises a plurality of front blades (6) sequentially and evenly arranged along the ring direction of the outer diffuser shell (2), the rear blade group comprises a plurality of rear blades (7) sequentially and evenly arranged along the ring direction of the outer diffuser shell (2), and the plurality of front blades (6) and the plurality of rear blades (7) are arranged one by one in the front and rear direction along the axial direction, so that the leading edge of the rear blade (7) receives the airflow of the trailing edge of the corresponding front blade (6), thereby keeping the smoothness and stability of the compressor outlet flow field, and the front blade group and the rear blade group are also arranged along the axial direction, so that there is a bladeless area between the front blade group and the rear blade group, on the one hand, the attack angle of the rear blade (7) can be designed according to the action of the front blade (6) on the airflow, so as to better adapt to the angle and pressure demand of the airflow output, thereby obtaining higher compressor efficiency; the front blade (6) and the rear blade (7) are combined with relatively small blade shapes, compared with a single large blade, a better weight reduction effect can be obtained to some extent, so as to improve the engine performance; airflow passages (201) are respectively formed between adjacent front blades (6), between adjacent rear blades (7), and between the front and rear continuous blades (4) and adjacent front blades (6) and adjacent rear blades (7).

2. The mixed axial diffuser of front and rear rows for the compressor according to claim 1, wherein the plurality of front and rear continuous blades (4) are evenly arranged along the ring direction of the outer 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.

3. The mixed axial diffuser of front and rear rows for the compressor according to claim 1, wherein 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 mixed axial diffuser of front and rear rows for the compressor according to claim 1, wherein ​ ​ The outer profile of the front row of blades (6) is different from that of the rear row of blades (7) to adapt to the angle and pressure changes of the axial airflow in the flow direction.

5. The mixed front and rear row axial diffuser of claim 1, wherein, The plurality of front row blades (6) between the two adjacent front and rear continuous blades (4) are evenly spaced along the circumferential direction of the diffuser shell (2), and the plurality of rear row blades (7) between the two adjacent front and rear continuous blades (4) are evenly spaced along the circumferential direction of the diffuser shell (2). The thickness of the front and rear continuous blade (4) along the circumferential direction is one width of the airflow passage (201).

6. The mixed front and rear row axial diffuser of claim 1, wherein, Each group of rear row blades further comprises at least one rear row intermediate blade (8) arranged between the two adjacent rear row blades (7). The rear row intermediate blade (8) is located between the two adjacent rear row blades (7), and the rear row intermediate blade (8) and the adjacent rear row blade (7) form an airflow passage (201); or The plurality of rear row intermediate blades (8) are sequentially and evenly spaced along the circumferential direction of the diffuser shell (2), and the airflow passage (201) is formed between the two adjacent rear row intermediate blades (8) and between the rear row intermediate blade (8) and the adjacent rear row blade (7).

7. The mixed front and rear row axial diffuser of claim 6, wherein, The plurality of rear row intermediate blades (8) between the two adjacent rear row blades (7) are evenly spaced along the circumferential direction of the diffuser shell (2). The outer profile of the rear row intermediate blade (8) is the same as that of the rear row blade (7).

8. The mixed front and rear row axial diffuser of claim 6, wherein, The front and 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 with the inner wall of the diffuser shell (2) on both sides, or are integrally formed with the diffuser shell (2). The mixed front and rear row axial diffuser of any one of claims 1-8.

9. An aeroengine characterised in that, ​

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