A wedge-shaped tube anti-vortex system for compressors

Abstract

This invention proposes a wedge-shaped tube vortex reduction system for compressors, relating to the field of vortex reduction technology in the compressor bleed section of the secondary air system of aero-engines. By designing a counter-rotating drum orifice, the development of free vortex structure within the disc cavity is effectively disrupted, thereby reducing pressure loss. The design of a wedge-shaped vortex-reducing straight tube effectively improves flow separation at the inlet of the vortex-reducing tube, reducing pressure loss when fluid enters the vortex-reducing tube, and also reducing the mass of the vortex-reducing tube, thus possessing significant engineering application value. The wedge-shaped tube vortex reduction system includes two symmetrically arranged compressor discs and an annular chuck and drum fixedly connected between them; the compressor discs, annular chuck, and drum are coaxial; several counter-rotating drum orifices are uniformly opened on the drum; several wedge-shaped vortex-reducing tubes extending radially along the internal cavity are uniformly fixedly connected to the annular chuck. This invention, using counter-rotating drum orifices and wedge-shaped vortex-reducing tubes, can reduce the total pressure loss coefficient by 15% to 32%.

Description

Technical Field

[0001] This invention relates to the field of vortex reduction technology in the compressor bleed section of the secondary air system of an aero-engine, and particularly to a wedge-shaped tube vortex reduction system for an aero-engine. Background Technology

[0002] With the continuous advancement of modern aviation technology, high-performance engines require higher thrust-to-weight ratios and lower bypass ratios. This necessitates high turbine inlet temperatures and high compressor pressure ratios, which can lead to insufficient material tolerance. Therefore, more advanced cooling technologies are needed to improve the quality of cooling airflow. Aero engines require secondary air systems to cool critical components and other related parts, including compressor disks, turbine disks, and blades. Secondary air systems have four main functions: First, in environments where temperatures may exceed the melting points of materials, they maintain the components within the primary hot airflow under safe operating conditions. Second, air extraction prevents backflow of high-temperature combustion gases, which can cause deformation of disks, blades, and casings, thus reducing component lifespan. Third, secondary air systems can pressurize bearing cavities to prevent oil leaks, thereby preventing odors and fire hazards. Finally, they can control bearing loads to reduce the risk of excessive stress caused by the high axial combined force generated by compressor and turbine airflow loads. Overall, these four objectives influence the design of the engine's cold and hot ends. Since the air drawn from the compressor accounts for approximately 20% of the core airflow, it affects engine thrust. Therefore, the design should prioritize improving the quality of the cooled air. Furthermore, after the airflow is radially introduced and axially exited from the blower orifice, its temperature and pressure continuously increase due to resistance as it reaches hot-end components such as the turbine. Therefore, a reasonable design is needed to reduce resistance and thus lower pressure loss. Consequently, the amount of cooled air used and pressure loss are priority considerations in the design of the compressor's secondary air system.

[0003] Currently, most aero-engines employ a method of radially introducing cooling airflow into the compressor drum between the compressor discs and then axially guiding it out to cool hot-end components. During this radial inward flow, due to the Coriolis effect of the rotating compressor discs, the airflow entering the drum orifice generates a large-scale free vortex structure, resulting in significant pressure loss. The most effective solution is to incorporate a vortex suppressor into the disc cavity. A well-designed vortex suppressor structure can suppress the development of high-speed vortices within the disc cavity, thus reducing drag.

[0004] Currently, all drum-type vortex suppressors are drilled along a circumferential tangential direction perpendicular to the surrounding screen, without reverse rotation. Furthermore, tubular vortex suppressors are the most widely used type in modern aero-engines. For example, CN103867235A discloses an air bleed system with an inlet-bent vortex suppressor tube. This system reduces localized losses at the vortex suppressor tube inlet by adding a bend to the straight tube and directing the tube inlet towards the incoming flow direction. However, this significantly exacerbates the vibration problem of the vortex suppressor tube, increases its weight and manufacturing difficulty, and has considerable limitations in practical aero-engine applications. Summary of the Invention

[0005] To address the above-mentioned problems, this invention proposes a wedge-shaped tube anti-vortex system for compressors, which overcomes or at least partially solves or mitigates these problems. By designing a counter-rotating drum orifice, the tangential velocity of the airflow entering the disk cavity is suppressed, effectively disrupting the development of free vortex structures within the disk cavity, thereby reducing pressure loss. The wedge-shaped anti-vortex straight tube design effectively improves flow separation at the inlet of the anti-vortex tube, reduces pressure loss when fluid enters the anti-vortex tube, and also reduces the mass of the anti-vortex tube, thus possessing significant engineering application value.

[0006] The technical solution of the present invention is as follows: the wedge-shaped tube vortex reduction system is uniformly arranged in the radial inward flow process of the compressor of the secondary air system of the aero-engine. The wedge-shaped tube vortex reduction system includes two compressor disks 1 arranged symmetrically and an annular chuck 4 and a drum 5 fixedly connected between the two. The drum 5 is located outside the annular chuck 4. The compressor disks 1, the annular chuck 4, and the drum 5 are coaxial and form an internal cavity between the two compressor disks 1 and the drum 5.

[0007] A plurality of anti-rotation drum holes 2 are evenly provided on the drum 5. Each anti-rotation drum hole has the same structure. The center line of the anti-rotation drum hole 2 is at an angle to the radial direction of the drum 5 to suppress the circumferential movement of the airflow.

[0008] Several wedge-shaped vortex deflectors 3 extending radially along the internal cavity are uniformly fixedly connected to the annular chuck 4. The inlet 31 of the wedge-shaped vortex deflector 3 facing the direction of the incoming airflow is oblique, and the plane on which it is located also leaves an angle with the central axis of the wedge-shaped vortex deflector 3. Each wedge-shaped vortex deflector has the same structure and the same installation height. Each wedge-shaped vortex deflector has a wedge-shaped vortex deflector inlet 31 and a wedge-shaped vortex deflector outlet 32, and the inlet and outlet have the same diameter. Each wedge-shaped vortex deflector inlet 31 faces the direction of the incoming flow to reduce the pressure loss caused by the generation of flow separation vortices at the inlet of the vortex deflector.

[0009] Under normal operating conditions, the plurality of anti-rotation drum holes and the plurality of wedge-shaped anti-vortex tubes rotate in the same direction, at the same speed, and coaxially with the two side discs of the compressor. Fluid enters the compressor cavity through the plurality of anti-rotation drum holes and is radially introduced into the axial channel of the compressor through the plurality of wedge-shaped anti-vortex tubes.

[0010] Furthermore, the centerline of the anti-rotation drum hole 2 forms an angle α with the radial direction of the drum 5, and the angle α is 20° to 80°.

[0011] Furthermore, the plane containing the wedge-shaped vortex reducer inlet 31 forms an angle β with the central axis of the wedge-shaped vortex reducer 3, wherein the angle β is 40° to 90°. When the wedge-shaped vortex reducer 3 is arranged perpendicular to the annular chuck 4, the central axis of the wedge-shaped vortex reducer 3 is arranged radially along the annular chuck 4.

[0012] Furthermore, along the radial direction of the annular chuck 4, the cross-sectional area of ​​the inner wall of the wedge-shaped vortex reducer 3 is equal at all points.

[0013] Furthermore, several of the wedge-shaped vortex reducers are located on the same circumference, which is coaxial with the annular chuck.

[0014] Furthermore, the cross-section of each counter-rotating drum bore is oblong.

[0015] Each drum hole is configured to improve the flow capacity of gas at the drum hole.

[0016] The present invention relates to a wedge-shaped tube anti-vortex system for a compressor, comprising an annular chuck, a plurality of anti-rotation drum holes, and a plurality of wedge-shaped anti-vortex tubes. Each anti-rotation drum hole is uniformly arranged circumferentially on the outer side of the compressor cavity. Each wedge-shaped anti-vortex tube is mounted on the annular chuck and uniformly arranged circumferentially, rotating coaxially with the two-stage compressor disk. Each anti-rotation drum hole and each wedge-shaped anti-vortex tube has the same structure and corresponding installation radius. Each drum hole is anti-rotated to suppress the circumferential movement of the airflow, prevent the generation of free vortex structures, and reduce flow resistance. Each wedge-shaped anti-vortex tube has a wedge-shaped inlet and a straight outlet with equal diameters at the inlet and outlet. The inlet of each wedge-shaped anti-vortex tube faces the incoming flow direction to further reduce the pressure loss caused by the generation of flow separation vortices at the inlet of the anti-vortex tube. Therefore, the wedge-shaped tube anti-vortex system of the present invention fully considers the flow field structure and aerodynamic characteristics in the disk cavity, prevents the development of free vortices in the disk cavity, suppresses the generation of flow separation vortices at the inlet of the anti-vortex tube, reduces the local loss at the inlet of the anti-vortex tube, and thus reduces the total pressure loss of the system. By using the anti-rotation drum orifice and the wedge-shaped anti-vortex straight tube, the total pressure loss coefficient can be reduced by 15% to 32%.

[0017] Furthermore, by using a counter-rotating drum-shaped orifice, the present invention suppresses the tangential development of airflow when it enters the disc cavity. The drum-shaped orifice used in the present invention has an elongated oval cross-section stretched circumferentially along the outer drum of the disc cavity, effectively improving the flow capacity of airflow into the disc cavity. Attached Figure Description

[0018] Figure 1 This is a radial sectional view of a portion of the disk cavity of the present invention;

[0019] Figure 2 This is an isometric view of part of the disk cavity of the present invention;

[0020] Figure 3 This is a cross-sectional view of the overall disk cavity of the present invention;

[0021] Figure 4 This is a perspective view of a wedge-shaped tube anti-vortex system for a compressor according to an embodiment of the present invention;

[0022] Figure 5 yes Figure 4 A schematic front view of the wedge-shaped tube vortex reduction system shown.

[0023] Figure 6 yes Figure 5 A schematic enlarged view of point A in the wedge-shaped tube vortex reduction system shown;

[0024] The meanings of the labels in the diagram are as follows:

[0025] 1 is the compressor disc, 2 is the anti-rotation drum bore, 21 is the inlet of the anti-rotation drum bore, 22 is the outlet of the anti-rotation drum bore; 3 is the wedge-shaped vortex reducer, 31 is the inlet of the wedge-shaped vortex reducer, 32 is the outlet of the wedge-shaped vortex reducer; 4 is the annular chuck, and 5 is the drum. Detailed Implementation

[0026] To clearly illustrate the technical features of this patent, the following detailed description is provided through specific embodiments and in conjunction with the accompanying drawings.

[0027] This design utilizes a counter-rotating drum-shaped orifice to suppress the tangential velocity of the airflow entering the disk cavity, effectively disrupting the development of free vortex structures within the cavity and thus reducing pressure loss. The wedge-shaped anti-vortex straight tube design effectively improves flow separation at the inlet of the anti-vortex tube, reducing pressure loss as fluid enters the tube and also lightening its mass, demonstrating significant engineering application value.

[0028] like Figures 1 to 6As shown, this embodiment provides a wedge-shaped tube vortex reduction system for a compressor, arranged in the radial bleed section of an aero-engine compressor. The compressor includes: compressor disks 1 arranged on both sides, and a drum 5 extending vertically along the outer periphery of the disk cavity, forming an internal cavity with the two-stage compressor disks and the drum. A plurality of anti-rotation drum holes 2 are evenly arranged circumferentially on the drum 5. The number of anti-rotation drum holes 2 is N, where N is a natural number greater than 1. Each anti-rotation drum hole is used to introduce air and suppress the circumferential movement of the airflow. The wedge-shaped tube vortex reduction system includes: a plurality of wedge-shaped vortex-reducing tubes 3 and an annular chuck 4. This invention sets up anti-rotation drum holes 2 and wedge-shaped vortex-reducing tubes 3 during the radial bleed process of the compressor to reduce pressure loss within the disk cavity.

[0029] Several counter-rotating drum holes are formed on the drum. The drum is located at the outer periphery of the compressor disk cavity on both sides, and the several counter-rotating drum holes are evenly distributed along the 360° circumference of the compressor disk on both sides. Each counter-rotating drum hole 2 is coaxial with the compressor disk 1 on both sides, and each counter-rotating drum hole 2 has the same structure, geometry, and installation radius. Each counter-rotating drum hole 2 penetrates the outer and inner walls of the drum. Each counter-rotating drum hole 2 has a counter-rotating drum hole inlet 21 and a counter-rotating drum hole outlet 22. Each counter-rotating drum hole 2 is used to suppress the circumferential movement of the airflow.

[0030] Several wedge-shaped anti-vortex tubes 3 are fixedly installed on the chuck 4 and located downstream of the several anti-vortex drum holes 2. They are evenly distributed circumferentially and extend radially along the 360° circumference of the chuck 4, and rotate together with the cavity. The inlet of the wedge-shaped anti-vortex tube 3 faces the incoming flow direction to reduce the pressure loss caused by flow separation at the inlet of the wedge-shaped anti-vortex tube 3. Each wedge-shaped anti-vortex tube 3 is coaxial with the compressor discs on both sides. Figure 4 As shown, each wedge-shaped vortex reducer 3 has the same structure and geometry, and all wedge-shaped vortex reducers 3 have a uniform diameter in the radial direction. The installation radius of each wedge-shaped vortex reducer 3 is the same. The number of wedge-shaped vortex reducers 3 is m, where m is a natural number greater than 1. Figure 5 and Figure 6 As shown, each wedge-shaped anti-vortex tube 3 has a wedge-shaped anti-vortex tube inlet 31 and a straight section outlet 32. Under normal operating conditions of the compressor, the plurality of counter-rotating drum holes 2 and the plurality of wedge-shaped anti-vortex tubes 3 rotate in the same direction, at the same speed, and coaxially with the two side discs of the compressor. Fluid enters the compressor cavity through the plurality of counter-rotating drum holes 2 and is radially introduced into the compressor axial passage via the plurality of wedge-shaped anti-vortex tubes 3. Compared with the current vertical drum holes and anti-vortex straight tubes of the same length, the anti-vortex system using the combination of counter-rotating drum holes 2 and wedge-shaped anti-vortex tubes 3 reduces the total pressure loss by 15% to 32%.

[0031] More specifically, such as Figure 6As shown, the structural dimensions of the anti-rotation drum bore 2 and the wedge-shaped anti-vortex tube 3 are described more clearly. Figure 5 A partial magnification has been provided. In this embodiment, the axis of the anti-rotation drum hole 2 forms an angle α with the radius of rotation of the center of the anti-rotation drum hole inlet 21, and the included angle α is 20° to 80°.

[0032] More specifically, in this embodiment, the surface of the wedge-shaped vortex inlet 31 forms an angle β with the radius of rotation of the center of the wedge-shaped vortex inlet 31, and the included angle β is 40° to 90°.

[0033] More specifically, such as Figure 3 As shown, the cross-section of each counter-rotating drum hole 3 in the tangential direction at the center point is an oblong shape.

[0034] There are many specific ways to implement this invention. The above description is only a preferred embodiment of this invention. It should be noted that for those skilled in the art, several improvements can be made without departing from the principle of this invention, and these improvements should also be considered within the scope of protection of this invention.

Claims

1. A wedge-shaped tube vortex reduction system for a compressor, the wedge-shaped tube vortex reduction system comprising two symmetrically arranged compressor discs (1) and an annular chuck (4) and a drum (5) fixedly connected between the two, the drum (5) being located outside the annular chuck (4); the compressor discs (1), the annular chuck (4), and the drum (5) are coaxial and form an internal cavity between the two compressor discs (1) and the drum (5); characterized in that, A plurality of counter-rotating drum holes (2) are evenly provided on the drum (5), and the center line of the counter-rotating drum hole (2) is at an angle to the radial direction of the drum (5). Several wedge-shaped vortex-reducing tubes (3) extending radially along the internal cavity are uniformly fixedly connected on the annular chuck (4). The wedge-shaped vortex-reducing tube inlet (31) facing the drum (5) is oblique, and the plane on which it is located also leaves an angle between it and the central axis of the wedge-shaped vortex-reducing tube (3).

2. The wedge-shaped tube vortex reduction system for a compressor according to claim 1, characterized in that, The centerline of the anti-rotation drum hole (2) forms an angle α with the radial direction of the drum (5), and the angle α is 20° to 80°.

3. A wedge-shaped tube vortex reduction system for a compressor according to claim 1, characterized in that, The plane where the inlet (31) of the wedge-shaped vortex reducer is located forms an angle β with the central axis of the wedge-shaped vortex reducer (3), and the angle β is 40° to 90°.

4. A wedge-shaped tube vortex reduction system for a compressor according to claim 1, characterized in that, Along the radial direction of the annular chuck (4), the cross-sectional area of ​​the inner wall of the wedge-shaped vortex reducer (3) is equal at all points.

5. A wedge-shaped tube vortex reduction system for a compressor according to claim 1, characterized in that, Several of the wedge-shaped vortex reducers are located on the same circumference, which is coaxial with the annular chuck.

6. A wedge-shaped tube vortex reduction system for a compressor according to claim 1, characterized in that, Each counter-rotating drum hole (2) has an elongated oval cross section.

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