A vortex reduction tube, vortex reduction device and aircraft engine

Abstract

The application provides a vortex-reducing pipe, a vortex reducer and an aero-engine, and relates to the technical field of aero-engines. The vortex-reducing pipe comprises a pipe body and a connecting part arranged at one end of the pipe body, the connecting part being used for connecting with a support ring and mounting the vortex-reducing pipe on the support ring. The vortex-reducing pipe further comprises a shoulder arranged on the pipe body, the shoulder having opposite first and second ends, the first end being provided with a first elastic sheet, and the second end being provided with a second elastic sheet, the first elastic sheet of one vortex-reducing pipe being used for abutting and matching with the second elastic sheet of an adjacent another vortex-reducing pipe. In the case that vibration occurs in a certain vortex-reducing pipe, the abutting and matching of the first and second elastic sheets can generate an elastic force to inhibit the vibration of the vortex-reducing pipe, thereby reducing the pressure loss of airflow in the vortex-reducing pipe and improving the bleed air efficiency.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more specifically, to a vortex reducer, a vortex reducer, and an aero-engine. Background Technology

[0002] An aero-engine is a highly complex and precise thermodynamic machine composed of many components. Air is compressed in the compressor, burned in the combustion chamber, and expands in the turbine to drive the turbine's rotation, providing power to the compressor. Finally, it is exhausted at high speed from the exhaust nozzle to power the aircraft. During engine operation, the temperature at locations such as the turbine inlet is relatively high. Cooling these high-temperature components can effectively improve engine performance, reliability, and lifespan.

[0003] Therefore, during aero-engine operation, some gas is drawn out from the compressor rotor to seal or cool other components. The gas in the compressor rotor typically enters the rotating disk cavity between the two stages through bleed holes on the rotor disc drum, forming strong vortices during radial inward flow. If the gas forms free vortices, the vortexes generated during radial inward flow will become increasingly intense, resulting in significant pressure loss. Adding a vortex reducer to the bleed device can effectively reduce this pressure loss. Currently, commonly used vortex reducer structures include tubular, deswirl nozzle, and finned types. Figure 1 This shows the current structure of the tubular vortex reducer 1 when it is installed on the compressor. Figure 1 The middle arrow indicates the direction of gas flow. The tubular vortex suppressor 1 is a series of radial vortex suppressor tubes 3 installed in the compressor bleed chamber 2. The vortex suppressor tubes 3 guide and promote the radial flow of airflow, destroy the formation of free vortices, thereby reducing pressure loss and airflow pressure drop, and making it easier for gas to flow from the bleed port 4 on the compressor drum to the disk center.

[0004] However, the inventors discovered that current tubular vortex reducers suffer from pressure loss and low induced draft efficiency. Summary of the Invention

[0005] The purpose of this invention is to provide a vortex-reducing tube that can improve the problem of pressure loss and low air extraction efficiency caused during the air extraction process.

[0006] Another objective of this invention is to provide a vortex reducer that can improve the problem of pressure loss and low bleed efficiency caused during the bleed process.

[0007] Another objective of this invention is to provide an aircraft engine that improves the problem of pressure loss and low bleed air efficiency caused during the bleed air process.

[0008] Embodiments of the present invention can be implemented in the following ways:

[0009] A vortex-reducing tube includes a tube body and a connecting portion disposed at one end of the tube body, the connecting portion being used to cooperate with a support ring to mount the vortex-reducing tube onto the support ring; the vortex-reducing tube further includes:

[0010] A shoulder is provided on the tube body, the shoulder having a first end and a second end opposite to each other, the first end being provided with a first spring piece, and the second end being provided with a second spring piece; the first spring piece of one of the anti-vortex tubes is used to abut against and cooperate with the second spring piece of the adjacent anti-vortex tube.

[0011] Optionally, the first spring has a convex arc portion for engaging with the second spring of another said vortex reducer; the second spring has a concave arc portion for engaging with the first spring of another said vortex reducer.

[0012] Optionally, the first spring sheet has a first planar portion and a second planar portion disposed on both sides of the circumferential arc portion;

[0013] The second spring has a third planar portion and a fourth planar portion disposed on both sides of the concave arc portion in the circumferential direction;

[0014] The first planar portion is used to engage with the third planar portion of another vortex reducer; the second planar portion is used to engage with the fourth planar portion of another vortex reducer.

[0015] Optionally, the first spring has a first connecting end and a first abutting end, and the second spring has a second connecting end and abutting end. Both the first connecting end and the second connecting end are fixedly connected to the shoulder, and the first abutting end is used to abut against the second abutting end of the other de-vortex tube.

[0016] The first connecting end is closer to the connecting portion than the first abutting end; the second connecting end is closer to the connecting portion than the second abutting end.

[0017] Optionally, the first spring piece extends in an arc shape from the first connecting end to the first abutting end, the center of curvature of the arc is closer to the tube body than the first spring piece, and the first abutting end is farther away from the tube body than the first connecting end;

[0018] The second spring sheet extends in an arc shape from the second connecting end to the second abutting end. The center of curvature of the arc is closer to the tube body than the second spring sheet, and the second abutting end is farther away from the tube body than the second connecting end.

[0019] Optionally, the first spring is disposed along the end contour of the first end; the second spring is disposed along the end contour of the second end.

[0020] Optionally, the connecting portion includes a first protrusion and a second protrusion located on both sides of the tube body along the radial direction of the tube body, wherein the direction from the first protrusion to the second protrusion is a first direction;

[0021] The direction from the first end to the second end is the second direction, and the first direction is perpendicular to the second direction.

[0022] A vortex suppressor includes a support ring and a plurality of the aforementioned vortex suppressor tubes. The support ring has a plurality of mounting holes distributed circumferentially, and the plurality of vortex suppressor tubes are installed in the mounting holes one-to-one. The shoulders of the plurality of vortex suppressor tubes are spliced ​​together to form a ring structure. Along the circumference of the ring structure, the first spring piece of one vortex suppressor tube abuts against the second spring piece of the previous vortex suppressor tube, and the second spring piece of one vortex suppressor tube abuts against the first spring piece of the next vortex suppressor tube.

[0023] Optionally, there is a gap between two adjacent shoulders.

[0024] Optionally, the mounting hole includes an interconnected circular hole and a through portion. The circular hole is used to mate with the tube body of the anti-vortex tube, and the shape of the through portion is adapted to the connecting portion so that the connecting portion is installed from the outer periphery of the support ring to the inner periphery of the support ring.

[0025] The support ring also has a receiving groove disposed on its inner circumference. The receiving groove communicates with the circular hole and is offset from the through portion along the circumference of the circular hole. The receiving groove is used to receive the connecting portion.

[0026] Optionally, the vortex reducer further includes a retaining ring fixedly connected to the support ring, the retaining ring being used to confine the connecting portion in the receiving groove and restrict the movement of the vortex reducer tube along the radial direction of the support ring.

[0027] An aero-engine includes a compressor body and the aforementioned vortex suppressor; the vortex suppressor is mounted on the compressor body, and the vortex suppressor tube is located between two adjacent stage disks of the compressor body.

[0028] The beneficial effects of the vortex suppressor, vortex reducer, and aero-engine provided by the embodiments of the present invention include:

[0029] The vortex suppressor provided in the embodiments of the present invention includes a tube body and a connecting portion disposed at one end of the tube body. The connecting portion is used to connect with a support ring, thereby mounting the vortex suppressor onto the support ring. The vortex suppressor also includes a shoulder disposed on the tube body. The shoulder has a first end and a second end opposite to each other. A first spring plate is disposed at the first end, and a second spring plate is disposed at the second end. The first spring plate of one vortex suppressor is used to abut against the second spring plate of an adjacent vortex suppressor. When a vortex suppressor vibrates, the abutment between the first and second spring plates generates an elastic force to suppress the vibration of the vortex suppressor, thereby reducing the pressure loss of the airflow in the vortex suppressor and improving the air intake efficiency.

[0030] Embodiments of the present invention also provide a vortex reducer, which includes the aforementioned vortex reducer tube, and thus also has the beneficial effect of reducing the pressure loss of the airflow in the vortex reducer tube and improving the air intake efficiency.

[0031] Embodiments of the present invention also provide an aero engine that includes the aforementioned vortex reducer, and thus also has the advantages of improving bleed air efficiency and improving the cooling effect on high-temperature components. Attached Figure Description

[0032] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0033] Figure 1 A schematic diagram of the installation structure of a tubular vortex reducer and compressor in the prior art is shown;

[0034] Figure 2 A schematic diagram of a vortex suppressor installed on a compressor body according to one aspect of the present invention is shown;

[0035] Figure 3 A schematic diagram of the overall structure of a vortex reducer according to one aspect of the present invention is shown;

[0036] Figure 4 A schematic diagram of the anti-vortex tube according to one aspect of the present invention is shown from a first perspective.

[0037] Figure 5 A schematic diagram of the anti-vortex tube according to one aspect of the present invention is shown from a second perspective.

[0038] Figure 6 A cross-sectional schematic diagram of the abutting structure of the first and second spring plates of two adjacent anti-vortex tubes provided according to one aspect of the present invention is shown.

[0039] Figure 7A schematic diagram of the support ring in a vortex reducer provided according to one aspect of the present invention is shown.

[0040] Figure label:

[0041] 1-Tube-type vortex reducer; 2-Air bleed chamber; 3-Vortex reducer tube; 4-Air bleed port;

[0042] 10-Vortex suppressor; 100-Vortex suppressor tube; 110-Tube body; 120-Shoulder; 121-First end; 122-Second end; 130-First spring piece; 131-First connecting end; 132-First contact end; 133-Convex arc portion; 134-First flat portion; 135-Second flat portion; 140-Second spring piece; 141-Second connecting end; 142-Second contact end; 143-Concave arc portion; 144-Third flat portion; 145-Fourth flat portion; 15 0-Connecting part; 151-First protrusion; 152-Second protrusion; 161-First anti-vortex tube; 162-Second anti-vortex tube; 163-Third anti-vortex tube; 200-Support ring; 210-Mounting hole; 211-Circular hole; 212-Through part; 213-Accommodation groove; 300-Snap ring; 311-First support ring; 312-Second support ring; 20-Compressor body; 21-First stage disc; 22-Second stage disc; 23-Air duct; 24-Locking nut. Detailed Implementation

[0043] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0044] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0045] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.

[0046] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0047] Currently, tubular vortex reducers and their installation structure in the compressor are as follows: Figure 1 As shown, the inventors discovered that one end of the vortex suppressor 3 in this structure is generally suspended, and the compressor rotor rotates at a high speed. The vortex suppressor inevitably vibrates as it rotates with the rotor. Therefore, if this vibration cannot be effectively suppressed, it may damage itself, reducing reliability. Furthermore, the vibration of the vortex suppressor 3 leads to energy loss in the airflow, causing pressure loss and consequently low bleed air efficiency. To improve these problems, this invention provides a vortex suppressor, a vortex suppressor, and an aero-engine.

[0048] Figure 2 This diagram shows a structural schematic of the vortex suppressor 10 provided in this embodiment mounted on the compressor body 20. Figure 3 This diagram shows the overall structure of the vortex reducer 10 provided in this embodiment. Figure 4 This shows a schematic diagram of the structure of the anti-vortex tube 100 provided in this embodiment from a first-view perspective. Figure 5 The diagram shows a structural schematic of the anti-vortex tube 100 provided in this embodiment from a second perspective. Please refer to the reference. Figures 2-5 This embodiment provides a vortex reducer 100, and correspondingly, also provides a vortex reducer 10 and an aero-engine (not shown in the figure).

[0049] The aero-engine includes a vortex suppressor 10 and a compressor body 20. The vortex suppressor 10 is mounted on the compressor body 20, and the vortex suppressor tubes 100 of the vortex suppressor 10 are located between two adjacent stage disks of the compressor body 20. Specifically, as... Figure 2 As shown, the compressor body 20 has multiple stage disks, with adjacent stage disks being a first stage disk 21 and a second stage disk 22, forming a rotating disk cavity between the first stage disk 21 and the second stage disk 22. The compressor body 20 is provided with an air vent 23 communicating with the rotating disk cavity, through which cooling gas is introduced into the rotating disk cavity. The vortex suppressor 10 has a vortex suppressor tube 100 positioned between the first stage disk 21 and the second stage disk 22, extending into the rotating disk cavity.

[0050] The vortex suppressor 10 includes a support ring 200 and multiple vortex suppressor tubes 100, such as Figure 3As shown, the support ring 200 has a hollow circular structure with an axial direction L, a circumferential direction R, and a radial direction. The radial direction is the direction extending outward from the axis of the support ring 200. In this embodiment, the axial direction of the vortex reducer 100 is the radial extension along the support ring 200. Multiple mounting holes 210 are distributed along the circumferential direction R of the support ring 200, and multiple vortex reducers 100 are installed in the mounting holes 210 one-to-one. The vortex reducers 100 guide the gas in the compressor's main flow channel from the bleed port 23 to the cavity of the support ring 200. The gas drawn out from the cavity inside the support ring 200 can be used for cooling, sealing, etc. Specifically, the support ring 200 is coaxially arranged with the compressor rotor, i.e. Figure 2 Only a portion of the first-stage disk 21, the second-stage disk 22, and the vortex reducer 10 are shown.

[0051] Furthermore, one end of the support ring 200 is provided with a thread for engaging with the locking nut 24, and the support ring 200 is fixed to the first-stage disc 21 by the locking nut 24. Furthermore, an annular stop is also provided on the support ring 200 adjacent to the thread, which engages with the first-stage disc 21, and together with the locking nut 24, enables the support ring 200 to be installed on the first-stage disc 21.

[0052] The anti-vortex tube 100 includes a tube body 110 and a connecting portion 150 disposed at one end of the tube body 110. The connecting portion 150 is used to connect with a support ring 200, thereby mounting the anti-vortex tube 100 onto the support ring 200. The anti-vortex tube 100 also includes a shoulder 120 disposed on the tube body 110. The shoulder 120 has a first end 121 and a second end 122 opposite to each other. The first end 121 is provided with a first spring plate 130, and the second end 122 is provided with a second spring plate 140. The first spring plate of one anti-vortex tube 100 is used to abut against the second spring plate 140 of the adjacent anti-vortex tube 100. When a certain anti-vortex tube 100 vibrates, the elastic contact between the first spring plate 130 and the second spring plate 140 can generate an elastic force to suppress the vibration of the anti-vortex tube 100, thereby reducing the pressure loss of the airflow in the anti-vortex tube 100 and improving the air intake efficiency.

[0053] Please refer to the reference. Figures 3-5After multiple vortex reducers 100 are installed circumferentially along the support ring 200, the shoulders 120 of the multiple vortex reducers 100 are spliced ​​into a ring structure. The circumferential direction of this ring structure can also be regarded as the circumferential direction of the support ring 200. The first spring piece 130 of one vortex reducer 100 abuts against the second spring piece 140 of the previous vortex reducer 100, and the second spring piece 140 of one vortex reducer 100 abuts against the first spring piece 130 of the next vortex reducer 100. Specifically, the fitting structure is explained with three adjacent vortex reducers 100 as an example. The three vortex reducers 100 are, in order, the first vortex reducer 161, the second vortex reducer 162, and the third vortex reducer 163. The first spring piece 130 of the second vortex reducer 162 abuts against the second spring piece 140 of the first vortex reducer 161, and at the same time, the second spring piece 140 of the second vortex reducer 162 abuts against the first spring piece 130 of the third vortex reducer 163.

[0054] Specifically, the shoulder 120 is fixedly connected to the tube body 110. It can be an integrally formed structure or a structure connected by welding or other means.

[0055] In this embodiment, the first spring plate 130 has a convex arc portion 133 for engaging with the second spring plate 140 of another vortex reducer 100, and the second spring plate 140 has a concave arc portion 143 for engaging with the first spring plate 130 of another vortex reducer 100. That is, the first spring plate 130 and the second spring plate 140 are engaged by an arc-shaped concave-convex structure. By setting the mating surfaces of the first spring plate 130 and the second spring plate 140 to be arc-shaped, elastic forces in multiple directions can be generated according to the vibration direction compared to planar contact. This can produce a good suppression effect on the vibrations in multiple directions generated by the vortex reducer 100, which helps to further improve the air intake efficiency.

[0056] Specifically, the shoulder 120 has a generally rectangular outline, with both length and width directions. The first end 121 and the second end 122 of the shoulder 120 are the two ends along the length direction of the shoulder 120. At the same time, the first end 121 and the second end 122 are located on both sides of the radial direction of the tube body 110.

[0057] Furthermore, the first spring piece 130 has a first flat portion 134 and a second flat portion 135 disposed on both sides of the convex arc portion 133. Correspondingly, the second spring piece 140 has a third flat portion 144 and a fourth flat portion 145 disposed on both sides of the concave arc portion 143. The first flat portion 134 is used to engage with the third flat portion 144 of another anti-vortex tube 100. The second flat portion 135 is used to engage with the fourth flat portion 145 of another anti-vortex tube 100.

[0058] Furthermore, the first planar portion 134 and the second planar portion 135 are respectively connected to the convex arc portion 133 via circular arcs; the third planar portion 144 and the fourth planar portion 145 are respectively connected to the concave arc portion 143 via circular arcs. Furthermore, the first planar portion 134, the second planar portion 135, the third planar portion 144, and the fourth planar portion 145 are respectively disposed perpendicular to the plane containing the shoulder 120 and extend along the width direction of the shoulder 120. By providing the first planar portion 134, the second planar portion 135, the third planar portion 144, and the fourth planar portion 145, the vibration reduction effect in the circumferential direction between two adjacent anti-vortex tubes 100 can be improved.

[0059] In this embodiment, the first spring piece 130 has a first connecting end 131 and a first abutting end 132, and the second spring piece 140 has a second connecting end 141 and abutting end 142. Both the first connecting end 131 and the second connecting end 141 are fixedly connected to the shoulder 120. Specifically, the first connecting end 131 is fixedly connected to the first end 121, and the second connecting end 141 is fixedly connected to the second end 122. The first abutting end 132 is used to engage with the second abutting end 142 of another vortex reducer 100, and correspondingly, the second abutting end 142 is used to engage with the first abutting end 132 of another vortex reducer 100.

[0060] Figure 6 This diagram shows a cross-sectional view of the first spring plate 130 and the second spring plate 140 of two adjacent anti-vortex tubes 100 engaging in contact. Please refer to the diagram. Figures 2-6 Furthermore, the first spring piece 130 extends in an arc shape from the first connecting end 131 to the first abutting end 132. The center of curvature of this arc (not shown in the figure) is closer to the tube body 110 than the first spring piece 130, and the first abutting end 132 is farther away from the tube body 110 than the first connecting end 131. The second spring piece 140 extends in an arc shape from the second connecting end 141 to the second abutting end 142. The center of curvature of this arc (not shown in the figure) is closer to the tube body 110 than the second spring piece 140, and the second abutting end 142 is farther away from the tube body 110 than the second connecting end 141. In this way, the first contact piece 130 and the second contact piece 140 only have their first contact end 132 and second contact end 142 in contact with each other, while the first connecting end 131 and the second connecting end 141 are spaced apart and do not contact each other. This increases the amount of elastic deformation when the first contact piece 130 and the second contact piece 140 come into contact, making the contact between the first contact piece 130 and the second contact piece 140 tighter. This helps to ensure that elastic force can be generated for vibrations in all directions, so as to better suppress vibrations.

[0061] In other words, in this embodiment, the first planar portion 134 only has its end end in contact with the end end of the third planar portion 144; the second planar portion 135 only has its end end in contact with the end end of the fourth planar portion 145; and the convex arc portion 133 only has its end end in contact with the end end of the concave arc portion 143.

[0062] In this embodiment, the first spring piece 130 is disposed along the end contour of the first end 121, and correspondingly, the end contour of the first end 121 of the shoulder 120 also has a convex arc shape. The second spring piece 140 is disposed along the end contour of the second end 122, and correspondingly, the end contour of the second end 122 of the shoulder 120 has a concave arc shape. Specifically, the end contour of the first end 121 is consistent with the shape of the first connecting end 131 of the first spring piece 130, and the end contour of the second end 122 is consistent with the shape of the second connecting end 141 of the second spring piece 140. At the same time, since the first connecting end 131 and the second connecting end 141 are spaced apart, correspondingly, in the vortex reducer 10, there is also a gap between two adjacent shoulders 120, that is, two adjacent shoulders 120 do not contact each other (e.g. Figure 6 (As shown).

[0063] Figure 7 This diagram illustrates the structure of the support ring 200 in the vortex reducer 10 provided in this embodiment. Please refer to the attached diagram. Figures 2-7 In this embodiment, the mounting hole 210 includes a circular hole portion 211 and a through portion 212 that are interconnected. The circular hole portion 211 is used to mate with the tube body 110 of the vortex reducer 100, that is, the shape and size of the circular hole portion 211 are approximately the same as the outer dimensions of the tube body 110. The shape of the through portion 212 is adapted to the connecting portion 150 so that the connecting portion 150 is installed from the outer periphery of the support ring 200 to the inner periphery of the support ring 200.

[0064] Specifically, the connecting portion 150 includes a first protrusion 151 and a second protrusion 152 located on both sides of the tube body 110 along the radial direction of the tube body 110. The first protrusion 151 and the second protrusion 152 can be regarded as parts of a rectangular structure. Correspondingly, the through portion 212 can be regarded as a rectangular hole overlapping with the round hole portion 211.

[0065] Furthermore, the support ring 200 also has a receiving groove 213 disposed on its inner circumference. The receiving groove 213 communicates with the circular hole 211, and along the axial direction of the circular hole 211, the receiving groove 213 and the through hole 212 are offset from each other. The receiving groove 213 is used to accommodate the mounting part. When installing the anti-vortex tube 100, the anti-vortex tube 100 can be inserted into the mounting hole 210 from the radially outer side to the radially inner side of the support ring 200. After the connecting part 150 passes through the through hole 212 and is located on the inner circumference of the support ring 200, the anti-vortex tube 100 is rotated at a certain angle so that the connecting part 150 is directly opposite the receiving groove 213. Then, the anti-vortex tube 100 is moved a certain distance in the radially outward direction of the support ring 200 segment so that the connecting part 150 enters the receiving groove 213 and abuts against the bottom of the receiving groove 213. Specifically, in this embodiment, the receiving groove 213 is rectangular. Optionally, the included angle between the receiving groove 213 and the through portion 212 is 90°. That is, after the connecting portion 150 is located on the inner circumference of the support ring 200, the anti-vortex tube 100 needs to be rotated 90° so that the connecting portion 150 and the receiving groove 213 are directly opposite each other. It is understood that in other embodiments, the relative position between the receiving groove 213 and the through portion 212 can also be specifically set.

[0066] Furthermore, the vortex reducer 10 also includes a retaining ring 300 fixedly connected to the support ring 200. The retaining ring 300 is used to confine the connecting portion 150 in the receiving groove 213 and restrict the radial movement of the vortex reducer tube 100 along the support ring 200, thereby preventing the vortex reducer tube 100 from detaching from the support ring 200. Specifically, the retaining ring 300 has an L-shaped cross-section, and the L-shaped retaining ring 300 includes a first support ring 311 and a second support ring 312 connected to each other. The first support ring 311 is supported at the bottom of the connecting portion 150, so that the connecting portion 150 is fixed radially between the retaining ring 300 and the support ring 200. The second support ring 312 is located on one side of the connecting portion 150 along the radial direction of the tube body 110 and is fixed between the support ring 200 and the connecting portion 150, thereby preventing the vortex reducer tube 100 from moving axially along the support ring 200.

[0067] In this embodiment, the direction from the first protrusion 151 to the second protrusion 152 is the first direction, and the direction from the first end 121 to the second end 122 of the shoulder 120 is the second direction. The first direction is perpendicular to the second direction, that is, after the vortex reducer 100 is installed on the support ring 200, the first direction is parallel to the axial direction of the support ring 200, and the second direction is parallel to the tangential direction of the support ring 200.

[0068] The vortex suppressor 100, vortex reducer 10, and aero-engine provided in the embodiments of the present invention have a shoulder 120 provided near the top of the tank of the vortex suppressor 100, and a first spring plate 130 and a second spring plate 140 provided at both ends of the shoulder 120. Through the elastic contact of the first spring plate 130 and the second spring plate 140, an elastic force is generated to suppress the vibration when the vortex suppressor 100 vibrates. Moreover, since the first spring plate 130 has a convex arc portion 133 and the second spring plate 140 has a concave arc portion 143, the contact between the convex arc portion 133 and the concave arc portion 143 enables the generation of elastic force in the corresponding direction according to multiple vibration directions, which further helps to suppress vibration, thereby reducing pressure loss, improving air intake efficiency, and enhancing the cooling effect on high-temperature components in the aero-engine. Furthermore, when the anti-vortex tube 100 is installed to the support ring 200, it can be inserted from the radial outer side to the inner side of the support ring 200. Compared with the current method of inserting it from the axis of the support ring 200 outward, the installation is more convenient. Moreover, the installation method of the anti-vortex tube 100 provided in this embodiment facilitates better contact and engagement between the first spring piece 130 and the second spring piece 140.

[0069] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A vortex reducer comprising a body and a connection portion provided at one end of the body, the connection portion being configured to cooperate with a support ring to mount the vortex reducer on the support ring; characterized in that, The vortex-reducing pipe further comprises: a shoulder arranged on the pipe body, the shoulder having opposite first and second ends, the first end being provided with a first elastic sheet, and the second end being provided with a second elastic sheet; a plurality of the shoulders of the vortex-reducing pipes are used to be spliced into a ring structure, along the circumference of the ring structure, the first elastic sheet of one vortex-reducing pipe is in abutting engagement with the second elastic sheet of the previous vortex-reducing pipe, and the second elastic sheet of one vortex-reducing pipe is in abutting engagement with the first elastic sheet of the next vortex-reducing pipe; the first elastic sheet has a first connecting end and a first abutting end, and the second elastic sheet has a second connecting end and a second abutting end, the first and second connecting ends are fixedly connected with the shoulder, and the first abutting end is used to be in abutting engagement with the second abutting end of another vortex-reducing pipe; the first connecting end is closer to the connecting portion than the first abutting end, and the second connecting end is closer to the connecting portion than the second abutting end.

2. The vortex-reducing pipe according to claim 1, characterized in that: the first elastic sheet has a convex arc portion used to be in abutting engagement with the second elastic sheet of another vortex-reducing pipe, and the second elastic sheet has a concave arc portion used to be in abutting engagement with the first elastic sheet of another vortex-reducing pipe.

3. The vortex-reducing pipe according to claim 2, characterized in that: the first elastic sheet has first and second planar portions arranged on both sides of the circumferential direction of the convex arc portion; the second elastic sheet has third and fourth planar portions arranged on both sides of the circumferential direction of the concave arc portion; the first planar portion is used to be in abutting engagement with the third planar portion of another vortex-reducing pipe, and the second planar portion is used to be in abutting engagement with the fourth planar portion of another vortex-reducing pipe.

4. The vortex-reducing pipe according to claim 1, characterized in that: the first elastic sheet has an arc shape from the first connecting end to the first abutting end, the curvature center of the arc shape is closer to the pipe body than the first elastic sheet, and the first abutting end is farther away from the pipe body than the first connecting end; the second elastic sheet has an arc shape from the second connecting end to the second abutting end, the curvature center of the arc shape is closer to the pipe body than the second elastic sheet, and the second abutting end is farther away from the pipe body than the second connecting end.

5. The vortex-reducing pipe according to claim 1, characterized in that: the first elastic sheet is arranged along the end profile of the first end, and the second elastic sheet is arranged along the end profile of the second end.

6. The vortex-reducing pipe according to claim 1, characterized in that: the connecting portion comprises first and second protruding portions located on both sides of the pipe body along the radial direction of the pipe body, and the direction from the first protruding portion to the second protruding portion is a first direction; the direction from the first end to the second end is a second direction, and the first direction is perpendicular to the second direction.

7. A vortex reducer, characterized in that: the vortex reducer comprises a support ring and a plurality of vortex-reducing pipes according to any one of claims 1-6; the support ring has a plurality of mounting holes distributed along the circumferential direction, and the plurality of vortex-reducing pipes are installed in the mounting holes one by one.

8. The vortex reducer according to claim 7, characterized in that: A gap is provided between two adjacent shoulders.

9. The vortex reducer of claim 7, wherein: The mounting hole comprises a circular hole portion for cooperating with the pipe body of the vortex reducer pipe, and a through portion which is shaped to fit the connecting portion, so that the connecting portion is mounted from the outer periphery of the support ring to the inner periphery of the support ring; The support ring further has a receiving groove provided at the inner periphery, the receiving groove being in communication with the circular hole portion and extending along the circumferential direction of the circular hole portion, and the receiving groove being distributed in a staggered manner with the through portion, the receiving groove being used for receiving the connecting portion.

10. The vortex reducer of claim 9, wherein: The vortex reducer further comprises a clamping ring fixedly connected with the support ring, the clamping ring being used for limiting the connecting portion in the receiving groove and limiting the movement of the vortex reducer pipe along the radial direction of the support ring.

11. An aero-engine, wherein: The aero-engine comprises a compressor body and the vortex reducer according to any one of claims 7-10; the vortex reducer is mounted on the compressor body, and the vortex reducer pipe of the vortex reducer is located between two adjacent stage discs of the compressor body.

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