Vortex reduction tube, vortex reduction device and aero-engine

Abstract

The invention provides a vortex reduction pipe, a vortex reduction device and an aero-engine, and relates to the technical field of aero-engines. The vortex reduction tube comprises a tube body and a connecting part arranged at one end of the tube body, and the connecting part is used for being connected with the supporting ring and installing the vortex reduction tube on the supporting ring. The vortex reduction tube further comprises a protruding shoulder arranged on the tube body, the protruding shoulder is provided with a first end and a second end which are opposite, the first end is provided with a first elastic piece, the second end is provided with a second elastic piece, and the first elastic piece of one vortex reduction tube is used for being matched with the second elastic piece of the other adjacent vortex reduction tube in an abutting mode. Under the condition that a certain vortex reduction tube vibrates, elastic force can be generated through abutting of the first elastic piece and the second elastic piece so as to restrain vibration of the vortex reduction tube, and therefore pressure loss of airflow in the vortex reduction tube is reduced, and the air entraining efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular to a vortex reducing tube, a vortex reducer and an aeroengine. Background Art

[0002] Aircraft engines are highly complex and sophisticated thermal machines composed of many parts. Air is compressed in the compressor, burned in the combustion chamber, expanded in the turbine, and then drives the turbine to rotate, providing power for the compressor. Finally, it is discharged from the tail nozzle at high speed to provide power for the aircraft. During the operation of the engine, the temperature of the turbine inlet and other locations is relatively high. Cooling high-temperature components can effectively improve engine performance, reliability and life.

[0003] Therefore, when the aircraft engine is working, part of the gas in the compressor rotor is led out to seal or cool other components. The gas in the compressor rotor generally enters the rotating disk cavity between the two-stage disks from the air intake holes on the rotor disk drum, and a strong vortex will be formed during the radial inflow. If the gas forms a free vortex, the swirl formed during the radial inflow will become more and more intense, resulting in a very large pressure loss. Adding a vortex reducer to the air intake device can effectively reduce the gas pressure loss. The commonly used vortex reducer structures are mainly tube type, deswirl nozzle type, fin type, etc. Figure 1 The structure of the current tubular vortex reducer 1 when installed on the compressor is shown. Figure 1 The arrow in the middle shows the direction of gas flow. The tubular vortex reducer 1 is a series of radial vortex reducing tubes 3 installed in the compressor bleed air chamber 2, which guide and promote the radial flow of the airflow through the vortex reducing tubes 3, destroy the formation of free vortices, thereby reducing pressure loss and airflow pressure drop, making it easier for the gas to flow from the bleed air holes 4 on the compressor drum to the disc center.

[0004] However, the inventors have found that the current tubular vortex reducer will have problems of pressure loss and low air induction efficiency. Summary of the invention

[0005] The object of the present invention is to provide a vortex reducing tube, which can improve the problem of pressure loss caused during air induction and resulting in low air induction efficiency.

[0006] Another object of the present invention is to provide a vortex reducer which can improve the problem of pressure loss caused during the air induction process and resulting in low air induction efficiency.

[0007] Another object of the present invention is to provide an aircraft engine that improves the problem of pressure loss caused during the air bleed process, which leads to low air bleed efficiency.

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

[0009] A vortex reducing tube comprises a tube body and a connecting portion arranged at one end of the tube body, wherein the connecting portion is used to cooperate with a support ring so as to install the vortex reducing tube on the support ring; the vortex reducing tube further comprises:

[0010] A boss is arranged on the tube body, and the boss has a first end and a second end opposite to each other, the first end is provided with a first elastic sheet, and the second end is provided with a second elastic sheet; the first elastic sheet of one vortex reducing tube is used to abut and cooperate with the second elastic sheet of another adjacent vortex reducing tube.

[0011] Optionally, the first spring sheet has a convex arc portion for abutting and cooperating with the second spring sheet of another vortex reducing tube; the second spring sheet has a concave arc portion for abutting and cooperating with the first spring sheet of another vortex reducing tube.

[0012] Optionally, the first elastic piece has a first plane portion and a second plane portion arranged on both sides of the convex arc portion in the circumferential direction;

[0013] The second elastic piece has a third plane portion and a fourth plane portion arranged on both sides of the concave arc portion in the circumferential direction;

[0014] The first plane portion is used for abutting and cooperating with the third plane portion of another vortex reducing tube; and the second plane portion is used for abutting and cooperating with the fourth plane portion of another vortex reducing tube.

[0015] Optionally, the first elastic sheet has a first connecting end and a first abutting end, the second elastic sheet has a second connecting end and a second abutting end, the first connecting end and the second connecting end are both fixedly connected to the boss, and the first abutting end is used to abut and cooperate with the second abutting end of the other vortex reducing tube;

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

[0017] Optionally, the first elastic sheet extends in an arc-shaped direction 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 elastic sheet, and the first abutting end is farther from the tube body than the first connecting end;

[0018] The extension direction of the second elastic sheet from the second connecting end to the second abutting end is arc-shaped, the curvature center of the arc is closer to the tube body than the second elastic sheet, and the second abutting end is farther from the tube body than the second connecting end.

[0019] Optionally, the first elastic sheet is arranged along the end contour of the first end; and the second elastic sheet is arranged 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, and the direction from the first protrusion to the second protrusion is a first direction;

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

[0022] A vortex reducer comprises a support ring and a plurality of the above-mentioned vortex reducer tubes; the support ring is provided with a plurality of mounting holes distributed in the circumference thereof, the plurality of the vortex reducer tubes are mounted in the mounting holes in a one-to-one correspondence, and the bosses of the plurality of the vortex reducer tubes are spliced ​​to form an annular structure, and along the circumference of the annular structure, the first spring sheet of one of the vortex reducer tubes abuts against the second spring sheet of the previous vortex reducer tube, and the second spring sheet of one of the vortex reducer tubes abuts against the first spring sheet of the next vortex reducer tube.

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

[0024] Optionally, the mounting hole comprises a circular hole portion and a through portion which are interconnected, the circular hole portion is used to cooperate with the tube body of the vortex reducing 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 arranged on the inner circumference, the receiving groove is communicated with the circular hole portion, and along the circumference of the circular hole portion, the receiving groove and the penetration portion are staggered and distributed, and the receiving groove is used to receive the connecting portion.

[0026] Optionally, the vortex reducer further comprises a clamping ring fixedly connected to the support ring, wherein the clamping ring is used to limit the connection portion in the receiving groove and limit the radial movement of the vortex reducer along the support ring.

[0027] An aircraft engine comprises a compressor body and the above-mentioned vortex reducer; the vortex reducer is installed on the compressor body, and the vortex reducer pipe of the vortex reducer is located between two adjacent stage disks of the compressor body.

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

[0029] The vortex reducer provided by an embodiment of the present invention includes a tube body and a connecting portion arranged at one end of the tube body, the connecting portion is used to connect with a support ring, and the vortex reducer is installed on the support ring. The vortex reducer also includes a boss arranged on the tube body, the boss has a first end and a second end opposite to each other, the first end is provided with a first spring sheet, the second end is provided with a second spring sheet, and the first spring sheet of one vortex reducer is used to cooperate with the second spring sheet of another adjacent vortex reducer. In the event that a certain vortex reducer vibrates, the friction between the first spring sheet and the second spring sheet can generate an elastic force to suppress the vibration of the vortex reducer, thereby reducing the pressure loss of the airflow in the vortex reducer and improving the air induction efficiency.

[0030] An embodiment of the present invention further provides a vortex reducer, which includes the above-mentioned vortex reducing tube, and thus also has the beneficial effect of reducing the pressure loss of the airflow in the vortex reducing tube and improving the air induction efficiency.

[0031] An embodiment of the present invention further provides an aircraft engine, which includes the above-mentioned vortex reducer, and thus also has the advantages of being able to improve the bleed air efficiency and improve the cooling effect on high-temperature components. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties 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 a compressor in the prior art is shown;

[0034] Figure 2 A schematic diagram showing a structure in which a vortex reducer provided according to one aspect of the present invention is installed on a compressor body;

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

[0036] Figure 4 A schematic structural diagram of a vortex reducing tube provided according to one aspect of the present invention at a first viewing angle is shown;

[0037] Figure 5 A schematic structural diagram of a vortex reducing tube provided according to one aspect of the present invention at a second viewing angle is shown;

[0038] Figure 6 A schematic cross-sectional structure diagram of the first elastic sheet and the second elastic sheet of two adjacent vortex reducing tubes according to one aspect of the present invention is shown;

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

[0040] Reference numerals:

[0041] 1- Tubular vortex reducer; 2- Air induction chamber; 3- Vortex reduction tube; 4- Air induction hole;

[0042] 10-vortex reducer; 100-vortex reducer; 110-tube body; 120-convex shoulder; 121-first end; 122-second end; 130-first spring piece; 131-first connecting end; 132-first abutting end; 133-convex arc portion; 134-first plane portion; 135-second plane portion; 140-second spring piece; 141-second connecting end; 142-second abutting end; 143-concave arc portion; 144-third plane portion; 145-fourth plane portion; 15 0-connecting part; 151-first protruding part; 152-second protruding part; 161-first vortex reducing tube; 162-second vortex reducing tube; 163-third vortex reducing tube; 200-supporting ring; 210-mounting hole; 211-circular hole; 212-through part; 213-accommodating groove; 300-clamping ring; 311-first branch ring; 312-second branch ring; 20-compressor body; 21-first stage disk; 22-second stage disk; 23-air inlet hole; 24-locking nut. DETAILED DESCRIPTION

[0043] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0044] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

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

[0046] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0047] At present, the structure of the tube type vortex reducer and its installation to the compressor is as follows Figure 1 As shown, the inventor has found that one end of the vortex reducer 3 in the structure is generally suspended in the air, and the compressor rotor has a high speed, and the vortex reducer will inevitably produce vibration problems during the rotation of the rotor. Therefore, if the vibration cannot be effectively suppressed, it may cause damage to itself and reduce reliability. In addition, the vibration of the vortex reducer 3 will cause energy loss of the airflow, resulting in pressure loss, and then lead to low air bleed efficiency. In order to improve the above problems, the present invention provides a vortex reducer, a vortex reducer and an aircraft engine.

[0048] Figure 2 The schematic diagram of the structure of the vortex reducer 10 provided in this embodiment installed on the compressor body 20 is shown. Figure 3 The overall structural diagram of the vortex reducer 10 provided in this embodiment is shown. Figure 4 FIG. 1 shows a schematic structural diagram of the vortex reducing tube 100 provided in this embodiment at a first viewing angle, Figure 5 The structure diagram of the vortex reducing tube 100 provided in this embodiment at a second viewing angle is shown. Figure 2-Figure 5 , this embodiment provides a vortex reducing tube 100, and accordingly, also provides a vortex reducer 10 and an aircraft engine (not shown).

[0049] The aircraft engine includes a vortex reducer 10 and a compressor body 20. The vortex reducer 10 is mounted on the compressor body 20, and a vortex reducer 100 of the vortex reducer 10 is located between two adjacent stage disks of the compressor body 20. Specifically, Figure 2 As shown, the compressor body 20 has a plurality of stage disks, two adjacent stage disks are respectively a first stage disk 21 and a second stage disk 22, a rotating disk cavity is formed between the first stage disk 21 and the second stage disk 22, and an air inlet hole 23 connected to the rotating disk cavity is provided on the compressor body 20, and cooling gas is introduced into the rotating disk cavity through the air inlet hole 23. The vortex reducing pipe 100 in the vortex reducer 10 is provided between the first stage disk 21 and the second stage disk 22, and extends into the rotating disk cavity.

[0050] The vortex reducer 10 includes a support ring 200 and a plurality of vortex reducing tubes 100, such as Figure 3As shown, the support ring 200 is a hollow circular ring structure, which has 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. A plurality of mounting holes 210 are distributed along the circumferential direction R of the support ring 200. A plurality of vortex reducers 100 are installed in the mounting holes 210 one by one. The gas in the main flow channel of the compressor is guided from the air inlet holes 23 to the cavity of the support ring 200 through the vortex reducer 100. 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, that is, Figure 2 The first stage disk 21, the second stage disk 22 and the vortex reducer 10 are only partially shown.

[0051] Furthermore, a thread for cooperating with the locking nut 24 is provided at the tail of one end of the support ring 200, and the support ring 200 is fixed on the first-stage disk 21 through the locking nut 24. Furthermore, an annular stopper is provided on the support ring 200 adjacent to the thread, and the annular stopper cooperates with the first-stage disk 21, and the support ring 200 is installed on the first-stage disk 21 through the joint action with the locking nut 24.

[0052] The vortex reducing 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 the support ring 200, and the vortex reducing tube 100 is installed on the support ring 200. The vortex reducing tube 100 also includes a boss 120 disposed on the tube body 110, the boss 120 has a first end 121 and a second end 122 opposite to each other, the first end 121 is provided with a first elastic sheet 130, and the second end 122 is provided with a second elastic sheet 140, and the first elastic sheet of one vortex reducing tube 100 is used to abut against the second elastic sheet 140 of another adjacent vortex reducing tube 100. In the case of vibration of a certain vortex reducing tube 100, the elastic abutment between the first elastic sheet 130 and the second elastic sheet 140 can generate an elastic force to suppress the vibration of the vortex reducing tube 100, thereby reducing the pressure loss of the airflow in the vortex reducing tube 100 and improving the air induction efficiency.

[0053] Please refer to Figure 3-Figure 5After the plurality of vortex reducing tubes 100 are installed along the circumference of the support ring 200, the bosses 120 of the plurality of vortex reducing tubes 100 are spliced ​​to form an annular structure. Along the circumference of the annular structure, which can also be regarded as the circumference of the support ring 200, the first spring piece 130 of a vortex reducing tube 100 is in conflict with the second spring piece 140 of the previous vortex reducing tube 100, and the second spring piece 140 of a vortex reducing tube 100 is in conflict with the first spring piece 130 of the next vortex reducing tube 100. Specifically, the matching structure is described by taking three adjacent vortex reducing tubes 100 as an example. The three vortex reducing tubes 100 are the first vortex reducing tube 161, the second vortex reducing tube 162 and the third vortex reducing tube 163 in sequence. The first spring piece 130 of the second vortex reducing tube 162 is in conflict with the second spring piece 140 of the first vortex reducing tube 161, and the second spring piece 140 of the second vortex reducing tube 162 is in conflict with the first spring piece 130 of the third vortex reducing tube 163.

[0054] Specifically, the boss 120 is fixedly connected to the tube body 110 , and may be an integrally formed structure, or may be a structure connected into one piece by welding or the like.

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

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

[0057] Further, the first elastic sheet 130 has a first plane portion 134 and a second plane portion 135 arranged on both sides of the convex arc portion 133 in the circumferential direction. Correspondingly, the second elastic sheet 140 has a third plane portion 144 and a fourth plane portion 145 arranged on both sides of the concave arc portion 143 in the circumferential direction. The first plane portion 134 is used to abut against the third plane portion 144 of another vortex reducing tube 100. The second plane portion 135 is used to be in contact with the fourth plane portion 145 of another vortex reducing tube 100.

[0058] Further, the first plane portion 134 and the second plane portion 135 are respectively connected to the convex arc portion 133 through a circular arc; the third plane portion 144 and the fourth plane portion 145 are respectively connected to the concave arc portion 143 through a circular arc. Further, the first plane portion 134, the second plane portion 135, the third plane portion 144 and the fourth plane portion 145 are respectively arranged perpendicular to the plane where the boss 120 is located, and extend along the width direction of the boss 120. By providing the first plane portion 134, the second plane portion 135, the third plane portion 144 and the fourth plane portion 145, the vibration reduction effect in the circumferential direction between two adjacent vortex reducing tubes 100 can be improved.

[0059] In this embodiment, the first elastic sheet 130 has a first connection end 131 and a first abutting end 132, and the second elastic sheet 140 has a second connection end 141 and a second abutting end 142. The first connection end 131 and the second connection end 141 are both fixedly connected to the boss 120. Specifically, the first connection end 131 is fixedly connected to the first end 121, and the second connection end 141 is fixedly connected to the second end 122. The first abutting end 132 is used to abut against the second abutting end 142 of another vortex reducing tube 100, and correspondingly, the second abutting end 142 is used to abut against the first abutting end 132 of another vortex reducing tube 100.

[0060] Figure 6 The cross-sectional structure diagram of the first spring sheet 130 and the second spring sheet 140 of two adjacent vortex reducing tubes 100 is shown. Figure 2-Figure 6 Further, the first elastic piece 130 extends in an arc shape from the first connection end 131 to the first abutting end 132, and the center of curvature of the arc (not shown) is closer to the tube body 110 than the first elastic piece 130, and the first abutting end 132 is farther from the tube body 110 than the first connection end 131. The second elastic piece 140 extends in an arc shape from the second connection end 141 to the second abutting end 142, and the center of curvature of the arc (not shown) is closer to the tube body 110 than the second elastic piece 140, and the second abutting end 142 is farther from the tube body 110 than the second connection end 141. In this way, only the first contact end 132 of the first spring piece 130 and the second contact end 142 of the second spring piece 140 are in contact with each other, and the first connecting end 131 and the second connecting end 141 are spaced apart and not in contact with each other, thereby increasing the elastic deformation amount when the first spring piece 130 and the second spring piece 140 are in contact with each other, making the contact between the first spring piece 130 and the second spring piece 140 tighter, which helps to ensure that elastic force can be generated for vibrations in all directions to better suppress vibrations.

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

[0062] In the present embodiment, the first spring piece 130 is arranged along the end contour of the first end 121, and accordingly, the end contour of the first end 121 of the boss 120 also has a convex arc shape. The second spring piece 140 is arranged along the end contour of the second end 122, and accordingly, the end contour of the second end 122 of the boss 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 is spaced apart from the second connecting end 141, accordingly, in the vortex reducer 10, there is also a gap between two adjacent bosses 120, that is, the two adjacent bosses 120 are not in contact (such as Figure 6 shown).

[0063] Figure 7 The structural diagram of the support ring 200 in the vortex reducer 10 provided in this embodiment is shown. Figure 2-Figure 7 In this embodiment, the mounting hole 210 includes a circular hole portion 211 and a through portion 212 which are interconnected. The circular hole portion 211 is used to match the tube body 110 of the vortex reducing tube 100, that is, the shape and size of the circular hole portion 211 are roughly consistent with the outer dimensions of the tube body 110. The outer 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 the rectangular structure. Accordingly, the through portion 212 can be regarded as a rectangular hole overlapping with the circular hole portion 211.

[0065] Furthermore, the support ring 200 also has a receiving groove 213 arranged on the inner circumference, the receiving groove 213 is connected to the circular hole portion 211, and along the axial direction of the circular hole portion 211, the receiving groove 213 and the through-portion 212 are staggered and distributed, and the receiving groove 213 is used to accommodate the mounting portion. When installing the vortex reducing tube 100, the vortex reducing tube 100 can be inserted into the mounting hole 210 from the radial outer side of the support ring 200 to the radial inner side, and after the connecting portion 150 passes through the through-portion 212 and is located on the inner circumference of the support ring 200, the vortex reducing tube 100 is rotated by a certain angle so that the connecting portion 150 is opposite to the receiving groove 213, and then the vortex reducing tube 100 moves a certain distance in the radial outward direction of the support ring 200 section, so that the connecting portion 150 enters the receiving groove 213 and abuts against the groove bottom of the receiving groove 213. Specifically, in the present embodiment, the receiving groove 213 is rectangular. Optionally, the angle between the receiving groove 213 and the through portion 212 is 90°, that is, after the connecting portion 150 is located at the inner periphery of the support ring 200, the vortex reducing tube 100 needs to be rotated 90° so that the connecting portion 150 is directly opposite to the receiving groove 213. It can be understood that in other embodiments, the relative position between the receiving groove 213 and the through portion 212 can also be specifically set.

[0066] Further, the vortex reducer 10 also includes a collar 300 fixedly connected to the support ring 200, and the collar 300 is used to limit the connection portion 150 in the receiving groove 213, and limit the radial movement of the vortex reducer 100 along the support ring 200, thereby preventing the vortex reducer 100 from detaching from the support ring 200. Specifically, the cross-section of the collar 300 is L-shaped, and the L-shaped collar 300 includes a first branch ring 311 and a second branch ring 312 connected to each other. The first branch ring 311 is supported at the bottom of the connection portion 150, so that the connection portion 150 is radially fixed between the collar 300 and the support ring 200. The second branch ring 312 is located on one side of the connection portion 150 along the radial direction of the tube body 110, and is fixed between the support ring 200 and the connection portion 150, thereby preventing the vortex reducer 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 boss 120 is the second direction. The first direction is arranged perpendicular to the second direction, that is, after the vortex reduction tube 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 reducer 100, vortex reducer 10 and aircraft engine provided by the embodiments of the present invention have a boss 120 arranged near the top of the tank body of the vortex reducer 100, and a first spring piece 130 and a second spring piece 140 arranged at both ends of the boss 120. Through the elastic interference between the first spring piece 130 and the second spring piece 140, an elastic force is generated to suppress the vibration when the vortex reducer 100 vibrates. Moreover, since the first spring piece 130 has a convex arc portion 133 and the second spring piece 140 has a concave arc portion 143, the interference between the convex arc portion 133 and the concave arc portion 143 enables elastic forces in corresponding directions to be generated according to multiple vibration directions, which further contributes to the suppression of vibration, thereby reducing pressure loss, improving air induction efficiency, and enhancing the cooling effect on high-temperature components in the aircraft engine. Moreover, when the vortex reducer 100 is installed on the support ring 200, it can be installed from the radial outer side to the inner side of the support ring 200. Compared with the current method of installing from the axis of the support ring 200 to the outside, the installation is more convenient. In addition, the installation method of the vortex reducer 100 provided in this embodiment facilitates better interference fit between the first spring piece 130 and the second spring piece 140.

[0069] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A vortex reducing tube, comprising a tube body and a connecting portion arranged at one end of the tube body, wherein the connecting portion is used to cooperate with a support ring to install the vortex reducing tube on the support ring; characterized in that: The vortex reducing tube further comprises: A boss is arranged on the tube body, and the boss has a first end and a second end opposite to each other, the first end is provided with a first elastic sheet, and the second end is provided with a second elastic sheet; the first elastic sheet of one vortex reducing tube is used to abut and cooperate with the second elastic sheet of another adjacent vortex reducing tube.

2. The vortex reducing tube according to claim 1, characterized in that: The first spring sheet has a convex arc portion for abutting and cooperating with the second spring sheet of another vortex reducing tube; the second spring sheet has a concave arc portion for abutting and cooperating with the first spring sheet of another vortex reducing tube.

3. The vortex reducing tube according to claim 2, characterized in that: The first elastic piece has a first plane portion and a second plane portion arranged on both sides of the convex arc portion in the circumferential direction; The second elastic piece has a third plane portion and a fourth plane portion arranged on both sides of the concave arc portion in the circumferential direction; The first plane portion is used for abutting and cooperating with the third plane portion of another vortex reducing tube; and the second plane portion is used for abutting and cooperating with the fourth plane portion of another vortex reducing tube.

4. The vortex reducing tube according to claim 1, characterized in that: The first elastic sheet has a first connecting end and a first abutting end, the second elastic sheet has a second connecting end and a second abutting end, the first connecting end and the second connecting end are both fixedly connected to the boss, and the first abutting end is used to abut and cooperate with the second abutting end of the other vortex reducing tube; The first connection end is closer to the connection portion than the first abutting end; and the second connection end is closer to the connection portion than the second abutting end.

5. The vortex reducing tube according to claim 4, characterized in that: The first elastic sheet 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 elastic sheet, and the first abutting end is farther from the tube body than the first connecting end; The extension direction of the second elastic sheet from the second connecting end to the second abutting end is arc-shaped, the curvature center of the arc is closer to the tube body than the second elastic sheet, and the second abutting end is farther from the tube body than the second connecting end.

6. The vortex reducing tube according to claim 1, characterized in that: The first elastic sheet is arranged along the end contour of the first end; and the second elastic sheet is arranged along the end contour of the second end.

7. The vortex reducing tube according to claim 1, characterized in that: The connecting portion includes a first protrusion and a second protrusion located at two sides of the tube body along the radial direction of the tube body, and the direction from the first protrusion to the second protrusion is a first direction; A direction from the first end to the second end is a second direction, and the first direction is perpendicular to the second direction.

8. A vortex reducer, characterized in that: The vortex reducer includes a support ring and a plurality of vortex reducer tubes as described in any one of claims 1 to 7; the support ring is provided with a plurality of mounting holes distributed in a circumferential direction, the plurality of vortex reducer tubes are mounted in the mounting holes in a one-to-one correspondence, and the bosses of the plurality of vortex reducer tubes are spliced ​​to form an annular structure, and along the circumference of the annular structure, the first spring sheet of one vortex reducer tube abuts against the second spring sheet of the previous vortex reducer tube, and the second spring sheet of one vortex reducer tube abuts against the first spring sheet of the next vortex reducer tube.

9. The vortex reducer according to claim 8, characterized in that: There is a gap between two adjacent shoulders.

10. The vortex reducer according to claim 8, characterized in that: The mounting hole comprises a circular hole portion and a through portion which are interconnected, the circular hole portion is used to cooperate with the tube body of the vortex reducing 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; The support ring also has a receiving groove arranged on the inner circumference, the receiving groove is communicated with the circular hole portion, and along the circumference of the circular hole portion, the receiving groove and the penetration portion are staggered and distributed, and the receiving groove is used to receive the connecting portion.

11. The vortex reducer according to claim 10, characterized in that: The vortex reducer also includes a clamping ring fixedly connected to the support ring, and the clamping ring is used to limit the connection portion in the accommodating groove and limit the radial movement of the vortex reducer along the support ring.

12. An aircraft engine, characterized in that: The aircraft engine includes a compressor body and a vortex reducer as described in any one of claims 8 to 11; the vortex reducer is installed on the compressor body, and the vortex reducer pipe of the vortex reducer is located between two adjacent stage disks of the compressor body.

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