Axial swirler and engine

Abstract

The present disclosure relates to the field of aviation technology, and in particular to an axial swirler and an engine, in order to solve the problem in the prior art of effectively adjusting the size of the axial swirler channel and ensuring that the blades are completely in contact with the channel wall. The axial swirler includes: a fixed swirler assembly, an adjustable swirler assembly, and a swirler sleeve. The swirler sleeve is arranged on the outer wall of the fixed swirler assembly, and the adjustable swirler assembly is rotatably connected to the swirler sleeve. The adjustable swirler assembly includes: a blade adjustment mechanism and a connecting block adjustment mechanism. The blade adjustment mechanism is used to adjust the gap between the blades and the swirler channel wall, and the connecting block adjustment mechanism is used to adjust the size of the swirler channel. The axial swirler and engine provided by the present disclosure are used in the design of axial swirlers.

Description

Technical Field

[0001] The present disclosure relates to the field of aviation technology, and in particular to an axial swirler and an engine. Background Art

[0002] As a core component in the combustion chamber system of an aircraft engine, the swirler plays an important role in constructing swirl and recirculation airflow. The variable geometry swirler can cooperate with flexible control strategies to meet the needs of different combustion conditions. With the development of artificial intelligence, it is expected to achieve intelligent adjustment with the help of data monitoring, and has great development potential.

[0003] Axial swirlers are widely used in high thrust-to-weight ratio turbofan engines. They have the advantages of low pressure loss, compact structure and good flow uniformity. However, the tangential velocity generated by the axial blades is limited, and the swirl intensity is weaker than that of radial swirlers, which affects combustion efficiency and stability. On the other hand, achieving geometric adjustability is difficult. In terms of adjusting the size of the flow channel, the swirlers made of traditional rigid alloy materials have a fixed radius of curvature of the inner and outer cylindrical ring walls, making it difficult to change the channel size. However, due to the shape of the traditional annular channel and the swing of the blades, the blades cannot completely fit the inner and outer ring walls of the channel, and the airflow will flow through the gap, weakening the swirl intensity and reducing combustion performance.

[0004] Therefore, how to solve the problem of effectively adjusting the size of the axial swirler channel in the prior art and ensuring that the blades are completely in contact with the channel wall is one of the important issues that need to be solved urgently in this field. Summary of the Invention

[0005] In view of this, embodiments of the present disclosure provide an axial swirler and an engine to solve the problem in the prior art of effectively adjusting the size of the axial swirler channel and ensuring that the blades are fully fitted with the channel wall.

[0006] According to one aspect of the present disclosure, an axial swirler is provided, comprising: a fixed swirler assembly, an adjustable swirler assembly, and a swirler sleeve. The swirler sleeve is disposed on an outer wall of the fixed swirler assembly, and the adjustable swirler assembly is rotatably connected to the swirler sleeve. The adjustable swirler assembly includes: a blade adjustment mechanism for adjusting the gap between the blades and the wall of the swirling channel, and a connecting block adjustment mechanism for adjusting the size of the swirling channel.

[0007] In addition, according to an aspect of the axial swirler of the present disclosure, the axial swirler further includes: a first drive unit, a support member and a first rotating member, the support member is fixedly connected to the swirler sleeve, the first drive unit is fixedly connected to the support member, the first rotating member is sleeved on the swirler sleeve, and the first drive unit is used to drive the first rotating member to rotate.

[0008] According to one aspect of the present disclosure, the axial swirler further comprises: a plurality of second rotating members and a plurality of positioning members for fixing the plurality of second rotating members, a plurality of receiving grooves are formed on the outer side wall of the swirler sleeve, and each second rotating member is disposed in the receiving groove via each positioning member;

[0009] When the first driving unit drives the first rotating member to rotate, the rotation of the first rotating member drives each of the second rotating members to rotate.

[0010] According to an axial swirler of one aspect of the present disclosure, the blade adjustment mechanism includes a first blade segment, a second blade segment, a third blade segment and a fourth blade segment, one end of the fourth blade segment is fixedly connected to the second rotating member, and the other end of the fourth blade segment is connected to the third blade segment by a lock; the first blade segment and the second blade segment are connected by a lock; the second blade segment and the third blade segment are detachably connected.

[0011] According to one aspect of the axial swirler of the present disclosure, the blade adjustment mechanism further includes a baffle, a first elastic member, and a second elastic member. The baffle is provided along the axial direction of the second blade segment near one end of the third blade segment, and the baffle is connected to the end of the second blade segment.

[0012] A first through hole is provided on the second blade segment for placing a first elastic member, one end of the first elastic member is connected to the baffle, and the other end of the first elastic member is connected to the first blade segment; a second through hole is provided on the third blade segment for placing a second elastic member, one end of the second elastic member is connected to the baffle, and the other end of the second elastic member is connected to the fourth blade segment.

[0013] According to the axial swirler of one aspect of the present disclosure, the second blade segment, the third blade segment, and the fourth blade segment are all provided with vent holes for discharging gas inside the blade adjustment mechanism.

[0014] According to an axial swirler of one aspect of the present disclosure, the connection block adjustment structure includes: a fixed plate, a drive disk, multiple connecting rods, multiple fixed wheels, a second drive unit and multiple connection blocks, the second drive unit is fixedly connected to the fixed plate, the drive disk is rotatably connected to the fixed plate, one end of each connecting rod is connected to each fixed wheel, and the other end of each connecting rod is connected to each connection block.

[0015] According to the axial swirler of one aspect of the present disclosure, a sliding groove for sliding the connecting rod is further provided on the driving disc.

[0016] According to an axial swirler of one aspect of the present disclosure, a slider and a positioning pin are provided on the side of each connecting block. The slider is fixed on the side of each connecting block, the positioning pin is slidably arranged in the slider, and the other end of the connecting rod is connected to the positioning pin.

[0017] According to another aspect of the present disclosure, the present disclosure further provides an aircraft engine, wherein the combustion chamber of the aircraft engine includes the above-mentioned axial swirler.

[0018] At least one of the above-mentioned technical solutions employed in the embodiments of the present disclosure can achieve the following beneficial effects: In the aforementioned axial swirler, the gap between the blades and the swirl channel wall is adjusted by the blade adjustment mechanism, enabling precise control of the air flow entering the swirler. The appropriate gap allows air to enter at a specific angle and velocity, effectively mixing with the fuel and improving combustion efficiency and performance. The connecting block adjustment mechanism adjusts the size of the swirl channel, enabling the axial swirler to be flexibly adjusted to varying operating conditions. Under high-load conditions, enlarging the swirl channel increases air flow, meeting the needs of burning more fuel. Under low-load conditions, reducing the swirl channel ensures sufficient swirl intensity and maintains a stable combustion process. Furthermore, properly adjusting the gap between the blades and the swirl channel wall helps reduce friction and collision between the blades and the wall, reducing wear and extending the blade life. Furthermore, stable airflow reduces vibration caused by unstable airflow, improving the stability and reliability of the entire swirler and its connected equipment, effectively resolving the existing problem of effectively adjusting the channel size of axial swirlers and ensuring that the blades fit perfectly with the channel wall. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0020] Figure 1 FIG2 is a schematic diagram of the overall structure of an axial swirler according to an embodiment of the present disclosure;

[0021] Figure 2 is a schematic structural diagram illustrating a first rotating member according to an embodiment of the present disclosure;

[0022] Figure 3 is a schematic diagram illustrating the structure of a cyclone sleeve according to an embodiment of the present disclosure;

[0023] Figure 4 is a schematic diagram illustrating the structure of a receiving tank according to an embodiment of the present disclosure;

[0024] Figure 5 is a schematic diagram illustrating the structure of a positioning member according to an embodiment of the present disclosure;

[0025] Figure 6 is a schematic structural diagram of a second rotating member according to an embodiment of the present disclosure;

[0026] Figure 7 is an exploded view illustrating a blade adjustment mechanism according to an embodiment of the present disclosure;

[0027] Figure 8 is a schematic diagram illustrating the cooperation structure of the first rotating member and the second rotating member according to an embodiment of the present disclosure;

[0028] Figure 9 is a schematic diagram illustrating a blade structure diagram of a blade adjustment mechanism according to an embodiment of the present disclosure;

[0029] Figure 10 is a schematic diagram illustrating a connection block structure according to an embodiment of the present disclosure;

[0030] Figure 11 is a schematic diagram illustrating a connection block adjustment mechanism according to an embodiment of the present disclosure;

[0031] Figure 12A is a schematic diagram illustrating an adjustment of a connection block adjustment mechanism according to an embodiment of the present disclosure;

[0032] Figure 12B is a schematic diagram illustrating medium adjustment of a channel of a connection block adjustment mechanism according to an embodiment of the present disclosure;

[0033] Figure 12C Is a diagram illustrating the minimum adjustment of the channel of the connecting block adjustment mechanism according to an embodiment of the present disclosure;

[0034] Figure 13 FIG1 is a schematic diagram illustrating the adjustment of the blade adjustment mechanism according to an embodiment of the present disclosure.

[0035] Reference numerals:

[0036] 1-fixed swirl assembly, 2-adjustable swirl assembly, 3-swirler sleeve, 4-first rotating member, 5-first driving unit, 6-accommodating groove, 7-positioning member, 8-second rotating member, 9-blade, 91-first blade segment, 92-second blade segment, 93-third blade segment, 94-fourth blade segment, 10-connecting block, 101-slider, 102-positioning pin, 11-fixed wheel, 12-connecting rod, 13-fixed plate, 14-drive disk. DETAILED DESCRIPTION

[0037] The following describes embodiments of the present disclosure in more detail with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are for illustrative purposes only and are not intended to limit the scope of protection of the present disclosure.

[0038] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0039] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". The relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0040] It should be noted that the modifications of "one" and "multiple" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, they should be understood as "one or more".

[0041] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0042] As a core component in the combustion chamber system of an aircraft engine, the swirler plays an important role in constructing swirl and recirculation airflow. The variable geometry swirler can cooperate with flexible control strategies to meet the needs of different combustion conditions. With the development of artificial intelligence, it is expected to achieve intelligent adjustment with the help of data monitoring, and has great development potential.

[0043] Axial swirlers are widely used in high thrust-to-weight ratio turbofan engines. They have the advantages of low pressure loss, compact structure and good flow uniformity. However, the tangential velocity generated by the axial blades is limited, and the swirl intensity is weaker than that of radial swirlers, which affects combustion efficiency and stability. On the other hand, achieving geometric adjustability is difficult. In terms of adjusting the size of the flow channel, the swirlers made of traditional rigid alloy materials have a fixed radius of curvature of the inner and outer cylindrical ring walls, making it difficult to change the channel size. However, due to the shape of the traditional annular channel and the swing of the blades, the blades cannot completely fit the inner and outer ring walls of the channel, and the airflow will flow through the gap, weakening the swirl intensity and reducing combustion performance.

[0044] In response to the above problems, exemplary embodiments of the present disclosure provide an axial swirler and an engine to solve the problem in the prior art of effectively adjusting the size of the axial swirler channel and ensuring that the blades are fully fitted with the channel wall.

[0045] Figure 1 FIG. 1 is a schematic diagram of the overall structure of the axial swirler according to an embodiment of the present disclosure. Figure 1 As shown, the axial swirler includes: a fixed swirler assembly 1, an adjustable swirler assembly 2, and a swirler sleeve 3. The swirler sleeve 3 is arranged on the outer wall of the fixed swirler assembly 1, and the adjustable swirler assembly 2 is rotatably connected to the swirler sleeve 3. The adjustable swirler assembly 2 includes: a blade adjustment mechanism and a connecting block 10 adjustment mechanism. The blade adjustment mechanism is used to adjust the gap between the blades and the wall of the swirling channel. The connecting block 10 adjustment mechanism is used to adjust the size of the swirling channel.

[0046] In actual application, the gap between the blades and the wall of the swirl channel is adjusted by the blade adjustment mechanism, which can accurately control the flow state of air entering the swirler. The appropriate gap allows air to enter at a specific angle and speed, better mix with the fuel, and improve combustion efficiency and performance. The adjustment mechanism of the connecting block 10 can adjust the size of the swirl channel, which enables the axial swirler to be flexibly adjusted according to different working conditions. Under high-load conditions, increasing the swirl channel can increase the air flow rate to meet the needs of burning more fuel. Under low-load conditions, reducing the swirl channel can ensure sufficient swirl intensity and maintain a stable combustion process. In addition, the reasonable adjustment of the gap between the blades and the wall of the swirl channel helps to reduce friction and collision between the blades and the wall, reduce the degree of wear, and extend the service life of the blades. At the same time, stable airflow can reduce vibration caused by unstable airflow, improve the stability and reliability of the entire swirler and the equipment connected to it, and effectively solve the problem of effectively adjusting the size of the axial swirler channel and ensuring that the blades are completely in contact with the channel wall in the prior art.

[0047] Figure 2 is a schematic structural diagram illustrating a first rotating member 4 according to an embodiment of the present disclosure, Figure 3 FIG2 is a schematic diagram illustrating the structure of the cyclone sleeve 3 according to an embodiment of the present disclosure. Figure 4 1 is a schematic diagram illustrating the structure of the receiving tank 6 according to an embodiment of the present disclosure. Figure 5 1 is a schematic structural diagram of a positioning member 7 according to an embodiment of the present disclosure. Figure 6 Schematic diagram of the structure of the second rotating member 8 according to an embodiment of the present disclosure. Figure 2-Figure 6 As shown, the axial cyclone further includes: a first drive unit 5, a support member and a first rotating member 4. The support member is fixedly connected to the cyclone sleeve 3, the first drive unit 5 is fixedly connected to the support member, and the first rotating member 4 is sleeved on the cyclone sleeve 3. It should be understood that the first rotating member 4 can be other transmission members such as gears, which will not be described in detail here. Taking the gear as an example, Figure 2As shown, the first rotating member 4 is a double gear structure, and an L-shaped bracket is designed between the double gears, so that the outer gear of the double gear and the driving disk 14 are staggered in axial position to avoid mutual influence between the rotational motions of the two. The first driving unit 5 is used to drive the first rotating member 4 to rotate.

[0048] In practice, the support member is fixed to the cyclone sleeve 3, providing a solid foundation for the first drive unit 5. This structural design ensures the stable position of the first drive unit 5 during operation, reducing displacement or shaking caused by vibration or external forces. The support member evenly transfers the weight of the first drive unit 5 and the forces generated during operation to the cyclone sleeve 3, ensuring a more balanced force distribution across the entire structure. This prevents localized stress concentration, extends the service life of cyclone components, and improves the reliability and durability of the equipment.

[0049] like Figure 3 As shown, the cyclone sleeve 3 is divided into a cylindrical section and a regular polygonal section. The number of sides of the regular polygon matches the number of blades in the blade adjustment mechanism. The regular polygonal section ensures that the blade roots are completely aligned with the inner wall of the regular polygon during blade angle rotation and adjustment, preventing gaps between the blade roots and the inner wall that could affect swirl intensity. The cylindrical section is used to mount the first rotating member 4, ensuring that it can rotate freely about the cyclone sleeve 3, thus achieving blade angle adjustment.

[0050] For example, Figure 4-Figure 6 As shown, the axial cyclone further comprises: a plurality of second rotating members 8 and a plurality of positioning members 7 for fixing the plurality of second rotating members 8. A plurality of receiving grooves 6 are provided on the outer wall of the cyclone sleeve 3. Figure 4 As shown, the receiving groove 6 has a cross-sectional structure that is narrow at the top and wide at the bottom. The width of the bottom is the same as the diameter of the blade root. The head adopts a semicircular design to achieve the purpose of positioning the blade tooth plate. Each second rotating member 8 is disposed in the receiving groove 6 through each positioning member 7. When the first driving unit 5 drives the first rotating member 4 to rotate, the first rotating member 4 rotates and drives each second rotating member 8 to rotate.

[0051] In actual use, multiple positioning members 7 secure the second rotating member 8 within the receiving groove 6 of the cyclone sleeve 3. This multi-point positioning method provides a stable installation foundation for the second rotating member 8. When the axial cyclone is operating at high speed or undergoing complex working conditions, the cooperation between the positioning members 7 and the receiving groove 6 can effectively limit the displacement and shaking of the second rotating member 8, preventing structural failure caused by loose components. At the same time, the dispersed fixing points can evenly distribute the load during operation, avoid local stress concentration, extend the service life of the entire cyclone, and ensure stable operation of the equipment. In addition, the first rotating member 4 drives the multiple second rotating members 8 to rotate synchronously, ensuring the consistency of the movement of each part of the adjustable cyclone assembly 2. This synchronous transmission mechanism can also reduce the additional wear and vibration caused by transmission differences, improving the stability and reliability of equipment operation. Secondly, the provision of multiple second rotating members 8 increases the freedom of the adjustable cyclone assembly 2, enabling more precise adjustment of the axial cyclone. According to different working conditions, the first driving unit 5 drives the first rotating member 4, and the rotation angles and amplitudes of the plurality of second rotating members 8 can be flexibly controlled, thereby making diversified adjustments to the blade gaps of the swirl channel.

[0052] Figure 7 is an exploded view illustrating a blade adjustment mechanism according to an embodiment of the present disclosure, Figure 8 1 is a schematic diagram illustrating the cooperation structure of the first rotating member 4 and the second rotating member 8 according to an embodiment of the present disclosure. Figure 9 Schematic diagram of the blade structure of the blade adjustment mechanism according to the embodiment of the present disclosure, as shown in FIG. Figure 7-Figure 9 As shown, the blade adjustment mechanism includes a first blade segment 91, a second blade segment 92, a third blade segment 93, and a fourth blade segment 94. One end of the fourth blade segment 94 is fixedly connected to the second rotating member 8, and the other end of the fourth blade segment 94 is connected to the third blade segment 93 via a lock. The first blade segment 91 and the second blade segment 92 are connected via a lock; and the second blade segment 92 and the third blade segment 93 are detachably connected. The blade adjustment mechanism also includes a baffle, a first elastic member, and a second elastic member. It should be understood that the first and second elastic members can be elastic bodies such as springs, and a detailed description thereof is not provided here. A baffle is provided along the axial direction of the second blade segment 92 near one end of the third blade segment 93, and the baffle is connected to the end of the second blade segment 92; a first through hole is provided on the second blade segment 92 for placing a first elastic member, one end of the first elastic member is connected to the baffle, and the other end of the first elastic member is connected to the first blade segment 91; a second through hole is provided on the third blade segment 93 for placing a second elastic member, one end of the second elastic member is connected to the baffle, and the other end of the second elastic member is connected to the fourth blade segment 94.

[0053] In practical applications, such as Figure 7-Figure 9As shown, before the axial cyclone is activated, the blade adjustment mechanism is in its initial state. Each blade segment is secured by a locking connection. The first and second elastic members are in their natural state, and a certain initial gap is maintained between the blade and the wall of the swirl channel. When the first drive unit 5 drives the first rotating member 4 to rotate, the first rotating member 4 drives the second rotating member 8 to rotate, and the fourth blade segment 94, which is fixedly connected to the second rotating member 8, rotates accordingly. The rotation of the fourth blade segment 94 causes the second elastic member to expand and contract. Since one end of the second elastic member is connected to the baffle and the other end is connected to the fourth blade segment 94, the expansion and contraction of the second elastic member drives the third blade segment 93 to move. At the same time, the first elastic member also expands and contracts due to the movement of the second blade segment 92, thereby driving the movement of the first blade segment 91. The relative movement of the first blade segment 91, the second blade segment 92, the third blade segment 93, and the fourth blade segment 94 enables the adjustment of the gap between the blade and the wall of the swirl channel.

[0054] During operation, the airflow pressure and velocity within the swirl channel fluctuate. When airflow pressure increases, the elastic member compresses, driving the blade segments toward the wall, reducing the gap between the blades and the wall to accommodate the airflow changes. When airflow pressure decreases, the elastic member expands, driving the blade segments away from the wall, increasing the gap and ensuring swirl stability. Furthermore, the blade adjustment mechanism consists of multiple blade segments, each connected via a locking or detachable connection, allowing the blade length and shape to be flexibly adjusted according to actual needs. When the gap between the blades and the swirl channel wall needs to be changed, the gap can be precisely fine-tuned by adjusting the connection method or position of each blade segment, thereby optimizing the swirl effect and improving combustion efficiency. Furthermore, the arrangement of the first and second elastic members enables the blade adjustment mechanism to adaptively adjust according to pressure and airflow changes within the swirl channel. When airflow pressure changes, the elastic member expands and contracts accordingly, driving the blade segments to move and automatically adjusting the gap between the blades and the wall to ensure swirl stability and uniformity.

[0055] On this basis, the first and second elastic members act as buffers during blade adjustment, absorbing and dissipating impact and vibration, reducing blade damage and fatigue, and extending blade service life. The baffle provides support and positioning for the elastic members, ensuring their proper function and preventing excessive movement of the blade segments during adjustment, thereby enhancing the structural stability and reliability of the blade adjustment mechanism.

[0056] For example, Figure 9As shown, the second, third, and fourth blade segments 92, 93, and 94 all feature vents for discharging gas from the blade adjustment mechanism. During operation, gas can easily accumulate within the blade adjustment mechanism, creating localized high- or low-pressure areas and causing turbulent airflow. These vents allow for the timely discharge of accumulated gas, preventing pressure fluctuations and ensuring stable and uniform airflow within the swirl channel, ensuring the swirler maintains efficient operation.

[0057] Figure 10 is a schematic structural diagram of a connection block 10 according to an embodiment of the present disclosure, Figure 11 Schematic diagram of the adjustment mechanism of the connection block 10 according to an embodiment of the present disclosure. Figure 10-11 As shown, the adjustment structure of the connecting block 10 includes: a fixed plate 13, a drive disc 14, multiple connecting rods 12, multiple fixed wheels 11, a second drive unit, and multiple connecting blocks 10. It should be understood that the connecting block 10 is specifically an isosceles triangle. The height of the isosceles triangle is designed according to the size of the drive disc 14, and the thickness of the connecting block 10 is designed according to the length of the cyclone channel. The second drive unit is fixedly connected to the fixed plate 13, and the drive disc 14 is rotatably connected to the fixed plate 13. One end of each connecting rod 12 is connected to each fixed wheel 11, and the other end of each connecting rod 12 is connected to each connecting block 10. The drive disc 14 also has a sliding groove for the connecting rod 12 to slide. The side of each connecting block 10 is provided with a slider 101 and a positioning pin 102. The slider 101 is fixed to the side of each connecting block 10, and the positioning pin 102 is slidably disposed within the slider 101. The other end of the connecting rod 12 is connected to the positioning pin 102.

[0058] In practical applications, such as Figure 10-11 As shown, when the second drive unit starts working, since the second drive unit is fixedly connected to the fixed plate 13, the power output of the second drive unit will drive the drive disc 14 connected thereto to rotate. The drive disc 14 performs a circular motion on the fixed plate 13, providing initial power for subsequent adjustment actions. The drive disc 14 is provided with a sliding groove for the connecting rod 12 to slide. When the drive disc 14 rotates, the sliding groove guides the connecting rod 12 connected thereto to move. One end of each connecting rod 12 is connected to the fixed wheel 11, which supports and positions the connecting rod 12 to ensure the stability of the movement of the connecting rod 12. The other end of the connecting rod 12 is connected to the slider 101 on the side of the connecting block 10 through the locating pin 102. As the connecting rod 12 moves driven by the locating groove of the drive disc 14, the locating pin 102 slides in the slider 101, thereby pushing the connecting block 10 to move. Since there are multiple connecting rods 12 and connecting blocks 10, they will work together to achieve precise adjustment of the position of the connecting block 10 according to the rotation direction and angle of the driving disk 14, thereby adjusting the size of the swirl channel.

[0059] Therefore, the rotation of the drive disc 14 can be achieved through precise control of the second drive unit, allowing the movement distance and position of the connecting block 10 to be precisely controlled. Secondly, the coordinated operation of the multiple connecting rods 12 and the connecting block 10 ensures consistent adjustment of all parts of the swirl channel, avoiding localized uneven adjustment and further improving adjustment accuracy. Furthermore, the fixed plate 13 provides a stable support base for the entire adjustment structure. The support and positioning of the connecting rod 12 by the fixed wheel 11, and the restraint of the movement of the connecting block 10 by the slider 101 and positioning pin 102, all enhance the stability of the structure. Even when the axial cyclone is operating at high speed or is subject to external vibration, the structure can maintain a stable operating state, ensuring the normal operation of the adjustment function. The guiding effect of the chute on the connecting rod 12 prevents it from shaking or deflecting during movement, further improving the stability and reliability of the structure. Furthermore, the rotation of the drive disc 14 enables continuous adjustment, allowing the size of the swirl channel to be adjusted flexibly and in real time according to different operating conditions. This allows for rapid response and appropriate adjustments under different operating conditions. The independent and coordinated movement of the multiple connecting blocks 10 enables the adjustment of the swirl channel to achieve diversified changes and adapt to different airflow distribution and swirl requirements.

[0060] Figure 12A is a schematic diagram illustrating the maximum adjustment of the channel of the connection block adjustment mechanism according to an embodiment of the present disclosure, Figure 12B is a schematic diagram illustrating the medium adjustment of the channel of the connection block adjustment mechanism according to an embodiment of the present disclosure, Figure 12C Schematic diagram of the minimum adjustment of the channel of the connection block adjustment mechanism according to an embodiment of the present disclosure, as shown in FIG. Figures 12A-12C As shown, when the drive disc 14 rotates counterclockwise, the connecting block 10 moves toward the center along the slideway groove, causing the connecting block 10 to gradually close, reducing the area of the swirl channel. This also causes the cyclone sleeve 3 and the first drive unit 5 to rotate slightly counterclockwise. At this point, if the first drive unit 5 stops operating, the first rotating member 4 does not rotate, and the motor gear is fixed, the transmission gear in the first drive unit 5 meshes with the external gear in the first rotating member 4, thereby driving the first rotating member to rotate. This prevents relative motion between the cyclone sleeve 3, the first drive unit 5, the first rotating member 4, and the second rotating member 8, all of which rotate slightly synchronously with the cyclone sleeve 3. This ensures that the blade angle remains unchanged during changes in the swirl channel when the first drive unit 5 is stationary. However, if the first drive unit 5 starts operating at this point, it causes the first rotating member 4 and the second rotating member 8 to rotate relative to each other along with the rotating cyclone sleeve 3, thereby driving the second rotating member 8 to rotate, achieving synchronous adjustment of the blade angle during changes in the swirl channel.

[0061] Figure 13Schematic diagram of the blade adjustment mechanism according to an embodiment of the present disclosure. Figure 13 As shown, the first driving unit 5 drives the first rotating member 4 to rotate, and also drives the second rotating member 8 to rotate, thereby realizing 360° full-angle adjustment of the blade angle, and the adjustment control strategy of the rotation angle of the first driving unit 5 is independent of whether the size of the swirl channel changes, which is more convenient and flexible to control.

[0062] An exemplary embodiment of the present disclosure provides an aircraft engine, wherein a combustion chamber of the aircraft engine includes the axial swirler according to an exemplary embodiment of the present disclosure.

[0063] Compared with the prior art, the beneficial effects of the aircraft engine provided by the embodiments of the present disclosure refer to the beneficial effects of the axial swirler, which will not be described in detail here.

[0064] The above descriptions are merely some embodiments of the present disclosure and illustrate the underlying technical principles. Those skilled in the art should understand that the scope of the present disclosure is not limited to technical solutions formed by specific combinations of the aforementioned technical features. It also encompasses other technical solutions formed by any combination of the aforementioned technical features or their equivalents, without departing from the aforementioned concepts. For example, a technical solution formed by replacing the aforementioned features with (but not limited to) technical features with similar functions disclosed in this disclosure.

[0065] Although some specific embodiments of the present disclosure have been described in detail by way of examples, those skilled in the art will appreciate that the above examples are for illustrative purposes only and are not intended to limit the scope of the present disclosure. Those skilled in the art will appreciate that modifications may be made to the above embodiments without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. An axial cyclone, characterized in that: The axial swirler comprises: a fixed swirler assembly, an adjustable swirler assembly and a swirler sleeve, wherein the swirler sleeve is arranged on the outer side wall of the fixed swirler assembly, and the adjustable swirler assembly is rotatably connected to the swirler sleeve; The adjustable swirl assembly includes: a blade adjustment mechanism and a connecting block adjustment mechanism, wherein the blade adjustment mechanism is used to adjust the gap between the blade and the wall of the swirl channel, and the connecting block adjustment mechanism is used to adjust the size of the swirl channel; The axial swirler further comprises: a first driving unit, a support member, and a first rotating member, wherein the support member is fixedly connected to the swirler sleeve, the first driving unit is fixedly connected to the support member, the first rotating member is sleeved on the swirler sleeve, and the first driving unit is used to drive the first rotating member to rotate; The axial swirler further comprises: a plurality of second rotating members and a plurality of positioning members for fixing the plurality of second rotating members, a plurality of receiving grooves are formed on the outer side wall of the swirler sleeve, and each of the second rotating members is arranged in the receiving groove through each of the positioning members; When the first driving unit drives the first rotating member to rotate, the rotation of the first rotating member drives each of the second rotating members to rotate; The blade adjustment mechanism includes a first blade segment, a second blade segment, a third blade segment, and a fourth blade segment, one end of the fourth blade segment is fixedly connected to the second rotating member, and the other end of the fourth blade segment is connected to the third blade segment via a lock; the first blade segment and the second blade segment are connected via a lock; and the second blade segment and the third blade segment are detachably connected; The blade adjustment mechanism further includes a baffle, a first elastic member, and a second elastic member. The baffle is provided along the axial direction of the second blade segment near one end of the third blade segment, and the baffle is connected to the end of the second blade segment. A first through hole is provided on the second blade segment for placing the first elastic member, one end of the first elastic member is connected to the baffle, and the other end of the first elastic member is connected to the first blade segment; a second through hole is provided on the third blade segment for placing the second elastic member, one end of the second elastic member is connected to the baffle, and the other end of the second elastic member is connected to the fourth blade segment.

2. The axial swirler according to claim 1, characterized in that The second blade segment, the third blade segment and the fourth blade segment are all provided with vent holes for discharging gas inside the blade adjustment mechanism.

3. The axial swirler according to claim 1, characterized in that The connecting block adjustment structure includes: a fixed plate, a driving disk, multiple connecting rods, multiple fixed wheels, a second driving unit and multiple connecting blocks, the second driving unit is fixedly connected to the fixed plate, the driving disk is rotatably connected to the fixed plate, one end of each connecting rod is connected to each fixed wheel, and the other end of each connecting rod is connected to each connecting block.

4. The axial swirler according to claim 3, characterized in that The driving disc is also provided with a sliding groove for the connecting rod to slide.

5. The axial swirler according to claim 3, characterized in that A slider and a positioning pin are provided on the side of each connecting block. The slider is fixed on the side of each connecting block. The positioning pin is slidably arranged in the slider. The other end of the connecting rod is connected to the positioning pin.

6. An aircraft engine, characterized in that: The combustion chamber of the aircraft engine comprises the axial swirler according to any one of claims 1 to 5.

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