Shape memory alloy actuated fan engine and aircraft

Abstract

The application provides a shape memory alloy turbofan engine and aircraft, comprising a wheel disc, a plurality of blades and a plurality of damping arms; each blade has a reserved hole, and the plurality of damping arms are inserted into the plurality of reserved holes one by one. A sinking groove is formed on the inner wall of the reserved hole, and the damping arm has a protruding part embedded in the sinking groove. During installation, the damping arm undergoes phase change in a low-temperature state to meet the softness requirement; after installation, the protruding part can undergo phase change in a high-temperature state, so that the protruding part and the sinking groove are in interference fit, ensuring the structural stability of the damping arm; the end part of the damping arm adopts a bevel structure to form face contact between two damping arms, ensuring that the damping generated by the friction force can offset the vibration effect. The shape memory alloy turbofan engine and aircraft provided by the application can separate the damping arm and the blade, so that the damping arm can be replaced alone during operation and maintenance, the blade that can still work stably is reserved, and the operation and maintenance cost of the turbofan engine is controlled.

Description

Technical Field

[0001] This application belongs to the field of aircraft technology, specifically relating to a shape memory alloy turbofan engine and an aircraft. Background Technology

[0002] A turbofan engine, also known as a turbofan engine, is a highly efficient power plant. Its core structure includes a front-end fan, a multi-stage compressor, a combustion chamber, a turbine assembly, and an exhaust nozzle. The fan is responsible for drawing in air and splitting it into two streams: one enters the inner duct for combustion, and the other enters the outer bypass duct to generate direct thrust. In practical applications, due to its compact structure and wide thrust adjustment range, turbofan engines are widely used in small and medium-sized unmanned aerial vehicles (UAVs) and other flight platforms.

[0003] A typical turbofan engine fan structure includes a rotating disk and multiple blades detachably connected to the disk. As a cantilever structure, the blades are highly susceptible to high-cycle fatigue due to their own vibration, which can lead to blade breakage. Therefore, existing technologies typically include a damping arm extending circumferentially along the disk at the center of the blade. After multiple blades are fixed together by tenon joints, adjacent damping arms abut against each other to dissipate the vibrational energy of the blades through friction and reduce the impact of vibration.

[0004] Based on the above structure, the inventors discovered that the damping arm and the blade are usually connected as a single unit. However, in actual use, the service life of the damping arm is usually shorter than that of the blade. That is, the damping arm is a wear part, while the blade can perform working tasks for a longer period of time. In this case, replacing the blade due to the damage of the damping arm becomes a material loss, which increases the maintenance cost of the turbofan engine. Utility Model Content

[0005] This application provides a shape memory alloy turbofan engine and aircraft, which aims to replace the damping arm separately to retain the blades that can still operate stably, thereby controlling the operation and maintenance costs of the turbofan engine.

[0006] To achieve the above objectives, the technical solution adopted in this application is as follows:

[0007] A shape memory alloy turbofan engine is provided, comprising a rotor disk and a plurality of blades arranged around the rotor disk; each blade has a pre-drilled hole at its center, the axial direction of the pre-drilled hole being perpendicular to the extension direction of the blade and also perpendicular to the axial direction of the rotor disk; furthermore, a recessed groove is formed on the inner wall of the pre-drilled hole; the turbofan engine further includes:

[0008] Multiple damping arms, corresponding one-to-one with multiple blades, all adopt a linear structure and are made of shape memory alloy material; each damping arm is inserted into the corresponding reserved hole, and has a protrusion suitable for being embedded in the sinking groove, and the protrusion and the sinking groove are interference fit;

[0009] When the blade is connected to the wheel disk, the damping arm is inserted into the reserved hole, and the protrusion is embedded in the sink groove, the ends of two adjacent damping arms along the circumference of the wheel disk are connected.

[0010] The end face of the damping arm adopts a beveled structure to form a surface contact between the two damping arms.

[0011] In one possible implementation, the end of the damping arm has an outwardly extending extension that is aligned with the inclined surface structure.

[0012] When the ends of two adjacent damping arms along the circumference of the wheel are connected, the two extensions are connected to increase the contact area of ​​the two damping arms.

[0013] In one possible implementation, the sinking trough extends circumferentially along the reserved hole and is connected end to end; the protrusion adopts an annular structure surrounding the damping arm to be adapted to be embedded in the sinking trough.

[0014] In one possible implementation, a gasket is provided between the ends of two adjacent damping arms along the circumference of the disc.

[0015] In one possible implementation, the blade has a snap-fit ​​block at one end facing the wheel, the wheel comprising:

[0016] Inner disc body; and

[0017] The outer disc body is coaxially disposed on one side of the inner disc body and is detachably connected to the inner disc body;

[0018] The inner disk body has a plurality of inner grooves on the side facing the outer disk body that correspond one-to-one with the plurality of blades, and each inner groove penetrates the outer peripheral surface of the inner disk body;

[0019] The outer disk body has a plurality of outer grooves on the side facing the inner disk body, each of which corresponds to one of the plurality of inner grooves and each of the outer grooves penetrates the outer peripheral surface of the outer disk body;

[0020] When the inner disc and the outer disc are connected, the corresponding inner groove and the outer groove communicate to form a combined cavity suitable for the insertion of the snap-fit ​​block.

[0021] In one possible implementation, the inner disc has a positioning screw extending toward the outer disc; the outer disc has an alignment hole suitable for insertion of the positioning screw, and the insertion end of the positioning screw is threaded with an anti-loosening nut.

[0022] The anti-loosening nut is used to abut against the side of the outer disc body facing away from the inner disc body, so as to restrict the relative movement of the inner disc body and the outer disc body along the axial direction.

[0023] In one possible implementation, the outer disc body has a mating groove on the side facing away from the inner disc body that is coaxially arranged with the alignment hole;

[0024] When the inner disc and the outer disc are in contact, the end of the positioning screw is located in the mating groove;

[0025] The anti-loosening nut is located inside the mating groove and abuts against the bottom of the mating groove.

[0026] In one possible implementation, a plug is embedded in the mating groove; the plug is located on the side of the anti-loosening nut facing the opening of the mating groove, so as to close the opening of the mating groove.

[0027] In one possible implementation, the connection between the blade and the snap-fit ​​block has an arc-shaped reinforcing plate;

[0028] When the snap-fit ​​block is embedded in the combined cavity, the reinforcing plate is attached to the outer circumferential surface of the wheel, and two adjacent reinforcing plates are connected along the circumferential direction of the wheel.

[0029] The beneficial effect of the shape memory alloy turbofan engine provided in this embodiment is that the blades and damping arms, which were originally connected as a single unit, are now connected by a plug-in joint. Therefore, when the damping arm suffers fatigue damage, it can be replaced separately.

[0030] When it is necessary to install damping arms on blades, it is usually done in a low-temperature environment, that is, the location of the protrusion is cooled down, so that the shape memory alloy changes from austenitic to martensitic, making the protrusion softer and easier to embed into the sinker and form an interference fit.

[0031] When it is necessary to remove the blade self-damping arm, the area where the protrusion is located is usually cooled down so that the shape memory alloy at the protrusion changes from austenite to martensite, making the protrusion softer and easier to remove from the sinking groove and allow the damping arm to exit the reserved hole.

[0032] When fatigue damage to damping bosses needs to be repaired, the damaged area can be locally heated to transform the shape memory alloy material in that area from martensitic to austenitic. Utilizing the inherent shape memory effect of the material, the damaged area that has undergone plastic deformation can automatically recover to a pre-set "memory shape," thereby achieving self-repair of the structural shape.

[0033] Compared with existing technologies, the damping arm can be replaced separately, meaning that the blades and damping arm do not need to be replaced and removed at the same time. This simplifies the overall operation and maintenance process and allows the blades that can still operate stably to be retained, thereby achieving the technical goal of controlling the operation and maintenance costs of turbofan engines.

[0034] The technical solution adopted in this application also provides an aircraft, including the shape memory alloy turbofan engine proposed in any of the foregoing claims.

[0035] The beneficial effects of the aircraft provided in this embodiment are the same as those of the aforementioned shape memory alloy turbofan engine, and will not be repeated here. Attached Figure Description

[0036] To more clearly illustrate the technical solutions in the embodiments of this application, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0037] Figure 1 A three-dimensional structural schematic diagram of a shape memory alloy turbofan engine provided for an embodiment of this application;

[0038] Figure 2 for Figure 1 A magnified view of a portion of the middle circle A;

[0039] Figure 3 This is a three-dimensional structural diagram of the blade used in the embodiments of this application;

[0040] Figure 4 for Figure 3 Top view;

[0041] Figure 5 For along Figure 4 Cross-sectional view of the middle BB line;

[0042] Figure 6 This is a partial schematic diagram of the blade used in the embodiments of this application in cross-sectional view;

[0043] Figure 7 This is a three-dimensional structural diagram of the damping arm and gasket used in the embodiments of this application from an explosion perspective.

[0044] Figure 8 This is a schematic diagram of the exploded structure of the wheel used in the embodiments of this application;

[0045] Figure 9 This is a partially enlarged schematic diagram of the roulette wheel used in the embodiments of this application, viewed from an exploded perspective and in cross-section.

[0046] Explanation of reference numerals in the attached drawings: 1. Wheel; 11. Inner disc; 111. Inner groove; 112. Positioning screw; 113. Anti-loosening nut; 12. Outer disc; 121. Outer groove; 122. Alignment hole; 123. Docking groove; 124. Plug; 2. Blade; 21. Reserved hole; 22. Sinking groove; 23. Snap-fit ​​block; 24. Reinforcing plate; 3. Damping arm; 31. Protrusion; 32. Extension; 4. Gasket. Detailed Implementation

[0047] To make the technical problems, technical solutions, and beneficial effects to be solved by this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the scope of this application.

[0048] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0049] It should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do 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. Therefore, they should not be construed as limitations on this application.

[0050] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0051] Please refer to the following: Figures 1 to 9The shape memory alloy turbofan engine provided in this application will now be described. The shape memory alloy turbofan engine proposed in this application includes a rotor 1, multiple blades 2, and multiple damping arms 3.

[0052] The wheel 1 adopts a conventional disc-shaped structure, with its center coaxially connected to the output shaft of the engine to achieve automated rotation of the wheel 1.

[0053] Multiple blades 2 are arranged around the disk 1. Each blade 2 is connected to the outer peripheral surface of the disk 1 and extends outward along the radial direction of the disk 1. Specifically, the thickness direction of each blade 2 maintains a certain angle with the axial direction of the disk 1 so that when the blade 2 moves along a circular trajectory as the disk 1 rotates, it can achieve a corresponding air intake effect, thereby realizing the airflow supply to the inner and outer bypass ducts.

[0054] The blade 2 has a pre-drilled hole 21 at its center. When the blade 2 is assembled with the wheel 1, the axial direction of the pre-drilled hole 21 is perpendicular to the extension direction of the blade 2 and also perpendicular to the axial direction of the wheel 1. Furthermore, a recessed groove 22 is formed on the inner wall of the pre-drilled hole 21.

[0055] Multiple damping arms 3 correspond one-to-one with multiple blades 2. Each damping arm 3 is inserted into a corresponding reserved hole 21 to achieve initial positioning of the damping arm 3 and the blade 2. Based on this, each damping arm 3 has a protrusion 31 on its outer wall. This protrusion 31 can be embedded into a recessed groove 22 after initial positioning to achieve further positioning of the damping arm 3 and the corresponding blade 2.

[0056] It should be noted that, in order to achieve the insertion relationship between the damping arm 3 and the reserved hole 21, the damping arm 3 adopts a linear structure to fit the reserved hole 21 which runs through in a straight line. In addition, both the damping arm 3 and the protrusion 31 are made of shape memory alloy material, which is usually NiTiHf (nickel-titanium alloy) material, which has phase transformation properties, as well as softening properties in the martensitic direction and hardening properties in the austenitic direction.

[0057] Specifically, the phase transformation of shape memory alloys refers to the reversible transformation of their crystal structure between a highly symmetric austenite phase and a low-symmetric martensite phase under temperature. The martensite phase (low-temperature phase) exhibits softening characteristics due to the ease of twin boundary movement, meaning it is prone to significant deformation under external force. This allows the damping arm 3 to be inserted into the pre-drilled hole 21 without interference from the protrusion 31, which can then be embedded into the recessed groove 22, achieving a snap-fit ​​connection. On the other hand, the austenite phase (high-temperature phase), due to its robust crystal structure and high symmetry, allows the combined structure of the damping arm 3 and the protrusion 31 to regain rigidity, exhibiting hardening characteristics. This drives shape recovery and provides a large restoring force, achieving an interference fit between the protrusion 31 and the recessed groove 22.

[0058] When the blade 2 is connected to the wheel disk 1, the damping arm 3 is inserted into the reserved hole 21, and the protrusion 31 is embedded in the recessed groove 22, the ends of two adjacent damping arms 3 along the circumference of the wheel disk 1 are connected to dissipate the energy generated by vibration through frictional damping generated by the contact. Based on this, the end face of the damping arm 3 adopts a beveled structure to form a surface contact between the two damping arms 3, thereby increasing the contact area and ensuring the stability of the aforementioned energy dissipation process.

[0059] Unlike traditional NiTi alloys, the shape memory alloy proposed in this application uses NiTiHf because it also has excellent material properties. By adding hafnium (Hf) to NiTi, its transformation temperature is increased, enabling the device to be applied to different devices, such as drones and unmanned vehicles. In addition to meeting the requirements of relevant fields, it can also be applied to the automotive and aerospace fields.

[0060] The beneficial effect of the shape memory alloy turbofan engine provided in this embodiment is that the blade 2 and damping arm 3, which were originally connected as a single unit, are changed to a plug-in connection. Therefore, when the damping arm 3 suffers fatigue damage, it can be replaced separately.

[0061] When it is necessary to install the damping arm 3 on the blade 2, it is usually done in a low temperature environment, that is, the position of the protrusion 31 is cooled down, so that the shape memory alloy is transformed from austenitic to martensitic, thereby making the protrusion 31 softer and easier to be embedded into the sinker 22 and form an interference fit.

[0062] When it is necessary to remove the self-damping arm 3 of blade 2, the position of the protrusion 31 is usually cooled so that the shape memory alloy at the protrusion 31 changes from austenite to martensite, thereby making the protrusion 31 softer and easier to remove from the sink 22 and allow the damping arm 3 to exit the reserved hole 21.

[0063] When fatigue damage to damping bosses needs to be repaired, the damaged area can be locally heated to transform the shape memory alloy material in that area from martensitic to austenitic. Utilizing the inherent shape memory effect of the material, the damaged area that has undergone plastic deformation can automatically recover to a pre-set "memory shape," thereby achieving self-repair of the structural shape.

[0064] Compared with existing technologies, the damping arm 3 can be replaced separately, that is, the blade 2 and the damping arm 3 do not need to be replaced and removed at the same time. Therefore, it simplifies the operation and maintenance process of the whole machine and can also retain the blade 2 that can still operate stably, thereby achieving the technical goal of controlling the operation and maintenance cost of turbofan engine.

[0065] In some embodiments, such as Figure 2 and Figure 7As shown, the end of the damping arm 3 has an outwardly extending extension 32, and the outer surface of the extension 32 is aligned with the inclined structure (i.e., coplanar).

[0066] By adopting the above technical solution, when the ends of two adjacent damping arms 3 are connected along the circumference of the wheel disk 1, the two extensions 32 are connected to increase the contact area of ​​the two damping arms 3. Its function is the same as the purpose of adopting the inclined structure at the end of the damping arm 3, that is, to ensure the stability of the process of friction damping generated by the contact of the two damping arms 3 to consume the energy generated by vibration.

[0067] It should be noted that in this embodiment, the length and thickness of the epitaxial portion 32 are both limited. That is, the epitaxial portion 32 is also made of shape memory alloy. In the martensitic phase, the epitaxial portion 32 can be rolled inward to avoid interfering with the process of inserting the damping arm 3 into the reserved hole 21, and to ensure the orderly combination of the various structures of this device.

[0068] In some embodiments, such as Figure 3 , Figure 5 , Figure 6 and Figure 7 As shown, the sinking trough 22 extends circumferentially along the reserved hole 21 and is connected end to end to form a rectangular trough structure. Correspondingly, the protrusion 31 adopts an annular structure surrounding the damping arm 3 to be suitable for embedding into the sinking trough 22.

[0069] By adopting the above technical solution, the design of the protrusion 31 and the groove structure can increase the contact area, ensure the stability of the damping arm 3 after further positioning, and the stability of the damping arm 3 and the sinking groove 22 when they are interference fit.

[0070] In some embodiments, such as Figure 2 and Figure 7 As shown, a pad 4 is provided between the ends of two adjacent damping arms 3 along the circumference of the wheel 1. The friction coefficient between the pad 4 and the end face of the damping arm 3 is greater than the friction coefficient between the two damping arms 3.

[0071] By adopting the above technical solution, the application of shim 4 can increase the damping generated by friction, thereby consuming more vibration energy, reducing the impact of vibration energy on damping arm 3, and thus extending the service life of damping arm 3. On the other hand, as a low-cost (shape memory alloy) consumable part, shim 4 can be replaced separately to reduce the damage to the end of damping arm 3, extend the service life of damping arm 3, and further reduce the operation and maintenance cost of this device.

[0072] In some embodiments, such as Figure 1 , Figure 3 and Figure 8As shown, the end of the blade 2 facing the wheel 1 has a locking block 23; in this embodiment, the locking block 23 is T-shaped. Based on this, the wheel 1 includes an inner disc body 11 and an outer disc body 12.

[0073] The inner disc 11 is used to connect coaxially with the output shaft of the engine to realize the transmission of kinetic energy.

[0074] The outer disc 12 is coaxially disposed on one side of the inner disc 11 and is detachably connected to the inner disc 11. In this embodiment, the outer disc 12 is also used to connect to the output shaft of the engine to ensure the stability of the kinetic energy transmission process.

[0075] The inner disk 11 has a plurality of inner grooves 111 on the side facing the outer disk 12, each corresponding to a plurality of blades 2, and each inner groove 111 penetrates the outer peripheral surface of the inner disk 11; the outer disk 12 has a plurality of outer grooves 121 on the side facing the inner disk 11, each corresponding to a plurality of inner grooves 111, and each outer groove 121 penetrates the outer peripheral surface of the outer disk 12.

[0076] By adopting the above technical solution, when the inner disc 11 and the outer disc 12 are connected, the corresponding inner groove 111 and outer groove 121 are connected to form a combined cavity suitable for the insertion of the locking block 23. The combined cavity is adapted to the structure of the aforementioned locking block 23, that is, the cross section of the combined cavity is also T-shaped, so that after the locking block 23 is inserted into the combined cavity, it can restrict the movement of the blade 2 away from the central axis of the wheel 1.

[0077] In some embodiments, such as Figure 8 and Figure 9 As shown, the inner disc 11 has a positioning screw 112 extending toward the outer disc 12; the outer disc 12 has an alignment hole 122 suitable for the insertion of the positioning screw 112, and the insertion end of the positioning screw 112 is threadedly connected with an anti-loosening nut 113.

[0078] The anti-loosening nut 113 is used to abut against the side of the outer disc 12 facing away from the inner disc 11, so as to restrict the relative movement of the inner disc 11 and the outer disc 12 along the axial direction, thereby realizing the detachable connection between the inner disc 11 and the outer disc 12.

[0079] In some embodiments, such as Figure 8 and Figure 9 As shown, the outer disc 12 has a mating groove 123 on the side facing away from the inner disc 11, which is coaxially arranged with the alignment hole 122.

[0080] When the inner disc 11 and the outer disc 12 are connected, the end of the positioning screw 112 is in the mating groove 123; correspondingly, the anti-loosening nut 113 is also in the mating groove 123 and abuts against the bottom of the mating groove 123, so as to realize the hidden installation of the anti-loosening nut 113.

[0081] In some embodiments, such as Figure 8 and Figure 9 As shown, a plug 124 is embedded in the mating groove 123; the plug 124 is located on the side of the anti-loosening nut 113 facing the opening of the mating groove 123, so as to seal the opening of the mating groove 123, prevent dust and oil from adhering, and protect the internal components of the mating groove 123.

[0082] In some embodiments, such as Figure 1 and Figure 3 As shown, the connection between the blade 2 and the snap-fit ​​block 23 has an arc-shaped reinforcing plate 24.

[0083] When the snap-fit ​​block 23 is embedded in the aforementioned combined cavity, the reinforcing plate 24 is located outside the wheel 1 and is attached to the outer circumferential surface of the wheel 1.

[0084] By adopting the above technical solution, the reinforcing plate 24 can increase the contact area between the blade 2 and the wheel 1, ensuring the stability of the process in which the wheel 1 drives the blade 2 to move along the circular trajectory.

[0085] Furthermore, the two adjacent reinforcing plates 24 along the circumference of the wheel 1 will connect when the blade 2 is fixed to the wheel 1 to form a ring structure around the outer circumference of the wheel 1, thereby improving the overall structural strength and stability during operation.

[0086] Based on the same inventive concept, embodiments of this application also provide an aircraft including a turbofan engine made of shape memory alloy as proposed in any of the preceding claims.

[0087] The beneficial effects of the aircraft provided in this embodiment are the same as those of the aforementioned shape memory alloy turbofan engine, and will not be repeated here.

[0088] The above content is only a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions and improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A shape memory alloy turbofan engine, comprising a disk and a plurality of blades arranged around said disk; characterized in that, The blade has a pre-drilled hole at its center, the axis of which is perpendicular to the extension direction of the blade and also perpendicular to the axis of the wheel; and a recessed groove is formed on the inner wall of the pre-drilled hole. The turbofan engine also includes: Multiple damping arms, corresponding one-to-one with multiple blades, all adopt a linear structure and are made of shape memory alloy material; each damping arm is inserted into the corresponding reserved hole, and has a protrusion suitable for being embedded in the sinking groove, and the protrusion and the sinking groove are interference fit; When the blade is connected to the wheel disk, the damping arm is inserted into the reserved hole, and the protrusion is embedded in the sink groove, the ends of two adjacent damping arms along the circumference of the wheel disk are connected. The end face of the damping arm adopts a beveled structure to form a surface contact between the two damping arms.

2. The shape memory alloy turbofan engine as described in claim 1, characterized in that, The end of the damping arm has an outwardly extending extension, and the extension is aligned with the inclined surface structure. When the ends of two adjacent damping arms along the circumference of the wheel are connected, the two extensions are connected to increase the contact area of ​​the two damping arms.

3. The shape memory alloy turbofan engine as described in claim 1, characterized in that, The sinking groove extends circumferentially along the reserved hole and is connected end to end; the protrusion adopts an annular structure surrounding the damping arm to be suitable for embedding in the sinking groove.

4. The shape memory alloy turbofan engine as described in claim 1, characterized in that, A gasket is provided between the ends of two adjacent damping arms along the circumference of the wheel.

5. The shape memory alloy turbofan engine as described in claim 1, characterized in that, The blade has a locking block at one end facing the wheel, and the wheel includes: Inner disc body; and The outer disc body is coaxially disposed on one side of the inner disc body and is detachably connected to the inner disc body; The inner disk body has a plurality of inner grooves on the side facing the outer disk body that correspond one-to-one with the plurality of blades, and each inner groove penetrates the outer peripheral surface of the inner disk body; The outer disk body has a plurality of outer grooves on the side facing the inner disk body, each of which corresponds to one of the plurality of inner grooves and each of the outer grooves penetrates the outer peripheral surface of the outer disk body; When the inner disc and the outer disc are connected, the corresponding inner groove and the outer groove communicate to form a combined cavity suitable for the insertion of the snap-fit ​​block.

6. The shape memory alloy turbofan engine as described in claim 5, characterized in that, The inner disc has a positioning screw extending toward the outer disc; the outer disc has an alignment hole suitable for inserting the positioning screw, and the insertion end of the positioning screw is threaded with an anti-loosening nut. The anti-loosening nut is used to abut against the side of the outer disc body facing away from the inner disc body, so as to restrict the relative movement of the inner disc body and the outer disc body along the axial direction.

7. The shape memory alloy turbofan engine as described in claim 6, characterized in that, The outer disk body has a mating groove on the side facing away from the inner disk body, which is coaxially arranged with the alignment hole. When the inner disc and the outer disc are in contact, the end of the positioning screw is located in the mating groove; The anti-loosening nut is located inside the mating groove and abuts against the bottom of the mating groove.

8. The shape memory alloy turbofan engine as described in claim 7, characterized in that, A plug is embedded in the mating groove; the plug is located on the side of the anti-loosening nut facing the opening of the mating groove, so as to close the opening of the mating groove.

9. The shape memory alloy turbofan engine as described in claim 5, characterized in that, The connection between the blade and the snap-fit ​​block has an arc-shaped reinforcing plate; When the snap-fit ​​block is embedded in the combined cavity, the reinforcing plate is attached to the outer circumferential surface of the wheel, and two adjacent reinforcing plates are connected along the circumferential direction of the wheel.

10. An aircraft, characterized in that, The turbofan engine made of shape memory alloy, as described in any one of claims 1-9.

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