Shaft breaking device and shaft breaking simulation system

Abstract

The present invention relates to the technical field of shaft fracture simulation, and in particular to a shaft fracture device and a shaft fracture simulation system. The shaft fracture device comprises: an inner ring, comprising a ring body and a lug, wherein a shaft hole for the shaft to pass through is provided at the center of the ring body, the lug protrudes radially outward from the ring body, and a connecting hole is provided on the lug, and the connecting hole is connected with the shaft hole; and an outer ring, which is sleeved on the outside of the inner ring, and a containing unit is provided on the outer ring, and the containing unit comprises two liquid storage chambers and a partition chamber provided between the two liquid storage chambers, and the two liquid storage chambers are both used to contain corrosive liquid for corroding the shaft, and a guide hole is provided on the side wall of the two liquid storage chambers facing the partition chamber; wherein the lug is inserted into the partition chamber, and a relative radial displacement occurs with the outer ring during the rotation of the shaft, so that the connecting hole and the guide hole are switched from a mutually disconnected state to a mutually connected state. In this way, the simulation of the shaft fracture process can be realized, and there is no need to make too many modifications to the aircraft engine, which is conducive to reducing the cost of the shaft fracture simulation test.

Description

Technical Field

[0001] The invention relates to the technical field of rotating shaft fracture simulation, and in particular to a shaft breaking device and a shaft breaking simulation system. Background Art

[0002] The rotating shaft of an aircraft engine (such as the low-pressure shaft) may break during actual operation, causing accidents such as overspeed rupture of the turbine disk. In order to ensure flight safety, the maximum possible speed of the engine rotor in the event of a shaft breakage needs to be determined during engine design and certification, and it must be ensured that the speed does not exceed the rupture speed of the turbine disk.

[0003] The turbine shaft break test is an important means to determine the law of the rotor speed increase after the shaft breaks. In the related technology, the turbine shaft break test generally uses cutting to break the shaft, that is, using a tool made of hard material to cut the shaft to achieve shaft breaking. This method often requires a lot of modification to the structure of the aircraft engine in order to install the cutting mechanism and its control mechanism, which will increase the cost and complexity of the test. Summary of the invention

[0004] A technical problem to be solved by the present invention is to reduce the cost of axle breakage simulation test.

[0005] In order to solve the above technical problems, the present invention provides a first aspect of a shaft breaking device, comprising:

[0006] The inner ring includes a ring body and a lug, wherein the center of the ring body is provided with an axial hole for the rotating shaft to pass through, the lug protrudes radially outward from the ring body, and the lug is provided with a communicating hole, which is connected with the axial hole; and

[0007] The outer ring is sleeved on the outer part of the inner ring. The outer ring is provided with a containing unit. The containing unit includes two liquid storage chambers and a separation chamber provided between the two liquid storage chambers. The two liquid storage chambers are used to contain the corrosive liquid used to corrode the rotating shaft. The side walls of the two liquid storage chambers facing the separation chamber are provided with guide holes.

[0008] The lug is inserted into the separation cavity and undergoes relative radial displacement with the outer ring during the rotation of the shaft, so that the communicating hole and the guide hole are switched from a mutually disconnected state to a mutually connected state.

[0009] In some embodiments, the ring body includes a first ring body and a second ring body, and the first ring body and the second ring body are separated from each other.

[0010] In some embodiments, the communicating hole includes a first hole segment and a second hole segment, the first hole segment is connected to both of the two guide holes located on both sides of the lug, and the second hole segment is connected to the first hole segment and the shaft hole.

[0011] In some embodiments, at least two accommodating units are provided on the outer ring, the at least two accommodating units are spaced apart along the circumference of the outer ring, the at least two accommodating units are not connected to each other, and the lugs correspond to the accommodating units one by one.

[0012] In some embodiments, the shaft breaking device includes an elastic ring, which is arranged between the inner ring and the outer ring. The elastic ring is provided with an opening, and the lug is inserted into the separation cavity after passing through the opening.

[0013] In some embodiments, the elastic ring is coated with heat-generating powder.

[0014] In some embodiments, the shaft breaking device includes an elastic pad, which is disposed in the separation cavity and located radially outside the lug.

[0015] In some embodiments, the inner ring and / or the outer ring are made of diamond or tungsten-cobalt cemented carbide material.

[0016] A second aspect of the present invention provides a broken shaft simulation system, which includes a rotating shaft and also includes a broken shaft device according to an embodiment of the present invention.

[0017] In some embodiments, a groove is provided on the rotating shaft, and the shaft breaking device is arranged in the groove.

[0018] The shaft breaking device provided in the embodiment of the present invention can release a corrosive liquid to the shaft when the shaft speed reaches a certain value, and utilize the corrosion of the shaft by the corrosive liquid to reduce the strength of the shaft, so that the shaft can be easily broken at the corroded position, thereby simulating the shaft breaking process. Since the shaft breaking device provided in the embodiment of the present invention does not require excessive modification of the aircraft engine, it is conducive to reducing the cost of the shaft breaking simulation test.

[0019] Other features and advantages of the present invention will become apparent from the following detailed description of exemplary embodiments of the present invention with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0021] Figure 1 The figure is a schematic diagram of an aircraft engine in an embodiment of the present invention.

[0022] Figure 2 The installation process of the shaft breaking device on the rotating shaft in the embodiment of the present invention is shown.

[0023] Figure 3 It is a three-dimensional diagram of the shaft breaking device in an embodiment of the present invention.

[0024] Figure 4 It is a partial cross-sectional view of the shaft breaking device in an embodiment of the present invention.

[0025] Figure 5 It is a stereogram of the inner ring in the embodiment of the present invention.

[0026] Figure 6 Schematic diagram of a three-dimensional elastic ring in an embodiment of the present invention.

[0027] Figure 7 A partial three-dimensional schematic diagram of the outer ring in an embodiment of the present invention

[0028] Figure 8 It is a three-dimensional diagram of the elastic pad in the embodiment of the present invention.

[0029] Description of reference numerals:

[0030] 100, aircraft engine; 10, fan; 20, additional stage; 30, high-pressure compressor; 40, high-pressure turbine; 50, low-pressure turbine; 60, rotating shaft; 601, low-pressure shaft; 602, high-pressure shaft; 603, fan shaft; 90, groove;

[0031] 200. Shaft breaking device;

[0032] 1. Inner ring; 11. Ring body; 12. First ring body; 13. Second ring body; 14. Lug; 15. Connecting hole; 16. First hole section; 17. Second hole section; 18. Shaft hole; 19. Retaining edge;

[0033] 2. elastic ring; 21. opening; 22. ring segment;

[0034] 3. Outer ring; 31. Accommodation unit; 32. Liquid storage chamber; 33. Separation chamber; 34. Diversion hole;

[0035] 4. Elastic pad. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without carrying out creative work are within the scope of protection of the present invention.

[0037] Technologies, methods, and equipment known to ordinary technicians in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and equipment should be considered as part of the specification.

[0038] In the description of the present invention, it should be understood that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0039] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0040] Figure 1 The structure of the aircraft engine 100 in some embodiments is shown. Figure 1 In some embodiments, the aircraft engine 100 is a twin-rotor turbofan engine, which includes a fan 10, an increase stage 20, a high-pressure compressor 30, a high-pressure turbine 40, a low-pressure turbine 50, and a rotating shaft 60. The fan 10, the increase stage 20, the high-pressure compressor 30, the high-pressure turbine 40, and the low-pressure turbine 50 are arranged in sequence along the direction of the airflow through the aircraft engine 100, and are supported by the rotating shaft 60. The rotating shaft 60 includes a fan shaft 603, a high-pressure shaft 602, and a low-pressure shaft 601. The fan shaft 603 supports the fan 10 and the increase stage 20. The high-pressure shaft 602 supports the high-pressure compressor 30 and the high-pressure turbine 40. The low-pressure shaft 601 supports the low-pressure turbine 50. The low-pressure shaft 601 passes through the high-pressure shaft 602 and is connected to the fan shaft 603. The fan 10, the increase stage 20, the low-pressure turbine 50, and the low-pressure shaft 601 constitute a low-pressure rotor. The high-pressure compressor 30, the high-pressure turbine 40 and the high-pressure shaft 602 constitute a high-pressure rotor.

[0041] During operation, air flows through the fan 10, the increasing stage 20 and the high-pressure compressor 30 in sequence and then enters the combustion chamber (not shown in the figure). After the air compressed by the compressor enters the combustion chamber, it mixes with the injected fuel and burns to generate high-temperature and high-pressure gas. Thereafter, the air flows through the high-pressure turbine 40 and the low-pressure turbine 50 in sequence, expands and does work, pushing the high-pressure turbine 40 to rotate the high-pressure compressor 30 through the high-pressure shaft 602, and pushing the low-pressure turbine 50 to rotate the increasing stage 20 and the fan 10 through the low-pressure shaft 601, thereby partially converting the chemical energy of the fuel into mechanical energy.

[0042] In actual operation, the shaft 60 may break due to over-torque, resonance, fatigue, corrosion, material defects or manufacturing errors, which is called a shaft breakage accident. Figure 1In some embodiments, the low-pressure shaft 601 may be fractured at position I. Alternatively, in an embodiment not shown, the fracture may also occur at other positions of the low-pressure shaft 601, or on the fan shaft 603 and the high-pressure shaft 602.

[0043] Although the probability of a shaft break accident is small, once it occurs, it may lead to harmful consequences. For example, since one end of the shaft 60 is connected to the turbine as a drive and the other end is connected to the compressor as a load, when a shaft break accident occurs, the turbine and the compressor are instantly decoupled, while the turbine continues to be affected by the high-energy gas discharged from the combustion chamber. Therefore, in the absence of load, the turbine speed will rise rapidly. When the speed rises to a speed that exceeds the rupture speed of the turbine disk, the turbine disk is in danger of rupture. Turbine disk rupture is not allowed in the engine design requirements and airworthiness certification requirements. In order to ensure flight safety, in the engine design and certification, it is necessary to determine the maximum possible speed of the engine rotor when the shaft breaks, and ensure that the maximum possible speed does not exceed the rupture speed of the turbine disk to prevent the turbine disk from rupturing due to shaft breakage.

[0044] After the shaft 60 breaks, the characteristics of the turbine, compressor and combustion chamber will change greatly in an instant, the original equilibrium state will be broken, and the engine state will deviate far from the design point. Therefore, the speed prediction model based on the normal working state and the equilibrium equation cannot predict the turbine rotor speed after the shaft breaks. Therefore, it is necessary to establish a transient prediction model after the shaft breaks, and carry out corresponding tests to verify the model. The broken shaft simulation test can reveal the characteristic changes of components such as the turbine and compressor after the shaft breaks, the law of the rotor speed increase, and the effectiveness of the overspeed protection device.

[0045] Due to the high rotor speed and harsh working conditions, it is difficult to break the shaft directly by relying on the rotation of the rotor itself. It is necessary to use a shaft breaking device to process the shaft during the shaft breaking test to reduce the difficulty of the shaft breaking in the shaft breaking test.

[0046] In the related art, the shaft breaking device generally uses cutting to break the shaft, that is, a tool made of hard material is used to cut the shaft 60 to achieve shaft breaking. This method often requires a lot of modifications to the aircraft engine structure, such as the need for an external bracket to install the cutting mechanism and its control mechanism, and the need for additional connection lines to connect the engine control system to control the cutting mechanism to cut the shaft 60 when needed, but this will increase the cost and complexity of the test.

[0047] For the above situation, see Figure 2-7 The embodiment of the present invention provides a broken shaft device 200, which is convenient for simulating broken shaft conditions and requires no or only minimal changes to the existing structure of the aircraft engine 100, which is beneficial to reducing the cost and complexity of broken shaft testing.

[0048] like Figure 2-7 As shown, in some embodiments, the shaft breaking device 200 includes an inner ring 1 and an outer ring 3 .

[0049] The inner ring 1 includes a ring body 11 and a lug 14. A shaft hole 18 is provided at the center of the ring body 11 for the shaft 60 to pass through. The lug 14 protrudes radially outward from the ring body 11. A communication hole 15 is provided on the lug 14. The communication hole 15 is connected to the shaft hole 18.

[0050] The outer ring 3 is sleeved outside the inner ring 1, and a containing unit 31 is provided on the outer ring 3. The containing unit 31 includes two liquid storage chambers 32 and a separation chamber 33 provided between the two liquid storage chambers 32. The two liquid storage chambers 32 are used to contain the etching liquid used to corrode the rotating shaft 60. The side walls of the two liquid storage chambers 32 facing the separation chamber 33 are provided with guide holes 34.

[0051] The lug 14 is inserted into the partition cavity 33 and undergoes relative radial displacement with the outer ring 3 during the rotation of the shaft 60 , so that the communicating hole 15 and the guide hole 34 are switched from a disconnected state to a connected state.

[0052] In the above arrangement, the inner ring 1 and the outer ring 3 are arranged inside and outside, the separation cavity 33 on the outer ring 3 separates the two liquid storage cavities 32 in the same accommodating unit 31, and is connected to the corresponding two liquid storage cavities 32 through the guide hole 34, the lug 14 on the inner ring 1 is inserted into the separation cavity 33, and through the radial movement relative to the outer ring 3, the connection and disconnection of the guide hole 34 on the lug 14 and the two guide holes 34 on the outer ring 3 are controlled, thereby controlling whether the corrosive liquid in the liquid storage cavity 32 flows into the shaft hole 18 to corrode the rotating shaft 60.

[0053] Based on the above arrangement, the shaft breaking device 200 no longer uses cutting to break the rotating shaft 60, but instead reduces the difficulty of breaking the rotating shaft 60 by corroding the rotating shaft 60, so that during the shaft breaking simulation test, the rotating shaft 60 can be easily broken at the corroded position under the action of axial force, thereby realizing the simulation of the shaft breaking condition.

[0054] When in use, before the shaft breaking simulation test, the corrosive liquid can be injected into the liquid storage chamber 32 through the guide hole 34, and then the shaft breaking device 200 is assembled. Figure 4 When just assembled, the connecting hole 15 is located radially inside the guide hole 34, and the lug 14 seals the guide hole 34, so that the connecting hole 15 and the guide hole 34 are not connected to each other and are disconnected from each other. Therefore, in the initial state, the corrosive liquid in the liquid storage chamber 32 is sealed and will not flow out; afterwards, refer to Figure 2 , the assembled shaft breaking device 200 is axially sleeved onto the shaft 60 from one end of the shaft 60 (such as Figure 2As shown by the middle arrow), that is, the shaft 60 passes axially through the shaft hole 18 of the inner ring 1 of the shaft breaking device 200 to realize the assembly of the shaft 60 and the shaft breaking device 200; after the preparation work is ready, the shaft 60 starts to run. When a certain speed is reached, the shaft 60 produces a certain radial displacement under the action of centrifugal force. At this time, the inner ring 1 undergoes radial movement and radial deformation under the action of centrifugal load and temperature load, so that the lug 14 produces a radial displacement relative to the outer ring 3 and moves radially outward relative to the outer ring 3, so that the connecting hole 15 moves radially outward from the position located radially inside the guide hole 34 to a position at least partially aligned with the guide hole 34. At this time, the connecting hole 15 and the guide hole 34, which were originally not connected to each other, are connected to each other, and the corrosive liquid can flow out from the guide hole 34, and flow to the shaft hole 18 through the connecting hole 15, and spray onto the shaft 60, so that the shaft 60 is corroded in a very short time, and the strength is rapidly weakened, so that it can be broken at the corroded position under the action of the strong axial force of the turbine rotor.

[0055] It can be seen that the inner ring 1 and the outer ring 3 of the provided shaft breaking device 200 can cooperate with each other to control the guide hole 34 and the connecting hole 15 to switch from a disconnected state to a connected state during the rotation of the shaft 60, release the corrosive liquid, corrode the shaft 60, and easily break the shaft 60, thereby simulating the real state of the aircraft engine 100 and realizing the shaft breaking simulation, so as to conduct experimental research on the characteristic changes of the components under the shaft breaking state, the maximum possible speed of the turbine rotor and the effectiveness of the over-speed protection device, so as to provide a basis for the design and approval of the aircraft engine 100 and improve the structural reliability and working safety of the aircraft engine 100.

[0056] The provided shaft breaking device 200 is sleeved on the rotating shaft 60, and automatically controls the corrosion of the rotating shaft 60 during the rotation of the rotating shaft 60. No external bracket is required, and no control of the aircraft engine 100 control system is required. There is no need to set up additional connecting lines to connect the engine control system. Therefore, there is less modification to the aircraft engine 100, the installation is more convenient, the cost is lower, and the applicability is stronger.

[0057] Since the rotating shaft 60 is generally made of metal, the corrosive liquid used to corrode the rotating shaft 60 may be a liquid with strong metal corrosiveness.

[0058] In order to avoid the corrosion of the inner ring 1 and the outer ring 3 by the corrosive liquid, the inner ring 1 and the outer ring 3 can be made of corrosion-resistant materials, so that the inner ring 1 and the outer ring 3 will not be corroded and damaged due to contact with the corrosive liquid, so as to improve the structural reliability of the shaft breaking device 200. For example, in some embodiments, the inner ring 1 and the outer ring 3 are both made of diamond material. The inner ring 1 and the outer ring 3 made of diamond material have strong corrosion resistance and can effectively prevent the inner ring 1 and the outer ring 3 from being corroded by the corrosive liquid. In addition, the outer ring 3 and the inner ring 1 made of diamond material have high hardness, low thermal expansion coefficient, and are not easy to deform. In particular, when the inner ring 1 is made of diamond material, the thermal expansion coefficient is much smaller than the shaft 60. When the shaft 60 undergoes radial displacement under the action of centrifugal force, a large radial displacement can be generated under the drive of the shaft 60, which facilitates the lug 14 to move radially outward relative to the outer ring 3 to connect the guide hole 34 and the connecting hole 15. Of course, the inner and outer rings are not limited to diamond materials. For example, in other embodiments, the inner and outer rings can also be made of other corrosion-resistant materials such as tungsten-cobalt cemented carbide, which have high hardness and low thermal expansion coefficient. In addition, the materials of the inner ring 1 and the outer ring 3 can be the same or different.

[0059] See also Figure 4 In some embodiments, the connecting hole 15 includes a first hole segment 16 and a second hole segment 17, the first hole segment 16 is connected to the two guide holes 34 located on both sides of the lug 14, and the second hole segment 17 is connected to the first hole segment 16 and the shaft hole 18. Specifically, Figure 4 As shown, in some embodiments, the first hole segment 16 penetrates the lug 14 along the circumference of the ring body 11 to form a circumferential through hole; the second hole segment 17 extends along the radial direction of the ring body 11 to connect the first hole segment 16 and the shaft hole 18. In this way, when the lug 14 moves to the radial outside and is in position, the first hole segment 16 is at least partially aligned with the two guide holes 34 located on both sides of the lug 14 along the circumference of the ring body 11, the corrosive liquid in the two liquid storage chambers 32 located on both sides of the lug 14 along the circumference of the ring body 11 can flow into the first hole segment 16 through the corresponding two guide holes 34, and the corrosive liquid flowing into the first hole segment 16 can flow into the shaft hole 18 through the second hole segment 17, fall onto the rotating shaft 60, and corrode the rotating shaft 60.

[0060] In the above embodiments, the number of the accommodating units 31 provided on the outer ring 3 and including the partition chamber 33 and the two liquid storage chambers 32 may be one, two or more. When at least two accommodating units 31 are provided on the outer ring 3, the at least two accommodating units 31 may be spaced apart and distributed along the circumference of the outer ring 3, and the at least two accommodating units 31 are not connected to each other. The lugs 14 correspond to the accommodating units 31 one by one. For example, in some embodiments, two accommodating units 31 are provided on the outer ring 3, and the two accommodating units 31 are not connected to each other and are evenly distributed along the circumference of the outer ring 3. The two liquid storage chambers 32 in the same accommodating unit 31 are symmetrical about the partition chamber 33. At this time, four liquid storage chambers 32 and two partition chambers 33 are provided on the outer ring 3, wherein the four liquid storage chambers 32 are distributed in the four quadrants of the outer ring 3, that is, each quadrant is provided with a liquid storage chamber 32, and the two partition chambers 33 are opposite to each other; accordingly, the inner ring 1 includes two lugs 14, and the two lugs 14 correspond one-to-one to the two partition chambers 33. After assembly, the two lugs 14 are respectively inserted into the two partition chambers 33.

[0061] To facilitate radial movement of the inner ring 1, see Figure 5 In some embodiments, the ring body 11 includes a first ring body 12 and a second ring body 13, and the first ring body 12 and the second ring body 13 are separated from each other. Based on this, the ring body 11 is no longer an integrated structure, but a split structure, which makes it easier for the inner ring 1 to undergo radial displacement during the rotation of the shaft 60. This effect is more significant when the inner ring 1 is made of hard materials such as diamond.

[0062] like Figure 5 As shown, when the ring body 11 includes a first ring body 12 and a second ring body 13, and the inner ring 1 includes two lugs 14, the two lugs 14 can be respectively arranged on the first ring body 12 and the second ring body 13, so that the two lugs 14 move radially outward along with the ring bodies where they are located, respectively, to control the corresponding connecting holes 15 to be connected with the guide holes 34.

[0063] In the above embodiments, see Figure 5 , a rib 19 may be provided on the ring body 11, and the rib 19 cooperates with the axial end face of the outer ring 3 to limit the relative displacement between the inner ring 1 and the outer ring 3 in the axial direction. Figure 5 and Figure 3It can be seen that in some embodiments, the front and rear ends of the ring body 11 are provided with flanges 19, and the flanges 19 are folded outward from the ring body 11 to form flanges, and the flanges 19 at the front and rear ends of the ring body 11 are respectively clamped on the axial end surfaces of the outer ring 3 to achieve axial positioning of the inner and outer rings. More specifically, when the ring body 11 includes the first ring body 12 and the second ring body 13, the flanges 19 at the axial ends of the ring body 11 respectively include two flange sections located on the first ring body 12 and the second ring body 13, that is, the inner ring 1 includes four flange sections, two of which are located at the axial ends of the first ring body 12, and the other two are located at the axial two sections of the second ring body 13.

[0064] By providing the rib 19 , the relative axial displacement between the inner and outer rings can be limited, so that the inner ring 1 can move radially relative to the outer ring 3 more reliably.

[0065] Also, see Figure 4 , Figure 6 and Figure 8 In some embodiments, the shaft breaking device 200 includes not only the inner ring 1 and the outer ring 3, but also other components.

[0066] For example, refer to Figure 4 and Figure 6 In some embodiments, the shaft breaking device 200 includes an inner ring 1 and an outer ring 3, and also includes an elastic ring 2. The elastic ring 2 is arranged between the inner ring 1 and the outer ring 3. For example, when the inner ring 1 is provided with flanges 19 at both axial ends, the elastic ring 2 is arranged between the ring body 11, the flanges 19 and the outer ring 3, so as to achieve reliable installation between the inner and outer rings. In addition, the elastic ring 2 is provided with an opening 21, and the lug 14 is inserted into the partition cavity 33 after passing through the opening 21. Among them, the opening 21 corresponds to the lug 14 one by one, for example, see Figure 6 , and combined with Figure 3-5 It can be seen that, when the inner ring 1 includes two lugs 14, two openings 21 are correspondingly provided on the elastic ring 2, so that each lug 14 can pass through the corresponding opening 21 and be inserted into the corresponding partition cavity 33. Figure 6 In some embodiments, the two openings 21 penetrate the elastic ring 2 axially, so that the elastic ring 2 becomes a split structure, including two ring segments 22 independent of each other.

[0067] Since the elastic ring 2 is an elastic member and has elasticity, the elastic ring 2 will not affect the radial displacement of the inner ring 1. When the inner ring 1 is squeezed by the rotating shaft 60 and moves radially outward, the elastic ring 2 is squeezed and deformed radially, so that the inner ring 1 can move smoothly, and the guide hole 34 and the connecting hole 15 that were originally not connected to each other are connected. In addition, the elastic ring 2 provided can play a filling and buffering role, which is conducive to better matching and sealing between the inner and outer rings, and improves the working reliability of the broken shaft device 200. Among them, the elastic ring 2 can have a smaller elastic modulus and a larger thermal expansion coefficient, so that the elastic ring 2 can be greatly deformed when subjected to centrifugal loads and thermal loads, so that the lug 14 can move radially into place during the rotation of the rotating shaft 60, and the guide hole 34 and the connecting hole 15 that were originally not connected to each other are connected.

[0068] In some embodiments, the elastic ring 2 is coated with heat-generating powder, for example, the inner wall and / or outer wall of the elastic ring 2 is coated with heat-generating powder. In this way, the elastic ring 2 is more susceptible to heat than other components, so that the radial expansion effect can be more significant, so as to achieve the release of the corrosive liquid.

[0069] For example, see Figure 4 and Figure 8 In some embodiments, the shaft breaking device 200 includes an inner ring 1 and an outer ring 3, and also includes an elastic pad 4. The elastic pad 4 is arranged in the partition cavity 33 and is located radially outside the lug 14, that is, the elastic pad 4 is arranged between the radial outer wall of the partition cavity 33 and the lug 14. In this way, the elastic pad 4 can play a filling and buffering role without hindering the radial movement of the lug 14, so that the lug 14 and the partition cavity 33 are better matched and sealed, and the working reliability of the shaft breaking device 200 is improved. Among them, the elastic pad 4 can have a smaller elastic modulus, so that the elastic pad 4 can undergo a larger displacement under the action of the radial force, and better play a filling and buffering role without hindering the radial movement of the lug 14.

[0070] For example, see Figure 4 In some embodiments, the shaft breaking device 200 includes not only the inner ring 1 and the outer ring 3, but also the elastic ring 2 and the elastic pad 4. In this way, the inner and outer rings are filled and buffered by the elastic ring 2 and the elastic pad 4 at the same time, and the reliability of the shaft breaking device 200 is higher.

[0071] In summary, the shaft breaking device 200 provided in the embodiment of the present invention can reduce the difficulty of breaking the shaft 60 by controlling the release of corrosive liquid to the shaft 60, thereby enhancing the controllability of the shaft breaking simulation test, and has the characteristics of simple structure, easy installation, no need for control system control, and less modification to the engine structure.

[0072] The provided broken shaft device 200 is applied to a broken shaft simulation system and assembled with the rotating shaft 60, so that the engine state can be close to the actual operating state, and a more accurate simulation of the broken shaft condition can be achieved to obtain more accurate test results.

[0073] See also Figure 2 In some embodiments, a groove 90 is provided on the rotating shaft 60, and the shaft breaking device 200 is arranged in the groove 90. The groove 90 can be provided to facilitate the installation of the shaft breaking device 200 on the rotating shaft 60 by utilizing the limiting effect of the groove 90 on the shaft breaking device 200. On the other hand, it is also convenient to simulate the fracture of the predetermined position of the rotating shaft 60, further enhancing the controllability of the test, because the groove 90 can be provided at the preset fracture position of the rotating shaft 60, so that during the simulation test, the position where the shaft breaking device 200 corrodes the rotating shaft 60 is the preset fracture position of the rotating shaft 60, so that the rotating shaft 60 can be fractured at the preset fracture position as expected, so as to realize the simulation of shaft fracture under corresponding conditions and obtain the required test data.

[0074] In the case where the groove 90 corresponds to the preset fracture position, the preset fracture position of the shaft 60 can be determined before the shaft fracture simulation test, and then the groove 90 cooperating with the shaft breaking device 200 is provided at the preset fracture position before the engine is assembled. Figure 2 As shown, the shaft breaking device 200 is sleeved onto the shaft 60 from one end of the shaft 60 and moved into the groove 90 .

[0075] Among them, the rotating shaft 60 can be a low-pressure shaft 601, a high-pressure shaft 602 or a fan shaft 603. Of course, the rotating shaft 60 may no longer be the rotating shaft in the aircraft engine 100, but other rotating shafts with similar breaking requirements. In other words, the breaking shaft device 200 provided in the embodiment of the present invention is not limited to simulating the breaking shaft condition of the aircraft engine, but can also be used to simulate other mechanical equipment with similar breaking shaft requirements.

[0076] The above description is only an exemplary embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A shaft breaking device (200), characterized in that: include: The inner ring (1) comprises a ring body (11) and a lug (14), wherein a shaft hole (18) is provided at the center of the ring body (11) for the rotation shaft (60) to pass through, the lug (14) protrudes radially outward from the ring body (11), and a communication hole (15) is provided on the lug (14), and the communication hole (15) is communicated with the shaft hole (18); and An outer ring (3) is sleeved on the outside of the inner ring (1); a containing unit (31) is provided on the outer ring (3); the containing unit (31) comprises two liquid storage chambers (32) and a separation chamber (33) arranged between the two liquid storage chambers (32); the two liquid storage chambers (32) are both used to contain a corrosive liquid used to corrode the rotating shaft (60); and a guide hole (34) is provided on the side walls of the two liquid storage chambers (32) facing the separation chamber (33); The lug (14) is inserted into the partition cavity (33) and undergoes relative radial displacement with the outer ring (3) during the rotation of the rotating shaft (60), so that the connecting hole (15) and the guide hole (34) are switched from a non-connected state to a connected state.

2. The shaft breaking device (200) according to claim 1, characterized in that: The ring body (11) comprises a first ring body (12) and a second ring body (13), and the first ring body (12) and the second ring body (13) are separated from each other.

3. The shaft breaking device (200) according to claim 1, characterized in that: The connecting hole (15) comprises a first hole section (16) and a second hole section (17), wherein the first hole section (16) is connected to the two guide holes (34) located on both sides of the lug (14), and the second hole section (17) is connected to the first hole section (16) and the shaft hole (18).

4. The shaft breaking device (200) according to claim 1, characterized in that: At least two accommodating units (31) are provided on the outer ring (3), and the at least two accommodating units (31) are distributed at intervals along the circumference of the outer ring (3). The at least two accommodating units (31) are not connected to each other, and the lugs (14) correspond to the accommodating units (31) one by one.

5. The shaft breaking device (200) according to any one of claims 1 to 4, characterized in that: The shaft breaking device (200) comprises an elastic ring (2), wherein the elastic ring (2) is arranged between the inner ring (1) and the outer ring (3), and an opening (21) is provided on the elastic ring (2), and the lug (14) passes through the opening (21) and is inserted into the separation cavity (33).

6. The shaft breaking device (200) according to claim 5, characterized in that: The elastic ring (2) is coated with heat-generating powder.

7. The shaft breaking device (200) according to any one of claims 1 to 4, characterized in that: The shaft breaking device (200) comprises an elastic pad (4), which is arranged in the separation cavity (33) and located radially outside the lug (14).

8. The shaft breaking device (200) according to claim 1, characterized in that: The inner ring (1) and / or the outer ring (3) are made of diamond or tungsten-cobalt cemented carbide material.

9. A broken shaft simulation system, comprising a rotating shaft (60), characterized in that: It also comprises an axle breaking device (200) as described in any one of claims 1-8.

10. The broken axle simulation system according to claim 9, characterized in that: The rotating shaft (60) is provided with a groove (90), and the shaft breaking device (200) is arranged in the groove (90).

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