Blade shedding test device and method

Abstract

The present invention provides a blade shedding test device and method, and relates to the technical field of aero-engine testing. The blade shedding test device comprises a blade disc structure, a test chamber, a camera unit and an electromagnetic generating assembly. The blade disc structure is used to connect blades and drive the blades to rotate. The electromagnetic generating assembly comprises a solenoid mounted on the blade disc structure, and the solenoid is used to make at least part of the blade disc structure generate electromagnetic properties when energized, so as to adsorb and fix the blades on the blade disc structure, and if the solenoid is powered off, the electromagnetic force disappears, and the blades can be separated from the blade disc structure under the action of the rotating centrifugal force. Since the flying moment of the blades is controlled by the power on and off of the solenoid, the flying timing control is more accurate, and the solenoid is mounted on the blade disc structure, and generates magnetic attraction to the blades through the blade disc structure, and the solenoid will not cause unexpected effects on the flying of the blades, so that the flying control of the blades is more accurate.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine testing, and in particular to a blade shedding testing device and method. Background Art

[0002] When a fan blade out (FBO) failure event occurs, the FBO causes the fallen blade to rub against the casing, and at the same time generates a rotor non-collision lateral load. In severe cases, it may penetrate the containment casing, causing serious damage to the aircraft fuselage and threatening the safety of passengers. Therefore, the fan blade out test is a key assessment test for turbofan engines to pass airworthiness certification ( Figure 1 (Photo of the engine inclusive airworthiness verification test site). During the forward development of the engine, due to the high cost of the engine FBO test, it is often necessary to conduct a large number of component-level tests of single or multiple fan blades falling off on a rotating test bench.

[0003] The blade shedding test generally uses a crack of a certain depth prefabricated at the blade root. As the blade speed increases, the centrifugal force increases, causing the blade to break within a certain speed range. However, the relationship between the crack size and the speed of the blade breaking is unclear, and the uncertainty represented by processing errors, material property deviations, etc. makes it difficult to accurately control the blade breaking at the expected speed. It is often necessary to preset a relatively wide preset speed range, which cannot fully meet the relevant requirements of the airworthiness test. In addition, this type of test often uses the try and error method, that is, it usually starts from a more conservative cutting fracture notch and gradually increases. Multiple iterative disassembly and assembly are required during the test, resulting in a significant increase in the test cycle and cost, delaying the development process.

[0004] Another popular method of blade shedding test is to simulate the process of fan blade breaking and blasting by detonating the detonator pre-placed at the blade break by wired or wireless means. The advantage of this method is that it can respond relatively quickly, so that the blades can be broken at the expected position, speed and phase. However, due to the large uncertainty of the explosion, the posture of the blades flying off cannot be controlled. The fire and smoke generated by the explosion not only affect the observation and recording of the test, but also pose certain safety hazards. In addition, due to the control restrictions on explosives, laboratory-level blasting and flying technology research is greatly constrained.

[0005] At the same time, it is also found in the prior art that the blade can be locally heated to achieve the blade flying off. Simply put, the tenon root of the blade is heated, and the local area of ​​the tenon root is higher after heating. After the tensile strength of the blade decreases, it flies off under the action of centrifugal force. For composite blades, there is no obvious temperature increase to significantly change the characteristics of the material's ultimate tensile strength, so this method is not applicable. In addition, there is also an improved utility model patent similar to local heating. The difference is that a hollow cavity is designed at the root of the prefabricated blade, and the cavity is filled with hot melt adhesive. The hot melt adhesive solidifies at room temperature and provides a certain support at the preset fracture of the root of the blade. A heating device is pre-installed at the tenon root of the blade. When the high-speed rotating equipment drives the fan blade to accelerate to a preset speed and stabilize, the blade heating and flying device is started. Heat will be transferred from the tenon root to the hollow cavity at the preset fracture of the blade. When the hot melt adhesive is heated and melted, the tensile strength of the blade decreases, and the blade flies off from the tenon root fracture under the action of centrifugal force. However, the relationship between crack size, breakage speed, and hot melt adhesive strength is unclear, and the uncertainty represented by processing errors and material performance deviations makes it difficult to accurately control the blade breakage at the expected speed. It is often necessary to preset a relatively wide preset speed range, which cannot fully meet the relevant requirements of airworthiness tests. Similarly, multiple iterations of disassembly and assembly are required during the test, resulting in a significant increase in the test cycle and cost, delaying the development process.

[0006] Therefore, developing a test device or method that can more accurately implement the fly-off test is a problem that needs to be solved urgently in the current fly-off test. Summary of the invention

[0007] The object of the present invention is to provide a blade fly-off test device, which can perform a blade fly-off test more accurately.

[0008] Another object of the present invention is to provide a blade fly-off test method, which can perform a blade fly-off test more accurately.

[0009] The embodiments of the present invention can be implemented in the following ways:

[0010] A blade flying test device, the blade flying test device is used to perform a blade flying test; the blade flying test device comprises:

[0011] A blade disc structure, the blade disc structure is used to connect the blades and drive the blades to rotate;

[0012] A test chamber, wherein the blade disc structure is arranged in the test chamber, and the test chamber surrounds the outer periphery of the blade disc structure along the circumference of the blade disc structure to simulate a casing;

[0013] A camera unit, the camera unit is used to record the blade flying trajectory; and

[0014] An electromagnetic generating component, the electromagnetic generating component includes a solenoid installed on the blade disk structure, the solenoid is used to make at least part of the blade disk structure generate electromagnetic properties when power is turned on, so as to adsorb and fix the blades on the blade disk structure; and the solenoid is also used to make the blades detach from the blade disk structure under the action of rotating centrifugal force when power is turned off.

[0015] Optionally, the blade disk structure includes a blade disk body and a tenon piece, and the blade flying test device also includes a ferromagnetic fixing block, the blade disk body is provided with a snap-in groove, the tenon piece has a tenon protrusion snap-fitted with the snap-in groove, and the tenon piece is connected to the solenoid to generate electromagnetic properties when the solenoid is energized; the ferromagnetic fixing block is used to fix the blade, and the ferromagnetic fixing block is used to be fixed on the tenon piece by electromagnetic adsorption, and the ferromagnetic fixing block is also used to fly off with the blade when the solenoid is powered off.

[0016] Optionally, a first clamping portion is provided on the tenon piece, and a second clamping portion is provided on the ferromagnetic fixing block, the first clamping portion is used to clamp with the second clamping portion, and the clamping pre-tightening force of the first clamping portion and the second clamping portion is set to be smaller than the centrifugal force corresponding to the preset blade flying speed.

[0017] Optionally, the tenon piece has a prefabricated crack, and the prefabricated crack is used to be destroyed when the solenoid is powered off, so as to make the blade fly off.

[0018] Optionally, the tenon member has a first clamping block and a second clamping block, the first clamping block and the second clamping block are arranged on the tenon protrusion relatively, and the first clamping block and the second clamping block are used to clamp the ferromagnetic fixing block;

[0019] The prefabricated crack is provided at the connection between the first clamping block and the tenon protrusion.

[0020] Optionally, the prefabricated crack and the first clamping block are integrally formed on the tenon protrusion by 3D printing.

[0021] Optionally, the blade shedding test device further comprises a test cabin cover, wherein the test cabin cover is arranged outside the test cabin, and a through hole is provided at the center of the test cabin cover, and the camera unit is used for acquiring the blade shedding trajectory in the test cabin cover through the through hole.

[0022] Optionally, the blade flying test device also includes a driving member, a transmission shaft and a test bench load-bearing platform, and both ends of the transmission shaft are respectively connected to the driving member and the blade disk structure in a transmission manner to drive the blade disk structure to rotate under the drive of the driving member; the driving member is installed on the test bench load-bearing platform.

[0023] Optionally, the electromagnetic generating assembly further comprises a current controller, an energy device and a movable connection housing, wherein the current controller is electrically connected to the energy device to control the current intensity output by the energy device; the energy device is movably connected to the solenoid through the movable connection housing, so that when the solenoid rotates with the blade disk structure, the solenoid is powered through the movable connection housing;

[0024] The transmission shaft passes through the movable connection housing, and the movable connection housing is fixedly connected to the load-bearing platform of the test bench.

[0025] A blade flying off test method, the blade flying off test method comprising:

[0026] The electromagnetic adsorption force is calculated according to the preset fly-off speed, and the solenoid of the electromagnetic generating component is controlled to be energized so that at least part of the blade disc structure generates electromagnetic properties; wherein the solenoid is installed on the blade disc structure;

[0027] Installing a blade to be subjected to a fly-off test on the blade disk structure, and driving the blade to rotate via the blade disk structure;

[0028] When the rotation speed of the blade reaches the preset fly-off speed, the solenoid is controlled to be powered off, so that the blade is separated from the blade disk structure under the action of the rotating centrifugal force;

[0029] The flying trajectory of the blade is obtained by a camera unit; wherein the flying trajectory includes the process trajectory of the blade detaching from the blade disk structure to the blade collision test chamber; the test chamber is arranged outside the blade disk structure.

[0030] The blade fly-off test device and the blade fly-off test method provided by the embodiments of the present invention have the following beneficial effects:

[0031] The embodiment of the present invention provides a blade flying test device, which includes a blade disc structure, a test chamber, a camera unit and an electromagnetic generating assembly. The blade disc structure is used to connect the blades and drive the blades to rotate. The electromagnetic generating assembly includes a solenoid installed on the blade disc structure, and the solenoid is used to make at least part of the blade disc structure generate electromagnetic properties when powered on, so that the blades are adsorbed and fixed on the blade disc structure, and if the solenoid is powered off, the electromagnetic force disappears, and the blades can be separated from the blade disc structure under the action of the rotating centrifugal force. Since the flying moment of the blade is controlled by the power on and off of the solenoid, the timing of the flying is more accurately controlled, and the solenoid is installed on the blade disc structure, and the magnetic attraction force is generated on the blade through the blade disc structure. The solenoid will not cause unexpected effects on the flying of the blade, so that the flying control of the blade is more accurate. The test chamber is arranged around the outer periphery of the blade disc structure along the circumference of the blade disc structure, so that the test chamber simulates the casing, and the camera unit is used to record the blade flying trajectory. The blade flying trajectory can simulate the position where the blade flies off and hits the casing, thereby providing data for the casing design.

[0032] The embodiments of the present invention also provide a blade shedding test method, which has the beneficial effects of being able to more accurately control the blade shedding rotation speed and reduce the influence of external factors on the shedding posture. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties or features may have the same or similar reference numerals.

[0034] Figure 1 The site diagram of the engine inclusive airworthiness verification test is shown;

[0035] Figure 2 The overall structural schematic diagram of the blade flying-off test device provided according to one aspect of the present invention is shown;

[0036] Figure 3 A partial structural schematic diagram of a blade shedding test device provided according to one aspect of the present invention is shown;

[0037] Figure 4 Shows Figure 3 A magnified schematic diagram of the local structure at position Ⅰ in the middle;

[0038] Figure 5 It shows a schematic structural diagram of a blade disk structure provided according to one aspect of the present invention;

[0039] Figure 6A schematic structural diagram of a blade disk structure provided according to one aspect of the present invention is shown in another viewing angle;

[0040] Figure 7 A schematic diagram of the structure of the connection between the blade disk structure and the blades provided according to one aspect of the present invention is shown;

[0041] Figure 8 A schematic structural diagram of a tenon member in a blade fly-off test device provided according to one aspect of the present invention is shown;

[0042] Fig. 9 A schematic structural diagram of a tenon member in a blade fly-off test device provided according to one aspect of the present invention is shown from another perspective.

[0043] Reference numerals:

[0044] 10-blade flying test device; 100-blade disk structure; 110-blade disk body; 111-clamping groove; 120-tenon piece; 121-tenon protrusion; 122-first clamping block; 123-second clamping block; 124-first clamping part; 125-prefabricated crack; 130-ferromagnetic fixing block; 131-second clamping part; 140-iron core; 150-counterweight block; 200-electromagnetic generating assembly; 211-current controller; 212-energy device; 213-movable connecting shell; 214-solenoid; 311-driving member; 312-test bench load-bearing platform; 313-test bench vertical plate; 314-transmission shaft; 315-test cabin; 316-camera unit; 320-test cabin cover; 321-through hole; 20-blade. DETAILED DESCRIPTION

[0045] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0046] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0047] At the same time, it should be noted that the terms "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0048] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0049] Related terms:

[0050] Inclusiveness: In view of the serious consequences of non-inclusive incidents of aircraft engines, in addition to having good performance, the containment capacity of the engine casing must be considered when designing and manufacturing aircraft engines, that is, the fragments of the failed rotor must not penetrate the casing, causing secondary damage to the aircraft. In this regard, all major aviation countries attach great importance to the issue of engine containment. There are special provisions in the civil and military aircraft engine specifications to make strict provisions for containment, such as the US Federal Aviation Regulations (FAR-33) and the Engine Structural Integrity Program (MIL-STD-1783B); the UK "General Specifications for Aviation Gas Turbine Engines" (00-971); China's "Aircraft Engine Airworthiness Regulations" (CCAR-33) and "Inclusiveness Requirements for Aviation Turbine Engines" (GJB3366-1998). The relevant airworthiness clauses all stipulate that aircraft engines must pass the inclusiveness verification test to prove that they have inclusiveness in order to obtain an airworthiness certificate. At the end of the development of a certain type of engine, each commercial aircraft engine company will generally conduct an engine fan blade fly-off containment test according to airworthiness clauses to prove the engine's containment capability and obtain airworthiness certification. The whole-machine containment test is of milestone significance to engine development.

[0051] Figure 2 The overall structure diagram of the blade flying test device 10 provided in this embodiment is shown. Figure 3 FIG. 1 shows a partial structural schematic diagram of a blade flying test device 10 provided in this embodiment. Figure 4 for Figure 3 The enlarged schematic diagram of the local structure at point Ⅰ in the middle. Figure 5 The schematic diagram of the structure of the blade disk structure 100 provided in this embodiment is as follows: Figure 6 This is a schematic diagram of the structure of the blade disk structure 100 provided in this embodiment at another viewing angle. Figure 2-Figure 6The present embodiment provides a blade flying test device 10, which includes a blade disc structure 100, a test chamber 315, a camera unit 316 and an electromagnetic generating assembly 200. The blade disc structure 100 is used to connect the blade 20 and drive the blade 20 to rotate. The electromagnetic generating assembly 200 includes a solenoid 214 installed on the blade disc structure 100. The solenoid 214 is used to make at least part of the blade disc structure 100 generate electromagnetic properties when powered on, so as to adsorb and fix the blade 20 on the blade disc structure 100. If the solenoid 214 is powered off, the electromagnetic force disappears, and the blade 20 can be separated from the blade disc structure 100 under the action of the rotating centrifugal force. Since the flying moment of the blade 20 is controlled by the power on and off of the solenoid 214, the timing of the flying is more accurately controlled. Moreover, the solenoid 214 is installed on the blade disc structure 100, and the solenoid 214 will not cause unexpected effects on the flying of the blade 20, so that the flying control of the blade 20 is more accurate. The test chamber 315 is arranged around the circumference of the blade disk structure 100 and on the outer periphery of the blade disk structure 100, so that the test chamber 315 simulates the casing. The camera unit 316 is used to record the flying trajectory of the blade 20. The flying trajectory of the blade 20 can simulate the position where the blade 20 flies off and hits the casing, thereby providing data for the casing design.

[0052] It should be noted that in Figure 3 and Figure 4 The structure shown shows the structure when a single blade 20 is subjected to a fly-off test. When a single blade 20 is subjected to a fly-off test, in order to avoid the phenomenon of rotor misalignment caused by a single blade 20, a counterweight 150 is further provided in the blade fly-off test device 10 provided in this embodiment. When the blade 20 is not blown off, the rotation center of gravity is adjusted by the counterweight 150. Accordingly, in other embodiments, if a fly-off test of multiple blades 20 is conducted, for example, two blades, the two blades 20 can be relatively arranged on both sides of the blade disk structure 100, and in this case, the counterweight 150 does not need to be provided. In other words, in some other embodiments, the blade fly-off test device 10 may not include the counterweight 150.

[0053] The blade flying test device 10 further includes a test bench stand 313 , on which a test cabin 315 is fixedly mounted.

[0054] Figure 7 The schematic diagram of the structure of the connection between the blade disk structure 100 and the blade 20 provided in this embodiment is shown. Figure 2-Figure 7In this embodiment, the blade disc structure 100 includes a blade disc body 110 and a tenon piece 120, and the blade flying test device 10 also includes a ferromagnetic fixing block 130. A clamping groove 111 is provided on the blade disc body 110, and the tenon piece 120 has a tenon protrusion 121 clamped with the clamping groove 111, and the tenon piece 120 is connected to the solenoid 214. When the solenoid 214 is energized, the tenon piece 120 can generate an electromagnetic adsorption force, thereby fixing the ferromagnetic fixing block 130 by electromagnetic adsorption. In other words, in this embodiment, the tenon piece 120 and the solenoid 214 can be regarded as forming an electromagnet structure. The ferromagnetic fixing block 130 is used to fix the blade 20, and when the solenoid 214 is powered off, that is, when the tenon piece 120 loses its electromagnetic property, the ferromagnetic fixing block 130 flies off with the blade 20.

[0055] Specifically, the ferromagnetic fixing block 130 is fixedly connected to the blade 20 by a snap-on method, so that it is convenient to use a real blade 20 to perform a fly-off test, and at the same time, the ferromagnetic fixing block 130 can be used to achieve connection with various blades, so as to perform a fly-off test on various blades 20. It can be understood that in other embodiments, the connection between the ferromagnetic fixing block 130 and the blade 20 can also be achieved by the previous method, such as the ferromagnetic fixing block 130 is integrally formed and set on the blade 20, etc.

[0056] The blade disc structure 100 also includes an iron core 140, and the solenoid 214 is wound around the iron core 140, so as to be fixedly connected to the blade disc body 110. The solenoid 214, the iron core 140 and the tenon 120 are electromagnets together to generate magnetic attraction along the radial direction of the blade disc body 110. At the same time, after the tenon 120 is installed on the blade disc body 110, the solenoid 214 passes through the iron core 140 so that the tenon 120 can have electromagnetic properties when the solenoid 214 is energized. In order to make the electromagnet structure formed by the tenon 120 and the solenoid 214 demagnetize immediately after power is cut off, the tenon 120 is made of silicon steel material, so that the electromagnet structure has electromagnetic properties when power is turned on and disappears immediately after power is cut off. Optionally, the solenoid 214 is detachably connected to the blade disc body 110, so that the solenoid 214 can be replaced according to the required electromagnetic force.

[0057] Furthermore, a first locking portion 124 is provided on the tenon piece 120, and a second locking portion 131 is provided on the ferromagnetic fixing block 130. The first locking portion 124 is used to be engaged with the second locking portion 131, and the locking pre-tightening force between the first locking portion 124 and the second locking portion 131 is set to be smaller than the centrifugal force corresponding to the preset blade 20 flying rotation speed. Since the first engaging portion 124 and the second engaging portion 131 are engaged with each other, a certain engaging pre-tightening force can be applied to the ferromagnetic fixing block 130 to connect the ferromagnetic fixing block 130 to the tenon 120. Thus, on the one hand, when the blade 20 is rotating at a low speed and the centrifugal force it receives is less than the engaging pre-tightening force, it is not necessary to energize the solenoid 214. On the other hand, when the blade 20 is rotating at a high speed and the centrifugal force it receives is greater than the engaging pre-tightening force, the fixed connection between the ferromagnetic fixing block 130 and the tenon 120 depends on the superposition of the engaging pre-tightening force and the electromagnetic force. The engaging pre-tightening force can reduce the required electromagnetic force, thereby reducing the requirements for the solenoid 214. Moreover, the connection between the two is achieved by engaging, which is conducive to mass production and replacement.

[0058] It is understandable that in some other embodiments, the blades may be fixed to the blade disc body 110 only by electromagnetic adsorption force, and in this case, no additional mechanical connection structure is required between the tenon piece 120 and the ferromagnetic fixing block 130 .

[0059] Figure 8 FIG. 1 shows a schematic structural diagram of the tenon member 120 in the blade fly-off test device 10 provided in this embodiment. Fig. 9 FIG. 1 is a schematic diagram showing the structure of the tenon 120 in the blade fly-off test device 10 provided in this embodiment from another perspective. Figure 2-Figure 9 In the present embodiment, the tenon member 120 further includes a first clamping block 122 and a second clamping block 123 which are arranged opposite to each other. The first clamping block 122 and the second clamping block 123 are both fixedly connected to the tenon protrusion 121, so that a slot for clamping and fixing the ferromagnetic fixing block 130 is formed between the first clamping block 122 and the second clamping block 123. The slot serves as the first clamping portion 124. Correspondingly, the second clamping portion 131 is a protrusion arranged on the ferromagnetic fixing block 130. The protrusion of the ferromagnetic fixing block 130 is clamped and fixed by the joint action of the first clamping block 122 and the second clamping block 123, and a clamping pre-tightening force is applied to the ferromagnetic fixing block 130.

[0060] In this embodiment, the tenon 120 has a prefabricated crack 125, which is used to be destroyed when the solenoid 214 is powered off, so that the blade 20 can fly off. Optionally, the prefabricated crack 125 is provided at the connection between the first clamping block 122 and the tenon protrusion 121. Therefore, in this embodiment, the mutual engagement of the first engaging portion 124 and the second engaging portion 131 can apply a pre-tightening force to the ferromagnetic fixing block 130, which is the maximum force that the prefabricated crack 125 can withstand. Figure 8 and Fig. 9 The structure shown is the structure after the prefabricated crack 125 is destroyed and the first clamping block 122 is separated from the tenon protrusion 121.

[0061] In this embodiment, the blade flying test device 10 realizes the connection between the ferromagnetic fixing block 130 and the tenon 120 through the combined action of the electromagnetic adsorption force and the snap-fit ​​preload force applied by the snap-fit ​​structure. On the one hand, under the condition of low rotation speed, it is not necessary to energize the solenoid 214 to form an electromagnet to generate the electromagnetic adsorption force to fix the blade 20; and as the rotation speed increases, the centrifugal force becomes larger, and the snap-fit ​​preload force alone cannot resist the blade pulling force. At this time, the solenoid 214 can be energized, and the electromagnetic adsorption force and the snap-fit ​​preload force can jointly resist the blade pulling force to prevent the blade 20 from flying off. However, when the blade flying test is to be carried out, it is only necessary to control the solenoid 214 to be powered off and demagnetized instantly. At this time, the centrifugal force is greater than the snap-fit ​​preload force, and the ferromagnetic fixing block 130 and the blade fixed thereon can fly off along the prefabricated crack 125, and the flying trajectory is controllable. Moreover, under this structure, the contact area between the tenon piece 120 and the ferromagnetic fixing block 130 can be effectively increased, thereby helping to enhance the magnetic attraction force exerted by the tenon piece 120 on the ferromagnetic fixing block 130 .

[0062] When the solenoid 214 loses power, the tenon piece 120 is immediately demagnetized, and the ferromagnetic fixing block 130 cannot maintain its fixation on the tenon piece 120 by relying on the clamping pre-tightening force. At this time, the prefabricated crack 125 is destroyed, and the first clamping block 122 is separated from the tenon protrusion 121. In this way, the clamping effect between the first clamping part 124 and the second clamping part 131 disappears, and the ferromagnetic fixing block 130 flies off with the blade 20.

[0063] Furthermore, the prefabricated crack 125 and the first clamping block 122 are integrally formed on the tenon protrusion 121 by 3D printing. Specifically, the tenon protrusion 121 can be manufactured by a low-cost mold casting process, and then the prefabricated crack 125 and the first clamping block 122 are integrally processed on the tenon protrusion 121 by metal 3D printing technology according to the pre-calculated structural strength, so as to form the tenon part 120. After the tenon part 120 manufactured in this way is subjected to a fly-off test and the prefabricated crack 125 is destroyed, the tenon part 120 (i.e. Figure 8 and Fig. 9The required prefabricated crack 125 and the first clamping block 122 are re-printed and manufactured by metal 3D printing technology on the structure after removing the first clamping block 122 as shown in the figure.

[0064] Please continue to refer to Figure 2-Figure 6 In this embodiment, the blade flying test device 10 also includes a driving member 311, a transmission shaft 314 and a test bench load-bearing platform 312. The two ends of the transmission shaft 314 are respectively connected to the driving member 311 and the blade disk structure 100, so that the transmission shaft 314 drives the blade disk structure 100 to rotate under the driving action of the driving member 311. The driving member 311 is installed on the test bench load-bearing platform 312. Specifically, the driving member 311 is a motor, and the motor is supported by the test bench load-bearing platform 312, so that the motor is coaxially arranged with the transmission shaft 314 and the blade disk structure 100. The axial direction of the transmission shaft 314 (i.e. Figure 2 The A direction in the figure is the rotation axis direction of the blade disk structure 100. The test bench vertical plate 313 is installed at one end of the test bench load-bearing platform 312, and the transmission shaft 314 passes through the test bench vertical plate 313, and the transmission shaft 314 can be rotatably supported by the test bench vertical plate 313.

[0065] In this embodiment, the electromagnetic generating assembly 200 further includes a current controller 211, an energy device 212, and a movable connection housing 213. The current controller 211 is electrically connected to the energy device 212, so that the current intensity output by the energy device 212 is controlled by the current controller 211. Specifically, the current intensity for generating the required electromagnetic force can be calculated according to the preset fly-off speed, and then the energy device 212 is controlled by the current controller 211 to output the current at the current intensity. The energy device 212 is movably connected to the solenoid 214 through the movable connection housing 213, so that when the solenoid 214 rotates with the blade disk structure 100, the solenoid 214 can be continuously colinear through the movable connection housing 213.

[0066] Specifically, the transmission shaft 314 is inserted into the movable connection housing 213, so that the movable connection housing 213 is coaxially arranged with the transmission shaft 314, and accordingly, the solenoid 214 coaxially rotating with the transmission shaft 314 is arranged together with the movable connection housing 213. The movable connection housing 213 is fixedly connected to the test bench load-bearing platform 312, so that the movable connection housing 213 is supported by the test bench load-bearing platform 312. The movable connection housing 213 can realize the rotation conduction of the solenoid 214, so as to avoid the wires of the solenoid 214 and the movable connection housing 213 being entangled on the transmission shaft 314 during the rotation of the solenoid 214. The specific structure of the movable connection housing 213 includes but is not limited to a high-speed slip ring (not shown in the figure), and the electrical connection during the rotation of the solenoid 214 is realized by the high-speed slip ring.

[0067] Specifically, the magnitude of the electromagnetic adsorption force generated by the electromagnet can be calculated according to the following formula:

[0068]

[0069] Among them, μ 0 =4π·10 -7 is the electromagnetic constant; I is the current in amperes; W is the number of turns of the solenoid 214; A is the contact area in square meters; δ is the length of the air gap in meters. The unit of the magnetic attraction is Newton.

[0070] According to the above formula, it is not difficult to find that the magnitude of the electromagnetic adsorption force (also referred to as magnetic attraction force) is positively correlated with the magnitude of the current. This theory lays the foundation for realizing the control of the electromagnetic magnetic attraction force by designing a control device. The energy device 212 can be an external energy source with a strong output current, and the magnitude of the current output to the solenoid 214 can be accurately controlled by the current controller 211.

[0071] The following is an example of the data of the blade flying off test with a mass of 1.8KG and a length of 0.26 meters. At the same time, in this flying off test, the preset flying off speed is 20000r / s. Correspondingly, the centrifugal force it is subjected to when reaching the preset flying off speed is 4.9348*10^5N. According to the above formula, when the solenoid 214 with a design number of turns of 500, the current of 10A, and the air gap length of 0.0001 meters is used, the magnetic force generated by the electromagnet can just balance the centrifugal force of the blade, so this detailed design parameter supports the feasibility of the device. If you want the blade not to fly off, just ensure that the magnetic attraction force is much greater than the centrifugal force of the blade. Table 1 below shows the setting parameters when it is fixed only by electromagnetic adsorption force (that is, the preload force is 0) and when it is fixed by electromagnetic adsorption force and the clamping preload force (that is, the preload force is not 0).

[0072] Table 1

[0073]

[0074] Please continue to refer to Figure 2-Figure 6 In this embodiment, the blade flying test device 10 also includes a test cabin cover 320, and the test cabin cover 320 is arranged outside the test cabin 315. In this way, the test cabin cover 320 limits the scope of the flying test to prevent the damaged parts from flying out and injuring the experimenters after the blade 20 flies off. At the same time, a through hole 321 is arranged at the center of the test cabin cover 320, and the camera unit 316 is arranged opposite to the through hole 321, so that the trajectory of the blade 20 flying off in the test cabin cover can be obtained through the through hole 321. Optionally, the test cabin cover 320 and the test cabin 315 can be set as an integrated structure.

[0075] The embodiment of the present invention further provides a blade fly-off test method, which can be implemented according to the blade fly-off test device 10 described above. Specifically, the blade fly-off test method includes:

[0076] S01: Calculate and obtain electromagnetic adsorption force according to a preset fly-off rotation speed, and control the solenoid 214 of the electromagnetic generating assembly 200 to be energized so that at least part of the blade disc structure 100 generates electromagnetic properties; wherein the solenoid 214 is installed on the blade disc structure 100 .

[0077] The required electromagnetic adsorption force is calculated according to the preset fly-off speed. Since the centrifugal force generated by the preset fly-off speed is counteracted by the clamping preload force and the electromagnetic adsorption force in the above-mentioned blade fly-off test device 10, the electromagnetic adsorption force can be set to a value greater than the centrifugal force minus the clamping preload force. Meanwhile, in other embodiments, if only the electromagnetic adsorption force is used to counteract the centrifugal force generated by the preset fly-off speed, the electromagnetic adsorption force is set to a value greater than the centrifugal force.

[0078] After the required electromagnetic adsorption force is calculated, the current intensity required to generate the electromagnetic adsorption force can be calculated according to the above formula, and then when the solenoid 214 is energized through the energy device 212, the current controller 211 controls the energy device 212 to output a current with a corresponding current intensity.

[0079] S02: Install the blade to be subjected to the flying-off test on the blade disk structure 100, and drive the blade to rotate via the blade disk structure 100.

[0080] The blade is installed on the ferromagnetic fixing block 130, and the tenon piece 120 is fixed on the blade disk body 110. The ferromagnetic fixing block 130 is connected to the tenon piece 120 through the joint action of the first clamping part 124 and the second clamping part 131, thereby realizing the installation of the blade on the blade disk structure 100.

[0081] Since the tenon 120 in the blade flying device provided in this embodiment can apply a certain clamping pre-tightening force to the ferromagnetic fixing block 130, the connection between the tenon 120 and the ferromagnetic fixing block 130 can be achieved when the solenoid 214 is not energized, so step S02 can be performed before step S01. Accordingly, the execution order between step S01 and step S02 can also be set according to demand, for example, step S01 is executed first, and then step S02 is executed, or step S01 and step S02 are executed simultaneously.

[0082] S03: When the rotation speed of the blade reaches the preset flying speed, the solenoid 214 is controlled to be powered off, and the blade is separated from the blade disk structure 100 under the action of the rotating centrifugal force.

[0083] When the rotation speed of the blade reaches the preset flying speed, that is, the blade state meets the flying test requirements, the current controller 211 controls the energy device 212 to cut off the current, the solenoid 214 is powered off, and the electromagnet is demagnetized immediately. At this time, the clamping pre-tightening force alone is difficult to resist the centrifugal force, and the prefabricated crack 125 is damaged. At the same time, the blade and the ferromagnetic fixing block 130 connected thereto fly off under the action of the rotating centrifugal force.

[0084] S04: The flying trajectory of the blade is acquired through the camera unit 316 .

[0085] During step S03 , the camera unit 316 performs camera recording to record the blade's flying trajectory, which includes the process trajectory from the blade's separation from the blade disk structure 100 to the blade's collision with the test chamber 315 .

[0086] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A blade fly-off test device, the blade fly-off test device is used to perform a blade fly-off test; characterized in that: The blade flying test device comprises: A blade disc structure, the blade disc structure is used to connect the blades and drive the blades to rotate; A test chamber, wherein the blade disc structure is arranged in the test chamber, and the test chamber surrounds the outer periphery of the blade disc structure along the circumference of the blade disc structure to simulate a casing; A camera unit, the camera unit is used to record the blade flying trajectory; and An electromagnetic generating component, the electromagnetic generating component includes a solenoid installed on the blade disk structure, the solenoid is used to make at least part of the blade disk structure generate electromagnetic properties when power is turned on, so as to adsorb and fix the blades on the blade disk structure; and the solenoid is also used to make the blades detach from the blade disk structure under the action of rotating centrifugal force when power is turned off.

2. The blade flying test device according to claim 1, characterized in that: The blade disc structure includes a blade disc body and a tenon piece, and the blade flying-off test device also includes a ferromagnetic fixing block. The blade disc body is provided with a clamping groove, and the tenon piece has a tenon protrusion clamped with the clamping groove, and the tenon piece is connected to the solenoid to generate electromagnetic properties when the solenoid is energized; the ferromagnetic fixing block is used to fix the blade, and the ferromagnetic fixing block is used to be fixed on the tenon piece by electromagnetic adsorption, and the ferromagnetic fixing block is also used to fly off with the blade when the solenoid is powered off.

3. The blade flying test device according to claim 2, characterized in that: A first clamping part is provided on the tenon piece, and a second clamping part is provided on the ferromagnetic fixing block. The first clamping part is used to clamp with the second clamping part, and the clamping pre-tightening force of the first clamping part and the second clamping part is set to be smaller than the centrifugal force corresponding to the preset blade flying rotation speed.

4. The blade flying test device according to claim 2, characterized in that: The tenon piece has a prefabricated crack, which is used to break when the solenoid is de-energized to make the blade fly off.

5. The blade flying test device according to claim 4, characterized in that: The tenon member has a first clamping block and a second clamping block, the first clamping block and the second clamping block are arranged on the tenon protrusion opposite to each other, and the first clamping block and the second clamping block are used to clamp the ferromagnetic fixing block; The prefabricated crack is provided at the connection between the first clamping block and the tenon protrusion.

6. The blade flying test device according to claim 5, characterized in that: The prefabricated crack and the first clamping block are integrally formed on the tenon protrusion through 3D printing.

7. The blade flying test device according to claim 1, characterized in that: The blade shedding test device further comprises a test cabin cover, which is arranged outside the test cabin and has a through hole at its center, and the camera unit is used to obtain the blade shedding trajectory in the test cabin cover through the through hole.

8. The blade flying test device according to claim 1, characterized in that: The blade flying test device also includes a driving member, a transmission shaft and a test bench load-bearing platform. The two ends of the transmission shaft are respectively connected to the driving member and the blade disk structure for driving, so as to drive the blade disk structure to rotate under the drive of the driving member; the driving member is installed on the test bench load-bearing platform.

9. The blade flying test device according to claim 8, characterized in that: The electromagnetic generating assembly further includes a current controller, an energy device and a movable connection housing, wherein the current controller is electrically connected to the energy device to control the current intensity output by the energy device; The energy device is movably connected to the solenoid through the movably connected housing, so that when the solenoid rotates with the blade disk structure, the solenoid is powered through the movably connected housing; The transmission shaft passes through the movable connection housing, and the movable connection housing is fixedly connected to the load-bearing platform of the test bench.

10. A blade flying test method, characterized in that: The blade flying test method comprises: The electromagnetic adsorption force is calculated according to the preset fly-off speed, and the solenoid of the electromagnetic generating component is controlled to be energized so that at least part of the blade disc structure generates electromagnetic properties; wherein the solenoid is installed on the blade disc structure; Installing a blade to be subjected to a fly-off test on the blade disk structure, and driving the blade to rotate via the blade disk structure; When the rotation speed of the blade reaches the preset fly-off speed, the solenoid is controlled to be powered off, so that the blade is separated from the blade disk structure under the action of the rotating centrifugal force; The flying trajectory of the blade is obtained by a camera unit; wherein the flying trajectory includes the process trajectory of the blade detaching from the blade disk structure to the blade collision test chamber; the test chamber is arranged outside the blade disk structure.

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