Rotor blade flying-off device

Abstract

The rotor blade fly-off device of the present invention comprises: a rotating shaft; the rotor disc is mounted on the rotating shaft and rotates coaxially with the rotating shaft; the simulation blades are arranged in the circumferential direction of the rotor disc and fly off under the action of centrifugal force of rotation of the rotor disc; the blade flying-off control movable block is arranged in the open hole of the rotor disc and can move along the axial direction of the open hole so as to control flying-off of the simulation blade; the blade limiting block is connected with the blade flying-off control movable block and is used for limiting the simulation blade; the locking block is mounted in the open hole of the rotor disc through a spring and abuts against the blade limiting block; the blade sliding guide frame is fixed on the rotor disc and is used for accommodating the simulation blade so as to guide the flying off of the simulation blade; the electromagnet and the rotor disc are arranged in the circumferential direction of the rotor disc in a spaced mode, when the electromagnet is powered on, the electromagnet generates electromagnetic force so as to trigger the blade flying-off control movable block on the rotor disc to move, and then the simulation blade is released.

Description

Technical Field

[0001] The invention belongs to the field of aviation engines, relates to the technical field of turbofan engine fan blade simulation test, and in particular to a rotor blade flying-off device. Background Art

[0002] The "Blade Containment and Rotor Imbalance Test" clause in the "Aircraft Engine Airworthiness Regulations" CCAR33.94 stipulates that aircraft engines need to undergo blade shedding tests. The blade shedding technology mainly includes the control of the shedding speed, the control of the shedding quality, and the stability of the shedding control technology.

[0003] Patent document 1 discloses a sudden unbalance application device for simulating blade flying off, in which the flying blade and the counterweight blade are installed on the overall fixing system through the blade clamping system, and the control drive system is installed on the overall fixing system, and can control the tongue and groove state of the flying blade of the blade clamping system, so as to control the blade flying off, and it uses a preload spring as a driving device, and after the fork-shaped slider moves a certain distance, the preload drive spring quickly releases the elastic force along the guide rail direction, so that the blade tongue and groove are quickly opened, and the blade flying off is quickly controlled. There is neither strong collision nor plastic deformation between the parts during the opening of the blade tongue and groove, so that repeated experiments can be carried out without damage to the sudden unbalance device.

[0004] Patent document 2 discloses an engine fan blade flying-off test device and method based on inertial restrained explosive cutting. A flexible explosive cord is pre-embedded along the blade body surface at the predetermined fracture section of the blade, and a heavy metal back skin is covered on the outside of the explosive cord to inertially restrain the explosion energy, so that the detonation wave and explosion gas pressure generated by the explosion act vertically on the blade surface to penetrate inward, and after local penetration damage occurs, the blade breaks and flies off in the damaged area under the action of the rotating centrifugal force.

[0005] Patent document 3 discloses a turbine blade with a customized fly-off fracture position and fly-off fracture speed, wherein the turbine blade has a reduced cross-sectional area by symmetrically setting a recessed portion at the root portion. Due to the notch effect, a stress concentration area is formed, which creates a weak link of structural fatigue, thereby reducing the fly-off fracture critical speed of the turbine blade and making it lower than the critical rupture speed of the wheel disc, so that the turbine blade flies off and breaks before the wheel disc.

[0006] Prior art literature

[0007] Patent Literature

[0008] Patent document 1: CN113280979A

[0009] Patent document 2: CN115372010B

[0010] Patent Document 3: CN109139123B Summary of the Invention

[0011] Technical problem to be solved by the present invention

[0012] In the technology related to Patent Document 1, a mechanical structure designed based on centrifugal force is used to achieve the control of blade fly-off. However, when conducting simulation tests with relatively low rotational speeds and low fly-off masses, since the centrifugal force received by the simulated fly-off blade is small at this time, and when the rotational speed changes within a certain range, the change in centrifugal force is not obvious. Therefore, it is difficult to accurately control the fly-off rotational speed under such working conditions. Moreover, the addition of the mechanical control structure will bring a large additional mass to the rotor system, thereby changing the original design state of the rotor system.

[0013] In the technology related to Patent Document 2, a flexible explosive cord is buried at a specified position. When the fan rotor reaches the specified rotational speed, it is detonated to make the fan blade fly off. Although this technology can be detonated at the specified rotational speed, the accuracy of mass control for the fly-off blade is relatively poor, and the impact generated by the explosion may form a large interference to the load measurement after fly-off. In addition, the explosive also has a certain degree of danger and is relatively troublesome to implement. Moreover, the explosive blasting scheme also has a certain degree of destructiveness, and the repeatability of the test is relatively poor.

[0014] In the technology related to Patent Document 3, the fly-off of the blade is achieved through the pre-set crack technology. Although this technology can control the fly-off mass, the control accuracy of the fly-off rotational speed is insufficient, and premature fly-off often occurs. The reason is that the fly-off of the blade is not a static tension. The blade also bears alternating stresses generated by vibration, etc. during rotation. This kind of stress is difficult to accurately estimate. When pre-setting the crack, if only the action of centrifugal force is considered, it is easy to make the strength of the reserved connection part insufficient, resulting in fracture and fly-off before reaching the expected rotational speed. On the contrary, if too much is reserved, it may lead to the situation of non-fly-off at the expected rotational speed.

[0015] The present invention is completed to solve the above problems, and its purpose is to provide a rotor blade fly-off device that can accurately control the fly-off rotational speed and fly-off mass, improve the safety of the fly-off experiment, reduce the cost of the fly-off test, and enable the fly-off test to have good repeatability.

[0016] Technical solution for solving the technical problem

[0017] According to an embodiment of the present disclosure, there is provided a rotor blade detachment device, characterized by comprising: a rotating shaft; a rotor disk, which is mounted on the rotating shaft and rotates coaxially with the rotating shaft; a simulated blade, which is arranged in the circumferential direction of the rotor disk and detaches under the action of the centrifugal force generated by the rotation of the rotor disk; a blade detachment control slider, which is installed in an opening of the rotor disk and can move axially along the opening to control the detachment of the simulated blade; a blade limiting block, which is connected to the blade detachment control slider to limit the simulated blade; a locking block, which is installed in the opening of the rotor disk via a spring and abuts against the blade limiting block; a blade sliding guide frame, which is fixed on the rotor disk and houses the simulated blade to guide the detachment of the simulated blade; and an electromagnet, which is arranged at an interval from the rotor disk in the circumferential direction of the rotor disk, and when the electromagnet is energized, the electromagnet generates an electromagnetic force to trigger the movement of the blade detachment control slider on the rotor disk, thereby releasing the simulated blade.

[0018] Further, if the electromagnetic force generated by the electromagnet is set as F1, the centrifugal force when the simulated blade detaches is set as F2, and the friction coefficient between the blade limiting block and the simulated blade is set as μ, then F1 > μF2.

[0019] Further, there are 2 simulated blades, one is arranged on one end side in the circumferential direction of the rotor disk, and the other is arranged on the opposite end side in the circumferential direction of the rotor disk.

[0020] Further, the locking block has an opening. When the opening faces the side of the simulated blade, the locking block can move axially along the opening. When the opening faces the side of the detachment control slider, the locking block cannot move axially along the opening.

[0021] Further, for the simulated blade arranged on one end side in the circumferential direction of the rotor disk, the opening faces the side of the simulated blade. For the simulated blade arranged on the opposite end side in the circumferential direction of the rotor disk, the opening faces the side of the detachment control slider.

[0022] Further, the blade detachment control slider and the blade limiting block are connected by a thread.

[0023] Further, the electromagnet is in a cylindrical shape and is arranged at a specified angular position on the circle corresponding to the rotation radius of the blade detachment control slider.

[0024] Further, the electromagnet is in an annular shape and is arranged at the entire angular position on the circle corresponding to the rotation radius of the blade detachment control slider.

[0025] Further, the simulated blade can be set to any mass.

[0026] Effects of the Invention

[0027] According to the present invention, a rotor blade ejection device can be provided, which uses electromagnetic force to trigger a triggering device on a rotating rotor part, so that a simulated blade with a specified mass can fly out precisely at a specified rotational speed, improving the safety of the ejection experiment, reducing the cost of the ejection test, and enabling the ejection test to have good repeatability. Description of the Drawings

[0028] By describing exemplary embodiments of the present disclosure in conjunction with the drawings, the present disclosure can be better understood. In the drawings:

[0029] Figure 1 is a perspective schematic view of the rotor blade ejection device according to an embodiment of the present invention.

[0030] Figure 2 is a cross-sectional schematic view of the rotor blade ejection device according to an embodiment of the present invention.

[0031] Figure 3 is a schematic view when the blade of the rotor blade ejection device according to an embodiment of the present invention flies off.

[0032] Figure 4 is a schematic diagram of the electromagnet arrangement of the rotor blade ejection device according to an embodiment of the present invention.

[0033] Figure 5 is a schematic diagram of the electromagnet arrangement of the rotor blade ejection device according to an embodiment of the present invention.

[0034] Reference Numerals in the Drawings:

[0035] 100 Rotor Blade Ejection Device, 1 Rotor Disk, 2 Blade Ejection Control Movable Block, 3 Spring, 4 Blade Movable Guide Frame, 5 Simulated Blade, 6 Blade Limiting Block, 7 Lock Block, 70 Openings, 8 Electromagnet, 9 Electromagnet, 10 Rotating Shaft. Detailed Embodiments

[0036] Specific embodiments of the present disclosure will be described below. It should be noted that in the specific description of these embodiments, for the sake of concise description, this specification cannot describe all features of the actual embodiments in detail. It should be understood that in the actual implementation process of any embodiment, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and these will also change from one embodiment to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for those of ordinary skill in the art related to the content disclosed in the present disclosure, some design, manufacturing, or production changes based on the technical content disclosed in the present disclosure are just conventional technical means and should not be understood as the content of the present disclosure being insufficient.

[0037] Unless otherwise defined, technical terms or scientific terms used in the claims and the specification shall have the ordinary meaning understood by those of ordinary skill in the technical field to which the present disclosure belongs. The terms "first", "second" and similar terms used in the specification and claims of this patent application of the present disclosure do not indicate any order, quantity or importance, but are only used to distinguish different components. The terms "a" or "an" and similar terms do not indicate a quantity limitation, but indicate that there is at least one. The terms "comprising" or "including" and similar terms mean that the elements or items appearing before "comprising" or "including" cover the elements or items listed after "comprising" or "including" and their equivalent elements, and do not exclude other elements or items. The terms "connected" or "coupled" and similar terms are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0038] In the present disclosure, if there is no special indication, all the embodiments and preferred embodiments mentioned herein can be combined with each other to form a new technical solution. In the present disclosure, if there is no special indication, all the technical features and preferred features mentioned herein can be combined with each other to form a new technical solution.

[0039] Embodiments of the present invention

[0040] Figure 1 is a three-dimensional schematic diagram of the rotor blade fly-off device 100 related to the embodiments of the present invention. Figure 2 is a cross-sectional schematic diagram of the rotor blade fly-off device 100 related to the embodiments of the present invention.

[0041] Such as Figure 1 and Figure 2As shown, the rotor blade ejection device 100 includes a rotor disk 1, a blade ejection control slider 2, a spring 3, a blade sliding guide frame 4, a simulated blade 5, a blade stop 6, a locking block 7, and a rotating shaft 10. The simulated blade can be set to any mass. By using such a simulated blade 5, various blades with different masses can be simulated and tested.

[0042] As Figure 2 shown, in order to avoid generating a large unbalance, simulated blades 5 are respectively arranged at both ends on the relative positions in the axial direction of the rotor disk 1. Specifically, among them, only the simulated blade 5 located on the upper side in Figure 2 can be ejected for an ejection test, while the simulated blade 5 located on the lower side in Figure 2 is in a fixed state. Under the working condition of the rotation of the rotor disk 1, if the simulated blade 5 is only arranged on one side in the circumferential direction of the rotor disk 1, the rotation state is not stable. Therefore, the simulated blade 5 is also arranged on the other side in the circumferential direction. Since the masses of the simulated blades 5 on both sides in the circumferential direction of the rotor disk 1 are the same, no large unbalance will be generated.

[0043] The blade ejection control slider 2 is installed in the opening of the rotor disk 1, and the locking block 7 is installed in the opening via the spring 3. The blade stop 6 is connected to the blade ejection control slider 2, and their connection methods can include screw fixation, welding fixation, adhesive fixation, etc. In this embodiment, the end of the blade ejection control slider 2 close to the simulated blade 5 has an external thread, and the end of the blade stop 6 opposite to the blade ejection control slider 2 has an internal thread, and the two are fixed by threads.

[0044] As Figure 2 shown, the locking block 7 abuts against the blade stop 6 and has an opening 70. Figure 2 The opening of the upper locking block 7 in

[0045] faces the side of the simulated blade 5. When the opening faces the side of the simulated blade 5, the locking block 7 can move along the axial direction of the opening. In this case, when the blade ejection control slider 2 is subjected to an external force and moves along the axial direction of the opening towards one side, since the blade stop 6 and the blade ejection control slider 2 are connected by threads, the blade ejection control slider 2 drives the blade stop 6 to move together, and the limit of the blade stop 6 on the simulated blade 5 is released, so that the simulated blade 5 can be ejected. At this time, the blade stop 6 presses the locking block 7, and the locking block 7 also moves accordingly.

[0046] On the other hand, Figure 2The opening of the locking block 7 on the lower middle side faces one side of the blade flying-off control block 2. At this time, the locking block 7 cannot move along the axial direction of the opening. In this case, even if an external force acts on the blade flying-off control block 2, since the blade limiting block 6 threadedly connected to the blade flying-off control block 2 is locked by the locking block 7, the blade limiting block 6 still limits the simulated blade 5, and the simulated blade 5 cannot fly off, which plays a role in avoiding the generation of a large unbalance.

[0047] The blade sliding guide frame 4 is fixed on the rotor disc 1. In this embodiment, it is fixed to the rotor disc 1 by screws. The simulated blade 5 is accommodated in the blade sliding guide frame 4 to guide the flying-off of the simulated blade 5.

[0048] Figure 3 It is a schematic diagram when the blade of the rotor blade flying-off device 100 involved in the embodiment of the present invention flies off. As Figure 3 shown, when an external force F1 acts on the blade flying-off control block 2, the blade flying-off control block 2 moves along the axial direction of the opening under the action of the force F1. In this embodiment, the blade flying-off control block 2 moves in a direction perpendicular to the surface of the rotor disc 1. In this case, the blade flying-off control block 2 and the blade limiting block 6 press the locking block 7 together and move towards one side in the axial direction of the opening, and the limitation of the simulated blade 5 by the blade limiting block 6 is released, so that the simulated blade 5 flies off under the action of the centrifugal force F2.

[0049] Next, the acting forces F1 and F2 will be described.

[0050] If the flying-off speed is set as ω, the mass of the simulated blade 5 to be flown off is set as m, and the centroid radius of the rotor disc 1 is set as r, then the centrifugal force F2 during flying-off = mrω 2 , and according to the friction force calculation formula, the required minimum pulling force F = μF2 = mrω 2 , where μ is the friction coefficient between the blade limiting block 6 and the simulated blade 5.

[0051] Therefore, during the flying-off test, as long as it is ensured that the external force F1 > F, the actuation control of the blade flying-off control block 2 can be achieved.

[0052] In the embodiment of the present invention, an electromagnetic force is adopted as F1.

[0053] Figure 4 It is a schematic diagram of the electromagnet setting of the rotor blade flying-off device 100 involved in the embodiment of the present invention. As Figure 4As shown, on one end side in the circumferential direction of the rotor disk 1, an electromagnet 8 is provided at a distance from the rotor disk 1. The electromagnet 8 is in a cylindrical shape and the distance from the rotor disk 1 is D. When the rotational speed of the rotor disk 1 reaches a specified rotational speed, the electromagnet 8 is energized. After being energized, the electromagnet 8 generates an electromagnetic force, and the electromagnetic force triggers the movement of the blade release control slider 2 on the rotor disk 1, thereby releasing the simulated blade 5, and further realizing the blade release test of the rotor blade. In this case, since the electromagnet 8 is provided at a specified angular position on the circle corresponding to the rotation radius of the blade release control slider 2, the angular position of the blade release can be controlled.

[0054] Figure 5 is a schematic diagram of the electromagnet setting of the rotor blade release device 100 according to the embodiment of the present invention. As Figure 4 shown, on the circumference of the rotor disk 1, an electromagnet 9 is provided at a distance from the rotor disk 1. The electromagnet 8 is in an annular shape and the distance from the rotor disk 1 is D. When the rotational speed of the rotor disk 1 reaches a specified rotational speed, the electromagnet 9 is energized. After being energized, the electromagnet 9 generates an electromagnetic force, and the electromagnetic force triggers the movement of the blade release control slider 2 on the rotor disk 1, thereby releasing the simulated blade 5, and further realizing the blade release test of the rotor blade. In this case, since the electromagnet 9 is in an annular shape and is provided at the entire angular position on the circle corresponding to the rotation radius of the blade release control slider 2, the blade release can be controlled at any angular position.

[0055] According to the embodiment of the present invention, an electromagnetic force is used to trigger a trigger device on a rotating rotor part, so that the simulated blade can fly out accurately at a specified rotational speed. By using a simulated blade to conduct the release test, the release tests of blades with different masses can be carried out. Since the electromagnetic force is adopted and the explosive method is abandoned, the safety of the release experiment can be improved. In addition, after the simulated blade flies out, it can be restored without damage and the next test can be carried out immediately, so the cost of the release test can be reduced, and the release test can have good repeatability. And by setting electromagnets with different shapes, the angular position of the blade release can be controlled, making the blade release experiment more accurate.

[0056] In addition, regarding the above-mentioned acting force F1, in order to smoothly conduct the release test, it is necessary to ensure that F1 > F. From the perspective of increasing F1, it can be considered to select a powerful electromagnet with a large current, many coils, and good magnetic conductivity, and a material with better magnetic conductivity can be used to manufacture the blade release control slider 2. From the perspective of reducing F, it can be considered to reduce the friction coefficient μ. For example, a linear rolling bearing can be provided between the blade limiting block 6 and the simulated blade 5.

[0057] It should be understood that the above description is illustrative rather than restrictive. For example, the above embodiments (and / or aspects thereof) can be used in combination with each other. In addition, many modifications can be made to adapt a particular situation or material to the teachings of various embodiments of the present invention without departing from the scope of the present invention. Although the dimensions and types of the materials described herein are used to define the parameters of various embodiments of the present invention, the various embodiments are not meant to be restrictive but are exemplary embodiments. Many other embodiments will be apparent to those skilled in the art upon reading the above description. Therefore, the scope of the various embodiments of the present invention should be determined with reference to the appended claims and the full scope of the equivalents claimed by these claims.

Claims

1. A rotor blade fly-off device, characterized in that, comprising: a rotating shaft; a rotor disk, which is mounted on the rotating shaft and rotates coaxially with the rotating shaft; simulated blades, which are arranged circumferentially on the rotor disk and fly off under the action of the centrifugal force generated by the rotation of the rotor disk; a blade fly-off control slider, which is installed in an opening of the rotor disk and moves axially along the opening to control the fly-off of the simulated blades; a blade limiting block, which is connected to the blade fly-off control slider to limit the simulated blades; a locking block, which is installed in the opening of the rotor disk via a spring and abuts against the blade limiting block; a blade sliding guide frame, which is fixed on the rotor disk and houses the simulated blades to guide the fly-off of the simulated blades; and an electromagnet, which is arranged circumferentially on the rotor disk at an interval from the rotor disk, when the electromagnet is energized, the electromagnet generates an electromagnetic force to trigger the movement of the blade fly-off control slider on the rotor disk, thereby releasing the simulated blades.

2. The rotor blade fly-off device according to claim 1, characterized in that, if the electromagnetic force generated by the electromagnet is set as F1, the centrifugal force when the simulated blades fly off is set as F2, and the friction coefficient between the blade limiting block and the simulated blades is set as μ, then F1 > μF2.

3. The rotor blade fly-off device according to claim 1, characterized in that, there are 2 simulated blades, one is arranged on one end side in the circumferential direction of the rotor disk, and the other is arranged on the opposite end side in the circumferential direction of the rotor disk.

4. The rotor blade fly-off device according to claim 3, characterized in that, the locking block has an opening, when the opening faces the side of the simulated blades, the locking block can move axially along the opening, when the opening faces the side of the fly-off control slider, the locking block cannot move axially along the opening.

5. The rotor blade fly-off device according to claim 4, characterized in that, for the simulated blade arranged on one end side in the circumferential direction of the rotor disk, the opening faces the side of the simulated blades, for the simulated blade arranged on the opposite end side in the circumferential direction of the rotor disk, the opening faces the side of the fly-off control slider.

6. The rotor blade fly-off device according to claim 1, characterized in that, the blade fly-off control slider and the blade limiting block are connected by threads.

7. The rotor blade fly-off device according to claim 1, characterized in that, the electromagnet is in a cylindrical shape and is arranged at a specified angular position on the circle corresponding to the rotation radius of the blade fly-off control slider.

8. The rotor blade fly-off device according to claim 1, characterized in that, the electromagnet is in an annular shape and is arranged at the entire angular position on the circle corresponding to the rotation radius of the blade fly-off control slider.

9. The rotor blade fly-off device according to claim 1, characterized in that, the mass of the simulated blades can be set arbitrarily.

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