Rotor supporting structure

Abstract

The invention relates to the technical field of aero-engines, in particular to a rotor supporting structure which comprises a supporting cylinder, a worm gear, a worm and a pressing block. A plurality of strip-shaped holes are formed in the side face of the supporting cylinder, and the strip-shaped holes are distributed in the circumferential side direction of the supporting cylinder. The worm gear rotationally sleeves the supporting cylinder; the worm is meshed with the worm gear; the pressing blocks are fixedly arranged on the inner wall of the worm gear, the pressing blocks correspond to the strip-shaped holes one to one, and the pressing blocks are partially located in the corresponding strip-shaped holes; when the worm gear rotates in the circumferential direction, the pressing blocks can be driven to extrude the side walls of the corresponding strip-shaped holes so as to change the rigidity of the rotor supporting structure. According to the variable-stiffness rotor supporting structure capable of performing active control, when a modern aero-engine operates under variable working conditions, the supporting stiffness can be actively controlled under different working conditions, the effects of being away from the critical rotating speed and reducing the resonance peak value are achieved, rotor vibration response suppression is achieved, and therefore the effect of reducing vibration of the aero-engine is achieved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aero-engines, and in particular to a rotor support structure. Background Art

[0002] As the power core of aviation flight, aircraft engines are a very complex and precise thermal rotary machine. Modern aircraft engines are generally developed in the direction of light weight, high thrust-to-weight ratio, high speed, safety and reliability. According to statistics, the number of aircraft engine failures caused by vibration accounts for 50% to 60% of the total engine failures. The rotor system is the core component of the aircraft engine. It is both the main body of the engine vibration and the main excitation source of the engine vibration. Therefore, how to reduce the vibration of the aircraft engine is one of the problems that need to be solved urgently in this field. Summary of the invention

[0003] The present disclosure is proposed in view of the above problems. The present disclosure provides a rotor support structure.

[0004] According to one aspect of the present disclosure, there is provided a rotor support structure, comprising a support cylinder, a worm wheel, a worm and a pressing block;

[0005] The side surface of the support tube is provided with strip holes, and there are multiple strip holes, which are distributed along the circumferential direction of the support tube; the worm wheel is rotatably sleeved on the support tube; the worm is meshed with the worm wheel; the pressure block is fixedly arranged on the inner wall of the worm wheel, and the pressure block corresponds to the strip holes one by one, and the pressure block is partially located in the corresponding strip hole; when the worm wheel rotates circumferentially, it can drive the pressure block to squeeze the side wall of the corresponding strip hole to change the stiffness of the rotor support structure.

[0006] In addition, according to a rotor support structure in one aspect of the present disclosure, a mounting groove is provided on the inner wall of the worm wheel, the pressure block is partially fixedly installed in the mounting groove, and the portion of the pressure block protruding from the mounting groove is located in the strip hole.

[0007] In addition, according to a rotor support structure in one aspect of the present disclosure, a limit plate is also provided on the pressure block, and there are two limit plates, which are respectively arranged at the two ends of the pressure block along the axial direction of the worm gear, and the limit plates are against the outer wall of the support tube. The limit plates are used to limit the pressure block in the radial direction of the support tube.

[0008] In addition, according to a rotor support structure in one aspect of the present disclosure, limiting surfaces are provided at both ends of the pressing block along the axial direction of the worm wheel, and the limiting surfaces are used to limit the pressing block along the axial direction of the support tube.

[0009] In addition, according to a rotor support structure of an aspect of the present disclosure, the worm is rotatably mounted on a worm seat, the position of the worm seat is relatively fixed with respect to the support cylinder, and one end of the worm is in transmission connection with a stepping motor mounted on the worm seat.

[0010] In addition, according to a rotor support structure of an aspect of the present disclosure, in the small stiffness state, the pressing block does not contact the side wall of the strip-shaped hole; in the large stiffness state, the circumferential rotation of the worm gear drives the pressing block to squeeze the corresponding side wall of the strip-shaped hole.

[0011] In addition, according to a rotor support structure of an aspect of the present disclosure, the strip-shaped hole is arranged along the axial direction of the support cylinder.

[0012] In addition, according to a rotor support structure of an aspect of the present disclosure, the support cylinder includes a first support ring, a second support ring and a connecting rod. The first support ring and the second support ring are arranged in parallel; one end of the connecting rod is fixedly connected to the first support ring, and the other end is fixedly connected to the second support ring. There are a plurality of connecting rods, and the plurality of connecting rods are arranged along the circumferential direction of the first support ring, and the strip-shaped holes are formed between adjacent two connecting rods.

[0013] In addition, according to a rotor support structure of an aspect of the present disclosure, when the pressing block squeezes the corresponding side wall of the strip-shaped hole, the stiffness K 支撑筒 of the support cylinder is calculated as follows:

[0014]

[0015] In the formula, b 等效 = cb, c is an equivalent coefficient, and c > 1, E is the Young's modulus of the support cylinder material, L is the length of the connecting rod, n is the number of the connecting rods, b is the width of the connecting rod, and h is the thickness of the connecting rod.

[0016] The present disclosure provides a support cylinder, a strip-shaped hole is arranged on the circumferential side surface of the support cylinder, a worm gear is rotatably sleeved outside the support cylinder, a pressing block is arranged on the inner ring of the worm gear, a part of the pressing block is located in the strip-shaped hole, the worm gear is in meshing transmission with the worm, the rotation of the worm drives the rotation of the worm gear, and further drives the pressing block to squeeze the side wall of the strip-shaped hole where it is located, so as to change the stiffness of the rotor support structure. By adopting an actively controllable variable stiffness rotor support structure, during the variable working conditions of a modern aeroengine, the support stiffness can be actively controlled under different working conditions, achieving the effects of staying away from the critical speed and reducing the resonance peak value, realizing the suppression of the rotor vibration response, and thus achieving the effect of reducing the vibration of the aeroengine. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and other objects, features, and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail with reference to the accompanying drawings. The drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation to the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0018] Figure 1 is a schematic structural diagram of a rotor support structure disclosed by the present disclosure.

[0019] Figure 2 is a structural diagram of a rotor support structure under small stiffness.

[0020] Figure 3 is a structural diagram of a rotor support structure under large stiffness.

[0021] Figure 4 is a structural diagram of a pressing block.

[0022] Figure 5 is a schematic structural diagram of a support cylinder.

[0023] Figure 6 is a schematic diagram of the mating relationship between a worm and worm gear structure and a pressing block.

[0024] Figure 7 is a schematic diagram of the mating relationship between a support cylinder and a pressing block structure.

[0025] Figure 8 is a schematic diagram of the mating relationship between a single pressing block and a worm structure.

[0026] Figure 9 is a schematic diagram of the vibration response suppression effect of an active control support structure - rotor system.

[0027] Explanation of reference numerals:

[0028] 1 - support cylinder, 2 - worm gear, 3 - worm, 4 - pressing block, 5 - strip hole, 6 - installation groove, 7 - limiting plate, 8 - limiting surface, 9 - worm seat, 10 - stepping motor, 11 - first support ring, 12 - second support ring, 13 - connecting rod, 14 - deep groove ball bearing. Detailed implementation manners

[0029] In order to make the purpose, technical solution, and advantages of the present disclosure more obvious, the exemplary embodiments according to the present disclosure will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure. It should be understood that the present disclosure is not limited by the exemplary embodiments described herein.

[0030] Refer to Figures 1-8As shown in the figure, the present disclosure discloses a rotor support structure, including a support cylinder 1, a worm gear 2, a worm 3, and a pressing block 4; a strip-shaped hole 5 is provided on the side surface of the support cylinder 1, and there are multiple strip-shaped holes 5, and the multiple strip-shaped holes 5 are distributed along the circumferential direction of the support cylinder 1. Here, it is taken as an example that the strip-shaped hole 5 is arranged along the axial direction of the support cylinder 1; the worm gear 2 is rotatably sleeved on the support cylinder 1; the worm 3 meshes with the worm gear 2, the worm 3 is rotatably installed on a worm seat 9, the position of the worm seat 9 is relatively fixed with respect to the support cylinder 1, and one end of the worm 3 is in transmission connection with a stepping motor 10 installed on the worm seat 9. Specifically, the worm 3 is fixed on the worm seat 9 through two deep groove ball bearings 14. The pressing block 4 is fixedly arranged on the inner wall of the worm gear 2, the pressing block 4 corresponds to the strip-shaped hole 5 one by one, and the pressing block 4 is partially located in the corresponding strip-shaped hole 5; when the worm gear 2 rotates circumferentially, it can drive the pressing block 4 to squeeze the side wall of the corresponding strip-shaped hole 5 to change the stiffness of the rotor support structure. By adopting the meshing of the worm 3 and the worm gear 2, and the transmission connection between the worm 3 and the stepping motor 10, and relying on the stepping motor 10 to provide power for the whole mechanism. When it is necessary to change the stiffness of the rotor support structure, by starting the stepping motor 10, the stepping motor 10 drives the worm 3 to rotate, the worm 3 drives the worm gear 2 to rotate circumferentially to drive the pressing block 4 to squeeze the side wall of the corresponding strip-shaped hole 5, and the stiffness of the rotor support structure can be changed. Determine the specific structure of the pressing block 4 based on the structural parameters of the support cylinder 1. The number of pressing blocks 4 is the same as the number of strip-shaped holes 5, and design the worm and worm gear structure based on the specific structure of the pressing block 4.

[0031] In the low stiffness state, the pressing block 4 does not come into contact with the side wall of the strip-shaped hole 5; in the high stiffness state, the circumferential rotation of the worm gear 2 drives the pressing block 4 to squeeze the side wall of the corresponding strip-shaped hole 5. By adjusting the driving force of the stepping motor 10, the pressing force between the pressing block 4 and the side wall of the strip-shaped hole 5 can be adjusted, and further the stiffness of the rotor support structure can be adjusted. As a preferred method, one pair of opposite side walls of the strip-shaped hole 5 is parallel to the axis of the support cylinder 1. In the low stiffness state, as Figure 2 shown, the pressing block 4 does not come into contact with the side wall of the strip-shaped hole 5 parallel to the axis of the support cylinder 1; in the high stiffness state, as Figure 3 shown, the circumferential rotation of the worm gear 2 drives the pressing block 4 to squeeze the side wall of the corresponding strip-shaped hole 5 parallel to the axis of the support cylinder 1.

[0032] In actual use, the rotor of an aero-engine first operates with a large support stiffness, that is, the pressing block 4 is controlled by the stepper motor 10 to press against the side wall of the strip-shaped hole 5. When the rotational speed of the engine rotor approaches the critical speed of the large support stiffness, the stepper motor 10 is precisely controlled to drive the pressing block 4 to disengage from the side wall of the strip-shaped hole 5 through the worm and worm gear structure, reducing the support stiffness, thereby reducing the critical speed, so that the operating speed at this time is far from the critical speed, achieving the effect of reducing the resonance peak value, realizing the suppression of the rotor vibration response, and thus achieving the effect of reducing the vibration of the aero-engine. On the premise of a simple structure, the rotor support structure of the present disclosure can achieve precise and rapid adjustment of the stiffness, thereby realizing the active control of the aero-engine rotor, and further realizing the suppression of the rotor vibration response in a wider speed range and more working conditions than the traditional support structure.

[0033] As a preferred embodiment, the support cylinder 1 includes a first support ring 11, a second support ring 12 and a connecting rod 13. The first support ring 11 and the second support ring 12 are arranged in parallel; one end of the connecting rod 13 is fixedly connected to the first support ring 11, and the other end is fixedly connected to the second support ring 12. There are multiple connecting rods 13, and the multiple connecting rods 13 are arranged along the circumferential direction of the first support ring 11, and a strip-shaped hole 5 is formed between adjacent two connecting rods 13. In the small stiffness state, the pressing block 4 does not come into contact with the connecting rod 13; in the large stiffness state, the circumferential rotation of the worm wheel 2 drives the pressing block 4 to squeeze the connecting rod 13 (i.e., squeeze the side wall of the strip-shaped hole 5), and the pressing force between the pressing block 4 and the connecting rod 13 can be adjusted by adjusting the driving force of the stepper motor 10, thereby adjusting the stiffness of the rotor support structure. The first support ring 11 can be an installation flange, and the second support ring 12 can be a bearing.

[0034] Support cylinder stiffness K 支撑筒 The empirical formula is:

[0035]

[0036] In the above formula, L is the length of the connecting rod 13, n is the number of the connecting rods 13, E is the Young's modulus of the material of the support cylinder 1, b is the width of the connecting rod 13, and h is the thickness of the connecting rod 13.

[0037] When the turbine structure drives the pressing block 4 to circumferentially press against the side wall of the corresponding strip-shaped hole 5, that is, squeeze the connecting rod 13, the pressing block 4 and the connecting rod 13 are completely pressed together, which is equivalent to increasing the equivalent width of the connecting rod 13. At this time, the stiffness K of the support cylinder 1 支撑筒 The calculation formula is as follows:

[0038]

[0039] In the formula, b 等效= cb, where c is the equivalent coefficient and c > 1, E is the Young's modulus of the material of the support cylinder 1, L is the length of the connecting rod 13, n is the number of the connecting rods 13, b is the width of the connecting rod 13, and h is the thickness of the connecting rod 13.

[0040] The stiffness of the rotor support structure disclosed in the present disclosure is provided jointly by the support cylinder 1 and the pressing block 4. Figure 2 In the case of small stiffness as shown, the stiffness of the rotor support structure is mainly provided by the support cylinder 1. In Figure 3 On the premise of large stiffness as shown, the stiffness of the rotor support structure is provided jointly by the support cylinder 1 and the pressing block 4.

[0041] As a preferred method, an installation groove 6 is provided on the inner wall of the worm gear 2, and part of the pressing block 4 is fixedly installed in the installation groove 6, and the part of the pressing block 4 protruding from the installation groove 6 is located in the strip-shaped hole 5. Such a setting facilitates installation. The pressing block 4 and the installation groove 6 can be fixedly connected by an interference fit.

[0042] The pressing block 4 is also provided with limiting plates 7. There are two limiting plates 7, and the two limiting plates 7 are respectively arranged at both ends of the pressing block 4 along the axial direction of the worm gear 2. The limiting plates 7 abut against the outer wall of the support cylinder 1, and the limiting plates 7 are used to limit the pressing block 4 in the radial direction of the support cylinder 1. Both ends of the pressing block 4 along the axial direction of the worm gear 2 are provided with limiting surfaces 8, and the limiting surfaces 8 are used to limit the pressing block 4 along the axial direction of the support cylinder 1. In specific implementation, the two limiting surfaces 8 of the pressing block 4 can be in contact with or have a certain gap with the opposite inner side walls of the strip-shaped hole 5 (here, the inner side walls refer to the two side walls of the strip-shaped hole 5 along the circumferential direction of the support cylinder 1), and can limit the pressing block 4 along the axial direction of the support cylinder 1.

[0043] In actual use, if the strip-shaped hole 5 is wedge-shaped, the cross-section of the pressing block 4 can be made wedge-shaped to adapt to the wedge shape of the strip-shaped hole 5.

[0044] In practical applications, first, the support cylinder is designed. According to the common working speed of the engine, the stiffness of the support cylinder is designed. The dynamic equation of the rotor-variable stiffness support structure system is:

[0045]

[0046] In the formula, M, C, G, and K respectively represent the mass matrix, damping matrix, gyroscopic moment matrix, and stiffness matrix of the controlled rotor structure, and F(t) is the rotor unbalance excitation force.

[0047] The stiffness K of the support cylinder 支撑筒 is a part of the dynamic equation of the rotor-variable stiffness support structure system.

[0048] The worm and worm gear transmission mechanism has the advantages of a wide transmission ratio range, compact structure, smooth movement, and small impact load. Moreover, it has a simple structure, is easy to manufacture, and is easy to self-lock to achieve safety protection. The rotor support structure in this disclosure adopts a cylindrical worm drive, and the worm tooth profile curve is an Archimedean worm.

[0049] The production material of the worm structure is 40Cr, which is processed by turning and milling, and is subjected to surface quenching heat treatment. The worm wheel is processed in an integral manner, and the material is cast copper alloy (ZCuSn10P1). The specific dimensions of the worm and worm gear are determined according to the rotor size, working conditions, and the size of the pressing block.

[0050] After the design of the worm and worm gear structure is completed, the transmission efficiency of the worm and worm gear should be calculated to select a suitable stepping motor. The efficiency of the worm and worm gear transmission generally consists of three parts: namely, the loss of tooth meshing friction, the loss of bearing friction, and the loss of the lubricating oil stirred by the parts immersed in the oil. Therefore, the total efficiency of the worm drive is:

[0051] η = η1η2η3,

[0052] In the formula, η1, η2, and η3 are the meshing efficiency, bearing efficiency, and oil churning efficiency of the rod drive respectively. Among them, the main one is the meshing efficiency η1 of the worm drive, and the general values of η2 and η3 are 0.95 - 0.96.

[0053] When the worm is the driving part, η1 can be approximately calculated according to the efficiency of the spiral drive, that is: In the formula, λ is the lead angle of the worm; ρ v equivalent friction angle, ρ v = arctanf v , ρ v decreases with the increase of the sliding speed υ s . This is because with the increase of υ s , it is easy to form an oil film, resulting in a decrease in the friction coefficient. The worm drive efficiency is related not only to the equivalent friction angle ρ v but also to the lead angle λ. In this design, λ ≤ ρ v , because when this condition is met, the worm and worm gear structure has self-locking property.

[0054] Since modern aero-engines change working conditions frequently, it is necessary to design the lubrication method for the worm and worm gear structure in this design. This design adopts a closed worm and worm gear drive, and the lubrication method is pressure oil injection lubrication.

[0055] After the design of the worm and worm gear structure is completed, a thermal balance calculation should be carried out on the worm and worm gear mechanism.

[0056] For a worm and worm gear mechanism with a transmission power of P Kw and an efficiency of η, the heat generated per unit time by the worm drive is H1, then

[0057] H1=1000P(1-η);

[0058] If the heat dissipation per unit time is H2 in natural cooling mode, then H2 = K d S(t-t0), where K d is the heat dissipation coefficient of the box surface, generally K d =8.15~17.45W / (m 2 ·℃) (related to ventilation conditions), S is the heat dissipation area of the box (the inner surface can be splashed by oil, and the outer surface can be cooled by the surrounding air), t is the working temperature of the oil, which should generally be limited to 60-70℃, and the maximum should not exceed 80℃, t max ≤80℃, t0 is the ambient temperature.

[0059] When thermal equilibrium is reached, 1000P(1-η)=K d S(t-t0),

[0060] The temperature at thermal equilibrium is

[0061] The thermal equilibrium temperature should be ensured to be less than 80°C.

[0062] When the aircraft engine rotor starts to run, the stepper motor controls the pressing block to press the connecting rod. Figure 3 As shown, the stiffness of the supporting structure is relatively large at this time; when the speed of the aircraft engine rotor approaches the critical speed under the larger stiffness, the stepper motor controls the pressure block to disengage from the connecting rod, as shown in FIG. Figure 2 As shown in the figure, at this time, the pressure block contributes very little to the stiffness of the support structure. The stiffness of the support structure is at a relatively low stiffness, which is equal to the stiffness of the support tube itself. At this time, the critical speed of the engine rotor becomes smaller, thus staggered with the engine rotor speed, which has the effect of reducing the vibration peak. The effect of using a variable stiffness rotor support structure to actively control the support stiffness on the rotor vibration response suppression is shown in the figure Figure 9 shown.

[0063] The influence of variable stiffness on the vibration response characteristics of the rotor system is as follows:

[0064] Considering the effect of resistance, the motion equation of the rotor system is: Where z = x + iy, n is the damping coefficient, The specific solution of the rotor system motion equation can be assumed to be It can be solved as follows:

[0065]

[0066] From the above formula, we can see that the rotor vibration characteristics (i.e., amplitude-frequency characteristics and phase characteristics) are related to the natural frequency ω n Directly related to changing ω nthe active control of the rotor vibration characteristics can be carried out. Since under the premise that the total control mass remains unchanged, this solution can effectively change the amplitude-frequency and phase-frequency characteristics of the rotor system by controlling the pressing degree of the pressing block and the connecting rod, thereby changing the stiffness. As shown in Figure 9 When the rotor support stiffness increases by pressing the cage bar with the pressing block, the critical speed of the rotor system increases and the amplitude decreases significantly, which proves that the variable stiffness rotor support structure of this solution can effectively improve the dynamic characteristics of the rotor system.

[0067] The control logic of the variable stiffness support structure is that when the rotor starts, the stepping motor controls the worm and worm gear structure to drive the pressing block to press the support cylinder structure, so that the stiffness of the support cylinder increases. At this time, the corresponding calculation formula for the stiffness of the support cylinder is:[[]]

[0068] b 等效 = cb, where c is the equivalent coefficient and c > 1.

[0069] As shown in the above formula, when the pressing block squeezes the connecting rod driven by the worm and worm gear structure, the equivalent width of the connecting rod changes, and the equivalent coefficient c needs to be used for formula correction. c is related to the pressing force of the hydraulic turntable driving the pressing block to press the connecting rod and the parameters of the entire variable stiffness rotor support structure, and needs to be determined based on experiments during the design process of the support structure; when the speed sensor monitors that the rotor speed is close to the critical speed of the rotor under high stiffness, the PLC control system controls the stepping motor to drive the worm and worm gear structure, and then drives the pressing block to disengage from the connecting rod (as shown in Figure 2 ), which is equivalent to reducing the equivalent width of the connecting rod, thereby reducing the stiffness of the support cylinder support structure, and the corresponding critical speed decreases accordingly, so that the working speed at this time is far from the critical speed, thereby achieving the effect of suppressing the rotor vibration response.

[0070] The basic principles of the present disclosure have been described above in conjunction with specific embodiments. However, it should be noted that the advantages, advantages, effects, etc. mentioned in the present disclosure are only examples and not limitations, and it cannot be considered that these advantages, advantages, effects, etc. are essential for each embodiment of the present disclosure. In addition, the above-mentioned specific details are only for the purpose of illustration and easy understanding, rather than limitations. The above details do not limit the present disclosure to necessarily adopt the above specific details to implement.

[0071] The block diagrams of the devices, apparatuses, equipment, and systems involved in this disclosure are only illustrative examples and are not intended to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including," "comprising," "having," etc. are open-ended terms that mean "including but not limited to" and can be used interchangeably with each other. The word "or" and "and" used herein refer to the phrase "and / or" and can be used interchangeably with it, unless the context clearly indicates otherwise. The phrase "such as" used herein refers to the phrase "such as but not limited to" and can be used interchangeably with it.

[0072] In addition, as used herein, the "or" used in the listing of items starting with "at least one" indicates a disjunctive listing. For example, the listing of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the term "exemplary" does not mean that the examples described are preferred or better than other examples.

[0073] It should also be noted that in the systems and methods of this disclosure, each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations should be regarded as equivalent solutions of this disclosure.

[0074] Various changes, substitutions, and alterations to the technologies described herein can be made without departing from the teachings defined by the appended claims. In addition, the scope of the claims of this disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of events, means, methods, and acts described above. Current or later-developed processes, machines, manufactures, compositions of events, means, methods, or acts that perform substantially the same function or achieve substantially the same result as the corresponding aspects described herein can be utilized. Accordingly, the appended claims include such processes, machines, manufactures, compositions of events, means, methods, or acts within their scope.

[0075] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use this disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of this disclosure. Therefore, this disclosure is not intended to be limited to the aspects shown herein, but rather to the broadest scope consistent with the principles and novel features disclosed herein.

[0076] The foregoing description has been presented for purposes of illustration and description. In addition, the description is not intended to limit embodiments of the disclosure to the form disclosed herein. Although several example aspects and embodiments have been discussed above, those of skill in the art will recognize some of their variations, modifications, alterations, additions, and subcombinations.

Claims

1. A rotor support structure, characterized in that, It includes a support cylinder (1), a worm gear (2), a worm (3) and a pressing block (4). A strip-shaped hole (5) is provided on the side surface of the support cylinder (1), and there are a plurality of the strip-shaped holes (5). The plurality of strip-shaped holes (5) are distributed along the circumferential direction of the support cylinder (1); the worm gear (2) is rotatably sleeved on the support cylinder (1); the worm (3) meshes with the worm gear (2); the pressing block (4) is fixedly arranged on the inner wall of the worm gear (2), the pressing block (4) corresponds to the strip-shaped hole (5) one by one, and a part of the pressing block (4) is located in the corresponding strip-shaped hole (5); when the worm gear (2) rotates circumferentially, it can drive the pressing block (4) to squeeze the side wall of the corresponding strip-shaped hole (5) so as to change the stiffness of the rotor support structure.

2. A rotor support structure according to claim 1, characterized in that, An installation groove (6) is formed on the inner wall of the worm gear (2), a part of the pressing block (4) is fixedly installed in the installation groove (6), and the part of the pressing block (4) protruding from the installation groove (6) is located in the strip-shaped hole (5).

3. The rotor support structure according to claim 2, characterized in that, The pressing block (4) is further provided with limiting plates (7), there are two limiting plates (7), and the two limiting plates (7) are respectively arranged at both ends of the pressing block (4) along the axial direction of the worm gear (2). The limiting plates (7) abut against the outer wall of the support cylinder (1), and the limiting plates (7) are used for limiting the pressing block (4) in the radial direction of the support cylinder (1).

4. A rotor support structure according to claim 3, characterized in that, Limiting surfaces (8) are arranged at both ends of the pressing block (4) along the axial direction of the worm gear (2), and the limiting surfaces (8) are used for limiting the pressing block (4) along the axial direction of the support cylinder (1).

5. A rotor support structure according to claim 1, characterized in that, The worm (3) is rotatably installed on a worm seat (9), the position of the worm seat (9) is relatively fixed with that of the support cylinder (1), and one end of the worm (3) is in transmission connection with a stepping motor (10) installed on the worm seat (9).

6. A rotor support structure according to claim 1, characterized in that, In the small stiffness state, the pressing block (4) does not contact the side wall of the strip-shaped hole (5); in the large stiffness state, the worm gear (2) rotates circumferentially to drive the pressing block (4) to squeeze the side wall of the corresponding strip-shaped hole (5).

7. A rotor support structure according to claim 1, characterized in that The strip-shaped hole (5) is arranged along the axial direction of the support cylinder (1).

8. A rotor support structure according to claim 1, characterized in that, The support cylinder (1) includes a first support ring (11), a second support ring (12) and connecting rods (13). The first support ring (11) and the second support ring (12) are arranged in parallel; one end of the connecting rod (13) is fixedly connected with the first support ring (11), and the other end is fixedly connected with the second support ring (12). There are a plurality of connecting rods (13), and the plurality of connecting rods (13) are arranged along the circumferential direction of the first support ring (11). The strip-shaped hole (5) is formed between two adjacent connecting rods (13).

9. The rotor support structure according to claim 8, wherein, When the pressing block (4) presses against the side wall of the corresponding strip-shaped hole (5), the stiffness K of the support cylinder (1) 支撑筒 is calculated as follows: where b 等效 = cb, c is the equivalent coefficient, and c > 1, E is the Young's modulus of the material of the support cylinder (1), L is the length of the connecting rod (13), n is the number of the connecting rods (13), b is the width of the connecting rod (13), and h is the thickness of the connecting rod (13).

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