Rubbing test device for rotor and stator of labyrinth sealing structure

Abstract

The invention relates to a rotor and stator rub-impact test device of a labyrinth seal structure, belongs to the technical field of rub-impact vibration tests of gas turbines, and solves the problem that an existing test device cannot simulate a complex nonlinear vibration phenomenon in an elastic supporting state. The rub-impact test device comprises a rotating shaft, a rotor elastic supporting assembly, a stator supporting seat, a rotor labyrinth drum and a stator honeycomb drum, the rotating shaft is supported by the rotor elastic supporting assembly; the rotor labyrinth drum and the rotating shaft are fixedly connected and synchronously rotate; the stator honeycomb drum is fixedly mounted on the stator supporting seat; the stator honeycomb drum and the rotor labyrinth drum are coaxial, and the edge of the stator honeycomb drum and the edge of the rotor labyrinth drum are mutually overlapped; the tail end of the rotor labyrinth drum is provided with a labyrinth top, and when the rotating shaft rotates, the labyrinth top can rub against the stator honeycomb drum. According to the invention, the rub-impact response of the rotor and the stator of the gas turbine can be simulated under laboratory conditions.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine rub-impact vibration tests, and particularly to a stator-rotor rub-impact test device for a labyrinth seal structure. Background Art

[0002] The labyrinth seal structure is a main technical means for dynamic seals of high-speed rotating machinery such as gas turbine units, aero gas turbine engines, and steam turbines. It usually consists of a rotating housing with multiple labyrinth teeth and a stationary housing with a honeycomb layer. Its operating state seriously affects the overall performance, economic benefits, and safety of the whole machine. However, with the continuous improvement of the overall performance and component efficiency of gas turbine units, the stator-rotor clearance of the labyrinth seal device is getting smaller and smaller, and the risk of stator-rotor rub-impact is getting higher and higher. Due to the weak static stiffness, multiple and dense vibration modes of the labyrinth seal structure of the gas turbine unit, it is extremely easy to generate large-amplitude vibrations under the excitation of dynamic loads such as stator-rotor rub-impact forces, causing adverse effects such as fatigue damage of parts and an increase in the overall vibration level of the equipment. It will also exacerbate the wear of the wear-resistant layer, resulting in an excessive sealing clearance, which may lead to deterioration of the sealing performance, changes in the rotor axial force, and invasion of high-temperature gas endangering the structural safety.

[0003] Currently, although there are relatively rich studies on existing labyrinth seal rub-impact tests, all relevant studies are based on a rigid labyrinth shaft or disk and a rigid stator. Its test apparatuses have two major limitations: one is that due to the too large stiffness of the stator-rotor structure, it is difficult to excite the structural vibration, and it cannot simulate the complex non-linear vibration phenomenon caused by stator-rotor rub-impact during the actual working process of the labyrinth seal structure of the gas turbine unit; the other is that the vibration of the rotor parts of the labyrinth seal structure in the actual gas turbine unit is affected by the whirling of the rotor shafting, and the rigid support structure of the existing test device cannot simulate the rotor whirling. In addition to the test apparatuses for the labyrinth seal structure, other existing types of stator-rotor rub-impact test apparatuses or vibrating test apparatuses for drum-like structures cannot simulate the rub-impact vibration of the labyrinth seal structure under laboratory conditions only through simple modification.

[0004] Therefore, it is necessary to provide a stator-rotor rub-impact test device for a labyrinth seal structure to realize the rub-impact experiment on the stator-rotor in an elastically supported state under laboratory conditions. Summary of the Invention

[0005] In view of the above analysis, the present invention aims to provide a stator-rotor rub-impact test device for a labyrinth seal structure to solve the problem that the existing rub-impact test device cannot simulate the complex non-linear vibration phenomenon generated in the elastically supported state.

[0006] The object of the present invention is mainly achieved through the following technical solutions:

[0007] A stator-rotor rubbing test device for a labyrinth seal structure, comprising: a rotating shaft, a rotor elastic support assembly, a stator support seat, a rotor labyrinth drum and a stator honeycomb drum; the rotating shaft is supported by the rotor elastic support assembly; the rotor labyrinth drum is fixedly connected to the rotating shaft and rotates synchronously therewith; the stator honeycomb drum is fixedly installed on the stator support seat; the stator honeycomb drum is coaxial with the rotor labyrinth drum and the edge of the stator honeycomb drum overlaps with the edge of the rotor labyrinth drum; a labyrinth tooth tip is provided at the end of the rotor labyrinth drum, and when the rotating shaft rotates, the labyrinth tooth tip can rub against the stator honeycomb drum.

[0008] Further, the rotor elastic support assembly includes: a rotor support seat, a bearing and an elastic ring; the rotating shaft is rotatably installed on the rotor support seat through the bearing and the elastic ring; the rotating shaft is connected to the inner ring of the bearing, and the elastic ring is provided between the outer ring of the bearing and the rotor support seat.

[0009] Further, the rotor elastic support assembly further includes: a locking nut; the locking nut is screwed onto the outside of the rotating shaft through a thread.

[0010] Further, the rotor elastic support assembly further includes: a shrink disc; the shrink disc is arranged between the rotor labyrinth drum and the rotating shaft for realizing the fixed connection between the two.

[0011] Further, a honeycomb ring is fixedly connected to the inner side of the edge of the stator honeycomb drum.

[0012] Further, the tip of the labyrinth tooth tip points to the middle of the honeycomb ring.

[0013] Further, it further includes: an assembly platform; the rotor support seat and the stator support seat are both installed on the assembly platform.

[0014] Further, a first T-shaped chute and a second T-shaped chute are provided on the assembly platform.

[0015] Further, multiple first T-shaped chutes and multiple second T-shaped chutes are both arranged in an array and the first T-shaped chutes and the second T-shaped chutes are arranged vertically and horizontally in a crisscross manner.

[0016] Further, sliding blocks are fixedly provided at the bottoms of the rotor support seat and the stator support seat; the sliding blocks are slidably installed in the first T-shaped chute or the second T-shaped chute; the rotor support seat and the stator support seat are both fixedly connected to the assembly platform through fastening screws.

[0017] The technical solution of the present invention can at least achieve one of the following effects:

[0018] 1. The stator-rotor rubbing test device for the labyrinth seal structure of the present invention supports the rotating shaft in the structural form of a rotor elastic support assembly. Under the action of the elastic ring, the support stiffness of the rotor is elastic, simulating the elastic support state of the gas turbine rotor. By adjusting the rotor speed, an obvious rotor whirl effect can be generated during the test, effectively simulating the whirl state of the gas turbine rotor.

[0019] 2. The stator-rotor rubbing test device for the labyrinth seal structure of the present invention conducts rubbing using the rotor labyrinth drum in the form of a thin-walled drum and the stator honeycomb drum. The static strength of the drum structure is weak, and the vibration modes are dense. The present invention effectively simulates the dynamic characteristics of the labyrinth seal structure of the real gas turbine device through the double-drum design, and can generate an obvious vibration effect during the test.

[0020] 3. The stator-rotor rubbing test device for the labyrinth seal structure of the present invention drives the rotating shaft to rotate through a motor. The rotor system is supported by a single fulcrum, which is convenient for adjusting the concentricity between the rotor labyrinth drum and the motor shaft; the stator system only includes two parts, namely the stator honeycomb drum and the stator support seat, with a simple structure and good manufacturability.

[0021] In the present invention, the above technical solutions can also be combined with each other to achieve more preferred combination schemes. Other features and advantages of the present invention will be described in the subsequent specification, and some advantages can be made obvious from the specification or understood by implementing the present invention. The objectives and other advantages of the present invention can be achieved and obtained through the content specifically pointed out in the specification and the drawings. Description of the Drawings

[0022] The drawings are only used for the purpose of showing specific embodiments and are not considered as a limitation to the present invention. Throughout the drawings, the same reference signs represent the same components.

[0023] Figure 1 is a schematic structural diagram of the stator-rotor rubbing test device for the labyrinth seal structure of Embodiment 1 of the present invention;

[0024] Figure 2 is a schematic semi-sectional view of the stator-rotor rubbing test device for the labyrinth seal structure of Embodiment 1 of the present invention;

[0025] Figure 3 is the labyrinth seal structure in an actual gas turbine;

[0026] Figure 4 is the honeycomb ring structure between the stator and the rotor of the gas turbine;

[0027] Figure 5 is a 1 / 4 sectional view of the elastic support assembly of the stator-rotor rubbing test device for the labyrinth seal structure of Embodiment 1 of the present invention;

[0028] Figure 6 Schematic structural diagram of the rotor labyrinth drum of the stator-rotor rubbing test device for the labyrinth sealing structure according to Embodiment 1 of the present invention;

[0029] Figure 7 Schematic structural diagram of the stator honeycomb drum of the stator-rotor rubbing test device for the labyrinth sealing structure according to Embodiment 1 of the present invention;

[0030] Figure 8 Schematic structural diagram of the elastic ring of the stator-rotor rubbing test device for the labyrinth sealing structure according to Embodiment 1 of the present invention;

[0031] Figure 9 Schematic diagram of the mating state between the labyrinth tooth tips of the rotor labyrinth drum and the honeycomb ring of the stator-rotor rubbing test device for the labyrinth sealing structure according to Embodiment 1 of the present invention;

[0032] Figure 10 Schematic diagram of the assembly effect of the stator-rotor rubbing test device for the labyrinth sealing structure according to Embodiment 2 of the present invention;

[0033] Figure 11 Schematic structural diagram of the elastic ring with adjustable stiffness of the stator-rotor rubbing test device for the labyrinth sealing structure according to Embodiment 2 of the present invention;

[0034] Figure 12 Schematic diagram of the misaligned state between the inner support ring and the outer support ring of the elastic ring with adjustable stiffness of the stator-rotor rubbing test device for the labyrinth sealing structure according to Embodiment 2 of the present invention.

[0035] Reference numerals:

[0036] 1 - Assembly platform; 2 - Rotor support seat; 3 - Rotating shaft; 4 - Locking nut; 5 - Bearing; 6 - Bearing end cover; 7 - Elastic ring; 8 - Expansion sleeve; 9 - Rotor labyrinth drum; 10 - Honeycomb ring; 11 - Stator honeycomb drum; 12 - Stator support seat; 13 - Gas turbine stator; 14 - Metal honeycomb layer; 15 - Gas turbine labyrinth rotor;

[0037] 101 - First T-shaped chute; 102 - Second T-shaped chute;

[0038] 71 - Inner convex platform; 72 - Outer convex platform; 73 - Elastic sheet; 74 - Limiting block;

[0039] 701 - Elastic inner ring; 702 - Elastic outer ring; 703 - First convex platform; 704 - Second convex platform; 705 - First positioning hole; 706 - Second positioning hole;

[0040] 91 - Labyrinth tooth tip; 92 - Rotor thin-walled cylinder; 93 - Rotor mounting disc;

[0041] 111 - Stator mounting disk; 112 - Stator thin - walled cylinder; 113 - Stator mounting hole. Detailed implementation manners

[0042] The following combines the accompanying drawings to specifically describe the preferred embodiments of the present invention. Among them, the accompanying drawings form a part of the present invention and are used together with the embodiments of the present invention to explain the principles of the present invention, rather than to limit the scope of the present invention.

[0043] Embodiment 1

[0044] A specific embodiment of the present invention discloses a stator - rotor rubbing test device for a labyrinth seal structure, as Figure 1 、 Figure 2 shown, including: a rotating shaft 3, a rotor elastic support assembly, a stator support seat 12, a rotor labyrinth drum 9, and a stator honeycomb drum 11; the rotating shaft 3 is supported by the rotor elastic support assembly; the rotor labyrinth drum 9 is fixedly connected to the rotating shaft 3 and rotates synchronously; the stator honeycomb drum 11 is fixedly installed on the stator support seat 12; the stator honeycomb drum 11 is coaxial with the rotor labyrinth drum 9 and the edge of the stator honeycomb drum 11 overlaps with the edge of the rotor labyrinth drum 9; the end of the rotor labyrinth drum 9 is provided with labyrinth tooth tips 91, and when the rotating shaft 3 rotates, the labyrinth tooth tips 91 can rub against the stator honeycomb drum 11.

[0045] The labyrinth seal device is a common means for air - path sealing in parts such as the main flow path and the internal cooling air system of an aero - gas turbine. As Figure 3 、 Figure 4 shown, the labyrinth seal structure in an actual gas turbine usually consists of a gas - turbine labyrinth rotor 15 with multiple labyrinths and a gas - turbine stator 13 with an easily - worn honeycomb layer 14. The vibration of the labyrinth seal structure caused by rubbing may induce stator - rotor coupled vibration, and even stator - rotor coupled resonance, threatening the structural safety. Stator - rotor coupled resonance means that the traveling - wave frequencies of the vibration modes with the same number of nodal diameters of the two are equal in the same reference coordinate system. The coupling of stator - rotor modes will produce coupled resonance and even trigger unstable vibration, causing adverse effects such as fatigue damage of parts and an increase in the overall vibration level of the gas turbine. During the rubbing process of the labyrinth seal in a gas turbine, complex behaviors such as plastic deformation, tearing, scraping, buckling, and even being melted by high temperature often occur. In engineering, it is often necessary to obtain the rotational speed range in which stator - rotor coupled resonance may occur for a specific labyrinth seal structure through theoretical or experimental means, which is called the coupled resonance speed range.

[0046] The actual labyrinth seal structure is complex and not suitable for conducting rubbing tests in a laboratory environment. To facilitate the reproduction of the rubbing state between the rotor and stator of the labyrinth seal structure, in the rubbing test device for the rotor-stator of the labyrinth seal structure of the present invention, the end of the rotor labyrinth drum 9 and the end of the stator honeycomb drum 11 are nested with each other. When the rotor labyrinth drum 9 rotates, the labyrinth tooth tips 91 at its end can generate diametral vibration along the radial direction, and then the labyrinth tooth tips 91 can rub against the honeycomb ring 10 installed inside the stator honeycomb drum 11, realizing the coupled vibration between the rotor labyrinth drum 9 and the stator honeycomb drum 11.

[0047] Further, as Figure 5 shown, the rotor elastic support assembly includes: a rotor support seat 2, a bearing 5, and an elastic ring 7; the rotating shaft 3 is rotatably installed on the rotor support seat 2 through the bearing 5 and the elastic ring 7; the rotating shaft 3 is connected to the inner ring of the bearing 5, and the elastic ring 7 is arranged between the outer ring of the bearing 5 and the rotor support seat 2.

[0048] Further, as Figure 5 shown, the rotor elastic support assembly further includes: a lock nut 4; the lock nut 4 is screwed onto the outside of the rotating shaft 3 through a thread.

[0049] As Figure 5 shown, the rotor elastic support assembly further includes: a shrink disc 8; the shrink disc 8 is arranged between the rotor labyrinth drum 9 and the rotating shaft 3 for realizing the fixed connection between the two. In this embodiment, the rotor labyrinth drum 9 and the rotating shaft 3 are rigidly connected by the shrink disc 8, and thus the rotor labyrinth drum 9 can rotate synchronously with the rotating shaft 3.

[0050] Further, a bearing end cover 6 is further arranged outside the bearing 5; the bearing end cover 6 is fixedly installed on the rotor support seat 2 by bolts.

[0051] In this embodiment, as Figure 6 shown, the rotor labyrinth drum 9 includes: labyrinth tooth tips 91, a rotor thin-walled cylinder 92, and a rotor mounting disc 93. Specifically, a rotor mounting hole is arranged in the middle of the rotor mounting disc 93, the shrink disc 8 is installed in the rotor mounting hole, and the fixed connection between the rotor labyrinth drum 9 and the rotating shaft 3 is realized through the shrink disc 8. The rotor thin-walled cylinder 92 is arranged at the edge of the rotor mounting disc 93 and is perpendicular to the rotor mounting disc 93. The labyrinth tooth tips 91 are annular structures arranged on the outside of the end of the rotor thin-walled cylinder 92.

[0052] Preferably, the tip 91 of the labyrinth tooth is trapezoidal in cross-section. When the rotor mounting disk 93 rotates at a high speed driven by the rotating shaft 3, it can excite the nodal diameter vibration of the tip 91 of the labyrinth tooth at the end of the rotor thin-walled cylinder 92, and then the tip 91 of the labyrinth tooth can rub against the honeycomb ring 10 inside the stator honeycomb cylinder 11.

[0053] In this embodiment, as Figure 7 shown, the stator honeycomb cylinder 11 includes: a stator mounting disk 111 and a stator thin-walled cylinder 112; specifically, the stator thin-walled cylinder 112 is arranged at the edge of the stator mounting disk 111 and is perpendicular to the stator thin-walled cylinder 112. Specifically, a plurality of stator mounting holes 113 are provided on the stator mounting disk 111, bolts are installed in the stator mounting holes 113, and are fixedly connected to the stator support seat 12 through the bolts.

[0054] Furthermore, a honeycomb ring 10 is fixedly connected to the inner side of the edge of the stator honeycomb cylinder 11. At the same time, the tip of the tip 91 of the labyrinth tooth points to the middle of the honeycomb ring 10.

[0055] In this embodiment, both the rotor labyrinth cylinder 9 and the stator honeycomb cylinder 11 are made of steel, and the wall thicknesses of the rotor thin-walled cylinder 92 and the stator thin-walled cylinder 112 are both not greater than 2 mm, making them have weak structural stiffness and dense vibration modes.

[0056] As Figure 1 、 Figure 2 、 Figure 5 shown, both the rotor labyrinth cylinder 9 and the stator honeycomb cylinder 11 are of thin-walled cylinder structures, and the roots of the cylinders are in the form of thick disks. This type of structure not only realizes low structural stiffness so that the nodal diameter vibration of the cylinder is easy to excite, but also tries to be similar to the structural form of the rigid disk and labyrinth ring combination of the labyrinth seal structure of the gas turbine device, so that the vibration modes generated by the test device are in good agreement with the vibration modes of the gas turbine.

[0057] In a specific embodiment of the present invention, the labyrinth seal structure rotor-stator rubbing test device further includes: an assembly platform 1; both the rotor support seat 2 and the stator support seat 12 are installed on the assembly platform 1.

[0058] Specifically, as Figure 1As shown in the figure, a first T-shaped chute 101 and a second T-shaped chute 102 are provided on the assembly platform 1. A plurality of the first T-shaped chutes 101 and the second T-shaped chutes 102 are both arranged in an array, and the first T-shaped chutes 101 and the second T-shaped chutes 102 are arranged vertically and horizontally in a crisscross manner. Correspondingly, sliding blocks are fixedly provided at the bottoms of the rotor support base 2 and the stator support base 12; the sliding blocks are slidably installed in the first T-shaped chute 101 or the second T-shaped chute 102; the rotor support base 2 and the stator support base 12 are both fixedly connected to the assembly platform 1 through fastening screws.

[0059] Specifically, when the fastening screw is tightened, the end of the fastening screw protrudes from the lower surface of the sliding block, and then the sliding block at the bottom of the rotor support base 2 or the stator support base 12 is jacked up, so that the sliding block is tightly abutted against the top surface of the first T-shaped chute 101 or the second T-shaped chute 102, realizing the firm connection between the rotor support base 2 or the stator support base 12 and the assembly platform 1.

[0060] In this embodiment, by sliding the rotor support base 2 and the stator support base 12 along the first T-shaped chute 101 or the second T-shaped chute 102, the distance and relative position between the rotor support base 2 and the stator support base 12 can be adjusted, and further, the distance between the rotor labyrinth drum 9 and the stator honeycomb drum 11 can be adjusted and the coaxiality between the two can be adjusted.

[0061] In a specific embodiment of the present invention, circumferentially uniformly distributed protrusions are provided on both the inner and outer ring surfaces of the elastic ring 7 for providing elastic support for the rotating shaft 3. Specifically, as Figure 8 shown, a plurality of inner protrusions 71 are circumferentially uniformly arranged on the inner ring surface of the elastic ring 7, a plurality of outer protrusions 72 are circumferentially uniformly arranged on the outer ring surface of the elastic ring 7, and the inner protrusions 71 and the outer protrusions 72 are arranged in a staggered manner.

[0062] In this embodiment, as Figure 8 shown, the ability of the elastic ring 7 to bear radial loads is limited by the bending stiffness of the elastic sheet 73 between the inner protrusions 71 and the outer protrusions 72. Therefore, when the elastic stiffness of the elastic ring 7 is small, the support stiffness of the rotor system composed of the rotating shaft 3 and the rotor labyrinth drum 9 is small; by designing the critical speed of the rotor, a certain lateral resonance can occur in the rotor system within the test operating speed, so as to excite obvious rotor whirl to simulate the rotor shaft whirl phenomenon in the gas turbine device.

[0063] In this embodiment, by changing the number of the inner protrusions 71 and the outer protrusions 72 and the thickness of the elastic sheet 73, the support stiffness of the rotor system can be adjusted, and further, the vibration modes of the rotor and stator under different stiffness support states can be simulated.

[0064] Further, a limiting block 74 is machined on the inner side of the elastic ring 7 for restricting the axial displacement of the bearing 5. Specifically, as Figure 8 shown, the limiting block 74 is arranged perpendicular to the inner surface of the elastic sheet 73; when the outer ring of the bearing 5 is sleeved on the inner side of the elastic ring 7, the limiting block 74 contacts one end face of the bearing 5.

[0065] Further, as Figure 5 shown, by screwing the fastening nut 4 onto the rotating shaft 3, the fastening nut 4 contacts the other end face of the bearing 5, enabling the two ends of the bearing 5 to be limited and restricting its installation position on the rotating shaft 3.

[0066] As Figure 9 shown, the honeycomb ring 10 is welded to the inner side of the stator honeycomb drum 11, and the stator honeycomb drum 11 and the rotor labyrinth drum 9 are concentrically installed; the axial position of the labyrinth tooth tip 91 is set in the middle of the honeycomb ring 10, and there is an assembly gap evenly distributed along the circumference between the two.

[0067] Preferably, the gap between the labyrinth tooth tip 91 and the honeycomb ring 10 is less than 0.5 mm.

[0068] Further, the rotating shaft 3 is connected to the driving motor through a coupling; thus, the rotating shaft 3 can rotate at a high speed under the drive of the driving motor.

[0069] Further, the labyrinth seal structure stator-rotor rubbing test device further includes a displacement sensor and a rotational speed sensor; the displacement sensor is used to monitor the vibration displacement at the end of the rotor thin-walled cylinder 92 when the rotor labyrinth drum 9 rotates; the rotational speed sensor is used to monitor the rotational speed of the rotating shaft 3. Preferably, the displacement sensor adopts a non-contact displacement sensor.

[0070] During implementation, when the rotational speed of the rotor system is near the critical speed and the rotor whirling displacement is large enough, that is, when the displacement of the labyrinth tooth tip 91 exceeds the stator-rotor clearance, the rotor labyrinth drum 9 rubs against the stator honeycomb drum 11. The rubbing will generate a strong non-linear rubbing force. Since the structural stiffness of the collision objects is weak, the rubbing will trigger obvious rubbing vibrations, facilitating the measurement and analysis of the rubbing vibration response of the labyrinth seal structure under laboratory conditions.

[0071] The specific working process of this example is as follows:

[0072] The rotating shaft 3 passes through the inner ring of the bearing 5 and is axially fixed by a locking nut 4. The outer ring of the bearing 5 is sleeved into an elastic ring 7, and then the bearing end cover 6 is fixed to the rotor support seat 2 by bolts. The rotor support seat 2 is installed on the assembly platform 1 by fastening screws. Secondly, the rotor labyrinth drum 9 is installed on the rotating shaft 3 through a shrink fit coupling sleeve 8. Then, the stator honeycomb drum 11 is installed on the stator support seat 12 by bolts. Before tightening the fastening screws, by adjusting the positions of the rotor support seat 2 and the stator support seat 12, the stator honeycomb drum 11 is made concentric with the rotor labyrinth drum 9, and the relative position between the labyrinth tooth tip 91 and the honeycomb ring 10 is adjusted by changing the axial position of the stator support seat 12. After the assembly is completed, the rotating shaft 3 is connected to the driving motor through a flat key and a coupling, and an eddy current displacement sensor and a speed sensor are arranged. The motor is started, and the motor speed is controlled to gradually increase until it is near the critical speed of the rotor system. At this time, the vibration displacement of the rotor labyrinth drum 9 increases, and it rubs against the stator honeycomb drum 11, exciting the vibration of the thin-walled drum structure. The data is collected by the displacement sensor and the speed sensor through a data acquisition device and sent to the computer.

[0073] Exemplarily, the stiffness of the elastic ring 7 is set to be 1×10 7 N / m, the assembly clearance between the labyrinth tooth tip 91 of the rotor and the stator honeycomb drum 11 is 0.2 mm, and the critical speed of the rotor is 2400 revolutions per minute; when in resonance, the whirling displacement of the labyrinth tooth tip 91 is not less than 0.5 mm, and the assembly clearance between the labyrinth tooth tip 91 of the rotor and the stator honeycomb drum 11 is less than the vibration displacement of the labyrinth tooth tip 91. Therefore, near the critical speed, the rotor and stator will rub against each other, generating a non-linear rubbing force. In the range of 1000 - 1600 Hz, there are at least 5 resonance modes between the two thin-walled drums, and obvious rubbing coupling vibration will be generated under the action of the non-linear rubbing force.

[0074] The labyrinth seal structure rotor-stator rubbing test device provided by the present invention adopts an elastic support and a thin-walled drum structure, and at the same time has the characteristics of elastic support of the rotor and weak stiffness of the rubbing parts, and can generate obvious rotor whirling effect and rubbing vibration response in the test.

[0075] Factors such as the structural size and material of the honeycomb layer also have a significant impact on the rubbing and rotor-stator coupling vibration phenomena. In the present invention, by replacing the honeycomb rings 10 of different structural types, it can be used to study the influence law of the honeycomb layer on the rubbing vibration under different structural types and different stiffness conditions.

[0076] Compared with the prior art, the technical solution provided by this embodiment has at least one of the following beneficial effects:

[0077] 1. The stator-rotor rubbing test device for the labyrinth seal structure of the present invention conducts dynamic design on the thin-walled drum structure so that it can simulate the dynamic characteristics of the actual labyrinth seal structure. On the one hand, the thin-walled drum structure of the present invention has the characteristics of weak stiffness. On the other hand, its coupled resonance speed range is near the rated speed of the laboratory motor, which is convenient for studying the vibration modes under the stator-rotor rubbing state of the gas turbine.

[0078] 2. In the stator-rotor rubbing test device for the labyrinth seal structure of the present invention, the rotor system adopts elastic supports, so that the rotor labyrinth drum 9 of the rotor system can generate sufficient whirling in the coupled resonance speed range to cause stator-rotor rubbing, thereby exciting the stator-rotor coupled vibration. By simulating the stator-rotor coupled vibration of the present invention and obtaining the structural parameters of the rotor labyrinth drum 9, the stator honeycomb drum 11 and the honeycomb ring 10 as well as the speed of the rotating shaft 3 under the corresponding vibration modes, it can inversely guide the structural strength of the stator-rotor system of the gas turbine and the design of the critical speed of the gas turbine.

[0079] 3. In the stator-rotor rubbing test device for the labyrinth seal structure of the present invention, the stator honeycomb drum 11 and the honeycomb ring 10 are combined to simulate the gas turbine stator 13 and the metal honeycomb layer 14 inside it. By replacing the stator honeycomb drum 11 welded with honeycomb rings 10 of different types and different stiffnesses and then conducting tests, the influence laws of the metal honeycomb layer 14 with different structures or materials on the rubbing vibration and the stator-rotor coupled vibration can be obtained through tests.

[0080] Embodiment 2

[0081] A specific embodiment of the present invention is an improved design based on Embodiment 1:

[0082] In this embodiment, as Figure 10 shown, the stator-rotor rubbing test device for the labyrinth seal structure of this embodiment adopts an elastic ring 7 structure with adjustable stiffness.

[0083] As Figure 11 , Figure 12 shown, the elastic ring 7 includes an elastic inner ring 701 and an elastic outer ring 702 that are sleeved with each other. A plurality of first protrusions 703 are equidistantly arranged on the outer surface of the elastic inner ring 701, and a plurality of second protrusions 704 are equidistantly arranged on the outer surface of the elastic outer ring 702. The outer end surface of the first protrusion 703 is in extrusion contact with the inner surface of the elastic outer ring 702. By relatively rotating the elastic inner ring 701 and the elastic outer ring 702 to adjust the first protrusion 703 and the second protrusion 704 to be aligned or misaligned, the overall stiffness of the elastic ring 7 can be adjusted.

[0084] Preferably, the number of the first bosses 703 and the second bosses 704 is set to four. That is to say, two adjacent first bosses 703 are arranged at an interval of 90° on the elastic inner ring 701; two adjacent second bosses 704 are arranged at an interval of 90° on the elastic outer ring 702.

[0085] Further, in this embodiment, after the elastic inner ring 701 and the elastic outer ring 702 are assembled, they can be clamped with each other and can rotate under the action of an external force. Preferably, the fitting relationship between the fitting surfaces of the elastic inner ring 701 and the elastic outer ring 702 is a small clearance fit or an interference fit, and the two are allowed to rotate relative to each other under the action of an external force.

[0086] Specifically, the elastic inner ring 701 and the elastic outer ring 702 are concentrically assembled, and a first positioning hole 705 and a second positioning hole 706 are respectively designed on the elastic inner ring 701 and the elastic outer ring 702; both the first positioning hole 705 and the second positioning hole 706 are threaded blind holes, and after screws are screwed into the first positioning hole 705 and the second positioning hole 706, a torque can be applied to the elastic inner ring 701 and / or the elastic outer ring 702 to make the two rotate relative to each other.

[0087] Further, as Figure 11 、 Figure 12 shown, by driving the relative rotation of the elastic inner ring 701 and the elastic outer ring 702, the relative positions of the first bosses 703 and the second bosses 704 can be adjusted, and further the overall stiffness of the elastic ring 7 can be adjusted; in this embodiment, by rotating the elastic inner ring 701 and / or the elastic outer ring 702 to adjust the support stiffness provided by the elastic ring 7 to the rotating shaft 3, the vibration modes of the gas turbine under different support stiffness conditions can be simulated, and at the same time, the influence of the support stiffness of the rotor on the rub-impact response can be studied, which has guiding significance for the design and application of the gas turbine.

[0088] Specifically, the relative positions of the first bosses 703 and the second bosses 704 are represented by the included angle θ between the connecting lines of the two and the center O of the elastic ring 7. As Figure 11 、 Figure 12 shown, when the first bosses 703 and the second bosses 704 of the elastic inner ring 701 and the elastic outer ring 702 are opposite to each other, that is, when θ = 0°, the elastic ring 7 transmits the radial force through the first bosses 703 and the second bosses 704, and the support stiffness provided to the rotating shaft 3 is the largest; when the elastic inner ring 701 and / or the elastic outer ring 702 are rotated so that the second boss 704 is located in the middle of two adjacent first bosses 703, that is, when θ = 45°, the elastic ring 7 is supported by the first bosses 703 and the elastic arc pieces of the elastic outer ring 702, and the support stiffness is the smallest at this time.

[0089] In this embodiment, the adjustable support stiffness is achieved by designing the elastic inner ring 701 and the elastic outer ring 702 to rotate at different angles. By adjusting the thickness of the elastic sheet, the number of convex platforms, the width of the convex platforms, and the included angle between the inner and outer elastic rings, the support stiffness is changed, so that the rotor system has a large enough whirling motion in the "coupling resonance speed range" to cause rubbing, and the rubbing coupling vibration response under different support stiffness conditions can be simulated.

[0090] The above are only the preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A stator-rotor rubbing test device for a labyrinth seal structure, characterized in that, Comprising: A rotating shaft (3), a rotor elastic support assembly, a stator support base (12), a rotor labyrinth drum (9) and a stator honeycomb drum (11); the rotating shaft (3) is supported by the rotor elastic support assembly; the rotor labyrinth drum (9) is fixedly connected to the rotating shaft (3) and rotates synchronously therewith; the stator honeycomb drum (11) is fixedly installed on the stator support base (12); a labyrinth tooth tip (91) is provided at the end of the rotor labyrinth drum (9), and when the rotating shaft (3) rotates, the labyrinth tooth tip (91) can rub against the stator honeycomb drum (11).

2. The stator-rotor rubbing test device for the labyrinth seal structure according to claim 1, characterized in that The rotor elastic support assembly includes: a rotor support base (2), a bearing (5) and an elastic ring (7).

3. The stator-rotor rubbing test device for the labyrinth seal structure according to claim 2, characterized in that, The rotating shaft (3) is rotatably installed on the rotor support base (2) through the bearing (5) and the elastic ring (7).

4. The stator-rotor rubbing test device for the labyrinth seal structure according to claim 3, characterized in that The rotating shaft (3) is connected to the inner ring of the bearing (5), and the elastic ring (7) is provided between the outer ring of the bearing (5) and the rotor support base (2).

5. The stator-rotor rubbing test device for the labyrinth seal structure according to any one of claims 1-3, characterized in that The rotor elastic support assembly further includes: a locking nut (4); the locking nut (4) is screwed onto the outside of the rotating shaft (3) by threads.

6. The stator-rotor rubbing test device for the labyrinth seal structure according to any one of claims 1-3, characterized in that The rotor elastic support assembly further includes: a shrink disc (8).

7. The stator-rotor rubbing test device for the labyrinth seal structure according to claim 6, wherein, The shrink disc (8) is arranged between the rotor labyrinth drum (9) and the rotating shaft (3) for realizing the fixed connection therebetween.

8. The stator-rotor rubbing test device for the labyrinth seal structure according to claim 1, characterized in that A honeycomb ring (10) is fixedly connected to the inner side of the edge of the stator honeycomb drum (11).

9. The stator-rotor rubbing test device for the labyrinth seal structure according to claim 8, characterized in that, The tip of the labyrinth tooth tip (91) points to the middle of the honeycomb ring (10).

10. The labyrinth seal structure stator-rotor rubbing test device according to claim 2, characterized in that, Further comprising: An assembly platform (1); both the rotor support base (2) and the stator support base (12) are installed on the assembly platform (1).

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