Aero-engine rotor experimental device

Abstract

The invention provides an aero-engine rotor experiment device, and relates to the field of aero-engine experiment and test. The aero-engine rotor experiment device comprises a rotor, a support, a bearing and a movable assembly. The support rotor is rotationally connected to the support; the movable assembly comprises a first movable part and a second movable part, and the first movable part is connected to the support and located in the radial direction of the rotor; the second movable part is connected to the support and movably connected to the first movable part. The second movable part can provide upward acting force for the first movable part; the first movable part can move back and forth relative to the second movable part in the direction perpendicular to the axial direction of the rotor. According to the aero-engine rotor experimental device in the embodiment of the invention, thermal expansion supported in a high-temperature environment is absorbed through the movable assembly, and the stability of a test result of an experiment is improved.

Description

Technical Field

[0001] The present invention relates to the field of aero-engine experiments and tests, and particularly to an aero-engine rotor experimental device. Background Art

[0002] In the related art, due to the complex structure and actual operating environment of an aero-engine, the prior art makes a dedicated experimental device for the aero-engine to simulate and analyze the structural system dynamics characteristics of the corresponding aero-engine in a preset experimental environment.

[0003] In order to further restore the real scenario of the aero-engine, the prior art has proposed an experimental device including a bracket, a rotor, a bearing and a casing. In the above experimental device, the rotor, the bearing and the casing are used as the whole experimental object, and the bracket is used to connect the bearing to fix the whole formed by the rotor, the bearing and the casing. By exploring the structural system dynamics characteristics of the rotor, the bearing and the casing, the distribution law of the deformation energy of the load-bearing structure and the dynamic load transfer law of the aero-engine under complex flight conditions can be further mastered.

[0004] When testing the experimental device under the high-temperature environment simulating the aero-engine, the bearing generating thermal strain will be affected by the bracket to squeeze the rotor, so that the rotor will also generate strain, thus affecting the test result of the experiment. Summary of the Invention

[0005] The present invention aims to at least solve one of the technical problems existing in the prior art. For this purpose, the present invention provides an aero-engine rotor experimental device, which absorbs the thermal expansion of the bearing in a high-temperature environment through a movable component to improve the stability of the test result of the experiment.

[0006] The aero-engine rotor experimental device according to the first aspect embodiment of the present invention includes: A rotor; A bracket; A bearing, the rotor is rotatably connected to the bearing; A movable component, including a first movable member and a second movable member, the first movable member is connected to the bearing and is located in the radial direction of the rotor; the second movable member is connected to the bracket and is movably connected to the first movable member; the second movable member can provide an upward acting force for the first movable member; the first movable member can move back and forth in a direction perpendicular to the axial direction of the rotor relative to the second movable member.

[0007] The aero-engine rotor experimental device according to an embodiment of the present invention has at least the following beneficial effects: The rotor is rotatably connected to the support. During the experiment, researchers can understand the structural system dynamics characteristics of the rotor and the support as a whole by referring to the relative movement of the rotor and the support as a whole relative to the bracket. When the support generates thermal stress due to a high-temperature environment, the first movable member connected to the support will move relative to the bracket in a direction perpendicular to the axial direction of the rotor due to the thermal strain of the support, thereby absorbing the thermal deformation of the support in the radial direction, reducing the strain of the rotor caused by the support squeezing the rotor, and improving the stability of the test results of the experiment.

[0008] According to some embodiments of the present invention, the movable assembly further includes an adjusting member. The adjusting member includes a first rotating portion and a second rotating portion connected to each other. The first rotating portion is rotatably connected to the bracket and has a first rotation axis; the first movable member is rotatably connected to the second rotating portion and has a second rotation axis; both the first rotation axis and the second rotation axis are parallel to the axis of the rotor. The first rotating portion is located above the second rotating portion and on one side of the rotor in a first direction. The first direction is perpendicular to the axis direction of the rotor and forms an acute angle or a right angle with the vertical direction.

[0009] According to some embodiments of the present invention, the adjusting member further includes an adjusting portion. One end of the adjusting portion is threadedly connected to the first rotating portion, and / or the other end of the adjusting portion is threadedly connected to the second rotating portion.

[0010] According to some embodiments of the present invention, the first rotating portion is slidably connected to the second rotating portion.

[0011] According to some embodiments of the present invention, the first movable member is slidably connected to the second movable member in a first direction. The first direction is perpendicular to the axis direction of the rotor and forms an acute angle or a right angle with the vertical direction.

[0012] According to some embodiments of the present invention, it further includes a casing. The casing is connected to the support. The casing has a receiving cavity. The rotor is partially received in the receiving cavity. The aero-engine rotor experimental device has a symmetric plane extending in the vertical direction. The axis of the rotor is located in the symmetric plane; The aero-engine rotor experimental device includes two movable assemblies. The first movable member of each movable assembly is connected to the support and the bracket; the two movable assemblies are symmetrically arranged with respect to the symmetric plane.

[0013] According to some embodiments of the present invention, the casing further has a first avoidance hole, and the first avoidance hole communicates the accommodation cavity with the outside; the aero-engine rotor experimental device further includes a first sensor, the first sensor is connected to the bracket and is located radially of the rotor, and can detect the radial displacement of the rotor through the first avoidance hole.

[0014] According to some embodiments of the present invention, the axes of the first sensor and the first avoidance hole are both located in the symmetry plane.

[0015] According to some embodiments of the present invention, the bracket includes a connecting shaft, the connecting shaft penetrates into the accommodation cavity through the first avoidance hole, and the first sensor is arranged on one side of the connecting shaft that is accommodated in the accommodation cavity.

[0016] According to some embodiments of the present invention, the rotor includes a rotating shaft, a compressor disk group and a turbine disk, the compressor disk group and the turbine disk are connected to the rotating shaft at different positions in the axial direction of the rotating shaft, the aero-engine rotor experimental device further includes an ignition assembly, the ignition assembly is located between the compressor disk group and the turbine disk in the axial direction of the rotor and is used to generate high-temperature and high-pressure airflow; the aero-engine rotor experimental device includes a plurality of the supports, the plurality of supports are respectively rotatably connected to the rotating shaft at different positions in the axial direction of the rotating shaft, a casing is arranged between the plurality of supports, and an accommodation cavity for accommodating at least a part of the rotor is provided inside the casing, and the ignition assembly is accommodated in the accommodation cavity; define the support located on one side in the second direction of the ignition assembly as the first support, and the support located in the opposite direction of the second direction of the ignition assembly as the second support, and the second direction is the direction from the compressor disk group to the turbine disk; the bracket is connected to one of the first supports through the movable assembly and is fixedly connected to one of the second supports.

[0017] Additional aspects and advantages of the present invention will be given in part in the following description, will become apparent in part from the following description, or will be understood through the practice of the present invention. Description of the Drawings

[0018] The following further describes the present invention in conjunction with the drawings and embodiments, where: Figure 1 is a schematic diagram of the overall aero-engine rotor experimental device according to some embodiments of the first aspect of the present invention; Figure 2 is Figure 1 a schematic diagram of the overall aero-engine rotor experimental device in which some components are removed; Figure 3 is Figure 1 a schematic diagram of the overall rotor in; Figure 4 is Figure 1 Schematic diagram of the connection of the middle rotor, casing and support; Figure 5 is Figure 1 Schematic diagram of the connection of the movable component and the support in; Figure 6 is Figure 5 Partial enlarged view at D in; Figure 7 Schematic diagram of the connection of the movable component and the support in some embodiments of the second aspect of the present invention; Figure 8 is Figure 2 Partial enlarged view at A in; Figure 9 is Figure 1 Schematic diagram of the setting position of the position sensor in; Figure 10 is Figure 8 Partial enlarged view at B in; Figure 11 is Figure 8 Partial enlarged view at C in.

[0019] Reference numerals: Bracket 100, connecting shaft 110; Rotor 200, rotating shaft 210, first mounting section 211, second mounting section 212, third mounting section 213, compressor disk group 230, turbine disk 240; Support 300, first support 300A, second support 300B, load-bearing frame 310, bearing housing 320, load-bearing web 330; Casing 400, accommodation cavity 410, first relief hole 420, second relief hole 430, third relief hole 440; First sensor 501; Movable component 600, first movable member 610, second movable member 620, adjusting member 630, first rotating portion 631, second rotating portion 632, adjusting portion 633; Oil pipeline 700. Detailed implementation manners

[0020] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings, in which the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions from beginning to end. The embodiments described below with reference to the drawings are exemplary and are only used to explain the present invention and should not be construed as a limitation of the present invention.

[0021] In the description of the present invention, it should be understood that for the orientation description, such as the orientation or positional relationship indicated by up, down, front, back, left, right, etc., it is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present invention.

[0022] In the description of the present invention, the meaning of several is more than one, and the meaning of multiple is more than two. Understandings such as greater than, less than, exceeding, etc. do not include the recited number, and understandings such as above, below, within, etc. include the recited number. If there is a description of first and second, it is only for the purpose of distinguishing technical features and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features or implicitly indicating the sequence relationship of the indicated technical features.

[0023] In the description of the present invention, unless otherwise clearly defined, terms such as setting, installing, connecting, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific content of the technical solution.

[0024] In the description of the present invention, the descriptions with reference to terms such as "one embodiment", "some embodiments", "schematic embodiments", "examples", "specific examples", or "some examples" mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0025] Please refer to Figures 1 to 11 as shown, where Figures 1 to 11 All are schematics of an aeroengine rotor experimental device. The present invention provides an aeroengine rotor experimental device, including a bracket 100, a rotor 200, a support 300, and a movable assembly 600.

[0026] The rotor 200 of the present invention is rotatably connected to the support 300. When the rotor 200 is in the experiment, the vibration generated by the rotor 200 will be transmitted to the support 300, and the mass of the support 300 itself will also affect the vibration of the rotor 200. Researchers can use the bracket 100 as a reference object to perform a dynamic analysis on the whole formed by the rotor 200 and the support 300.

[0027] Please refer to Figure 1 、 Figure 5 、 Figure 7As shown, the movable component 600 of the present invention includes a first movable member 610 and a second movable member 620. The first movable member 610 is connected to the support 300 and is located in the radial direction of the rotor 200. The second movable member 620 is connected to the bracket 100 and is movably connected to the first movable member 610. The second movable member 620 can provide an upward acting force for the first movable member 610. The first movable member 610 can reciprocate relative to the second movable member 620 in a direction perpendicular to the axial direction of the rotor 200. It should be understood that since the second movable member 620 provides an upward acting force for the first movable member 610, the support 300 connected to the first movable member 610 can also be supported by the bracket 100 under the action of the second movable member 620.

[0028] The support 300 has a tendency to thermally expand in a high-temperature environment simulating an aeroengine, resulting in the overall expansion of the support 300 in the radial direction of the rotor 200. The first movable member 610 connected to the support 300 can move relative to the second movable member 620 in a direction perpendicular to the axial direction of the rotor 200, which is equivalent to providing a space for the part of the support 300 connected to the first movable member 610 to expand in a direction perpendicular to the axial direction of the rotor 200. The relative movement between the first movable member 610 and the second movable member 620 absorbs the thermal expansion of the support 300 in the moving direction of the first movable member 610, reduces the thermal stress generated by the restricted thermal expansion of the support 300, reduces the strain of the rotor 200 caused by the support 300 squeezing the rotor 200, and thus improves the stability of the operation of the rotor 200 and the stability of the test results of the experiment.

[0029] It should be understood that in the prior art rotor experiment device, considering the length of the rotor, multiple supports rotatably connected to the rotor are arranged in the axial direction of the rotor, and the rotor is located in a fixed position through the rigid connection of multiple supports and the bracket. However, the present invention can replace part of the rigid connection between the support and the bracket of the prior art rotor experiment device, and on the basis of realizing the auxiliary support for the rotor 200, absorb the thermal expansion of part of the support 300.

[0030] Exemplarily, please refer to Figure 4 As shown, in some embodiments, the aeroengine rotor experiment device includes multiple supports 300 connected to the rotor 200, and the multiple supports 300 are respectively located in the axial direction of the rotating shaft 210 (i.e., Figure 4at different positions in the front-rear direction). Among them, the rear support 300 is rigidly connected to the bracket 100, and the front support 300 is connected to the bracket 100 through the movable assembly 600. Then, during the experiment, when the researcher heats the rear support 300 separately in order to verify the dynamic characteristics of the overall structural system of the rotor 200 and the support 300 under high-temperature environment, the heated rear support 300 can generate thermal expansion under high-temperature conditions, reducing the influence of the thermal stress of the rear support 300 itself on the rotor 200.

[0031] Further, please refer to Figure 1 As shown, in some embodiments, the aero-engine rotor experimental device further includes a casing 400. The casing 400 is connected to the support 300 and has a receiving cavity 410. The rotor 200 is partially received in the receiving cavity 410. In the prior art, an aero-engine also includes a rotor, a support, and a casing. Therefore, performing a dynamic analysis on the whole formed by the rotor 200, the support 300, and the casing 400 is beneficial for the researcher to understand the actual working condition of the aero-engine and is beneficial for the structural optimization of the aero-engine.

[0032] Under the simulated high-temperature environment of the aero-engine, the casing 400 is more likely to undergo thermal expansion than the support 300, which will further drive the support 300 to deform. The relative movement of the first movable member 610 and the second movable member 620 in the direction perpendicular to the axial direction of the rotor 200 can also absorb the expansion of the casing 400, reduce the thermal stress generated by the limited thermal expansion of the casing 400, and reduce the possibility of plastic deformation of the casing 400, which is beneficial to improving the overall stability of the aero-engine rotor experimental device and extending the service life of the aero-engine rotor experimental device.

[0033] It should be noted that the present invention does not limit the specific structures of the rotor 200, the support 300, and the casing 400. Please refer to Figures 1 to 4 As shown, in some embodiments, the rotor 200 includes a rotating shaft 210, a compressor disk group 230, and a turbine disk 240. The compressor disk group 230 and the turbine disk 240 are both connected to the rotating shaft 210. The rotating shaft 210 includes an axial direction (i.e., Figures 1 to 4The first mounting section 211, the second mounting section 212 and the third mounting section 213 are arranged in sequence (in the front-to-back direction in FIG), wherein the compressor disk group 230 is arranged between the first mounting section 211 and the second mounting section 212, and the rotating shaft 210 is arranged between the second mounting section 212 and the third mounting section 213; the aircraft engine rotor experimental device includes two casings 400 and three supports 300, the first mounting section 211, the second mounting section 212 and the third mounting section 213 are each rotatably connected to one support 300, one casing 400 is arranged between the support 300 connected to the first mounting section 211 and the support 300 connected to the second mounting section 212, and the other casing 400 is arranged between the support 300 connected to the second mounting section 212 and the support 300 connected to the third mounting section 213.

[0034] Based on the above embodiment, those skilled in the art may adjust the structure and quantity of the support 300, rotor 200, and casing 400 to simulate the operating conditions of aircraft engines with different structures. For example, the position of the support 300 may be adjusted based on the above embodiment, for example, by positioning the first mounting section 211 and the second mounting section 212, which rotatably connect the support 300, between the compressor disk assembly 230 and the turbine disk 240. Furthermore, based on the above embodiment, the number of supports 300 and casing 400, as well as the dimensions of the rotor 200, support 300, and casing 400, may be adjusted. Adjustments based on the above embodiment also fall within the scope of protection of the present invention.

[0035] Without departing from the inventive concept of the present invention, those skilled in the art may choose an implementation method on their own so that the second movable part 620 can provide an upward force to the first movable part 610, and realize that the first movable part 610 can move back and forth relative to the second movable part 620 in a direction perpendicular to the axial direction of the rotor 200.

[0036] As a preferred method, please refer to Figure 1 、 Figure 7 As shown, in some embodiments, the first movable member 610 is slidably connected to the second movable member 620 along a first direction, and the first direction is perpendicular to the axis direction of the rotor 200 (that is, the axis direction of the rotor 200 is Figure 1 (in the front-to-back direction in the vertical direction), and the angle between the first direction and the vertical direction is an acute angle or a right angle. With the above solution, since the angle between the first direction and the vertical direction is an acute angle or a right angle, the second movable member 620 can apply a supporting force perpendicular to the first direction to the first movable member 610, thereby providing an upward force component to the first movable member 610, so that the support 300 can ultimately be supported by the bracket 100.

[0037] On the other hand, when the support 300 has a tendency to expand in the radial direction of the rotor 200 due to the high-temperature environment simulating an aero-engine, the first movable member 610 can slide relative to the second movable member 620 in the first direction, thereby absorbing the expansion of the support 300 in the first direction, reducing the thermal stress generated by the limited thermal expansion of the support 300, reducing the strain of the rotor 200 caused by the support 300 squeezing the rotor 200, and further improving the stability of the operation of the rotor 200 and the stability of the test results of the experiment.

[0038] To facilitate further understanding of the above solution by those skilled in the art, by way of example, please refer to Figure 7 As shown, in some embodiments, the second movable member 620 is a sleeve structure extending in the first direction (i.e., Figure 7 the left-right direction in Figure 7 ), and the first movable member 610 is an optical axis extending in the first direction and passing through the second movable member 620. Then, the first movable member 610 can receive a supporting force perpendicular to the first direction from the second movable member 620 (i.e., Figure 7 the acting force in the upward direction in ), so that the support 300 connected to the first movable member 610 is supported by the bracket 100.

[0039] On the basis of the above solution, further, in some embodiments, the first direction is the radial direction of the rotor 200. Through the above solution, the thermal expansion generated by a part of the support 300 connected to the first movable member 610 in the radial direction of the rotor 200 can be completely absorbed by the relative movement between the first movable member 610 and the second movable member 620, further reducing the thermal stress generated by the support 300 due to the high-temperature environment, and further improving the stability of the operation of the rotor 200 and the stability of the test results of the experiment.

[0040] As a preferred mode, please refer to Figure 1 、 Figure 5 and Figure 6 As shown, in some other embodiments, the movable assembly 600 further includes an adjusting member 630. The adjusting member 630 includes a connected first rotating portion 631 and a second rotating portion 632. The first rotating portion 631 is rotatably connected to the bracket 100 and has a first rotation axis; the first movable member 610 is rotatably connected to the second rotating portion 632 and has a second rotation axis; both the first rotation axis and the second rotation axis are parallel to the axis of the rotor 200. The first rotating portion 631 is located above the second rotating portion 632 and on one side of the rotor 200 in the first direction. The first direction is perpendicular to the axis direction of the rotor 200 and forms an acute angle or a right angle with the vertical direction.

[0041] The first rotating part 631 and the second rotating part 632 are connected by an adjusting part 630, and the first rotating part 631 is located above the second rotating part 632. Then, the second movable part 620 connected to the first rotating part 631 can apply an upward supporting force to the first movable part 610 connected to the second rotating part 632, so that the support 300 can be supported by the bracket 100.

[0042] On the other hand, since both the first rotation axis of the first rotating part 631 and the second rotation axis of the second rotating part 632 are parallel to the axis of the rotor 200, and the first rotating part 631 is located on one side of the rotor 200 in the first direction, the first direction is perpendicular to the axis direction of the rotor 200 and the included angle with the vertical direction is an acute angle or a right angle. Then, when the support 300 has a tendency to expand in the radial direction of the rotor 200 due to simulating the high-temperature environment of an aeroengine, the first movable part 610 swings relative to the first rotation axis in a direction away from the rotor 200 around the second rotation axis, and at the same time rotates relative to the second rotation axis, so that a part of the support 300 can also expand in the moving direction of the first movable part 610, reducing the thermal stress generated by the limited thermal expansion of the support 300 and reducing the strain of the rotor 200 caused by the support 300 squeezing the rotor 200. Furthermore, the stability of the operation of the rotor 200 is improved, and the stability of the test results of the experiment is improved.

[0043] Furthermore, please refer to Figure 5 、 Figure 6 As shown, in some embodiments, the adjusting part 630 further includes an adjusting portion 633, and one end of the adjusting portion 633 is threadedly connected to the first rotating part 631. By the relative rotation of the adjusting portion 633 and the first rotating part 631, the distance between the adjusting portion 633 and the first rotating part 631 can be adjusted, thereby adjusting the length of the adjusting part 630, adjusting the distance between the first movable part 610 and the second movable part 620, and finally adjusting the overall position of the support 300 and the rotor 200 relative to the bracket 100.

[0044] In some embodiments, one end of the adjusting portion 633 is threadedly connected to the second rotating part 632. By the relative rotation of the adjusting portion 633 and the first rotating part 631, the distance between the adjusting portion 633 and the second rotating part 632 can be adjusted, thereby adjusting the length of the adjusting part 630, adjusting the distance between the first movable part 610 and the second movable part 620, and finally adjusting the overall position of the support 300 and the rotor 200 relative to the bracket 100.

[0045] As a preferred mode, in some embodiments, one end of the adjusting part 633 is threadedly connected to the first rotating part 631, and the other end is connected to the second rotating part 632. By relatively rotating the adjusting part 633 and the first rotating part 631, the distance between the adjusting part 633 and the first rotating part 631 can be adjusted, or by adjusting the distance between the adjusting part 633 and the second rotating part 632, the length of the adjusting member 630 can be adjusted, the distance between the first movable member 610 and the second movable member 620 can be adjusted, and finally the overall position of the support 300 and the rotor 200 relative to the bracket 100 can be adjusted.

[0046] The above-mentioned multiple embodiments can adjust the overall length of the adjusting member 630 through the adjusting part 633. Before conducting the experiment simulating the high-temperature conditions of an aero-engine, the researchers can also change the overall length of the adjusting member 630 according to actual needs, and then comprehensively adjust the swing angle, swing arc length of the first movable member 610 relative to the second movable member 620, and the attitude of the rotor 200, so as to provide different experimental conditions for the researchers on the premise of realizing that the movable assembly 600 absorbs the thermal expansion of the support 300.

[0047] Those skilled in the art can also make other improvements to the adjusting member 630. Please refer to Figure 5 、 Figure 6 As shown, in some embodiments, the first rotating part 631 is slidably connected to the second rotating part 632. The first rotating part 631 and the second rotating part 632 can slide relative to each other, thereby changing the distance between the second movable member 620 and the first movable member 610, and adjusting the rotation radius of the first movable member 610 relative to the second movable member 620. This is beneficial to keeping the moving direction of the first movable member 610 unchanged during the thermal expansion of the support 300, and avoiding the attitude change of the rotor 200 caused by the support 300 driving the rotor 200 to tilt.

[0048] Specifically, please refer to Figure 1 、 Figure 4 、 Figure 5 、 Figure 6As shown, in some embodiments, an aeroengine rotor experimental device includes a plurality of supports 300 connected to a rotor 200, and the plurality of supports 300 are respectively located at different positions in the axial direction of a rotating shaft 210. Among them, the rear support 300 is rigidly connected to a bracket 100, and the front support 300 is connected to the bracket 100 through a movable assembly 600. A first rotating part 631 and a second rotating part 632 are slidably connected in the up and down direction. When the front support 300 expands due to heat, it will drive a first movable part 610 and the second rotating part 632 to rotate around a first rotation axis. During the above process, the relative sliding of the first rotating part 631 and the second rotating part 632 causes the distance between the first movable part 610 and the second movable part 620 to become longer, and the turning radius of the first movable part 610 increases. The first movable part 610 that was originally supposed to swing upward to the upper right becomes a translational movement to the right direction, avoiding the front part of the rotor 200 from tilting upward relative to the rear part, so that the attitude of the rotor 200 is kept as consistent as possible.

[0049] Without departing from the inventive concept of the present invention, those skilled in the art can independently select the sliding connection method between the first rotating part 631 and the second rotating part 632. In some embodiments, the first rotating part 631 is of a sleeve structure, and the second rotating part 632 is a smooth shaft disposed in the sleeve structure. Those skilled in the art can also, on the basis of the above solution, connect the first rotating part 631 and the second rotating part 632 through a spring, so that the second movable part 620 can move relative to the first movable part 610 and can provide an upward supporting force for the first movable part 610.

[0050] The present invention can absorb the thermal expansion of the support 300 through the movable assembly 600 under the experimental conditions simulating the high temperature of an aeroengine, and reduce the thermal stress generated by the limited thermal expansion of the support 300. Those skilled in the art can reasonably set the position of the movable assembly 600 according to the above inventive concept.

[0051] As a preferred solution, please refer to Figures 1 to 5As shown, in some embodiments, the rotor 200 includes a rotating shaft 210, a compressor disk set 230, and a turbine disk 240. The compressor disk set 230 and the turbine disk 240 are connected to the rotating shaft 210 at different positions in the axial direction of the rotating shaft 210. The aero-engine rotor experimental device further includes an ignition assembly (not shown), and the ignition assembly is located between the compressor disk set 230 and the turbine disk 240 in the axial direction of the rotor 200 and is used to generate high-temperature and high-pressure air flow. The aero-engine rotor experimental device includes a plurality of supports 300, and the plurality of supports 300 are respectively rotatably connected to the rotating shaft 210 at different positions in the axial direction of the rotating shaft 210. A casing 400 is provided between the plurality of supports 300, and the interior of the casing 400 has a receiving cavity 410 for receiving at least a part of the rotor 200. The ignition assembly is received in the receiving cavity 410. Through the above solution, when simulating the high-temperature conditions of an aero-engine, after the compressor blades are installed on the compressor disk set 230, compressed air can be delivered towards the ignition assembly, enabling the ignition assembly to generate high-temperature and high-pressure gas. The high-temperature and high-pressure gas drives the turbine blades installed on the turbine disk 240 to rotate, simulating the working process of an aero-engine.

[0052] Based on the above solution, in some embodiments, please refer to Figure 4 As shown, the support 300 located on one side in the second direction of the ignition assembly is defined as the first support 300A, and the support 300 located in the opposite direction of the second direction of the ignition assembly is defined as the second support 300B. The second direction is the direction from the compressor disk set 230 to the turbine disk 240 (i.e., the second direction is Figure 1 the rear direction in

[0053] Please refer to Figure 1 , Figure 3 ,Figure 4 As shown, in some embodiments, the bracket 100 is fixedly connected to a first support 300A and connected to a second support 300B through a movable assembly 600. When performing a rotor experiment at room temperature, when a high-speed motor (not shown in the figure) is drivingly connected to the side of the rotor 200 provided with a turbine disk, the fixed connection between the bracket 100 and the first support 300A can keep the support 300 and the rotor 200 stable, avoiding the additional vibration caused by the axial movement of the rotor 200.

[0054] The embodiments of connecting the casing 400 to the support 300 have been described above. Based on the above embodiments, please refer to Figure 5 、 Figure 7 As shown, in some embodiments, the aero-engine rotor experimental device has a symmetric plane extending in the vertical direction, and the axis of the rotor 200 is located in the symmetric plane. The aero-engine rotor experimental device includes two movable assemblies 600, and the first movable member 610 of each movable assembly 600 is connected to the support 300 and the bracket 100. Relative to the symmetric plane, the two movable assemblies 600 are symmetrically arranged. Since the two movable assemblies 600 are symmetrically arranged, the two movable assemblies 600 can simultaneously provide acting forces with the same magnitude and symmetric with respect to the symmetric plane in direction, and can absorb the same degree of thermal expansion. The thermal expansion of the support 300 toward one side in the horizontal direction is the same as that toward the other side in the horizontal direction. The above solution is beneficial for researchers to simplify the analysis of the support 300 in a high-temperature state. Exemplarily, please refer to Figure 5 、 Figure 7 As shown, the support 300 is a structure symmetric with respect to the symmetric plane, so the thermal expansion degrees on both sides in the horizontal direction are the same after heating, and researchers can separately analyze the thermal expansion situation of one side of the support 300 in the horizontal direction.

[0055] On the other hand, the two movable assemblies 600 can reduce the supporting force exerted on the support 300 by a single movable assembly 600, which is beneficial to improving the service life of the movable assembly 600, and the overall force composed of the support 300, the casing 400 and the rotor 200 is more uniform, and the stability in the experiment is higher, which is beneficial to measuring the rotor 200 during the experiment.

[0056] Without departing from the inventive concept of the present invention, those skilled in the art can independently set sensors for detecting the radial movement of the rotor 200 on the aero-engine rotor experimental device. In some embodiments, a sensor for detecting the radial displacement of the rotor 200 and facing the rotor 200 is fixed on the casing 400 or the support 300.

[0057] As a preferred solution, please refer to Figure 1 、 Figure 2 、 Figure 9, Figure 11 As shown, in some embodiments, the casing 400 further has a first avoidance hole 420, and the first avoidance hole 420 communicates the accommodation cavity 410 with the outside. The aeroengine rotor experimental device further includes a first sensor 501, and the first sensor 501 is connected to the bracket 100 and is located radially of the rotor 200, and can detect the radial displacement of the rotor 200 through the first avoidance hole 420.

[0058] By providing the first avoidance hole 420 on the casing 400, the first sensor 501 connected to the bracket 100 can detect the radial displacement of the rotor 200 relative to the bracket 100 during the experiment through the first avoidance hole 420, thereby avoiding the influence of the mass of the first sensor 501 on the structural system dynamic characteristics of the rotor 200, the support 300 and the casing 400, and improving the accuracy of the test results.

[0059] Without departing from the inventive concept of the present invention, the present invention does not limit the manner in which the first sensor 501 detects the radial displacement of the rotor 200 through the first avoidance hole 420.

[0060] In some embodiments, the first sensor 501 is a laser displacement sensor. The first sensor 501 is located outside the casing 400, and the first avoidance hole 420 exposes a part of the rotor 200 accommodated in the casing 400 to the outside, and the probe facing the first avoidance hole 420 can use laser to obtain the radial displacement of the rotor 200 during the experiment.

[0061] Please refer to Figure 9 , Figure 11 As shown, as a preferred solution, in some embodiments, the bracket 100 includes a connecting shaft 110. The connecting shaft 110 penetrates into the accommodation cavity 410 through the first avoidance hole 420, and the first sensor 501 is provided on one side of the connecting shaft 110 accommodated in the accommodation cavity 410. Through the above solution, the first sensor 501 can extend into the accommodation cavity 410 through the connecting shaft 110, reducing the distance between the first sensor 501 and the rotor 200. During the installation process of the first sensor 501 by the researchers, due to the reduction of the distance between the first sensor 501 and the rotor 200, it is easier to adjust the measurement position of the first sensor 501, which is beneficial to improving the test accuracy of the first sensor 501 during the test and improving the accuracy of the experimental results.

[0062] It should be understood that when conducting experiments under the high-temperature conditions of an analog aero-engine, the first avoidance hole 420 provided on the casing 400 will also shrink and move due to thermal expansion. Those skilled in the art can enlarge the first avoidance hole 420 according to the specific situation of the shrinkage and movement of the first avoidance hole 420, so that the first avoidance hole 420 still enables the first sensor 501 to detect the radial displacement of the rotor 200 after the casing 400 undergoes thermal expansion.

[0063] As a preferred embodiment, please refer to Figures 9 to 11 As shown, in some embodiments, the axes of both the first sensor 501 and the first avoidance hole 420 are located in the symmetry plane. Through the above solution, since the thermal expansion of the casing 400 connected thereto is restricted by the support 300, when the thermal expansion degrees on both sides of the support 300 in the horizontal direction are the same, the thermal expansion degrees on both sides of the casing 400 in the horizontal direction are also the same. The axis position of the first avoidance hole 420 located in the symmetry plane will not shift due to the thermal expansion of the casing 400, and the first sensor 501 located in the symmetry plane can still detect the radial displacement of the rotor 200 through the first avoidance hole 420.

[0064] Compared with setting the first avoidance hole 420 at other positions, setting the first avoidance hole 420 in the symmetry plane can avoid the offset of the first avoidance hole 420 during the thermal expansion of the casing 400, and thus can reduce the specification of the first avoidance hole 420, making the structure of the casing 400 closer to that of a real aero-engine, improving the simulation degree of the experiment, and being conducive to further exploration of the structural dynamics properties of a real aero-engine by researchers.

[0065] Exemplarily, in some embodiments, taking Figure 11 the position of the first avoidance hole 420 shown as an example, if the first avoidance hole 420 is located in the symmetry plane, then the axis position of the first avoidance hole 420 is still located in the symmetry plane after the casing 400 undergoes thermal expansion, and the reduced first avoidance hole 420 still maintains a distance from the connecting shaft 110. If the first avoidance hole 420 with the same specification as above is set at a position spaced from the symmetry plane, then when the casing 400 undergoes thermal expansion, in addition to the first avoidance hole 420 itself shrinking due to the thermal expansion of the casing 400, the axis position of the first avoidance hole 420 will further move away from the symmetry plane, and the overall inner wall of the first avoidance hole 420 will move in the direction away from the symmetry plane, which may cause the connecting shaft 110 to collide with the inner wall of the first avoidance hole 420, or cause the expanded casing 400 to block the first sensor 501, making the first sensor 501 unable to detect the radial displacement of the rotor 200.

[0066] The above embodiments of the present invention have been described in detail with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge scope of those of ordinary skill in the art. In addition, the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict.

Claims

1. An aero-engine rotor experimental device, characterized in that, Comprising: A rotor; A bracket; A support, the rotor being rotatably connected to the support; A movable assembly, including a first movable member and a second movable member, the first movable member being connected to the support and located radially of the rotor; the second movable member being connected to the bracket and movably connected to the first movable member; the second movable member being capable of providing an upward acting force to the first movable member; the first movable member being capable of reciprocating relative to the second movable member in a direction perpendicular to the axial direction of the rotor.

2. The aero-engine rotor experimental device according to claim 1, characterized in that, The movable assembly further includes an adjusting member, the adjusting member including a connected first rotating portion and a second rotating portion, the first rotating portion being rotatably connected to the bracket and having a first rotation axis; the first movable member being rotatably connected to the second rotating portion and having a second rotation axis; both the first rotation axis and the second rotation axis being parallel to the axis of the rotor, the first rotating portion being located above the second rotating portion and on one side of the rotor in a first direction, the first direction being perpendicular to the axial direction of the rotor and having an acute or right angle with the vertical direction.

3. The aero-engine rotor experimental device according to claim 2, characterized in that, The adjusting member further includes an adjusting portion, one end of the adjusting portion being threadedly connected to the first rotating portion, and / or the other end of the adjusting portion being threadedly connected to the second rotating portion.

4. The aero-engine rotor experimental device according to claim 2, characterized in that, The first rotating portion is slidably connected to the second rotating portion.

5. The aero-engine rotor experimental device according to claim 1, wherein, The first movable member is slidably connected to the second movable member in a first direction, the first direction being perpendicular to the axial direction of the rotor and having an acute or right angle with the vertical direction.

6. The aero-engine rotor experimental device according to claim 1, wherein, It further includes a casing, the casing being connected to the support, the casing having a receiving cavity, a part of the rotor being received in the receiving cavity, the aero-engine rotor experimental device having a symmetric plane extending in the vertical direction, the axis of the rotor being located in the symmetric plane; The aero-engine rotor experimental device includes two movable assemblies, the first movable member of each movable assembly being connected to the support and the bracket; the two movable assemblies are symmetrically arranged with respect to the symmetric plane.

7. The aero-engine rotor experimental device according to claim 6, characterized in that, The casing further has a first avoidance hole, the first avoidance hole communicating the receiving cavity and the outside; the aero-engine rotor experimental device further includes a first sensor, the first sensor being connected to the bracket and located radially of the rotor, and being capable of detecting the radial displacement of the rotor through the first avoidance hole.

8. The aero-engine rotor experimental device according to claim 7, characterized in that, The axes of the first sensor and the first avoidance hole are both located in the symmetric plane.

9. The aero-engine rotor experimental device according to claim 7 or 8, characterized in that, The bracket includes a connecting shaft, the connecting shaft passing through the first avoidance hole into the receiving cavity, the first sensor being provided on one side of the connecting shaft received in the receiving cavity.

10. The aero-engine rotor experimental device according to claim 1, characterized in that, The rotor includes a rotating shaft, a compressor disk group, and a turbine disk. The compressor disk group and the turbine disk are connected to the rotating shaft at different positions in the axial direction of the rotating shaft. The aero-engine rotor experimental device further includes an ignition assembly, which is located between the compressor disk group and the turbine disk in the axial direction of the rotor and is used to generate high-temperature and high-pressure airflows. The aero-engine rotor experimental device includes a plurality of the supports, and the plurality of supports are respectively rotatably connected to the rotating shaft at different positions in the axial direction of the rotating shaft. A casing is provided between the plurality of supports, and an accommodation cavity for accommodating at least part of the rotor is provided inside the casing. The ignition assembly is accommodated in the accommodation cavity. Define the support located on one side in the second direction of the ignition assembly as the first support, and the support located in the opposite direction of the second direction of the ignition assembly as the second support. The second direction is the direction from the compressor disk group to the turbine disk. The bracket is connected to one of the first supports through the movable assembly and fixedly connected to one of the second supports.

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