Shared bearing rotor system vibration coupling characteristic test device

Abstract

The invention belongs to a simulation test device in the field of rotary machinery, and particularly relates to a shared support rotor system vibration coupling characteristic test device which comprises a rotor driving system, a front support structure, a fuel gas generator simulation rotor, a shared support structure and a power turbine rotor equivalent excitation system. A rotor front journal of the fuel gas generator simulation rotor is rotationally connected with the front supporting structure, the rotor front journal penetrates through the front supporting structure and then is connected with the rotor driving system, and a rotor rear journal of the fuel gas generator simulation rotor is rotationally connected with the common supporting structure. And one side, far away from the fuel gas generator simulation rotor, of the common supporting structure is connected with the power turbine rotor equivalent excitation system. The device for testing the vibration coupling characteristic of the shared bearing rotor system is provided for the first time aiming at the test research of the shared bearing rotor system, and can simulate various working load environments of the shared bearing rotor system.

Description

Technical Field

[0001] The invention belongs to a simulation test device in the field of rotating machinery, and in particular relates to a vibration coupling characteristic test device for a common support rotor system. Background Art

[0002] While pursuing high performance, modern advanced turboshaft engines also put forward higher requirements for structural efficiency. On the basis of meeting performance parameters, the structural mass is required to be as small as possible, that is, a high power-to-weight ratio design is adopted. To achieve this goal, the gas generator rotor design mostly adopts high speed and small radial size design, the support scheme is a large-span 1-0-1 support, and the connection structure adopts multi-stage arc end teeth to transmit torque and the center tie rod is segmented and clamped; in the design of the load-bearing system, in order to minimize the number of load-bearing frames, a common load-bearing frame design is adopted between turbine stages, and the rear support points of the gas generator rotor and the power turbine rotor are supported at the same time.

[0003] Engineering practice shows that since the shared load-bearing frame between turbine stages works in a harsh high-temperature environment, its stiffness is relatively low, and it is simultaneously subjected to dynamic excitation by the combustion rotor and the power turbine rotor, it is prone to produce large foundation vibrations, causing the vibration of one rotor to be transmitted to the other rotor through the shared support structure, directly affecting the motion state of the other rotor, causing vibration coupling between the combustion rotor and the power turbine rotor, and possibly causing dangerous resonance within certain characteristic speed ranges, affecting the safe operation of the rotor system.

[0004] Therefore, it is necessary to establish a vibration coupling characteristics test device for a shared support rotor system, fully consider the structural characteristics of the combustion rotor and the shared support, simulate the load environment and rotor interaction excitation characteristics during the actual working process of the shared support rotor system, study the vibration coupling characteristics of the rotor system and the vibration transfer characteristics between the supports, and provide a reference for the dynamics and vibration reduction and isolation design of the shared support rotor system.

[0005] At present, there are few simulation test devices designed for the vibration coupling characteristics test of the shared support rotor system. Most simulation test devices are proposed for the intermediate support point dual rotor system and the gear-driven dual rotor system. For example, Beijing University of Chemical Technology proposed a simulation test bench CN116625692A for the gear-driven coaxial counter-rotating dual rotor system; for the intermediate support point dual rotor system, Guangxi University of Science and Technology proposed a series bolt-connected dual rotor test bench and its test method CN117268771A, China Aero Engine Guiyang Engine Design Institute proposed an aviation engine simulation dual rotor with sudden imbalance CN116818187A, and Huang Kai proposed an aviation dual rotor comprehensive vibration test bench CN215065140U. In the invention patent applications CN118670731A and CN117825054A published by Beijing Information Science and Technology University and Northwestern Polytechnical University, although the use of a shared support structure was considered, the shared support configuration was quite different from the actual engine structure, lacking similarity in geometric configuration and mechanical properties.

[0006] In summary, the simulation test devices currently proposed are mainly aimed at the dual-rotor system with an intermediate support point, and have not fully considered the similarity between the geometric configuration and mechanical properties of the shared support structure. The similarity with the actual structure is poor, resulting in a large difference between the vibration characteristics of the shared support structure and the actual structure, and cannot accurately reflect the vibration coupling characteristics of the rotor system and the vibration transmission law between the supports. Summary of the invention

[0007] In order to solve the above technical problems, the present invention provides a vibration coupling characteristic test device for a common support rotor system.

[0008] The present invention is implemented as follows: a common support rotor system vibration coupling characteristic test device is provided, comprising a rotor drive system, a front support structure, a gas generator simulated rotor, a common support structure and a power turbine rotor equivalent excitation system, wherein the rotor front journal of the gas generator simulated rotor is rotationally connected to the front support structure via a front ball bearing, and the rotor front journal is connected to the rotor drive system after passing through the front support structure, the rotor rear journal of the gas generator simulated rotor is rotationally connected to the common support structure via a rear roller bearing, and the side of the common support structure away from the gas generator simulated rotor is connected to the power turbine rotor equivalent excitation system.

[0009] Preferably, the gas generator simulation rotor also includes a center tie rod and a first-stage compressor simulation disk, a second / third-stage compressor simulation drum, a fourth-stage compressor simulation disk, a first-stage turbine simulation disk and a second-stage turbine simulation disk, which are sequentially sleeved on the center tie rod from the front shaft neck of the rotor to the rear shaft neck of the rotor and pressed by the center tie rod; one end of the center tie rod is fixedly connected to the front shaft neck of the rotor, a first-stage arc end tooth connection structure is formed at a position where the first-stage compressor simulation disk and the second / third-stage compressor simulation drum are docked, a second-stage arc end tooth connection structure is formed at a position where the second / 3rd-stage compressor simulation drum and the fourth-stage compressor simulation disk are docked, a third-stage arc end tooth connection structure is formed at a position where the fourth-stage compressor simulation disk and the first-stage turbine simulation disk are docked, and the rear shaft neck of the rotor is also sleeved on the center tie rod and connected to the second-stage turbine simulation disk through a flange-bolt, and is pressed by the center tie rod.

[0010] Further preferably, the first-stage turbine simulation disk and the second-stage turbine simulation disk are integrated two-stage turbine simulation disks;

[0011] The center tie rod is provided with a middle clamping sleeve, a middle clamping nut, a rear shaft neck clamping sleeve and a clamping nut at the end of the tie rod. The middle clamping sleeve is arranged in the center hole of the 4th stage compressor simulation disk. By tightening the middle clamping nut, the front section of the center tie rod clamps the 1st stage compressor simulation disk, the 2nd / 3rd stage compressor simulation drum and the 4th stage compressor simulation disk, and the rear shaft neck clamping sleeve presses against the rear shaft neck of the rotor. By tightening the clamping nut at the end of the tie rod, the rear section of the center tie rod clamps the integrated two-stage turbine simulation disk and the rear shaft neck of the rotor.

[0012] Further preferably, the gas generator simulation rotor adopts a 1-0-1 support scheme, a front ball bearing is arranged on the front shaft neck of the rotor, and is rotatably connected to the front support structure through the front ball bearing, and a rear roller bearing is arranged on the rear shaft neck of the rotor, and the ratio of the span between the front ball bearing and the rear roller bearing to the outer diameter of the front shaft neck of the first-stage turbine simulation disk exceeds 13.

[0013] Further preferably, both sides of the inner ring of the front ball bearing are pressed against the front first clamping sleeve and the front second clamping sleeve, and then are pressed and fixed to the front shaft neck of the rotor by the front clamping nut; both sides of the inner ring of the rear roller bearing are pressed against the rear first clamping sleeve and the rear second clamping sleeve, and then are pressed and fixed to the rear shaft neck of the rotor by the rear clamping nut.

[0014] Further preferably, the first-stage compressor simulation disk is provided with circumferentially evenly distributed first-stage compressor simulation disk threaded holes, the two simulation drums of the second / third-stage compressor simulation drums are provided with circumferentially evenly distributed second-stage compressor simulation drum threaded holes and circumferentially evenly distributed third-stage compressor simulation drum threaded holes, the fourth-stage compressor simulation disk is provided with circumferentially evenly distributed fourth-stage compressor simulation disk threaded holes, the first-stage turbine simulation disk is provided with circumferentially evenly distributed first-stage turbine simulation disk threaded holes, and the second-stage turbine simulation disk is provided with circumferentially evenly distributed second-stage turbine simulation disk threaded holes.

[0015] Preferably, the rotor drive system comprises a high-speed motor and a coupling, and the coupling is used to connect the motor output shaft of the high-speed motor and the rotor front journal.

[0016] Further preferably, the maximum speed of the high-speed motor is not less than 15000r / min, the coupling is a bellows flexible coupling, high-speed dynamic balancing is required, the balancing quality needs to reach G2.5, the maximum compensation capacity of the coupling for angular misalignment is not less than ±2°, and the maximum compensation capacity for lateral misalignment is not less than ±1mm.

[0017] Preferably, the front supporting structure includes a front supporting frame, a front support plate, a front bearing seat and a front squirrel cage spring support. The front supporting frame is fixed to the test platform by anchor bolts, the front support plate is fixedly connected to the front supporting frame by bolts, the outer flange edge of the front bearing seat and the inner flange edge of the front support plate are positioned by a stopper and fixedly connected by bolts, the outer flange edge of the front squirrel cage spring support and the front bearing seat are positioned by an end face and a cylindrical surface and fixedly connected by bolts, and the front shaft neck of the rotor passes through the front squirrel cage spring support and is rotatably connected to the front squirrel cage spring support through a front ball bearing.

[0018] Preferably, the common supporting structure includes a rear supporting frame, a rear support plate, a bearing drum, a combustion simulation bearing seat, a dynamic vortex simulation bearing seat, a rear squirrel cage support, an oil baffle plate and an oil baffle cover. The bearing drum is a folding structure with a similar geometric configuration to the actual structure. The rear supporting frame is connected and fixed to the test platform by anchor bolts, the rear support plate is fixedly connected to the rear supporting frame by bolts, the inner flange edge of the rear support plate and the outer flange edge of the bearing drum are positioned by a stopper and fixedly connected by bolts, the outer flange edges of the combustion simulation bearing seat and the dynamic vortex simulation bearing seat and the inner flange edge of the bearing drum are fixedly connected by a stopper The rear squirrel cage support and the oil shield are matched with the combustion simulation bearing seat through the cylindrical surface of the outer flange and are fixedly connected by bolts. The oil shield plate is matched with the flange edge of the combustion simulation bearing seat through the outer flange and is fixedly connected by bolts. The oil shield plate is designed with a brush-type sealing structure, which together with the oil shield forms a relatively closed lubricating oil chamber. The oil supply hole and the oil return hole are respectively located at the top and bottom ends of the combustion simulation bearing seat. The dynamic vortex simulation bearing seat is used to be connected to the equivalent excitation system of the power turbine rotor. The rear shaft neck of the rotor is rotatably connected to the rear squirrel cage support through the rear roller bearing.

[0019] Preferably, the power turbine rotor equivalent excitation system includes a vertical exciter, a first vertical excitation top rod, a second vertical excitation top rod, a horizontal exciter, a first horizontal excitation top rod, a second horizontal excitation top rod, a horizontal force sensor and a vertical force sensor; the vertical exciter is connected to the upper end of the first vertical excitation top rod, the lower end of the first vertical excitation top rod is connected to the vertical force sensor, the upper end of the second vertical excitation top rod is connected to the vertical force sensor, and the lower end of the second vertical excitation top rod is connected to the dynamic vortex simulation bearing seat through nuts tightened in opposite directions to ensure that the excitation force is effectively transmitted to the dynamic vortex simulation bearing seat; the horizontal exciter is connected to one end of the first horizontal excitation top rod, the other end of the first horizontal excitation top rod is connected to the horizontal force sensor, one end of the second horizontal excitation top rod is connected to the horizontal force sensor, and the other end of the second horizontal excitation top rod is connected to the dynamic vortex simulation bearing seat through nuts tightened in opposite directions to ensure that the excitation force is effectively transmitted to the dynamic vortex simulation bearing seat.

[0020] Further preferably, the vertical vibrator is arranged on a vertical vibrator support frame, the vertical vibrator support frame is a gantry structure, the bases on both sides are provided with grooves for adjustably fixing the vertical vibrator support frame to the test platform through anchor bolts, and the support plates on both sides of the vertical vibrator support frame are provided with square grooves, which reasonably reduce the weight of the support frame and facilitate the horizontal excitation top rod to pass through;

[0021] The horizontal exciter is arranged on a horizontal exciter frame, the horizontal exciter frame is arranged on a horizontal exciter base, the horizontal exciter base is fixedly connected to the test platform, and the height of the horizontal exciter base needs to make the center line of the horizontal excitation top rod and the center line of the power turbine simulation bearing seat have the same center height.

[0022] Compared with the prior art, the advantages of the present invention are:

[0023] 1) In the present invention, the gas generator simulation rotor is designed by similarity and has good similarity with the actual engine rotor in terms of geometric configuration, arc end tooth connection structure, support constraint, mass-stiffness distribution, critical speed distribution, preload force transmission route and clamping state, etc., which can ensure that the simulated rotor has a similar motion state to the actual rotor within the corresponding working speed range, so that the dynamic excitation effect on the shared support structure is also similar to the actual situation.

[0024] 2) In the present invention, the geometric features and mechanical properties of the front support structure and the common support structure are fully considered. The front support structure is similar to the actual casing structure in geometric configuration, and the front support frame, front support plate, and front bearing seat all have good rigidity. The common support structure takes into account the folding configuration of the load-bearing drum, so that the simulated bearing seat has similar vibration characteristics to the actual structure under the dynamic excitation of the rotor and the exciter. The combustion simulation bearing seat and the power turbine simulation bearing seat are connected to the load-bearing drum through the same flange edge, and the dynamic excitation of the gas generator simulation rotor and the power turbine rotor equivalent excitation system can be transmitted interactively, so that the common support rotor system exhibits vibration coupling characteristics.

[0025] 3) In the present invention, the excitation frequency of the horizontal exciter and the vertical exciter in the equivalent excitation system of the power turbine rotor can be arbitrarily adjusted within the range of 1 to 1000 Hz, which can cover the frequency range corresponding to the operating speed of the gas generator simulation rotor and the power turbine rotor. The excitation amplitude of the exciter can be adjusted to simulate the dynamic excitation of the common support structure under different unbalanced states of the power turbine rotor; the excitation phase of the horizontal exciter and the vertical exciter can be adjusted independently to simulate the motion trajectory of the power turbine rotor at different speeds, such as circular trajectory, elliptical trajectory, straight trajectory, etc.

[0026] 4) In the present invention, various working load environments of the shared support rotor system can be simulated, including: the dynamic excitation state of the gas generator simulated rotor, the equivalent excitation state of the power turbine rotor, and the common working state of the shared support rotor system, and then a number of experimental studies can be carried out: the vibration characteristics of the shared support structure and the simulated rotor motion state under the gas generator simulated rotor excitation, and the transmission characteristics of the combustion simulated rotor vibration in the shared support structure; the vibration transmission characteristics in the shared support structure under the equivalent excitation of the power turbine rotor; the vibration coupling characteristics of the shared support rotor system under the common working state, and the influence of the power turbine equivalent excitation on the gas generator simulated rotor motion state. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0028] Figure 2 is a three-dimensional structural diagram of a test device according to an embodiment of the present invention;

[0029] Figure 3 is a simplified diagram of the structure of a simulated rotor of a gas generator according to an embodiment of the present invention;

[0030] Figure 4 is a three-dimensional structural diagram of a simulated rotor of a gas generator according to an embodiment of the present invention;

[0031] Figure 5 is a schematic diagram of the front support structure of an embodiment of the present invention;

[0032] Figure 6 is a schematic diagram of a common support structure of an embodiment of the present invention;

[0033] Figure 7 is a three-dimensional structural diagram of a power turbine rotor equivalent excitation system according to an embodiment of the present invention;

[0034] In the figure: test platform 1B, rotor drive system 10, motor output shaft 11, coupling 12, front support structure 20, front support frame 21, front support plate 22, front bearing seat 23, front squirrel cage spring support 24, front ball bearing 25, gas generator simulated rotor 30, rotor front journal 31, front clamping nut 32, front first clamping sleeve 33A, front second clamping sleeve 33B, first stage compressor simulated disk 34, first stage compressor simulated disk threaded hole 34A, 2nd / 3rd stage compressor simulated drum 35, 2nd stage compressor simulated drum threaded hole 35A, third stage compressor simulation drum threaded hole 35B, fourth stage compressor simulation disk 36, fourth stage compressor simulation disk threaded hole 36A, middle clamping sleeve 37, middle clamping nut 38, first stage turbine simulation disk 39, first stage turbine simulation disk threaded hole 39A, second stage turbine simulation disk 40, second stage turbine simulation disk threaded hole 40A, rotor rear journal 41, rear first clamping sleeve 42A, rear second clamping sleeve 42B, rear clamping nut 43, tie rod end clamping nut 44, rear journal clamping sleeve 45, third stage arc end tooth Connection structure 46, second-stage arc end tooth connection structure 47, first-stage arc end tooth connection structure 48, center pull rod 49, common support structure 50, rear support frame 51, rear support plate 52, load-bearing drum 53, combustion simulation bearing seat 54, oil supply hole 54A, oil return hole 54B, oil baffle plate 55, brush-type sealing structure 55A, rear squirrel cage spring support 56, rear roller bearing 57, oil baffle cover 58, dynamic vortex simulation bearing seat 59, vertical excitation hole 59A, horizontal excitation hole 59B, dynamic vortex simulation bearing seat centerline 59L, power turbine rotor equivalent Excitation system 70, vertical vibrator 71, vertical vibrator frame 71A, vertical vibrator base 71B, vertical vibrator support frame 72, first vertical vibrator top rod 73, vertical force sensor 74, second vertical vibrator top rod 75, vertical vibrator top rod axis 75A, outer fastening nut 75C, inner fastening nut 75D, horizontal vibrator 76, horizontal vibrator frame 76A, horizontal vibrator base 76B, first horizontal vibrator top rod 77, horizontal force sensor 78, second horizontal vibrator top rod 79, horizontal vibrator top rod axis 79A. DETAILED DESCRIPTION

[0035] The following will be combined with the embodiments of the present invention Figure 1-Figure 7 , the technical solutions in the embodiments of the present invention are clearly and completely described. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention. Unless otherwise specified, the technical means used in the embodiments are conventional means well known to those skilled in the art.

[0036] Figure 1 Schematic diagram of the overall structure of a common support rotor system vibration coupling characteristics test device according to an embodiment of the present invention. Figure 2This is a three-dimensional structural diagram of a test device according to an embodiment of the present invention. A test device for vibration coupling characteristics of a common support rotor system mainly comprises: a rotor drive system 10, a front support structure 20, a gas generator simulation rotor 30, a common support structure 50, and a power turbine rotor equivalent excitation system 70.

[0037] Figure 3 This is a simplified diagram of the structure of the gas generator simulation rotor according to an embodiment of the present invention. The gas generator simulation rotor 30 adopts a 1-0-1 support scheme, wherein the front bearing is a front ball bearing 25 and the rear bearing is a rear roller bearing 57. The above bearing layout facilitates the assembly of the simulation rotor and the common support structure.

[0038] The ratio of the span between the front ball bearing 25 and the rear roller bearing 57 of the gas generator simulation rotor 30 to the front journal outer diameter of the first stage turbine simulation disk 39 exceeds 13.

[0039] The inner ring of the simulated rotor front ball bearing 25 is pressed against the front first clamping sleeve 33A and the front second clamping sleeve 33B, and then is pressed and fixed to the simulated rotor front journal 31 by the front clamping nut 32. The inner ring of the simulated rotor rear bearing 57 is pressed against the rear first clamping sleeve 42A and the rear second clamping sleeve 42B, and then is pressed and fixed to the simulated rotor rear journal 41 by the rear clamping nut 43.

[0040] The front end of the gas generator simulated rotor 30 is supported by the front support structure 20 , and the rear end is supported by the common support structure 50 .

[0041] The gas generator simulation rotor 30 is mainly composed of a first-stage compressor simulation disk 34, a second / third-stage compressor simulation drum 35, a fourth-stage compressor simulation disk 36, a first-stage turbine simulation disk 39, a second-stage turbine simulation disk 40, a rotor rear journal 41, a center pull rod 49 and other structures.

[0042] The gas generator simulation rotor 30 includes a three-stage arc end tooth connection structure: the first-stage end tooth connection structure 48 is located between the first-stage compressor simulation disk 34 and the second / third-stage compressor simulation drum 35, the second-stage end tooth connection structure 47 is located between the second / third-stage compressor simulation drum 35 and the fourth-stage compressor simulation disk 36, and the third-stage end tooth connection structure 46 is located between the fourth-stage compressor simulation disk 36 and the first-stage turbine simulation disk 39.

[0043] The first-stage turbine simulation disk 39 and the second-stage turbine simulation disk 40 are integrated components, and the two-stage turbine simulation disk component is connected to the rotor rear journal 41 through flange-bolts.

[0044] The gas generator simulated rotor 30 is compressed in sections by a center tie rod 49. The front section of the center tie rod compresses the first-stage compressor simulated disk 34, the second / third-stage compressor simulated drum 35 and the fourth-stage compressor simulated disk 36, and the rear section of the center tie rod compresses the two-stage turbine simulated disk and the rotor rear journal 41.

[0045] The front end of the middle clamping sleeve 37 is pressed against the center hole of the 4th stage compressor simulation disk 36, and by tightening the middle clamping nut 38, the front section of the center tie rod is pressed against the front section of the gas generator simulation rotor 30. The rear journal clamping sleeve 45 is pressed against the rotor rear journal 41, and by tightening the clamping nut 44 at the end of the tie rod, the rear section of the center tie rod is pressed against the rear section of the gas generator simulation rotor 30.

[0046] Figure 4 This is a three-dimensional structural diagram of the simulated rotor of the gas generator embodiment of the present invention, wherein each simulated wheel disc is provided with threaded holes evenly distributed along the circumferential direction, including: threaded holes 34A of the first-stage compressor simulated disk, threaded holes 35A of the second-stage compressor simulated drum, threaded holes 35B of the third-stage compressor simulated drum, threaded holes 36A of the fourth-stage compressor simulated disk, threaded holes 39A of the first-stage turbine simulated disk, and threaded holes 40A of the second-stage turbine simulated disk.

[0047] By adding bolts as unbalanced masses in the same phase as the threaded holes, the center of mass offset state of the wheel can be equivalent to that of the wheel; by adding bolts as unbalanced masses in the opposite phases of the threaded holes, the inclination state of the wheel inertia axis can be equivalent to that of the wheel, thereby generating different dynamic excitations on the common supporting structure when the combustion simulation rotor rotates at high speed.

[0048] Figure 5 This is a schematic diagram of the front support structure of an embodiment of the present invention. The rotor drive system 10 mainly includes: a high-speed motor and a coupling. The coupling is used to connect the motor output shaft 11 and the front shaft journal 31 of the gas generator rotor, thereby driving the gas generator simulated rotor 30 to rotate at high speed. The maximum speed of the high-speed motor is not less than 15000r / min. The motor output shaft 11 of the high-speed motor is connected to the front shaft journal 31 of the gas generator rotor through a coupling 12, and the coupling 12 is a bellows flexible coupling.

[0049] The coupling 12 needs to be dynamically balanced at high speed, and the balance quality needs to reach G2.5. The maximum compensation capacity of the angular misalignment of the bellows flexible coupling 12 is not less than ±2°, and the maximum compensation capacity of the lateral misalignment is not less than ±1mm.

[0050] The front support structure 20 is composed of a front support frame 21, a front support plate 22, a front bearing seat 23 and a front squirrel cage spring support 24. The front support frame 21 is connected and fixed to the test platform 1B by anchor bolts, the front support plate 22 is fastened to the front support frame 21 by bolts, the outer flange of the front bearing seat 23 and the inner flange of the front support plate 22 are positioned by stoppers and fastened by bolts. The outer flange of the front squirrel cage spring support 24 and the front bearing seat 23 are positioned by end faces and cylindrical surfaces and fastened by bolts.

[0051] Figure 6 This is a simplified diagram of the common support structure of an embodiment of the present invention. The common support structure 50 is mainly composed of a rear support frame 51, a rear support plate 52, a bearing drum 53, a combustion simulation bearing seat 54, a dynamic vortex simulation bearing seat 59, a rear squirrel cage spring support 56, an oil baffle plate 55, and an oil baffle cover 58. The bearing drum 53 is a folding structure and has a similar geometric configuration to the actual structure. The rear support frame 51 is connected and fixed to the test platform 1B by anchor bolts, and the rear support plate 52 is fastened to the rear support frame 51 by bolts. The inner flange edge of the rear support plate 52 is positioned with the outer flange edge of the bearing drum 53 through a stopper, and is fastened by bolts. The outer flange edges of the combustion simulation bearing seat 54 and the dynamic vortex simulation bearing seat 59 are positioned with the inner flange edge of the bearing drum 53 through a stopper, and are fastened by bolts.

[0052] Furthermore, the rear squirrel cage spring support 56 and the oil shield 58 are matched with the combustion simulation bearing seat 54 through the cylindrical surface of the outer flange edge and are fastened by bolts. The oil shield 55 is positioned by matching the flange edge of the combustion simulation bearing seat 54 through the outer flange edge and is fastened by bolts.

[0053] The combustion simulation bearing seat 54 is designed with a squeeze film damper, and the lubricating oil enters the combustion simulation bearing seat oil collecting groove through the oil supply hole 54A. The rear squirrel cage spring support 56 serves as the oil film journal. The lubricating oil forms a squeeze oil film between the combustion simulation bearing seat 54 and the rear squirrel cage spring support 56, which can ensure that the gas generator simulation rotor 30 passes the critical speed smoothly. The oil baffle plate 55 is designed with a brush-type sealing structure 55A, which together with the oil baffle cover 58 forms a relatively closed lubricating oil cavity to prevent the leaked lubricating oil from forming oil mist when the rotor rotates at high speed. The oil return hole 54B is located at the bottom of the combustion simulation bearing seat, which is used to collect the leaked lubricating oil to prevent the lubricating oil from leaking to the test platform.

[0054] A vertical excitation hole 59A and a horizontal excitation hole 59B are opened at the rear end of the dynamic vortex simulation bearing seat 59. The positions of the excitation holes are close to the positions of the actual power turbine rotor fulcrums. The excitation holes are through holes to facilitate the vertical excitation push rod and the horizontal excitation push rod to penetrate.

[0055] Figure 7This is a three-dimensional structural diagram of the power turbine rotor equivalent excitation system of an embodiment of the present invention. The power turbine rotor equivalent excitation system 70 mainly includes: a vertical exciter 71 and a first vertical excitation top rod 73, a second vertical excitation top rod 75, a vertical exciter support frame 72, a horizontal exciter 76 and a first horizontal excitation top rod 77, a first horizontal excitation top rod 79, a horizontal exciter base 76B, a horizontal force sensor 74 and a vertical force sensor 78.

[0056] The vertical vibrator 71 is supported by a vertical vibrator frame 71A, which is connected to a vertical vibrator base 71B by bolts, and the vertical vibrator base 71B is connected to a vertical vibrator support frame 72 by bolts. The vertical vibrator support frame 72 is a gantry structure, and grooves are provided on the bases on both sides thereof. Angle bolts are inserted from the frame base grooves to fix the vertical support frame 72 to the test platform 1B, and the position of the support frame can be adjusted with the help of the base grooves. Square grooves are provided on the support plates on both sides of the vertical support frame 72, which reasonably reduces the weight of the support frame and facilitates the passage of the horizontal excitation top rod.

[0057] The vertical exciter 71 is connected to the front end of the first vertical excitation rod 73 by threading, the end of the first vertical excitation rod 73 is connected to the vertical force sensor 74 by threading, the front end of the second vertical excitation rod 75 is connected to the vertical force sensor 74 by threading, and the end of the second vertical excitation rod 75 is connected to the dynamic vortex simulation bearing seat 59 by nuts tightened in opposite directions ( Figure 6 The outer and inner fastening nuts 75C and the inner fastening nuts 75D) are used to ensure that the exciting force is effectively transmitted to the dynamic vortex simulation bearing seat 59. The vertical exciting mandrel axis 75A is perpendicular to the power turbine simulation bearing seat centerline 59L and the horizontal exciting mandrel centerline 79A.

[0058] The horizontal exciter 76 is supported by a horizontal exciter frame 76A, which is connected to a horizontal exciter base 76B by bolts. The horizontal exciter base 76B has lug grooves on both sides, and the ground angle bolts are inserted through the lug grooves to fix the horizontal exciter base 76B to the test platform 1B.

[0059] The height of the horizontal exciter base 76B needs to ensure that the center line 79A of the horizontal exciter top rod and the center line 59L of the power turbine simulation bearing seat have the same center height.

[0060] The horizontal exciter 76 is connected to the front end of the first horizontal excitation top rod 77 by threading, the end of the first horizontal excitation top rod 77 is connected to the horizontal force sensor 78 by threading, the front end of the second horizontal excitation top rod 79 is connected to the horizontal force sensor 78 by threading, and the end of the second horizontal excitation top rod 79 is connected to the dynamic vortex simulation bearing seat 59 by nuts tightened in opposite directions to ensure that the exciting force is effectively transmitted to the dynamic vortex simulation bearing seat.

[0061] A common support rotor system vibration coupling characteristic test device of the present invention can simulate the following working load conditions:

[0062] 1) Gas generator simulated rotor excitation state: By adding bolts as unbalanced masses on the simulated rotor disk, the disk mass center offset or inertia main axis tilt state can be simulated. Only the motor drives the gas generator simulated rotor to rotate at high speed, that is, the gas generator simulated rotor works alone, so that it produces dynamic excitation on the common support. The vibration characteristics of the common support structure and the simulated rotor motion state under the excitation of the gas generator simulated rotor can be studied, as well as the transmission characteristics of the gas generator simulated rotor vibration in the common support structure.

[0063] 2) Equivalent excitation state of power turbine rotor: The horizontal exciter and the vertical exciter are used to excite the dynamic vortex simulation bearing seat at the same time, which is equivalent to the dynamic excitation generated by the actual power turbine rotor on the common support structure, and the transmission characteristics of the equivalent excitation of the power turbine rotor in the common support structure can be studied. By adjusting the excitation phase difference between the horizontal exciter and the vertical exciter, the excitation trajectory can be changed, such as circular trajectory, elliptical trajectory, linear trajectory, etc., to simulate different motion states of the power turbine rotor. The excitation frequency of the exciter can be adjusted arbitrarily within the range of 1 to 1000 Hz, which can cover the frequency range corresponding to the operating speed of the gas generator simulation rotor and the power turbine rotor. The excitation amplitude of the exciter can be adjusted to simulate the dynamic excitation of the common support structure under different unbalanced states of the power turbine rotor.

[0064] 3) Dual-rotor interactive excitation state: While the motor drives the gas generator simulated rotor to rotate at high speed, the horizontal exciter and the vertical exciter dynamically excite the moving vortex simulated bearing seat, which can simulate the state of the gas generator simulated rotor and the power turbine rotor working together, and study the vibration coupling characteristics of the shared support rotor system, as well as the influence of the power turbine equivalent excitation on the motion state of the gas generator simulated rotor.

[0065] The embodiments described above are only descriptions of the preferred modes of the present invention and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various deformations, modifications, and substitutions made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A common support rotor system vibration coupling characteristics test device, characterized in that: The invention comprises a rotor drive system (10), a front support structure (20), a gas generator simulated rotor (30), a common support structure (50) and a power turbine rotor equivalent excitation system (70); a rotor front journal (31) of the gas generator simulated rotor (30) is rotatably connected to the front support structure (20), and the rotor front journal (31) is connected to the rotor drive system (10) after passing through the front support structure (20); a rotor rear journal (41) of the gas generator simulated rotor (30) is rotatably connected to the common support structure (50), and a side of the common support structure (50) away from the gas generator simulated rotor (30) is connected to the power turbine rotor equivalent excitation system (70).

2. The common support rotor system vibration coupling characteristic test device according to claim 1, characterized in that: The gas generator simulation rotor (30) further comprises a center tie rod (49) and a first stage compressor simulation disk (34), a second / third stage compressor simulation drum (35), a fourth stage compressor simulation disk (36), a first stage turbine simulation disk (39) and a second stage turbine simulation disk (40) which are sequentially sleeved on the center tie rod (49) from the rotor front journal (31) to the rotor rear journal (41) and pressed by the center tie rod (49); one end of the center tie rod (49) is fixedly connected to the rotor front journal (31), and the first stage compressor simulation disk (34) is fixedly connected to the second stage turbine simulation disk (40). The docking position of the 2 / 3 stage compressor simulation drum (35) forms the 1st stage arc end tooth connection structure (48), the docking position of the 2 / 3 stage compressor simulation drum (35) and the 4th stage compressor simulation disk (36) forms the 2nd stage arc end tooth connection structure (47), the docking position of the 4th stage compressor simulation disk (36) and the 1st stage turbine simulation disk (39) forms the 3rd stage arc end tooth connection structure (46), and the rotor rear journal (41) is also sleeved on the center tie rod (49) and fixedly connected to the 2nd stage turbine simulation disk (40), and is pressed by the center tie rod (49).

3. The common support rotor system vibration coupling characteristic test device according to claim 2, characterized in that: The first-stage turbine simulation disk (39) and the second-stage turbine simulation disk (40) are integrated two-stage turbine simulation disks; The center tie rod (49) is provided with a middle clamping sleeve (37), a middle clamping nut (38), a rear journal clamping sleeve (45), and a tie rod end clamping nut (44). The middle clamping sleeve (37) is arranged in the center hole of the 4th stage compressor simulation disk (36). By tightening the middle clamping nut (38), the front section of the center tie rod (49) presses the 1st stage compressor simulation disk (34), the 2nd / 3rd stage compressor simulation drum (35), and the 4th stage compressor simulation disk (36). The rear journal clamping sleeve (45) presses against the rotor rear journal (41). By tightening the tie rod end clamping nut (44), the rear section of the center tie rod (49) presses the integrated two-stage turbine simulation disk and the rotor rear journal (41).

4. The common support rotor system vibration coupling characteristic test device according to claim 2, characterized in that: The gas generator simulation rotor (30) adopts a 1-0-1 support scheme, a front ball bearing (25) is arranged on the front shaft neck (31) of the rotor, and is rotatably connected to the front support structure (20) through the front ball bearing (25), and a rear roller bearing (57) is arranged on the rear shaft neck (41) of the rotor, and the ratio of the span between the front ball bearing (25) and the rear roller bearing (57) to the outer diameter of the front shaft neck of the first-stage turbine simulation disk (39) exceeds 13.

5. The common support rotor system vibration coupling characteristic test device according to claim 2, characterized in that: The first-stage compressor simulation disk (34) is provided with first-stage compressor simulation disk threaded holes (34A) uniformly distributed along the circumferential direction; the two simulation drums of the second / third-stage compressor simulation drum (35) are provided with second-stage compressor simulation drum threaded holes (35A) and third-stage compressor simulation drum threaded holes (35B) uniformly distributed along the circumferential direction; the fourth-stage compressor simulation disk (36) is provided with fourth-stage compressor simulation disk threaded holes (36A) uniformly distributed along the circumferential direction; the first-stage turbine simulation disk (39) is provided with first-stage turbine simulation disk threaded holes (39A) uniformly distributed along the circumferential direction; and the second-stage turbine simulation disk (40) is provided with second-stage turbine simulation disk threaded holes (40A) uniformly distributed along the circumferential direction.

6. The common support rotor system vibration coupling characteristic test device according to claim 1, characterized in that: The rotor drive system (10) comprises a high-speed motor and a coupling (12), wherein the coupling (12) is used to connect a motor output shaft (11) of the high-speed motor and the rotor front journal (31).

7. The common support rotor system vibration coupling characteristic test device according to claim 4, characterized in that: The front support structure (20) comprises a front support frame (21), a front support plate (22), a front bearing seat (23) and a front squirrel cage spring support (24); the front support frame (21) is connected and fixed to the test platform (1B); the front support plate (22) is fixedly connected to the front support frame (21); the outer flange edge of the front bearing seat (23) and the inner flange edge of the front support plate (22) are fixedly connected after being positioned by means of stopper fit; the outer flange edge of the front squirrel cage spring support (24) and the front bearing seat (23) are fixedly connected after being positioned by means of end face and cylindrical surface fit; the rotor front journal (31) passes through the front squirrel cage spring support (24) and is rotatably connected to the front squirrel cage spring support (24) through a front ball bearing (25).

8. The common support rotor system vibration coupling characteristic test device according to claim 4, characterized in that: The common support structure (50) comprises a rear support frame (51), a rear support plate (52), a bearing drum (53), a combustion simulation bearing seat (54), a dynamic vortex simulation bearing seat (59), a rear squirrel cage spring support (56), an oil baffle plate (55) and an oil baffle cover (58); the bearing drum (53) is a folding structure; the rear support frame (51) is connected and fixed to the test platform (1B); the rear support plate (52) is fixedly connected to the rear support frame (51); the inner flange edge of the rear support plate (52) and the outer flange edge of the bearing drum (53) are positioned and fixedly connected through stoppers; the outer flange edges of the combustion simulation bearing seat (54) and the dynamic vortex simulation bearing seat (59) and the inner flange edge of the bearing drum (53) are positioned and fixedly connected through stoppers. The rear squirrel cage spring support (56) and the oil shield (58) are matched and fixedly connected with the combustion simulation bearing seat (54) through the cylindrical surface of the outer flange edge. The oil shield plate (55) is positioned and fixedly connected with the flange edge of the combustion simulation bearing seat (54) through the outer flange edge. The oil shield plate (55) is designed with a brush-type sealing structure (55A) and together with the oil shield (58) forms a relatively closed lubricating oil cavity. The oil supply hole (54A) and the oil return hole (54B) are respectively located at the top and bottom ends of the combustion simulation bearing seat (54). The dynamic vortex simulation bearing seat (59) is used to connect with the power turbine rotor equivalent excitation system (70). The rotor rear shaft neck (41) is rotatably connected with the rear squirrel cage spring support (56) through the rear roller bearing (57).

9. The common support rotor system vibration coupling characteristic test device according to claim 1, characterized in that: The power turbine rotor equivalent excitation system (70) comprises a vertical exciter (71), a first vertical excitation top rod (73), a second vertical excitation top rod (75), a horizontal exciter (76), a first horizontal excitation top rod (77), a second horizontal excitation top rod (79), a horizontal force sensor (78) and a vertical force sensor (74); the vertical exciter (71) is connected to the upper end of the first vertical excitation top rod (73), the lower end of the first vertical excitation top rod (73) is connected to the vertical force sensor (74), and the second horizontal excitation top rod (79) is connected to the horizontal force sensor (78). The upper end of the second vertical excitation rod (75) is connected to the vertical force sensor (74), and the lower end of the second vertical excitation rod (75) is connected to the common support structure (50); the horizontal exciter (76) is connected to one end of the first horizontal excitation rod (77), and the other end of the first horizontal excitation rod (77) is connected to the horizontal force sensor (78); one end of the second horizontal excitation rod (79) is connected to the horizontal force sensor (78), and the other end of the second horizontal excitation rod (79) is connected to the common support structure (50).

10. The common support rotor system vibration coupling characteristic test device according to claim 9, characterized in that: The vertical vibrator (71) is arranged on a vertical vibrator support frame (72). The vertical vibrator support frame (72) is a gantry structure. The bases on both sides are provided with grooves for adjustably fixing the vertical vibrator support frame (72) to the test platform (1B). The support plates on both sides of the vertical vibrator support frame (72) are provided with square grooves. The horizontal vibrator (76) is arranged on a horizontal vibrator frame (76A), the horizontal vibrator frame (76A) is arranged on a horizontal vibrator base (76B), and the horizontal vibrator base (76B) is fixedly connected to the test platform (1B).

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