A test device for vibration coupling characteristics of a common support rotor system

Abstract

The present invention relates to a simulation test device in the field of rotating machinery, specifically a device for testing the vibration coupling characteristics of a shared-support rotor system. The device comprises a rotor drive system, a front support structure, a gas generator simulated rotor, a shared support structure, and a power turbine rotor equivalent excitation system. The front rotor journal of the gas generator simulated rotor is rotatably connected to the front support structure, and the front rotor journal passes through the front support structure and is connected to the rotor drive system. The rear rotor journal of the gas generator simulated rotor is rotatably connected to the shared support structure, and the side of the shared support structure facing away from the gas generator simulated rotor is connected to the power turbine rotor equivalent excitation system. The present invention's shared-support rotor system vibration coupling characteristics test device is the first of its kind proposed for testing shared-support rotor systems and can simulate various operating load environments for shared-support rotor systems.

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 place higher demands on structural efficiency. While meeting performance parameters, they require the structural mass to be as small as possible, that is, to adopt a high power-to-weight ratio design. To achieve this goal, the gas generator rotor design often adopts a high-speed, small radial dimension design. The support scheme adopts a long-span 1-0-1 support. The connection structure adopts a multi-stage arc end tooth torque transmission and a center tie rod segmented compression form. In the design of the load-bearing system, in order to minimize the number of load-bearing frames, a shared load-bearing frame design is adopted between turbine stages, simultaneously supporting the rear support points of the gas generator rotor and the power turbine rotor.

[0003] Engineering practice shows that since the shared load-bearing frame between turbine stages operates 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 large foundation vibrations. As a result, the vibration of one rotor can 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 dangerous resonance within certain characteristic speed ranges, affecting the safe operation of the rotor system.

[0004] Therefore, it is necessary to establish a test device for the vibration coupling characteristics of 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] Currently, there are relatively few simulation test devices designed for testing the vibration coupling characteristics of shared-support rotor systems. Most simulation test devices are designed for dual-rotor systems with intermediate pivot points and gear-driven dual-rotor systems. For example, Beijing University of Chemical Technology proposed a simulation test bench (CN116625692A) for a gear-driven coaxial counter-rotating dual-rotor system. For dual-rotor systems with intermediate pivot points, Guangxi University of Science and Technology proposed a serial bolt-connected dual-rotor test bench and its testing method (CN117268771A). The China Aero Engine Guiyang Engine Design Institute proposed a simulated dual-rotor aircraft engine with a sudden imbalance (CN116818187A). Huang Kai proposed an aviation dual-rotor comprehensive vibration test bench (CN215065140U). Inventive patent applications (CN118670731A and CN117825054A) published by Beijing Information Science and Technology University and Northwestern Polytechnical University, while considering the use of a shared support structure, their shared support configuration differs significantly 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 they do not fully consider 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 achieved by providing a vibration coupling characteristics test device for a shared support rotor system, comprising a rotor drive system, a front support structure, a gas generator simulated rotor, a shared support structure, and a power turbine rotor equivalent excitation system. The front rotor journal of the gas generator simulated rotor is rotatably connected to the front support structure via a front ball bearing, and the front rotor journal is connected to the rotor drive system after passing through the front support structure. The rear rotor journal of the gas generator simulated rotor is rotatably connected to the shared support structure via a rear roller bearing, and the side of the shared 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 pull 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 pull rod from the front shaft neck of the rotor to the rear shaft neck of the rotor and pressed by the center pull rod; one end of the center pull rod is fixedly connected to the front shaft neck of the rotor, and the position where the first-stage compressor simulation disk and the second / third-stage compressor simulation drum are docked forms a first-stage arc end tooth connection structure, the position where the second / third-stage compressor simulation drum and the fourth-stage compressor simulation disk are docked forms a second-stage arc end tooth connection structure, and the position where the fourth-stage compressor simulation disk and the first-stage turbine simulation disk are docked forms a third-stage arc end tooth connection structure. The rear shaft neck of the rotor is also sleeved on the center pull rod and connected to the second-stage turbine simulation disk through a flange-bolt, and is pressed by the center pull 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 presses the 1st stage compressor simulation disk, the 2 / 3rd stage compressor simulation drum, and the 4th stage compressor simulation disk. The rear shaft neck clamping sleeve is pressed 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 presses 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 provided 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 provided 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] It is further preferred that the two 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; the two 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] It is further preferred that the first-stage compressor simulation disk is provided with circumferentially uniformly distributed first-stage compressor simulation disk threaded holes, the two simulation drums of the second / third-stage compressor simulation drum are provided with circumferentially uniformly distributed second-stage compressor simulation drum threaded holes and circumferentially uniformly distributed third-stage compressor simulation drum threaded holes, the fourth-stage compressor simulation disk is provided with circumferentially uniformly distributed fourth-stage compressor simulation disk threaded holes, the first-stage turbine simulation disk is provided with circumferentially uniformly distributed first-stage turbine simulation disk threaded holes, and the second-stage turbine simulation disk is provided with circumferentially uniformly distributed second-stage turbine simulation disk threaded holes.

[0015] Preferably, the rotor drive system includes 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, which needs to be dynamically balanced at high speed, 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 fixed 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 then fixed 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 then fixed 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 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 fixed to the test platform by anchor bolts, the rear support plate is fixed 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 fixed 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 fixed 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 baffle 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 baffle 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 connect with the power turbine rotor equivalent excitation system. 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 vibrator, a first vertical vibrator pin, a second vertical vibrator pin, a horizontal vibrator, a first horizontal vibrator pin, a second horizontal vibrator pin, a horizontal force sensor and a vertical force sensor; the vertical vibrator is connected to the upper end of the first vertical vibrator pin, the lower end of the first vertical vibrator pin is connected to the vertical force sensor, the upper end of the second vertical vibrator pin is connected to the vertical force sensor, and the lower end of the second vertical vibrator pin 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 vibrator is connected to one end of the first horizontal vibrator pin, the other end of the first horizontal vibrator pin is connected to the horizontal force sensor, one end of the second horizontal vibrator pin is connected to the horizontal force sensor, and the other end of the second horizontal vibrator pin 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, and the vertical vibrator support frame is a gantry structure, and 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 passage of the horizontal excitation rod;

[0021] The horizontal vibrator is set on the horizontal vibrator frame, the horizontal vibrator frame is set on the horizontal vibrator base, the horizontal vibrator base is fixedly connected to the test platform, and the height of the horizontal vibrator base must ensure that the center line of the horizontal excitation push 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 simulated rotor is designed to be similar to the actual engine rotor in terms of geometric configuration, arc end tooth connection structure, support constraints, mass-stiffness distribution, critical speed distribution, preload force transmission path and compression state. This ensures that the simulated rotor has a similar motion state to the actual rotor within the corresponding operating 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 shared support structure are fully considered. The front support structure is similar in geometry to the actual casing structure, and the front support frame, front support plate, and front bearing seat all have good rigidity. The shared 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. The dynamic excitation of the equivalent excitation system of the gas generator simulation rotor and the power turbine rotor can be transmitted interactively, so that the shared support rotor system exhibits vibration coupling characteristics.

[0025] 3) In the present invention, the horizontal and vertical exciters in the power turbine rotor equivalent excitation system have adjustable excitation frequencies within a range of 1 to 1000 Hz, covering the frequency range corresponding to the operating speeds of the gas generator simulated rotor and the power turbine rotor. The excitation amplitude of the exciters is adjustable to simulate the dynamic excitation of the shared support structure under different imbalance states of the power turbine rotor. The excitation phases of the horizontal and vertical exciters are independently adjustable to simulate the motion trajectories of the power turbine rotor at different speeds, such as circular, elliptical, and linear trajectories.

[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 simulated gas generator rotor, the equivalent excitation state of the power turbine rotor, and the joint working state of the shared support rotor system. Therefore, a variety of experimental studies can be carried out: the vibration characteristics of the shared support structure and the simulated rotor motion state under the excitation of the simulated gas generator rotor, as well as 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 joint working state, and the influence of the equivalent excitation of the power turbine on the motion state of the simulated gas generator rotor. 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 This is a simplified diagram of the simulated rotor structure of a gas generator according to an embodiment of the present invention;

[0030] Figure 4 3D 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 simplified diagram of a common support structure according to an embodiment of the present invention;

[0033] Figure 7 3D structural diagram of a power turbine rotor equivalent excitation system according to an embodiment of the present invention;

[0034] Figure 1 shows: 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, second / third stage compressor simulated drum 35, second 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 55, brush-type sealing structure 55A, rear squirrel cage spring support 56, rear roller bearing 57, oil baffle 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 is a combination of 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 illustrate the present invention and are not intended 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 the test device of an embodiment of the present invention. The main structure of a common support rotor system vibration coupling characteristic test device includes: 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 a simulated gas generator rotor according to an embodiment of the present invention. The simulated gas generator 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. This bearing arrangement facilitates assembly of the simulated rotor and the shared 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 first front pressing sleeve 33A and the second front pressing sleeve 33B, and then compressed and fixed to the simulated rotor front journal 31 by the front compression nut 32. The inner ring of the simulated rotor rear bearing 57 is pressed against the first rear pressing sleeve 42A and the second rear pressing sleeve 42B, and then compressed and fixed to the simulated rotor rear journal 41 by the rear compression 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 shaft neck 41.

[0045] The front end of the central compression sleeve 37 presses against the center hole of the fourth-stage compressor simulated disk 36. By tightening the central compression nut 38, the front section of the center tie rod presses against the front section of the gas generator simulated rotor 30. The rear journal compression sleeve 45 presses against the rotor rear journal 41. By tightening the compression nut 44 at the end of the tie rod, the rear section of the center tie rod presses against the rear section of the gas generator simulated rotor 30.

[0046] Figure 4 This is a three-dimensional structural diagram of the simulated rotor of a gas generator according to an embodiment of the present invention. Each simulated disc has threaded holes uniformly distributed along the circumference, including: threaded holes 34A for the simulated disc of the first-stage compressor, threaded holes 35A for the simulated drum of the second-stage compressor, threaded holes 35B for the simulated drum of the third-stage compressor, threaded holes 36A for the simulated disc of the fourth-stage compressor, threaded holes 39A for the simulated disc of the first-stage turbine, and threaded holes 40A for the simulated disc of the second-stage turbine.

[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's 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 simplified diagram of the front support structure of an embodiment of the present invention. The rotor drive system 10 primarily comprises a high-speed motor and a coupling. The coupling connects the motor output shaft 11 to the front journal 31 of the gas generator rotor, thereby driving the gas generator simulated rotor 30 to rotate at high speed. The high-speed motor has a maximum speed of no less than 15,000 rpm. The motor output shaft 11 is connected to the front journal 31 of the gas generator rotor via a coupling 12, which is a flexible bellows 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 bellows flexible coupling 12 for angular misalignment is not less than ±2° and the maximum compensation capacity for lateral misalignment is not less than ±1mm.

[0050] The front support structure 20 consists of a front support frame 21, a front support plate 22, a front bearing seat 23, and a front cage spring support 24. The front support frame 21 is fixed to the test platform 1B via anchor bolts. The front support plate 22 is fastened to the front support frame 21 via bolts. The outer flange of the front bearing seat 23 and the inner flange of the front support plate 22 are positioned with stoppers and fastened with bolts. The outer flange of the front cage spring support 24 and the front bearing seat 23 are positioned with their end faces and cylindrical surfaces and fastened with 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 55, and an oil baffle cover 58. The bearing drum 53 is a folding structure with 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 with bolts. The outer flange edge of the combustion simulation bearing seat 54 and the dynamic vortex simulation bearing seat 59 is positioned with the inner flange edge of the bearing drum 53 through a stopper and is fastened with bolts.

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

[0053] The combustion simulation bearing seat 54 is designed with a squeeze film damper. Lubricating oil enters the combustion simulation bearing seat oil sump through the oil supply port 54A. The rear squirrel cage spring 56 acts as an oil film journal. Lubricating oil forms a squeeze film between the combustion simulation bearing seat 54 and the rear squirrel cage spring 56, ensuring that the gas generator simulated rotor 30 smoothly passes the critical speed. The oil baffle 55 is designed with a brush seal structure 55A. Together with the oil baffle 58, it forms a relatively closed lubricating oil chamber to prevent leaked lubricating oil from forming oil mist during high-speed rotor rotation. The oil return port 54B, located at the bottom of the combustion simulation bearing seat, is used to collect leaked lubricating oil to prevent it from leaking onto the test platform.

[0054] The rear end of the dynamic vortex simulation bearing seat 59 is provided with a vertical excitation hole 59A and a horizontal excitation hole 59B. 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 insertion of the vertical excitation push rod and the horizontal excitation push rod.

[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 bolted to a vertical vibrator base 71B. The vertical vibrator base 71B is bolted to a vertical vibrator support frame 72. The vertical vibrator support frame 72 is a gantry-style structure with grooves on either side of the base. Angle bolts penetrate through the frame base grooves to secure the vertical support frame 72 to the test platform 1B. The base grooves allow for adjustment of the support frame's position. The support plates on either side of the vertical support frame 72 have square grooves, which reduce the support frame's mass while facilitating the passage of horizontal excitation rods.

[0057] The vertical exciter 71 is connected to the front end of the first vertical excitation rod 73 by a thread, the end of the first vertical excitation rod 73 is connected to the vertical force sensor 74 by a thread, the front end of the second vertical excitation rod 75 is connected to the vertical force sensor 74 by a thread, 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 75D are tightened 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 center line 59L of the power turbine simulation bearing seat and the center line 79A of the horizontal exciting mandrel.

[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 push 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 rod 77 through a threaded connection, the end of the first horizontal excitation rod 77 is connected to the horizontal force sensor 78 through a threaded connection, the front end of the second horizontal excitation rod 79 is connected to the horizontal force sensor 78 through a threaded connection, and the end of the second horizontal excitation rod 79 is connected to the dynamic vortex simulation bearing seat 59 through nuts tightened in opposite directions to ensure that the excitation force is effectively transmitted to the dynamic vortex simulation bearing seat.

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

[0062] 1) Gas generator simulated rotor excitation state: By adding bolts to the simulated rotor disc as unbalanced masses, the disc center of mass offset or inertia 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, causing it to generate dynamic excitation on the common support. Under the excitation of the gas generator simulated rotor, the vibration characteristics of the common support structure and the simulated rotor motion state 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 the power turbine rotor: The horizontal and vertical exciters are used to simultaneously excite the dynamic vortex simulation bearing seat, equivalent to the dynamic excitation generated by the actual power turbine rotor on the shared support structure. This allows the transfer characteristics of the equivalent excitation of the power turbine rotor in the shared support structure to be studied. By adjusting the excitation phase difference between the horizontal and vertical exciters, the excitation trajectory can be changed to a circular trajectory, an elliptical trajectory, a linear trajectory, etc., simulating 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, covering 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 is adjustable to simulate the dynamic excitation of the shared support structure under different imbalance 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 and vertical exciters dynamically excite the moving vortex simulated bearing seat. This can simulate the state of the gas generator simulated rotor and the power turbine rotor working together, and can 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 merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the 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 fall within the scope of protection 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), wherein 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); The gas generator simulation rotor (30) adopts a 1-0-1 support scheme, a front ball bearing (25) is provided on the front journal (31) of the rotor, and is rotatably connected to the front support structure (20) via the front ball bearing (25), and a rear roller bearing (57) is provided on the rear journal (41) of the rotor; The common support structure (50) includes 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 (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 a stopper. The outer flange edges of the combustion simulation bearing seat (54) and the dynamic vortex simulation bearing seat (59) are positioned and fixedly connected to the inner flange edge of the bearing drum (53) through a stopper. 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 (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 (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 to the rear squirrel cage spring support (56) through the rear roller bearing (57).

2. The common support rotor system vibration coupling characteristics test device according to claim 1, characterized in that: The gas generator simulation rotor (30) further includes 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 position where the 2 / 3 stage compressor simulation drum (35) is connected forms the first stage arc end tooth connection structure (48), the position where the 2 / 3 stage compressor simulation drum (35) is connected with the fourth stage compressor simulation disk (36) is connected forms the second stage arc end tooth connection structure (47), the position where the fourth stage compressor simulation disk (36) is connected with the first stage turbine simulation disk (39) is connected forms the third 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 second 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; A middle pressing sleeve (37), a middle pressing nut (38), a rear journal pressing sleeve (45), and a rod end pressing nut (44) are provided on the center tie rod (49). The middle pressing sleeve (37) is arranged in the center hole of the 4th stage compressor simulation disk (36). By tightening the middle pressing 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 pressing sleeve (45) presses against the rotor rear journal (41). By tightening the rod end pressing 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 characteristics test device according to claim 2, characterized in that: The ratio of the span between the front ball bearing (25) and the rear roller bearing (57) to the outer diameter of the front journal of the first-stage turbine simulation disk (39) exceeds 13.

5. The common support rotor system vibration coupling characteristics 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 characteristics 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 characteristics test device according to claim 4, characterized in that: The front support structure (20) includes a front support frame (21), a front support plate (22), a front bearing seat (23) and a front squirrel cage elastic 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 a stopper, the outer flange edge of the front squirrel cage elastic support (24) and the front bearing seat (23) are fixedly connected after being positioned by an end face and a cylindrical surface, and the rotor front journal (31) passes through the front squirrel cage elastic support (24) and is rotatably connected to the front squirrel cage elastic support (24) through a front ball bearing (25).

8. The common support rotor system vibration coupling characteristics test device according to claim 1, characterized in that: The power turbine rotor equivalent excitation system (70) includes a vertical exciter (71), a first vertical excitation rod (73), a second vertical excitation rod (75), a horizontal exciter (76), a first horizontal excitation rod (77), a second horizontal excitation 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 rod (73), the lower end of the first vertical excitation rod (73) is connected to the vertical force sensor (74), and the second horizontal excitation rod (79) is connected to the horizontal force sensor (78). The upper ends of the two vertical excitation rods (75) are connected to the vertical force sensor (74), and the lower ends of the second vertical excitation rods (75) are 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).

9. The common support rotor system vibration coupling characteristics test device according to claim 8, 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 adjusting and 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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