Aero-engine rotor test system and test method

Abstract

The invention discloses an aero-engine rotor test system and method, and the system comprises an explosion-proof cavity, a switching assembly, a floating connecting shaft, a front supporting assembly, a rear supporting assembly and an oil return assembly, the explosion-proof cavity is internally provided with a test platform, and the switching assembly, the front supporting assembly and the rear supporting assembly are sequentially arranged on the test platform in the horizontal direction. The adapter assembly is used for being connected with the driving end of a tester, the front supporting assembly and the rear supporting assembly are used for supporting the two opposite ends of an aero-engine rotor, and the floating connecting shaft is connected with the movable end of the adapter assembly, used for being connected with the aero-engine rotor and capable of axially moving by a preset distance relative to the adapter assembly and the aero-engine rotor. The oil return assembly comprises a first oil return piece arranged on the switching assembly, a second oil return piece arranged on the front supporting assembly, a third oil return piece arranged on the rear supporting assembly and an external oil tank arranged outside the anti-explosion cavity and communicated with the first oil return piece, the second oil return piece and the third oil return piece.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engines, and in particular, to an aircraft engine rotor test system and an aircraft engine rotor test method using the aircraft engine rotor test system. Background Art

[0002] Aircraft engines are high-speed rotating machines, and their rotor dynamics test research is of great significance in the engine development process. In the prior art, aircraft engine rotor dynamics tests are generally conducted on a horizontal rotating tester. During the test, after fixing both ends of the rotor, the lubricating oil system provides lubricating oil to the rotor bearings, and the rotor is driven to rotate by the power device (main traction motor). The test data is collected by the data acquisition device, and the data is further analyzed to obtain rotor characteristics, such as rotor dynamic characteristics, dynamic balance characteristics, vibration characteristics, etc.

[0003] For example, Chinese invention patent application CN118913703A discloses a power turbine rotor maximum imbalance test device and test method, including a fully assembled engine shaft system, a torque measurement unit, a turbine simulation disk and a tester. The mass characteristics and dynamic characteristics of the turbine simulation disk are consistent with the two-stage power turbine disk assembly of the engine so as to replace the two-stage power turbine disk and be installed on the engine shaft system; a counterweight installation structure is evenly distributed along the circumference of the turbine simulation disk, which is used to connect a first counterweight at one or more preset circumferential positions according to test requirements to thereby change the imbalance of the wheel position.

[0004] However, the above test device has the following deficiencies in actual tests: 1) The above device cannot effectively recover the lubricating oil during the test. If the lubricating oil flows back directly from the test platform, it is easy to cause the lubricating oil to flow out and the oil supply and return system of the tester to be blocked.

[0005] 2) During the aircraft engine rotor test, the driving end of the tester is directly connected to the aircraft engine rotor to drive the aircraft engine rotor to rotate. However, in actual tests, the vibration of the tester itself will affect the vibration characteristics of the aircraft engine rotor, thereby interfering with the test results, making the reliability of the test results low. In addition, the high-speed rotating engine rotor is also prone to damage the tester after being damaged. Summary of the invention

[0006] The invention provides an aero-engine rotor test system and a test method to solve the technical problems of low reliability of test results, inability to effectively recover lubricating oil and easy damage to the tester in the existing aero-engine rotor test device.

[0007] According to one aspect of the present invention, there is provided an aircraft engine rotor test system, comprising an explosion-proof cavity, an adapter assembly, a floating connecting shaft, a front bearing assembly, a rear bearing assembly and an oil return assembly, wherein a test platform is arranged in the explosion-proof cavity, the adapter assembly, the front bearing assembly and the rear bearing assembly are arranged in sequence on the test platform in a horizontal direction, the adapter assembly is used to be connected to the driving end of the tester, the front bearing assembly and the rear bearing assembly are used to support the opposite ends of the aircraft engine rotor, the floating connecting shaft is connected to the movable end of the adapter assembly and is used to connect the aircraft engine rotor and can move axially by a preset distance relative to the adapter assembly and the aircraft engine rotor, and the oil return assembly comprises a first oil return member for lubricating oil return arranged on the adapter assembly, a second oil return member for lubricating oil return arranged on the front bearing assembly, a third oil return member for lubricating oil return arranged on the rear bearing assembly, and an external oil tank for containing lubricating oil arranged outside the explosion-proof cavity and connected to the first oil return member, the second oil return member and the third oil return member, respectively.

[0008] As a further improvement of the above technical solution: Furthermore, the adapter assembly includes an adapter support with an installation through hole, an adapter bearing seat arranged in the installation through hole, and a torque transmission shaft arranged in the adapter bearing seat and connected to the floating connecting shaft for connecting to the driving end of the tester.

[0009] Furthermore, the first oil return member includes an oil return port opened on the adapter support and connected to the internal lubricating oil channel of the adapter bearing seat, and an oil return pipe 1 connected to the oil return port and the external oil tank respectively. The oil return port is located below the adapter bearing seat.

[0010] Furthermore, the floating connecting shaft includes a hollow shaft body, a first spline arranged on the circumferential outer wall of the first end of the shaft body for cooperating with the spline of the torque transmission shaft, and a second spline arranged on the circumferential outer wall of the second end of the shaft body for cooperating with the spline of the aircraft engine rotor. The first spline and the second spline are arranged in a drum-shaped tooth structure, and the shaft body is slidably matched with the torque transmission shaft and is used to slidably match with the aircraft engine rotor so that it can move axially a preset distance.

[0011] Furthermore, the front support assembly includes a front support with a second mounting through hole, a front transition section arranged in the second mounting through hole, and a front bearing seat arranged in the front transition section for supporting the rotor of the aircraft engine.

[0012] Furthermore, the second oil return member includes an oil return hole 1 opened on the front transition section for returning the lubricating oil in the front bearing seat, an oil blocking boss 1 arranged on the front transition section for axially blocking the lubricating oil, a vertical oil return chamber 1 opened vertically in the front support and connected with the oil return hole 1, a horizontal oil return chamber 1 opened horizontally in the front support and connected with the vertical oil return chamber 1, and an oil return pipe 2 respectively connected with the horizontal oil return chamber 1 and the external oil tank.

[0013] Furthermore, the second oil return member also includes an oil receiving box arranged on the front support for collecting lubricating oil at the rotor bearing position axially located outside the front support, and an inclined oil return chamber opened in the front support and connected to the oil receiving box and the vertical oil return chamber respectively.

[0014] Furthermore, the rear support assembly includes a rear support with a third installation through hole, a rear transition section arranged in the third installation through hole, and a rear bearing seat arranged in the rear transition section for supporting the rotor of the aircraft engine.

[0015] Furthermore, the third oil return part includes an oil return hole 2 opened on the rear transition section for returning the lubricating oil in the rear bearing seat, an oil blocking boss 2 arranged on the rear transition section for axially blocking the lubricating oil, a vertical oil return chamber 2 opened vertically in the rear support and connected with the oil return hole 2, a horizontal oil return chamber 2 opened horizontally in the rear support and connected with the vertical oil return chamber 2, and an oil return pipe 3 respectively connected with the horizontal oil return chamber 2 and the external oil tank.

[0016] According to another aspect of the present invention, there is also provided an aircraft engine rotor test method, which includes the above-mentioned aircraft engine rotor test system, and includes the following steps: S1, test-assembling the aircraft engine rotor on a test platform to adjust the front support assembly and the rear support assembly to the set axial position respectively, and removing the aircraft engine rotor after the test-assembly is completed; S2, using a laser alignment instrument and a centering tool to sequentially align the center holes of the front support assembly and the rear support assembly relative to the center hole of the test adapter assembly, and after the alignment is completed, fixing the front support assembly and the rear support assembly on the test platform; S3, the tester is idling to ensure that the test system operates normally; S 4. Install the aircraft engine rotor on the front support assembly and the rear support assembly, and connect the aircraft engine rotor to the tester through a floating connecting shaft; S5. Install the first oil return component, the second oil return component and the third oil return component on the adapter assembly, the front support assembly and the rear support assembly respectively, and connect the first oil return component, the second oil return component and the third oil return component to the external oil tank; S6. Install the measuring sensor and complete the connection and debugging of the measuring sensor; S7. Set the pressure in the explosion-proof cavity according to the test needs. After the pressure stabilizes, start the tester to drive the aircraft engine rotor to rotate, collect test data through the measuring sensor, and obtain the dynamic characteristics of the aircraft engine rotor.

[0017] The present invention has the following beneficial effects: The aircraft engine rotor test system of the present invention forms a relatively closed space through an explosion-proof cavity to conduct aircraft engine rotor tests, and contains high-energy fragments after the rotor is damaged to ensure test safety; the adapter assembly, the front support assembly and the rear support assembly are arranged in sequence on the test platform in the horizontal direction, connected to the driving end of the tester through the adapter assembly, and the opposite ends of the aircraft engine rotor are supported by the front support assembly and the rear support assembly, and then the movable end of the adapter assembly and the aircraft engine rotor are respectively connected through a floating connecting shaft, so that the driving end of the tester is indirectly connected to the aircraft engine rotor, and the vibration of the tester is isolated by the axial movement of the floating connecting shaft. On the one hand, it can greatly reduce the influence of the vibration of the tester itself on the vibration characteristics of the engine rotor, reduce the test risk, and further ensure the accuracy of the test results. On the other hand, it can effectively reduce the damage to the tester caused by the high-speed rotating engine rotor being damaged during the test; during the test, under the action of the oil return assembly , the lubricating oil in the lubricating adapter assembly, the front bearing assembly and the rear bearing assembly are returned to the external oil tank outside the explosion-proof cavity through the first oil return part, the second oil return part and the third oil return part respectively. On the one hand, it can be reduced to prevent the outflow of lubricating oil, which can greatly reduce the consumption of test lubricating oil, and at the same time completely eliminate the problem of the test platform being full of lubricating oil, which brings convenience to the test operation and optimizes the test site environment; on the other hand, since the lubricating oil does not flow through the test platform, the impurity content in the return oil is greatly reduced, which can effectively solve the problem of easy blockage of the oil supply and return system of the tester; in addition, it can also improve the problem of difficulty in oil return caused by the reverse pressure gradient in the test chamber relative to the external oil tank during the rotor test, and improve the lubricating oil return efficiency during the test; this scheme cooperates with the explosion-proof cavity, the adapter assembly, the floating connecting shaft, the front bearing assembly, the rear bearing assembly and the oil return assembly to carry out aircraft engine rotor testing. Compared with the existing technology, the test results are highly reliable, the lubricating oil can be effectively recovered, the tester is not easy to be damaged, and it is highly practical, which is suitable for wide promotion and application.

[0018] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 It is a structural schematic diagram of an aircraft engine rotor test system according to a preferred embodiment of the present invention; Figure 2 It is a structural schematic diagram of a switching assembly in an aero-engine rotor test system in a preferred embodiment of the present invention; Figure 3It is a structural schematic diagram of a floating connection shaft in an aero-engine rotor test system in a preferred embodiment of the present invention; Figure 4 It is a cross-sectional schematic diagram of a front support in an aero-engine rotor test system according to a preferred embodiment of the present invention; Figure 5 It is a cross-sectional schematic diagram of a rear support in an aero-engine rotor test system according to a preferred embodiment of the present invention; Figure 6 It is a structural schematic diagram of a front transfer section in an aero-engine rotor test system in a preferred embodiment of the present invention; Figure 7 It is a structural schematic diagram of a rear transfer section in an aero-engine rotor test system in a preferred embodiment of the present invention; Figure 8 It is a cross-sectional schematic diagram of a front support in an aero-engine rotor test system in a preferred embodiment of the present invention.

[0020] Legend: 100, explosion-proof cavity; 200, adapter assembly; 210, adapter support; 211, oil inlet; 220, adapter bearing seat; 230, torque transmission shaft; 300, floating connecting shaft; 310, shaft body; 320, first spline; 330, second spline; 400, front support assembly; 410, front support; 420, front adapter section; 430, front bearing seat; 500, rear support assembly; 510, rear support; 520, rear adapter section; 530, rear bearing seat; 600, oil return assembly; 611, oil return port; 612, oil return pipe 1; 621, oil return hole 1; 622, oil baffle boss 1; 623, vertical oil return chamber 1; 624, horizontal oil return chamber 1; 625, oil return pipe 2; 626, oil receiving box; 627, inclined oil return chamber; 631, oil return hole 2; 632, oil baffle boss 2; 633, vertical oil return chamber 2; 634, horizontal oil return chamber 2; 635, oil return pipe 3. DETAILED DESCRIPTION

[0021] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0022] like Figure 1As shown, the aircraft engine rotor test system of this embodiment includes an explosion-proof cavity 100, an adapter assembly 200, a floating connecting shaft 300, a front supporting assembly 400, a rear supporting assembly 500 and an oil return assembly 600. A test platform is provided in the explosion-proof cavity 100. The adapter assembly 200, the front supporting assembly 400 and the rear supporting assembly 500 are sequentially arranged on the test platform in a horizontal direction. The adapter assembly 200 is used to connect with the driving end of the tester, the front supporting assembly 400 and the rear supporting assembly 500 are used to support the opposite ends of the aircraft engine rotor, and the floating connecting shaft 300 is used to connect with the driving end of the tester. 0 is connected to the movable end of the adapter assembly 200 and is used to connect the aircraft engine rotor and can move axially by a preset distance relative to the adapter assembly 200 and the aircraft engine rotor, the oil return assembly 600 includes a first oil return member for lubricating oil return arranged on the adapter assembly 200, a second oil return member for lubricating oil return arranged on the front support assembly 400, a third oil return member for lubricating oil return arranged on the rear support assembly 500, and an external oil tank for containing lubricating oil arranged outside the explosion-proof cavity 100 and connected to the first oil return member, the second oil return member and the third oil return member respectively.

[0023] like Figure 1As shown, specifically, the aircraft engine rotor test system of the present invention forms a relatively closed space through an explosion-proof cavity 100 to conduct aircraft engine rotor tests, and contains high-energy fragments after the rotor is damaged to ensure test safety; the adapter assembly 200, the front support assembly 400 and the rear support assembly 500 are arranged in sequence on the test platform in the horizontal direction, connected to the driving end of the tester through the adapter assembly 200, and the opposite ends of the aircraft engine rotor are supported by the front support assembly 400 and the rear support assembly 500, and then the movable end of the adapter assembly 200 and the aircraft engine rotor are respectively connected through the floating connection shaft 300, so that the driving end of the tester is indirectly connected to the aircraft engine rotor, and the vibration of the tester is isolated by the axial movement of the floating connection shaft 300. On the one hand, it can greatly reduce the influence of the vibration of the tester itself on the vibration characteristics of the engine rotor, reduce the test risk, and further ensure the accuracy of the test results. On the other hand, it can effectively reduce the damage to the tester caused by the high-speed rotating engine rotor being damaged during the test; during the test, in the oil return assembly 6 00, the lubricating oil in the lubricating adapter assembly 200, the front support assembly 400 and the rear support assembly 500 respectively flows back to the external oil tank outside the explosion-proof cavity 100 through the first oil return member, the second oil return member and the third oil return member. On the one hand, it can reduce to prevent the lubricating oil from flowing out, which can greatly reduce the consumption of test lubricating oil, and completely eliminate the problem of the test platform being full of lubricating oil, which brings convenience to the test operation and optimizes the test site environment; on the other hand, since the lubricating oil does not flow through the test platform, the impurity content in the return oil is greatly reduced, which can effectively solve the problem of supplying and returning oil to the tester. The system is prone to clogging. In addition, the problem of difficulty in oil return caused by the reverse pressure gradient in the test chamber relative to the external oil tank during the rotor test can be improved, and the efficiency of lubricating oil return during the test can be improved. The scheme cooperates with the explosion-proof cavity 100, the adapter assembly 200, the floating connecting shaft 300, the front support assembly 400, the rear support assembly 500 and the oil return assembly 600 to carry out aircraft engine rotor testing. Compared with the existing technology, the test results are highly reliable, the lubricating oil can be effectively recovered, the tester is not easy to be damaged, the practicability is strong, and it is suitable for wide promotion and application.

[0024] Optionally, the explosion-proof chamber 100 also has a vacuum pumping function, so that the aircraft engine can be operated under vacuum conditions, thereby greatly improving the versatility of the test system.

[0025] It should be understood that when the aircraft engine rotor is not tested in a vacuum environment, the aerodynamic load will affect the dynamic characteristics of the rotor. At the same time, if the rotor with real engine blades is tested, the presence of aerodynamic loads will significantly increase the load on the power unit (main traction motor). Due to the power limitation of the power unit (main traction motor), it will be impossible to conduct high-speed real engine rotor tests, and only some low-speed simulated rotor tests with simulated disks can be carried out, which have poor versatility.

[0026] Optionally, when the explosion-proof cavity 100 is in a vacuum state, the pressure inside the cavity has a reverse pressure gradient relative to the external oil tank, and the setting of the oil return assembly 600 can effectively improve the oil return efficiency.

[0027] like Figure 2 As shown, in this embodiment, the adapter assembly 200 includes an adapter support 210 with a mounting through hole 1, an adapter bearing seat 220 arranged in the mounting through hole 1, and a torque transmission shaft 230 arranged in the adapter bearing seat 220 and connected to the floating connecting shaft 300 for connecting to the driving end of the tester.

[0028] Optionally, the adapter bearing seat 220 reliably mounts the torque transmission shaft 230 through a bearing, and the adapter support 210 is provided with an oil inlet 211 connected to the internal lubricating oil channel of the adapter bearing seat 220 so that lubricating oil for lubricating the bearing can flow into the oil inlet 211.

[0029] like Figure 2 As shown, specifically, the adapter support 210 is a solid triangular structure, which is detachably connected to the test platform, and the mounting through hole 1 is axially arranged at the upper end of the adapter support 210 and passes through the plate surface of the adapter support 210; the adapter bearing seat 220 is fixedly installed in the mounting through hole 1 of the support along the axial direction, and the torque transmission shaft 230 is axially installed in the bearing seat hole of the adapter bearing seat 220 through a bearing, and the input end of the torque transmission shaft 230 extending out of the bearing seat hole is connected to the driving end of the tester, and the opposite output end thereof extends out of the bearing seat hole and is connected to the aircraft engine rotor through a sleeve gear adapter; the interior of the adapter bearing seat 220 is also provided with a lubricating oil circuit structure for lubricating the bearing and the torque transmission shaft 230, so that the torque transmission shaft 230 can stably and reliably transmit power and torque; the torque transmission shaft 230 and the floating connecting shaft 300 are driven to rotate by the tester to drive the aircraft engine rotor to rotate, so as to test the dynamic characteristics of the aircraft engine rotor.

[0030] like Figure 1 and Figure 2 As shown, in this embodiment, the first oil return member includes an oil return port 611 opened on the adapter support 210 and connected to the internal lubricating oil channel of the adapter bearing seat 220, and an oil return pipe 1 612 connected to the oil return port 611 and the external oil tank respectively, and the oil return port 611 is located below the adapter bearing seat 220. Specifically, during the test, the lubricating oil in the adapter assembly 200 is returned by gravity, and the lubricating oil in the adapter bearing seat 220 flows to the external oil tank in turn through the oil return port 611 and the oil return pipe 1 612 below the adapter bearing seat 220 under the action of gravity and inertia. Optionally, part of the pipeline of the oil return pipe 1 612 is buried in the test platform.

[0031] like Figure 3As shown, in this embodiment, the floating connecting shaft 300 includes a hollow shaft body 310, a first spline 320 arranged on the circumferential outer wall of the first end of the shaft body 310 for spline cooperation with the torque transmission shaft 230, and a second spline 330 arranged on the circumferential outer wall of the second end of the shaft body 310 for spline cooperation with the aircraft engine rotor. The first spline 320 and the second spline 330 are arranged in a drum-shaped tooth structure, and the shaft body 310 is slidably cooperated with the torque transmission shaft 230 and is used to slide with the aircraft engine rotor so that it can move axially by a preset distance. Specifically, the weight is reduced by hollowing the shaft body 310, the first spline 320 on the circumferential outer wall of the first end of the shaft body 310 is spline-matched with the torque transmission shaft 230, the second spline 330 on the circumferential outer wall of the second end of the shaft body 310 is spline-matched with the aircraft engine rotor, the first spline 320 and the second spline 330 are arranged in a drum-shaped tooth structure to achieve angular compensation, and the shaft body 310 is respectively slidably matched with the torque transmission shaft 230 and the aircraft engine rotor, so that it can move a preset distance along the axial direction to isolate the vibration of the tester. Optionally, the preset distance is 1mm-2mm.

[0032] like Figure 1 As shown, in this embodiment, the front support assembly 400 includes a front support 410 with a second mounting through hole, a front transition section 420 arranged in the second mounting through hole, and a front bearing seat 430 arranged in the front transition section 420 for supporting the rotor of the aircraft engine.

[0033] Specifically, the front support 410 is fixed to the test platform by anchor bolts, the front transition section 420 is reliably installed in the second installation through hole, and the front bearing seat 430 is reliably installed in the front transition section 420 to support the front end of the aircraft engine rotor.

[0034] like Figure 4 As shown, optionally, the front support 410 includes an upper cover, a lower seat, a base plate and a trim strip, the trim strip is arranged below the base plate, the lower seat is arranged above the base plate, the upper cover is arranged above the lower seat, and the lower seat is arranged in a "convex" shape, the trim strip and the base plate are positioned by pins and fixed by screws; the front support 410 is positioned with the test platform through the trim strip, and the base plate is fixed to the test platform through the positioning blocks and screws in the T-slot of the test platform; the base plate and the lower seat are fixed by screws; the lower longitudinal slope and the upper cover are positioned by pins and fixed by screws; two circles of 10×M8 threaded holes are designed on both sides of the end of the front support 410 for fixing the test rotor, and threaded holes for installing vibration acceleration sensors are designed in the vertical and horizontal directions of the upper cover.

[0035] like Figure 1As shown, optionally, the front transition section 420 is used to realize the connection between the rotor front bearing seat 430 and the front support 410, and the front transition section 420 and the front support 410, as well as the front transition section 420 and the rotor front bearing seat 430, are connected by cylindrical surface centering and bolt fastening.

[0036] like Figure 1 , Figure 4 and Figure 6 As shown, in this embodiment, the second oil return member includes an oil return hole 621 opened on the front transition section 420 for returning the lubricating oil in the front bearing seat 430, an oil blocking boss 622 arranged on the front transition section 420 for axially blocking the lubricating oil, a vertical oil return chamber 623 opened vertically in the front support 410 and connected to the oil return hole 621, a horizontal oil return chamber 624 opened in the front support 410 along the horizontal direction and connected to the vertical oil return chamber 623, and an oil return pipe 625 respectively connected to the horizontal oil return chamber 624 and the external oil tank.

[0037] like Figure 1 , Figure 4 and Figure 6 As shown, specifically, after the lubricating oil in the front bearing seat 430 lubricates the bearing and the aircraft engine rotor, and under the obstruction of the oil blocking boss 622, it flows into the vertical oil return chamber 623 through the oil return hole 621, then flows into the horizontal oil return chamber 624, and then flows into the external oil tank through the oil return pipe 625 to complete the oil return of the lubricating oil in the front support assembly 400.

[0038] Optionally, part of the oil return pipe 2 625 is buried in the test platform.

[0039] like Figure 8 As shown, in this embodiment, the second oil return member also includes an oil collecting box 626 arranged on the front support 410 for collecting lubricating oil at the rotor bearing position axially located outside the front support 410, and an inclined oil return chamber 627 opened in the front support 410 and connected to the oil collecting box 626 and the vertical oil return chamber 623 respectively.

[0040] like Figure 8 As shown, specifically, the lubricating oil at the rotor bearing position axially located outside the front support 410 is collected by the oil collecting box 626, and then flows to the vertical oil return chamber 623 through the inclined oil return chamber 627, thereby realizing the oil return at this position.

[0041] like Figure 1 As shown, in this embodiment, the rear support assembly 500 includes a rear support 510 with a third mounting through hole, a rear transition section 520 arranged in the third mounting through hole, and a rear bearing seat 530 arranged in the rear transition section 520 for supporting the rotor of the aircraft engine.

[0042] like Figure 1 As shown, specifically, the rear support 510 is fixed to the test platform by anchor bolts, the rear transition section 520 is reliably installed in the installation through hole three, and the rear bearing seat 530 is reliably installed in the rear transition section 520 to support the rear end of the aircraft engine rotor.

[0043] like Figure 4 As shown, optionally, the specific structure of the rear support 510 is the same as or similar to that of the front support 410 .

[0044] like Figure 1 , Figure 5 and Figure 7 As shown, in this embodiment, the third oil return member includes an oil return hole 631 opened on the rear transition section 520 for returning the lubricating oil in the rear bearing seat 530, an oil blocking boss 632 arranged on the rear transition section 520 for axially blocking the lubricating oil, a vertical oil return chamber 633 opened vertically in the rear support 510 and connected to the oil return hole 631, a horizontal oil return chamber 634 opened in the rear support 510 along the horizontal direction and connected to the vertical oil return chamber 633, and an oil return pipe 635 respectively connected to the horizontal oil return chamber 634 and the external oil tank.

[0045] like Figure 1 , Figure 5 and Figure 7 As shown, specifically, after the lubricating oil in the rear bearing seat 530 lubricates the bearing and the aircraft engine rotor, and under the obstruction of the oil blocking boss 632, it flows into the vertical oil return chamber 633 through the oil return hole 631, then flows into the horizontal oil return chamber 634, and then flows into the external oil tank through the oil return pipe 635 to complete the oil return of the lubricating oil in the rear support assembly 500.

[0046] like Figure 1As shown, the aircraft engine rotor test method of this embodiment adopts the above-mentioned aircraft engine rotor test system, and includes the following steps: S1, test-assemble the aircraft engine rotor on the test platform to adjust the front support assembly 400 and the rear support assembly 500 to the set axial position respectively, and remove the aircraft engine rotor after the test assembly is completed; S2, use a laser alignment instrument and a centering tool to sequentially align the center holes of the front support assembly 400 and the rear support assembly 500 relative to the center hole of the test adapter assembly 200, and after the alignment is completed, fix the front support assembly 400 and the rear support assembly 500 on the test platform; S3, the tester is idling to ensure that the test system operates normally; S4, the aircraft The engine rotor is installed on the front support assembly 400 and the rear support assembly 500, and the aircraft engine rotor is connected to the tester through the floating connecting shaft 300; S5, respectively install the first oil return component, the second oil return component and the third oil return component on the adapter assembly 200, the front support assembly 400 and the rear support assembly 500, and connect the first oil return component, the second oil return component and the third oil return component with the external oil tank; S6, install the measuring sensor and complete the connection and debugging of the measuring sensor; S7, set the pressure in the explosion-proof cavity 100 according to the test needs, and after the pressure stabilizes, start the tester to drive the aircraft engine rotor to rotate, collect test data through the measuring sensor, and obtain the dynamic characteristics of the aircraft engine rotor.

[0047] Specifically, the aircraft engine rotor test system of the present invention can truly simulate the aircraft engine rotor dynamic boundary conditions under actual working conditions by adopting the above-mentioned aircraft engine rotor test system, and fully consider the return oil collection of the rotor in a low-pressure environment. An adapter assembly 200 and a floating connecting shaft 300 are arranged between the driving end of the tester and the aircraft engine rotor. On the one hand, it can greatly reduce the influence of the vibration of the tester itself on the vibration characteristics of the engine rotor, reduce the test risk, and further ensure the accuracy of the test results. On the other hand, it can effectively reduce the risk of the high-speed rotating engine rotor in the test process. The damage to the tester caused by natural destruction is avoided; the return oil component 600 is provided to realize the return of the lubricating oil, and the lubricating oil does not flow out, which can greatly reduce the consumption of the test lubricating oil. At the same time, the problem of the test platform being covered with lubricating oil can be completely eliminated, which brings convenience to the test operation and optimizes the test site environment; the impurity content in the return oil is greatly reduced, which can effectively solve the problem of easy blockage of the oil supply and return system of the tester; the problem of difficulty in oil return caused by the reverse pressure gradient in the test chamber relative to the external oil tank during the rotor test is improved, and the efficiency of lubricating oil return during the test is improved; it has good versatility, and the test system and method can be used / referenced for rotor tests with different structural layouts.

[0048] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft engine rotor test system, characterized in that: The invention comprises an explosion-proof cavity (100), an adapter assembly (200), a floating connecting shaft (300), a front supporting assembly (400), a rear supporting assembly (500) and an oil return assembly (600). A test platform is arranged in the explosion-proof cavity (100). The adapter assembly (200), the front supporting assembly (400) and the rear supporting assembly (500) are arranged in sequence on the test platform in a horizontal direction. The adapter assembly (200) is used to be connected to the driving end of the tester. The front supporting assembly (400) and the rear supporting assembly (500) are used to support the opposite ends of the rotor of the aircraft engine. The floating connecting shaft (300) is connected to the rotor. The movable end of the connecting assembly (200) is connected and used to connect to the aircraft engine rotor and can move axially by a preset distance relative to the adapter assembly (200) and the aircraft engine rotor. The oil return assembly (600) includes a first oil return member for lubricating oil return arranged on the adapter assembly (200), a second oil return member for lubricating oil return arranged on the front support assembly (400), a third oil return member for lubricating oil return arranged on the rear support assembly (500), and an external oil tank for containing lubricating oil arranged outside the explosion-proof cavity (100) and connected to the first oil return member, the second oil return member and the third oil return member, respectively.

2. The aircraft engine rotor test system according to claim 1, characterized in that: The adapter assembly (200) comprises an adapter support (210) having a first installation through hole, an adapter bearing seat (220) arranged in the first installation through hole, and a torque transmission shaft (230) arranged in the adapter bearing seat (220) and connected to a floating connection shaft (300) for connecting to the driving end of the tester.

3. The aircraft engine rotor testing system according to claim 2, characterized in that: The first oil return member comprises an oil return port (611) which is opened on the transfer support (210) and is connected to the internal lubricating oil passage of the transfer bearing seat (220), and an oil return pipe (612) which is respectively connected to the oil return port (611) and the external oil tank. The oil return port (611) is located below the transfer bearing seat (220).

4. The aircraft engine rotor testing system according to claim 2, characterized in that: The floating connecting shaft (300) comprises a hollow shaft body (310), a first spline (320) arranged on the circumferential outer wall of the first end of the shaft body (310) for spline cooperation with the torque transmission shaft (230), and a second spline (330) arranged on the circumferential outer wall of the second end of the shaft body (310) for spline cooperation with the aircraft engine rotor. The first spline (320) and the second spline (330) are arranged in a drum-shaped tooth structure. The shaft body (310) is slidably cooperated with the torque transmission shaft (230) and is used to slidably cooperate with the aircraft engine rotor so as to be able to move axially a preset distance.

5. The aircraft engine rotor testing system according to any one of claims 1 to 4, characterized in that: The front support assembly (400) comprises a front support seat (410) provided with a second installation through hole, a front transition section (420) arranged in the second installation through hole, and a front bearing seat (430) arranged in the front transition section (420) for supporting an aircraft engine rotor.

6. The aircraft engine rotor testing system according to claim 5, characterized in that: The second oil return member comprises an oil return hole (621) provided on the front transition section (420) for returning the lubricating oil in the front bearing seat (430), an oil blocking boss (622) provided on the front transition section (420) for axially blocking the lubricating oil, a vertical oil return chamber (623) provided in the front support (410) along the vertical direction and connected to the oil return hole (621), a horizontal oil return chamber (624) provided in the front support (410) along the horizontal direction and connected to the vertical oil return chamber (623), and an oil return pipe (625) respectively connected to the horizontal oil return chamber (624) and the external oil tank.

7. The aircraft engine rotor testing system according to claim 6, characterized in that: The second oil return member also includes an oil receiving box (626) arranged on the front support (410) for collecting lubricating oil at a rotor bearing position axially located outside the front support (410), and an inclined oil return chamber (627) opened in the front support (410) and connected to the oil receiving box (626) and the vertical oil return chamber (623) respectively.

8. The aircraft engine rotor testing system according to any one of claims 1 to 4, characterized in that: The rear support assembly (500) comprises a rear support (510) provided with a third installation through hole, a rear transition section (520) arranged in the third installation through hole, and a rear bearing seat (530) arranged in the rear transition section (520) for supporting an aircraft engine rotor.

9. The aircraft engine rotor testing system according to claim 8, characterized in that: The third oil return member comprises an oil return hole (631) opened on the rear transition section (520) for returning the lubricating oil in the rear bearing seat (530), an oil blocking boss (632) arranged on the rear transition section (520) for axially blocking the lubricating oil, a vertical oil return chamber (633) opened vertically in the rear support (510) and connected to the oil return hole (631), a horizontal oil return chamber (634) opened horizontally in the rear support (510) and connected to the vertical oil return chamber (633), and an oil return pipe (635) respectively connected to the horizontal oil return chamber (634) and the external oil tank.

10. An aero-engine rotor testing method, characterized in that: The aircraft engine rotor test system according to any one of claims 1 to 9 comprises the following steps: S1, test-assembling the aircraft engine rotor on a test platform to adjust the front support assembly (400) and the rear support assembly (500) to a set axial position, and removing the aircraft engine rotor after the test-assembly is completed; S2, using a laser alignment instrument and a centering tool to sequentially align the center holes of the front support assembly (400) and the rear support assembly (500) relative to the center hole of the test adapter assembly (200), and after the alignment is completed, the front support assembly (400) and the rear support assembly (500) are fixed on the test platform; S3, the tester is run idle to ensure that the test system operates normally; S4, installing the aircraft engine rotor on the front support assembly (400) and the rear support assembly (500), and connecting the aircraft engine rotor to the tester via a floating connection shaft (300); S5, respectively installing a first oil return component, a second oil return component and a third oil return component on the adapter component (200), the front support component (400) and the rear support component (500), and connecting the first oil return component, the second oil return component and the third oil return component to an external oil tank; S6, installing the measuring sensor and completing the connection and debugging of the measuring sensor; S7, setting the pressure in the explosion-proof cavity (100) according to test requirements, starting the tester to drive the aircraft engine rotor to rotate after the pressure is stabilized, collecting test data through measuring sensors, and thus obtaining the dynamic characteristics of the aircraft engine rotor.

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