Test device and test method for maximum unbalance of power turbine rotor

Abstract

The present invention discloses a power turbine rotor maximum unbalance test device and test method, comprising an assembled engine shaft system, a torque measuring 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 unbalance amount of the wheel disc position.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular to a maximum unbalance test device for a power turbine rotor. In addition, the present invention also relates to a test method comprising the maximum unbalance test device for a power turbine rotor. Background Art

[0002] The maximum imbalance test of civil turboshaft engines is a mandatory test subject for civil aircraft airworthiness certification. By determining the maximum imbalance allowed for prefabricated rotor components, the engine vibration level under maximum rotor imbalance excitation is obtained, providing a basis for the formulation of engine vibration limit values.

[0003] Since the unbalance amount imposed by the rotor components in the maximum unbalance test of the engine is much greater than the unbalance amount in the normal engine whole machine test, it may bring test risks such as increased vibration of the whole machine and scraping of the rotor and stator. At present, there are few related studies carried out in China, and the foundation is relatively weak. The selection of the prefabricated unbalance amount of the rotor components in the maximum unbalance test of the engine should not only consider the unbalance amount caused by the engine design, manufacturing, operation, etc., but also ensure that the engine parts will not transmit excessive vibration force to the aircraft under the specified vibration limit value, and have a certain high-cycle fatigue life. Therefore, the selection of the prefabricated unbalance amount of the rotor components is the key to this test. Due to the lack of test experience and data support, it is usually necessary to carry out multiple groups of whole machine tests under different rotor unbalance amounts to achieve the purpose of finding out the maximum unbalance of the engine. However, with this implementation plan, the engine has to be disassembled, assembled, and put on and off the test bench many times, with high test costs and long cycles. In addition, due to the increase in unbalance, it may bring test risks such as increased vibration of the whole machine and scraping of the rotor and stator. The loss of the engine will also increase if the maximum unbalance test of the whole machine is carried out many times.

[0004] In the prior art, for example, Patent No. 201811302839.5 discloses a device for simulating the unbalanced characteristics of a turboshaft engine with a dual-rotor structure and a design method thereof. Based on the design principle of similar rotor dynamics, the basic dimensions and relative positions are adjusted and matched so that the ratio of the critical speed of the first two-stage rotors of the designed simulation experimental device to the operating speed is equal to the ratio of the critical speed of the first two-stage rotors of the turboshaft engine rotor being simulated to the operating speed, and the first two-stage vibration modes of each rotor are similar. An integral model is built for simulation to obtain the characteristic curve variation law of the unbalanced characteristics of the engine rotor, but the dynamic characteristics in the maximum unbalance test, such as rotor deflection, have completely different characteristics under different masses and volumes. Therefore, the above technical solution can only obtain the characteristic curve variation law and is completely unable to obtain the maximum unbalance amount based on experiments on models of different proportions. Summary of the invention

[0005] The invention provides a power turbine rotor maximum unbalance test device and test method to solve the technical problems in the prior art of large number of disassembly and assembly times, long cycle and high loss cost of engine maximum unbalance test.

[0006] According to one aspect of the present invention, a power turbine rotor maximum unbalance test device is provided, comprising an assembled engine shaft system, a torque measuring unit, a turbine simulation disk and a rotating tester for performing an engine maximum unbalance test, wherein the turbine simulation disk comprises a first disk body and a second disk body connected to each other, the turbine simulation disk comprises a connecting portion for connecting to the engine shaft system, the first disk body and the second disk body are respectively integrally formed circular disk structures, the first disk body is used to replace a first-stage power turbine disk assembly structure consisting of a first-stage power turbine disk and a first-stage blade of the engine and is installed on the engine shaft system, the second disk body is used to replace a second-stage power turbine disk assembly structure consisting of a second-stage power turbine disk and a second-stage blade of the engine and is installed on the engine shaft system, the outer edges of the first disk body and the second disk body are both cylindrical surfaces, the mass characteristics and dynamic characteristics of the turbine simulation disk are consistent with those of a two-stage power turbine disk assembly of the engine; a counterweight installation structure is evenly distributed along the circumference on the turbine simulation disk, which is used to connect a first counterweight at one or more preset circumferential positions to thereby change the position imbalance of the wheel disc.

[0007] As a further improvement of the above technical solution, a floating connecting shaft is arranged between the engine shaft system and the power output shaft of the rotation tester, and both ends of the floating connecting shaft are spline-connected to the engine shaft system and the power output shaft respectively, and the spline is provided with a drum-shaped tooth structure.

[0008] As a further improvement of the above technical solution, the outer edge of the turbine simulation disk is a cylindrical surface, and the test device also includes a displacement detection unit for testing the deflection of the rotor.

[0009] As a further improvement of the above technical solution, the counterweight installation structure is a threaded hole, and the first counterweight piece is a counterweight screw.

[0010] As a further improvement of the above technical solution, one or more balancing bosses are arranged on the shaft system along the axial direction for connecting the second counterweight.

[0011] According to another aspect of the present invention, a method for testing the maximum unbalance of a power turbine rotor is provided, which is applied to any of the above-mentioned maximum unbalance testing devices for a power turbine rotor. The method comprises:

[0012] S1. Test preparation, centering of the rotating tester, installation and inspection of the engine shaft system and turbine simulation disk, connection and debugging of the torque measurement unit;

[0013] S2. Set the position where the unbalance is applied;

[0014] S3. Set the unbalance value and apply the unbalance value for testing.

[0015] As a further improvement of the above technical solution, step S2 includes: applying imbalance to the balancing surfaces of the turbine simulation disk and each balancing boss respectively, with the imbalance on each balancing surface starting at the angular position of 0°. If the maximum imbalance test at the current angular position of the current balancing surface is completed, the preset angle is incremented as the imbalance application position. If the maximum imbalance test at each angular position of the current balancing surface is completed, the maximum imbalance test at each angular position of other balancing surfaces is performed.

[0016] As a further improvement of the above technical solution, in step S2, the preset angle is 90°.

[0017] As a further improvement of the above technical solution, step S3 includes:

[0018] S31. Set the initial unbalance And precision , ;

[0019] S32. Settings Start the test. If it can run to the rated working speed, take , , repeat step S32, if it cannot run to the rated working speed, go to step S33;

[0020] S33. Settings for The rated speed can be set to the minimum value. for It cannot run to the maximum value of the rated working speed;

[0021] S34. Take , apply Start the test. If it can run to the rated working speed, go to step S341. If it cannot run to the rated working speed, go to step S342.

[0022] S341. If , output maximum unbalance , complete the test, if not, go to step S33;

[0023] S342. If , output maximum unbalance , complete the test, if not, go to step S33.

[0024] As a further improvement of the above technical solution, the test device includes a front support and a rear support, and step S1 includes:

[0025] S11. According to the test installation of the test rotor on the rotation tester, adjust the front support and the rear support to the appropriate axial position respectively;

[0026] S12. Use a laser alignment instrument and a special alignment tool to align the center hole of the front support relative to the power output shaft of the rotation tester and the center hole of the rear support relative to the center hole of the front support. The opening error of each adjacent center hole of the support is no more than Φ0.05mm / 100mm, and the parallel error in the vertical and horizontal directions is no more than 0.05mm;

[0027] S13. Fix the front support and the rear support after the alignment on the test platform;

[0028] S14. Complete the installation of the test rotor on the front support and the rear support;

[0029] S15. When the rotor is installed, check the lubrication and oil return of the bearings, and manually turn the rotor to check its flexibility;

[0030] S16. Use a dial indicator to measure the radial runout of the rotor at the relevant axial position in a static state, and check the machining, assembly and installation quality of the rotor;

[0031] S17. Install the measuring sensor, and complete the connection and debugging of the measuring sensor, strain gauge, thermocouple and data acquisition system.

[0032] The present invention has the following beneficial effects:

[0033] This test device obtains the maximum unbalance that each axial characteristic position of the rotor can withstand by conducting a maximum unbalance test of the power turbine rotor on a component rotation tester, providing a basis for the selection of prefabricated unbalance of the power turbine rotor components in the maximum unbalance airworthiness test of the whole machine, which can greatly reduce the number of whole machine tests, reduce test costs and risks, and accelerate the progress of model development; by using an integral turbine simulation disk to replace the original engine blade disk, the part below the bottom of the tenon groove of the original engine blade disk keeps the same configuration, and the turbine simulation disk is an axisymmetric structure that replaces the part above the tenon groove and the blades. It is consistent with the mass, center of mass, polar moment of inertia and diameter moment of inertia of the two-stage power turbine disk assembly. When the structural strength meets the requirements, based on the principles of cost saving and reduced processing, the turbine simulation disk structure is simplified and made of low-cost materials; in addition to replacing the two-stage power turbine disk assembly with a turbine simulation disk with consistent quality characteristics Except for the above, the rest of the components are exactly the same as the original engine power turbine rotor and have been assembled. Through rotor dynamics calculation and dynamic characteristics test, it can be known that the power turbine simulation rotor with turbine simulation disk is consistent with the dynamic characteristics of the original engine power turbine rotor. Therefore, the research results of the maximum imbalance test on the power turbine simulation rotor on the component rotation tester can be directly applied to the original engine power turbine rotor without the need for secondary processing of the data, thus ensuring the validity of the data and guiding the maximum imbalance test of the whole machine; by setting a counterweight installation structure on the turbine simulation disk, the wheel position imbalance adjustment can be completed by disassembling and assembling the counterweight during the test without disassembling the rotor, which is convenient to operate, improves test efficiency and reduces test costs; the manufacturing cost of the turbine simulation disk is significantly lower than that of the original engine blade disk, and the maximum imbalance test is a high-risk test, which greatly reduces the economic losses caused by test failure.

[0034] 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

[0035] The accompanying drawings constituting a part of the present invention 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 accompanying drawings:

[0036] Figure 1 It is a schematic diagram of the structure of a power turbine rotor of a turboshaft engine in the prior art;

[0037] Figure 2 It is a structural schematic diagram of a turbine simulation disk installed on a power turbine rotor of a turboshaft engine according to an embodiment of the present invention;

[0038] Figure 3 is a schematic structural diagram of a floating connecting shaft according to an embodiment of the present invention;

[0039] Figure 4 It is a simplified structural diagram of a test device according to an embodiment of the present invention;

[0040] Figure 5 is a flow chart of step S3 of a preferred embodiment of the present invention;

[0041] Figure 6 It is a structural schematic diagram of a two-stage power turbine disk assembly of an engine according to a preferred embodiment of the present invention;

[0042] Figure 7 It is a schematic structural diagram of a turbine simulation disk according to a preferred embodiment of the present invention.

[0043] Legend:

[0044] 1. Test platform; 2. Vacuum box; 3. Front support; 4. Rear support; 5. Front transfer section; 6. Rear transfer section; 7. Turbine simulation disk; 71. Counterweight installation structure; 8. Engine shaft system; 81. First bearing; 82. Second bearing; 83. First balancing boss; 84. Second balancing boss; 85. Third balancing boss; 86. Fourth balancing boss; 87. Third bearing; 88. Fourth bearing; 9. Floating connecting shaft; 91. Spline; A1~A4, acceleration sensor; D1~D4, vibration displacement sensor; S1~S4, strain gauge; T1~T2, thermocouple. DETAILED DESCRIPTION

[0045] 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.

[0046] Figure 1 It is a schematic diagram of the structure of a power turbine rotor of a turboshaft engine in the prior art; Figure 2 It is a structural schematic diagram of a turbine simulation disk installed on a power turbine rotor of a turboshaft engine according to an embodiment of the present invention; Figure 3 is a schematic structural diagram of a floating connecting shaft according to an embodiment of the present invention; Figure 4 It is a simplified structural diagram of a test device according to an embodiment of the present invention; Figure 5 is a flow chart of step S3 of a preferred embodiment of the present invention; Figure 6 It is a structural schematic diagram of a two-stage power turbine disk assembly of an engine according to a preferred embodiment of the present invention; Figure 7 It is a schematic structural diagram of a turbine simulation disk according to a preferred embodiment of the present invention.

[0047] like Figures 1 to 4As shown, the power turbine rotor maximum unbalance test device of this embodiment includes an assembled engine shaft system 8, a torque measuring unit, a turbine simulation disk 7 and a rotating tester for performing an engine maximum unbalance test, the turbine simulation disk 7 includes a first disk body and a second disk body connected to each other, the turbine simulation disk 7 includes a connecting portion for connecting to the engine shaft system 8, the first disk body and the second disk body are respectively integrally formed circular disk structures, the first disk body is used to replace the first-stage power turbine disk assembly structure composed of the first-stage power turbine disk and the first-stage blades of the engine and is installed on the engine shaft system 8, the second disk body is used to replace the second-stage power turbine disk assembly structure composed of the second-stage power turbine disk and the second-stage blades of the engine and is installed on the engine shaft system 8, the outer edges of the first disk body and the second disk body are both cylindrical surfaces, the mass characteristics and dynamic characteristics of the turbine simulation disk 7 are consistent with the two-stage power turbine disk assembly of the engine; a counterweight installation structure 71 is evenly distributed along the circumference on the turbine simulation disk 7, which is used to connect the first counterweight at one or more preset circumferential positions to change the imbalance of the wheel disc position.

[0048] In a specific embodiment, the test device is applied to a certain type of turboshaft engine rotor, referring to Figure 1 The rotor structure includes a first bearing 81, a second bearing 82, a first balancing boss 83, a second balancing boss 84, a third balancing boss 85, a fourth balancing boss 86, a third bearing 87, a fourth bearing 88 and a two-stage power turbine disk assembly; refer to Figure 2 , a schematic diagram of the rotor structure of a two-stage power turbine disk assembly replaced by a turbine simulation disk 7 after using the test device;

[0049] refer to Figure 6 and Figure 7 The first disc body and the second disc body of the turbine simulation disc 7 are both integral disc-type structures. The first disc body replaces the combined connection structure of the first-stage power turbine disc and the first-stage power turbine blades, and the second disc body replaces the second-stage power turbine disc assembly.

[0050] It can be understood that this test device obtains the maximum unbalance that each axial characteristic position of the rotor can withstand by conducting a maximum unbalance test of the power turbine rotor on a component rotation tester, which provides a basis for the selection of prefabricated unbalance of the power turbine rotor components in the maximum unbalance airworthiness test of the whole machine, can greatly reduce the number of whole machine tests, reduce test costs and risks, and accelerate the progress of model development; by using an integral turbine simulation disk 7 to replace the original engine blade disk, the part below the bottom of the tenon groove of the original engine blade disk remains unchanged, and the turbine simulation disk 7 is an axisymmetric structure that replaces the part above the tenon groove and the blades. It is consistent with the mass, center of mass, polar moment of inertia and diameter moment of inertia of the two-stage power turbine disk assembly. Under the condition that the structural strength meets the requirements, based on the principles of cost saving and reduced processing volume, the structure of the turbine simulation disk 7 is simplified and made of low-cost materials; except that the two-stage power turbine disk assembly is replaced by the turbine simulation disk 7 with consistent quality characteristics, the rest The components are exactly the same as the original engine power turbine rotor and are assembled. Through rotor dynamics calculation and dynamic characteristic test, it can be known that the power turbine simulation rotor with turbine simulation disk 7 is consistent with the dynamic characteristics (critical speed, vibration mode and steady-state unbalance response) of the original engine power turbine rotor. Therefore, the research results of the maximum unbalance test on the power turbine simulation rotor carried out on the component rotation tester can be directly applied to the original engine power turbine rotor without the need for secondary processing of the data, thereby ensuring the validity of the data and guiding the maximum unbalance test of the whole machine; by arranging a counterweight installation structure 71 on the turbine simulation disk 7, the wheel position unbalance adjustment can be completed by disassembling and assembling the counterweight parts during the test without disassembling the rotor, which is convenient to operate, improves the test efficiency and reduces the test cost; the manufacturing cost of the turbine simulation disk 7 is significantly lower than that of the original engine blade disk, and the maximum unbalance test is a high-risk test, which greatly reduces the economic losses caused by test failure.

[0051] Among them, the outer edge of the turbine simulation disk 7 is a cylindrical surface, and the test device also includes a displacement detection unit for testing the rotor deflection. It should be noted that the outer edge of the original engine blade disk assembly is the blade tip, and the rotor deflection at the axial position of the blade cannot be measured by the displacement sensor during the test. After replacing the blade disk with the turbine simulation disk 7, the outer edge surface is a regular cylindrical surface. During the test, the rotor deflection at the axial position of the blade can be measured by the displacement sensor, thereby providing guidance on whether rotor-stator scraping will occur during the maximum imbalance test of the whole machine.

[0052] In this embodiment, the counterweight installation structure 71 is a threaded hole, and the first counterweight is a counterweight screw. It should be noted that the original engine blade disc assembly has no counterweight application position, and the low-speed dynamic balancing adopts the method of removing material at the boss. When conducting the maximum unbalance test of the power turbine rotor, if the wheel disc position unbalance amount is to be changed, it is necessary to complete a series of operations such as rotor removal, rotor disassembly, adjusting the wheel disc position unbalance amount by removing material at the boss, and reinstalling the rotor. The process is complicated, and multiple disassembly and assembly of the rotor will also introduce other uncertain factors that affect the rotor vibration response. After using the turbine simulation disc 7 for replacement, the outer edge of the simulation disc is provided with a circle of threaded holes for applying counterweight screws. During the test, the wheel disc position unbalance amount can be directly changed on the rotating tester, which is convenient to operate.

[0053] In this embodiment, a floating connecting shaft 9 is arranged between the engine shaft system 8 and the power output shaft of the rotary tester. The two ends of the floating connecting shaft 9 are connected to the engine shaft system 8 and the power output shaft respectively by splines 91, and the splines 91 are provided with a drum-shaped tooth structure; wherein, the splines 91 at both ends of the floating connecting shaft 9 adopt a drum-shaped tooth structure to achieve angular compensation and isolate the influence of the vibration of the rotary tester on the vibration response of the test rotor; on the other hand, under the premise that the strength meets the requirements of the standard, the floating connecting shaft 9 should be designed to be lightweight as much as possible to reduce the mass, thereby reducing the influence of the floating connecting shaft 9 on the dynamic characteristics of the test rotor, and the natural mode of the floating connecting shaft 9 is not coupled with the vibration characteristics of the rotor.

[0054] In this embodiment, one or more balancing bosses are arranged axially on the shaft system for connecting the second counterweight, that is, arranged on each balancing plane of the rotor. The maximum unbalance that each balancing plane can withstand is found out by applying an unbalance on each balancing plane and measuring the vibration response of the rotor. If the unbalance applied to a balancing plane is about to cause the rotor to be unable to safely cross the critical speed, then the unbalance is the maximum unbalance that the balancing plane can withstand. The second counterweight is a counterweight wire. Taking copper wire as an example, the counterweight wire is tied to the balancing plane to be tested. The applied unbalance and the angular position can be clearly determined based on the diameter of the balancing plane position and parameters such as the length and diameter of the counterweight wire.

[0055] The maximum unbalance test method of the power turbine rotor of this embodiment is applied to the maximum unbalance test device of the power turbine rotor, and the test method includes:

[0056] S1. Experimental preparation;

[0057] S2. Set the position where the unbalance is applied;

[0058] S3. Set the unbalance value and apply the unbalance value for testing.

[0059] In this embodiment, the test method is performed based on a horizontal high-speed rotation tester, which includes a test platform 1, a vacuum box 2 disposed on the test platform 1, and a mounting support disposed on the test platform 1 and located in the vacuum box 2. The mounting support of the rotation tester includes a front support 3 and a rear support 4. The test rotor is connected to the mounting support through a high-rigidity front transfer section 5 and a rear transfer section 6, respectively. Specifically, step S1 includes:

[0060] S11. According to the test installation of the test rotor on the rotation tester, adjust the front support and the rear support to the appropriate axial position respectively;

[0061] S12. Use a laser alignment instrument and a special alignment tool to complete the alignment of the center hole of the front support relative to the power output shaft of the rotation tester and the center hole of the rear support relative to the center hole of the front support. The opening error of each adjacent center hole of the support is no more than Φ0.05mm / 100mm, and the parallel error in the vertical and horizontal directions is no more than 0.05mm;

[0062] S13. Fix the front support and the rear support after the alignment on the test platform;

[0063] S14. Complete the installation of the test rotor on the front support and the rear support. It should be noted that during the installation of the test rotor and the test process, each support remains fixed and does not move to ensure the validity of the test results;

[0064] S15. When the rotor is installed, check the lubrication and oil return of the bearings, and manually turn the rotor to check its flexibility;

[0065] S16. Use a dial indicator to measure the radial runout of the rotor at the relevant axial position in a static state, and check the machining, assembly and installation quality of the rotor;

[0066] S17. Install the measuring sensor, complete the connection and debugging of the measuring sensor, strain gauge, thermocouple and data acquisition system; it should be understood that the measuring sensor includes a vibration displacement sensor ( Figure 4 D1~D4) and vibration acceleration sensor ( Figure 4 A1~A4), photoelectric sensor measures rotor speed, displacement sensor measures rotor deflection, vibration acceleration sensor measures support vibration acceleration, strain gauge measures elastic support strain ( Figure 4 S1~S4), thermocouple ( Figure 4 (T1~T2) measure the bearing temperature; Figure 4 In the figure, “⊥” indicates the vertical direction, and “=” indicates the horizontal direction.

[0067] In this embodiment, step S2 includes: applying unbalance to the balancing surfaces of the turbine simulation disk and each balancing boss respectively, with the unbalance on each balancing surface starting at an angular position of 0°, and if the maximum unbalance test at the current angular position of the current balancing surface is completed, then the preset angle is incremented as the unbalance application position, and if the maximum unbalance test at each angular position of the current balancing surface is completed, then the maximum unbalance test at each angular position of other balancing surfaces is performed;

[0068] Among them, the preset angle is 90°, that is, the unbalance on each balancing surface is applied at 4 angular positions of 0°, 90°, 180° and 270° respectively. Based on the application of the turbine simulation disk, the maximum unbalance test at multiple angular positions on each balancing surface can be completed quickly, efficiently and at low cost; that is, the maximum unbalance test at each angular position on each balancing surface is completed in sequence, and the maximum unbalance that each balancing surface can withstand is found out by measuring the vibration response of the rotor. If the unbalance applied to a certain balancing surface is about to cause the rotor to be unable to safely cross the critical speed, then the unbalance is the maximum unbalance that this balancing surface can withstand. During the test, when the maximum unbalance test is performed on a certain balancing surface, the value of the unbalance applied each time the engine is started is implemented based on step S3;

[0069] Specifically, step S3 includes:

[0070] S31. Set the initial unbalance And precision , ;

[0071] S32. Settings Start the test. If it can run to the rated working speed, take , , repeat step S32, if it cannot run to the rated working speed, go to step S33;

[0072] S33. Settings for The rated speed can be set to the minimum value. for It cannot run to the maximum value of the rated working speed;

[0073] S34. Take , apply Start the test. If it can run to the rated working speed, go to step S341. If it cannot run to the rated working speed, go to step S342.

[0074] S341. If , output maximum unbalance , complete the test, if not, go to step S33;

[0075] S342. If , output maximum unbalance , complete the test, if not, go to step S33.

[0076] It should be understood that before the test, various preparations need to be checked and the vacuum box pressure and the test section oil supply pressure need to be adjusted; and, in order to reduce the influence of external factors on the rotor vibration response, the pressure in the test vacuum box and the test section oil supply pressure need to be kept the same at the beginning of each test;

[0077] This test method is based on the application of the test device and the above-mentioned test steps. By conducting a maximum unbalance test of the power turbine rotor on a component rotation tester, the maximum unbalance that each axial characteristic position of the rotor can withstand is obtained, which provides a basis for the selection of prefabricated unbalance amounts of power turbine rotor components in the maximum unbalance airworthiness test of the whole machine. This can greatly reduce the number of whole machine tests, reduce test costs and risks, accelerate the progress of model development, and has significant engineering application value.

[0078] 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. A method for testing the maximum unbalance of a power turbine rotor, characterized in that: A power turbine rotor maximum unbalance test device is used, comprising an assembled engine shaft system (8), a torque measuring unit, a turbine simulation disk (7), and a rotation tester for performing a maximum unbalance test on the engine, wherein the turbine simulation disk (7) comprises a first disk body and a second disk body connected to each other, the turbine simulation disk (7) comprises a connecting portion for connecting to the engine shaft system (8), the first disk body and the second disk body are respectively integrally formed circular disk structures, the first disk body is used to replace a first-stage power turbine disk assembly structure composed of a first-stage power turbine disk and a first-stage blade of the engine, and The second disk is installed on the engine shaft system (8); the second disk body is used to replace the secondary power turbine disk assembly structure composed of the secondary power turbine disk and the secondary blades of the engine and is installed on the engine shaft system (8); the outer edges of the first disk body and the second disk body are both cylindrical surfaces; the mass characteristics and dynamic characteristics of the turbine simulation disk (7) are consistent with the two-stage power turbine disk assembly of the engine; the turbine simulation disk (7) is evenly distributed along the circumference and is provided with a counterweight installation structure (71) for connecting the first counterweight at one or more preset circumferential positions to thereby change the wheel position imbalance; the test method comprises: S1. Test preparation, centering of the rotating tester, installation and inspection of the engine shaft system and turbine simulation disk, connection and debugging of the torque measurement unit; S2. Set the position where the unbalance is applied; S3. Setting the unbalance amount and applying the unbalance amount for testing, step S3 includes, S31. Set the initial unbalance And precision , ; S32. Settings Start the test. If it can run to the rated working speed, take , , repeat step S32, if it cannot run to the rated working speed, go to step S33; S33. Settings for The rated speed can be set to the minimum value. for It cannot run to the maximum value of the rated working speed; S34. Take , apply Start the test. If it can run to the rated working speed, go to step S341. If it cannot run to the rated working speed, go to step S342. S341. If , output maximum unbalance , complete the test, if not, go to step S33; S342. If , output maximum unbalance , complete the test, if not, go to step S33.

2. The maximum unbalance test method of a power turbine rotor according to claim 1, characterized in that: A floating connection shaft (9) is arranged between the engine shaft system (8) and the power output shaft of the rotation tester. The two ends of the floating connection shaft (9) are connected to the engine shaft system (8) and the power output shaft respectively by splines (91), and the splines (91) are provided with a drum-shaped tooth structure.

3. The maximum unbalance test method of a power turbine rotor according to claim 1, characterized in that: The outer edge of the turbine simulation disk (7) is a cylindrical surface, and the test device also includes a displacement detection unit for testing the deflection of the rotor.

4. The maximum unbalance test method of a power turbine rotor according to claim 1, characterized in that: The counterweight installation structure (71) is a threaded hole, and the first counterweight component is a counterweight screw.

5. The maximum unbalance test method of a power turbine rotor according to claim 1, characterized in that: One or more balancing bosses are axially distributed on the shaft system for connecting the second counterweight.

6. The method for testing the maximum unbalance of a power turbine rotor according to claim 1, characterized in that: Step S2 includes: applying unbalance to the balancing surfaces of the turbine simulation disk and each balancing boss respectively, with the unbalance on each balancing surface starting at the 0° angular position. If the maximum unbalance test at the current angular position of the current balancing surface is completed, the preset angle is incremented as the unbalance application position. If the maximum unbalance test at each angular position of the current balancing surface is completed, the maximum unbalance test at each angular position of other balancing surfaces is performed.

7. The method for testing the maximum unbalance of a power turbine rotor according to claim 6, characterized in that: In step S2, the preset angle is 90°.

8. The method for testing the maximum unbalance of a power turbine rotor according to claim 1, characterized in that: The test device includes a front support and a rear support, and step S1 includes: S11. According to the test installation of the test rotor on the rotation tester, the front support and the rear support are adjusted to the preset axial position; S12. Use a laser alignment instrument and a special alignment tool to align the center hole of the front support relative to the power output shaft of the rotation tester and the center hole of the rear support relative to the center hole of the front support. The opening error of each adjacent center hole of the support is no more than Φ0.05mm / 100mm, and the parallel error in the vertical and horizontal directions is no more than 0.05mm; S13. Fix the front support and the rear support after the alignment on the test platform; S14. Complete the installation of the test rotor on the front support and the rear support; S15. When the rotor is installed, check the lubrication and oil return of the bearings, and manually turn the rotor to check its flexibility; S16. Use a dial indicator to measure the radial runout of the rotor at the relevant axial position in a static state, and check the machining, assembly and installation quality of the rotor; S17. Install the measuring sensor, and complete the connection and debugging of the measuring sensor, strain gauge, thermocouple and data acquisition system.

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