Turbine engine complete machine bearing clearance uncertainty test device and test method

Abstract

The invention discloses a turbine engine complete machine bearing clearance uncertainty test device and test method, and belongs to the technical field of aero-engine complete machine dynamics research. The turbine engine complete machine bearing clearance uncertainty test device comprises a rotor casing system, a tester base, a base support and a bearing structure. The rotor casing system comprises a rotor system and a casing system, the rotor system comprises a fan disc, a gas compressor rotor and a turbine disc which are concentrically connected in sequence, the casing system comprises a fan stator casing, a gas compressor casing, a combustion chamber casing and a spray pipe casing which are matched and connected in sequence, and the supporting structure comprises a first support, a second support and a third support. The first support is arranged on the rear side of the fan disc, the second support is arranged on the rear side of the compressor rotor, and the third support is arranged on the front side of the turbine disc. According to the method, a reliable technical approach is provided for carrying out uncertainty analysis and research on the dynamic characteristics of the whole machine.

Description

Technical Field

[0001] The invention relates to a turbine engine complete machine support clearance uncertainty test device and test method, belonging to the technical field of aero-engine complete machine dynamics research. Background Art

[0002] Aircraft engines are complex systems. In the study of rotor dynamics of aircraft engines, uncertainty factors have an important impact on the accuracy and reliability of analysis results. In-depth research on these uncertainty factors can improve the performance and safety of engines under various working conditions. Carrying out simulation analysis of the uncertainty of the whole machine system dynamics and conducting whole machine uncertainty verification tests to verify the accuracy of the whole machine uncertainty analysis and whole machine dynamics uncertainty simulation analysis can provide strong technical support for the study of the uncertainty of the whole machine dynamics.

[0003] In the prior art, there are relatively few studies on the influence of support gap uncertainty on the dynamic characteristics of the whole machine system, and there is no systematic research method. There is even less experimental method for conducting dynamic tests on the uncertainty of support gap of the whole machine. At the same time, conducting uncertainty tests requires certain test samples, that is, it is necessary to design multiple sets of testers with different parameters, which greatly increases the research cost. Summary of the invention

[0004] The purpose of the present invention is to overcome the technical defects of the prior art, design a whole machine uncertainty dynamic test based on the simulation prediction results of the nonlinear uncertainty model of the whole machine, carry out dynamic tests on the whole machine dynamic tester including the support gap uncertainty, and verify the validity and accuracy of the simulation prediction results.

[0005] The present invention specifically adopts the following technical scheme: a turbine engine whole machine support clearance uncertainty test device, including a rotor casing system, a tester base, a base bracket, and a support structure, wherein the rotor casing system is installed on the tester base through the base bracket; the rotor casing system includes a rotor system and a casing system, wherein the rotor system includes a fan disk, a compressor rotor, and a turbine disk that are concentrically connected in sequence, and the casing system includes a fan stator casing, a compressor casing, a combustion chamber casing, and a nozzle casing that are matched and connected in sequence, and the support structure includes a first support, a second support, and a third support, wherein the first support is arranged at the rear side of the fan disk, the second support is arranged at the rear side of the compressor rotor, and the third support is arranged at the front side of the turbine disk.

[0006] As a preferred embodiment, the first bearing adopts a gap bearing structure, and a gap fit is adopted between the bearing sleeve and the bearing, and 5 bearing sleeves with different matching sizes can be installed respectively on the first bearing bearing seat on the fan stator casing where the first bearing is located, and a bearing locking nut is provided on the rear side of the first bearing, and a bearing gap is provided between the first bearing and the bearing sleeve.

[0007] As a preferred embodiment, the plurality of bearing bushings of different matching sizes include bearing bushings of different inner diameter sizes, which are used to describe the uncertainty of the system support clearance.

[0008] The present invention also provides a test method for a turbine engine whole support clearance uncertainty test device, comprising the following steps:

[0009] Step SS1: Building an engine whole machine support clearance uncertainty dynamic test device, including assembling a rotor casing system and a support structure and installing them on a tester base, and connecting the tester rotor system and a drive system;

[0010] Step SS2: Arrange sensors, arrange displacement sensors through the sensor holes reserved on the casing, and arrange displacement sensors in the horizontal and vertical directions of the compressor rotor and the horizontal and vertical directions of the nozzle casing respectively, so as to collect the displacement response data of the system; arrange acceleration sensors on the base bracket on the front support of the tester, so as to test the overall vibration of the system and correct the displacement response data of the rotor system; arrange photoelectric probes at a position about 20 cm next to the fan disk, so as to collect the speed data of the tester;

[0011] Step SS3: Control the motor of the driving system to drive the whole machine to perform a dynamic simulation test;

[0012] Step SS4: Monitor the rotor vibration to ensure that no destructive vibration occurs and the first critical speed is passed smoothly;

[0013] Step SS5: According to the test data of the rotor displacement sensor, the Bode diagram of the rotor system is obtained, and the first-order critical speed and the maximum vibration response are extracted;

[0014] Step SS6: After exceeding the first critical speed, turn off the motor drive and naturally decelerate to a standstill;

[0015] Step SS7: Replace the bearing bushing with different matching sizes of the first support of the tester, repeat the above test steps, and obtain the dynamic response results of the whole machine tester under different support gap size conditions;

[0016] Step SS8: Based on the established nonlinear uncertainty model of the whole machine, the distribution range of the calculation results is determined by simulation calculation and compared with the test results.

[0017] Beneficial effects achieved by the present invention: The present invention is directed to a dynamic test device for the uncertainty of the support clearance of a small turbine engine as a whole and a test method for verifying the uncertainty of the whole machine. The test device is mainly aimed at the support structure behind the fan disk of the whole machine, and 5 sets of bearing bushings with different matching sizes are designed to study the influence of the uncertainty of the support clearance on the dynamic characteristics of the whole machine. The disclosed test method for verifying the uncertainty of the whole machine dynamics builds a whole machine tester for bearing bushings with different matching sizes, conducts dynamic tests respectively, and compares the dynamic response results obtained from the test with the prediction results of the dynamic simulation of the whole machine system, so as to verify the accuracy of the prediction results of the dynamic simulation of the whole machine system. The tester and test method designed by the present invention provide a reliable technical approach for conducting uncertainty analysis research on the dynamic characteristics of the whole machine, and at the same time provide strong technical support for further promoting in-depth research on the dynamic characteristics of the whole machine, as well as the dynamic design and dynamic response control of the whole machine of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a structural schematic diagram of a turbine engine whole machine support clearance uncertainty test device of the present invention.

[0019] Figure 2 yes Figure 1 Schematic cross-sectional view of .

[0020] Figure 3 It is a structural schematic diagram of the gap support structure of the present invention.

[0021] Figure 4 It is a structural schematic diagram of the gap support structure of the present invention rotated at an angle.

[0022] Figure 5 It is a comparison diagram of the whole machine uncertainty test results and the whole machine uncertainty simulation prediction boundary of the present invention.

[0023] The meanings of the marks in the figure are: 1-rotor casing system, 2-test device base, 3-base bracket, 4-fan disk, 5-first support, 6-fan stator casing, 7-compressor rotor, 8-compressor casing, 9-rotor sleeve gear connection structure, 10-second support, 11-combustion chamber casing, 12-third support, 13-turbine disk, 14-nozzle casing, 15-bearing bushing, 16-bearing clearance, 17-bearing locking nut, 18-first support bearing seat. DETAILED DESCRIPTION

[0024] The present invention will be further described below in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present invention, and cannot be used to limit the protection scope of the present invention.

[0025] Example 1: Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the present invention proposes a turbine engine whole machine support clearance uncertainty test device, including a rotor casing system 1, a tester base 2, a base bracket 3, and a support structure. The rotor casing system 1 is installed on the tester base 2 through the base bracket 3; the rotor casing system 1 includes a rotor system and a casing system. The rotor system includes a fan disk 4, a compressor rotor 7, and a turbine disk 13 that are concentrically connected in sequence. The casing system includes a fan stator casing 6, a compressor casing 8, a combustion chamber casing 11, and a nozzle casing 14 that are matched and connected in sequence. The support structure includes a first support 5, a second support 10, and a third support 12. The first support 5 is arranged on the rear side of the fan disk 4, the second support 10 is arranged on the rear side of the compressor rotor 7, and the third support 12 is arranged on the front side of the turbine disk 13.

[0026] As a preferred embodiment, the first support 5 adopts a gap support structure, and a gap fit is adopted between the bearing sleeve and the bearing. The first support bearing seat 18 on the fan stator casing 6 where the first support 5 is located can be respectively installed with five bearing sleeves 15 of different matching sizes. A bearing locking nut 17 is provided on the rear side of the first support 5, and a support gap 16 is provided between the first support 5 and the bearing sleeve 15.

[0027] As a preferred embodiment, a plurality of bearing bushings 15 with different matching sizes include bearing bushings with different inner diameter sizes, which are used to describe the uncertainty of the system support clearance.

[0028] Embodiment 2: Design 5 groups of support structures with different gap sizes to carry out the whole machine support gap uncertainty dynamic test.

[0029] Design 5 bearing bushings with different matching sizes, the bearing bushings and the bearings are clearance matched, and ensure that the first support 5 of the whole machine tester is a clearance support. The 5 bearing matching clearances are: -10μm (interference), -6μm (interference), -2μm (interference), clearance 8μm, and clearance 11μm. The present invention also proposes a test method for a turbine engine whole machine support clearance uncertainty test device, comprising the following steps:

[0030] Step SS1: constructing an engine whole machine support clearance uncertainty dynamic test device, including assembling a rotor casing system 1 and a support structure and installing them on a tester base 2, and connecting the tester rotor system and a drive system;

[0031] Step SS2: Arrange sensors. Arrange displacement sensors through the sensor holes reserved on the casing. Arrange displacement sensors in the horizontal and vertical directions of the compressor rotor 7 and the horizontal and vertical directions of the nozzle casing 14, respectively, to collect the displacement response data of the system; arrange acceleration sensors on the base bracket 3 on the front support of the tester, to test the overall vibration of the system and to correct the displacement response data of the rotor system; arrange photoelectric probes at a position of about 20 cm next to the fan disk 4, to collect the speed data of the tester;

[0032] Step SS3: Control the motor of the driving system to drive the whole machine to perform a dynamic simulation test;

[0033] Step SS4: Monitor the rotor vibration to ensure that no destructive vibration occurs and the first critical speed is passed smoothly;

[0034] Step SS5: According to the test data of the rotor displacement sensor, the Bode diagram of the rotor system is obtained, and the first-order critical speed and the maximum vibration response are extracted;

[0035] Step SS6: After exceeding the first critical speed, turn off the motor drive and naturally decelerate to a standstill;

[0036] Step SS7: Replace the bearing bushing 15 of different matching sizes of the first support 5 of the tester, repeat the above test steps, and obtain the dynamic response results of the whole machine tester under conditions of different support gap sizes;

[0037] Step SS8: Based on the established nonlinear uncertainty model of the whole machine, the distribution range of the calculation results is determined by simulation calculation and compared with the test results.

[0038] The dynamic characteristics response results of the whole system with support gap uncertainty obtained through the test are shown in Table 1. The test results are compared with the simulation calculation results of the whole system response with support gap uncertainty. Figure 5 As shown, from Figure 5 It can be seen that the test results are all within the prediction boundary of the response results of the simulation calculation, and the effectiveness of the simulation prediction results is verified through experiments.

[0039] Table 1 Critical speed values ​​and vibration amplitudes measured for each bearing seat assembly

[0040]

[0041] The test apparatus and test method designed in the present invention provide a reliable technical approach for conducting uncertainty analysis research on the dynamic characteristics of the whole machine, and at the same time provide strong technical support for further promoting in-depth research on the dynamic characteristics of the whole machine, as well as the dynamic design and dynamic response control of the whole machine of the aircraft engine.

[0042] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment in combination with software and hardware. Moreover, the present application may adopt the form of a computer program product implemented in one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that include computer-usable program code.

[0043] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 These computer program instructions can also be stored in a computer-readable memory that can guide a computer or other programmable data processing device to work in a specific way, so that the instructions stored in the computer-readable memory produce a product including an instruction device, which implements the functions specified in the process. Figure 1 A process or multiple processes and / or boxes Figure 1 These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to produce a computer-implemented process, so that the instructions executed on the computer or other programmable device provide for implementing the process in the process. Figure 1 A process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0044] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. Turbine engine whole machine support clearance uncertainty test device, characterized in that: The invention comprises a rotor casing system (1), a test device base (2), a base bracket (3), and a supporting structure. The rotor casing system (1) is installed on the test device base (2) through the base bracket (3); the rotor casing system (1) comprises a rotor system and a casing system. The rotor system comprises a fan disk (4), a compressor rotor (7), and a turbine disk (13) which are concentrically connected in sequence. The casing system comprises a fan stator casing (6), a compressor casing (8), a combustion chamber casing (11), and a nozzle casing (14) which are matched and connected in sequence. The supporting structure comprises a first support (5), a second support (10), and a third support (12). The first support (5) is arranged on the rear side of the fan disk (4), the second support (10) is arranged on the rear side of the compressor rotor (7), and the third support (12) is arranged on the front side of the turbine disk (13).

2. The turbine engine whole machine support clearance uncertainty test device according to claim 1, characterized in that: The first support (5) adopts a clearance support structure, and a clearance fit is adopted between the bearing sleeve and the bearing. The first support bearing seat (18) on the fan stator casing (6) where the first support (5) is located can be respectively installed with five bearing sleeves (15) of different matching sizes. The rear side of the first support (5) is matched with a bearing locking nut (17), and a support gap (16) is provided between the first support (5) and the bearing sleeve (15).

3. The turbine engine whole machine support clearance uncertainty test device according to claim 1, characterized in that: The plurality of bearing bushings (15) of different matching sizes include bearing bushings of different inner diameter sizes, and are used to describe the uncertainty of the system support clearance.

4. The test method based on the turbine engine whole machine support clearance uncertainty test device according to claim 1 is characterized in that: The steps include: Step SS1: constructing an engine whole machine support clearance uncertainty dynamic test device, including assembling a rotor casing system (1) and a support structure and installing them on a tester base (2), and connecting the tester rotor system and a drive system; Step SS2: arranging sensors, arranging displacement sensors through sensor holes reserved on the casing, and arranging displacement sensors in the horizontal and vertical directions of the compressor rotor (7) and the horizontal and vertical directions of the nozzle casing (14) respectively, for collecting displacement response data of the system; An acceleration sensor is arranged on the base bracket (3) on the front support of the tester to test the vibration of the entire system and to correct the displacement response data of the rotor system; a photoelectric probe is arranged at a position 20 cm next to the fan disk (4) to collect the rotation speed data of the tester; Step SS3: Control the motor of the driving system to drive the whole machine to perform a dynamic simulation test; Step SS4: Monitor the rotor vibration to ensure that no destructive vibration occurs and the first critical speed is passed smoothly; Step SS5: According to the test data of the rotor displacement sensor, the Bode diagram of the rotor system is obtained, and the first-order critical speed and the maximum vibration response are extracted; Step SS6: After exceeding the first critical speed, turn off the motor drive and naturally decelerate to a standstill; Step SS7: Replace the bearing bushing (15) of the first support (5) of the tester with a different matching size, repeat the above test steps, and obtain the dynamic response results of the whole machine tester under conditions of different support gap sizes; Step SS8: Based on the established nonlinear uncertainty model of the whole machine, the distribution range of the calculation results is determined by simulation calculation and compared with the test results.

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