Aero-engine double-rotor complete machine simulation tester considering basic impact

Abstract

The invention discloses an aero-engine double-rotor complete machine simulation tester considering foundation impact, and belongs to the technical field of aero-engines, the aero-engine double-rotor complete machine simulation tester comprises a drop table, a foundation platform is arranged on the drop table, the foundation platform comprises a first platform and a second platform, a supporting assembly is installed on the foundation platform, and a force bearing structure is installed on the supporting assembly. The force bearing structure comprises a rear force bearing case, one side of the rear force bearing case is connected with a turbine case, one side of the turbine case is connected with a combustion chamber case, one side of the combustion chamber case is connected with an intermediate case, and one side of the intermediate case is connected with an air inlet force bearing case. According to the aero-engine double-rotor complete machine simulation tester considering the foundation impact, segmented design is adopted, the aero-engine double-rotor complete machine simulation tester has the thin-wall characteristic, circumferential bolt connection is adopted, a connecting face structure serves as a reinforcing rib, vibration loads can be effectively transmitted, and research and analysis of a transmission path are facilitated; and a mouse cage elastic support is adopted to reduce the supporting rigidity at the mass concentration turntable so as to adjust the critical rotating speed to reach a safe range.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engines, in particular to an aero-engine dual-rotor complete machine simulation tester taking foundation impact into consideration. Background Art

[0002] Modern aircraft engines generally adopt a dual-rotor structure, and the characteristics of light weight and heavy load are more obvious. In terms of load characteristics, their working environment is becoming increasingly harsh. In addition to conventional vibration loads, they may also be subjected to various types of impact excitation loads, such as radial and axial impacts caused by hard landing and catapult takeoff. This poses new challenges to the dynamic design of aircraft engines, and it is urgent to reveal the coupled dynamic characteristics of the whole machine under such impact loads and the transmission mechanism of vibration energy in the rotor-support-casing system from an experimental perspective.

[0003] In terms of similar tester technology, there are either rotor testers or rotor-casing testers under basic fixation, or simple rotor testers that only consider individual maneuvering flight actions (without considering dual rotors or casings). These testers cannot simulate the typical axial and radial impact loads of the engine, and cannot consider the transmission law of the impact load in the dual rotor-support-casing system. In order to be able to carry out more realistic aircraft engine whole-machine dynamics tests under typical impact loads, a basic impact dual rotor-support-casing system tester that can reflect its actual structural mechanics characteristics is designed and manufactured based on the structural characteristics and load characteristics of typical dual rotor aircraft engines. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft engine dual-rotor whole machine simulation tester taking foundation impact into consideration, which adopts a segmented design, has a thin-wall feature, is connected by circumferential bolts, and the connection surface structure acts as a reinforcing rib, which can effectively transmit vibration loads and is conducive to studying and analyzing the transmission path. The squirrel cage elastic support is used to reduce the support stiffness at the mass concentrated turntable to adjust the critical speed to a safe range.

[0005] To achieve the above-mentioned objectives, the present invention provides an aircraft engine dual-rotor whole machine simulation tester that takes foundation impact into consideration, including a drop shock platform, a basic platform is provided on the drop shock platform, the basic platform includes a first platform and a second platform, a support assembly is installed on the basic platform, a load-bearing structure is installed on the support assembly, the load-bearing structure includes a rear load-bearing casing, one side of the rear load-bearing casing is connected to a turbine casing, one side of the turbine casing is connected to a combustion chamber casing, one side of the combustion chamber casing is connected to an intermediate casing, and one side of the intermediate casing is connected to an intake load-bearing casing.

[0006] Preferably, a first spoke is fixedly connected inside the rear bearing casing, the first spoke is fixedly connected to the first bearing seat, and a squirrel cage elastic support is installed inside the first bearing seat.

[0007] Preferably, a second spoke is fixedly connected inside the intermediate casing, the second spoke is fixedly connected to the second bearing seat, and a first bearing cover and a second bearing cover are respectively installed on both sides of the second bearing seat.

[0008] Preferably, a third spoke is fixedly connected inside the air intake bearing casing, and the third spoke is fixedly connected to the third bearing seat.

[0009] Preferably, a rotor structure is installed inside the load-bearing structure, and the rotor structure includes an outer rotor shaft, a high-pressure turntable is sleeved on the outer side of the outer rotor shaft, a third separate fixing ring is sleeved on the outer rotor shaft on one side of the high-pressure turntable, the outer rotor shaft is connected to the inner rotor shaft through a fourth bearing, a fan turntable and a turbine turntable are sleeved on both sides of the inner rotor shaft, a first separate fixing ring is sleeved on the inner rotor shaft on one side of the fan turntable, and a second separate fixing ring is sleeved on the inner rotor shaft on one side of the turbine turntable.

[0010] Preferably, a first bearing is installed between the inner rotor shaft and the third bearing seat, a second bearing is installed between the inner rotor shaft and the third bearing seat, one side of the second bearing is in contact with the first bearing cover, a third bearing is installed between the outer rotor shaft and the second bearing cover, and a fifth bearing is installed between the inner rotor shaft and the squirrel cage elastic support.

[0011] Preferably, the first brushless DC motor is connected to the inner rotor shaft, the first brushless DC motor and the inner rotor shaft are coaxially arranged, the bottom of the first brushless DC motor is connected to the motor support, the motor support is connected to the base platform, the second brushless DC motor is connected to the first pulley, the first pulley is connected to the second pulley through a belt, and the second pulley is fixedly connected to the outer rotor shaft.

[0012] Preferably, the rear load-bearing casing is connected to two auxiliary mounting sections, the rear load-bearing casing is connected to the turbine casing by bolts, the turbine casing is connected to the combustion chamber casing by bolts, the combustion chamber casing is connected to the intermediate casing by bolts, the intermediate casing is connected to the intake load-bearing casing by bolts, the intermediate casing is connected to two main mounting sections, the two auxiliary mounting sections are connected to the auxiliary mounting section base through thrust rods, the two main mounting sections are connected to the main mounting section base, and the auxiliary mounting section base and the main mounting section base are both connected to the base platform.

[0013] Preferably, a circular through hole is provided at the bottom of the thrust rod, and a fixing nut is provided at the top, and the fixing nut is connected to the thrust rod through threads.

[0014] Preferably, sensor brackets are provided at the rear bearing casing, the turbine casing and the air intake bearing casing.

[0015] Therefore, the present invention adopts the above-mentioned aircraft engine dual-rotor whole machine simulation tester considering the foundation impact, which has the following beneficial effects:

[0016] 1) It adopts segmented design with thin-wall features and is fastened with circumferential bolts. The connection surface structure acts as the reinforcement ribs of each casing, which can effectively transmit vibration loads and facilitate the study and analysis of the transmission path;

[0017] 2) The connection structure between each turntable and the inner rotor shaft and the outer rotor shaft can be installed and disassembled without damaging the structural strength, meeting the experimental design requirements under different turntable assemblies;

[0018] 3) The squirrel cage elastic support used reduces the support stiffness at the mass concentrated turntable to adjust the critical speed to a safe range;

[0019] 4) Vibration tests of the dual rotors under impact in two falling postures were realized. In the coupled dynamics problem, the coupled dynamics problem of the dual rotors-support-casing under basic excitation was studied. By combining the data of the deployed sensors and theoretical analysis, the transmission mechanism of the excitation load and unbalanced load in the typical rotor-support-casing structure can be accurately studied.

[0020] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a three-dimensional structural schematic diagram of an aero-engine dual-rotor whole machine simulation tester under axial impact considering foundation impact of the present invention;

[0022] Figure 2 It is a three-dimensional structural schematic diagram of a vertical impact of an aircraft engine dual-rotor whole machine simulation tester considering foundation impact of the present invention;

[0023] Figure 3 It is a three-dimensional structural schematic diagram of a dual-rotor complete machine simulation tester for an aero-engine considering foundation impact, a basic platform and a driving system of the present invention;

[0024] Figure 4 It is a three-dimensional cross-sectional view of the load-bearing structure of an aircraft engine dual-rotor complete machine simulation tester considering foundation impact of the present invention;

[0025] Figure 5 It is a three-dimensional structural schematic diagram of a rotor system of an aero-engine dual-rotor complete machine simulation tester considering foundation impact of the present invention;

[0026] Figure 6 It is a cross-sectional view of the rotor structure of an aircraft engine dual-rotor complete machine simulation tester considering foundation impact of the present invention;

[0027] Figure 7 It is a cross-sectional view of the bearing and positioning of an aero-engine dual-rotor complete machine simulation tester taking into account foundation impact of the present invention;

[0028] Figure 8 The present invention Figure 7 A partial enlarged view of the middle A;

[0029] Fig. 9 It is a partial enlarged view of the bearing and its position B of an aero-engine dual-rotor complete machine simulation tester considering foundation impact of the present invention;

[0030] Fig.10 It is a partial enlarged view of the bearing and the positioning C of an aero-engine dual-rotor complete machine simulation tester considering the foundation impact of the present invention;

[0031] Fig.11 It is a partial enlarged view of the bearing and its position D of an aero-engine dual-rotor complete machine simulation tester considering foundation impact of the present invention;

[0032] Fig.12 It is a partial enlarged view of the bearing and its position E of an aero-engine dual-rotor complete machine simulation tester considering foundation impact of the present invention;

[0033] Fig.13 It is a three-dimensional structural schematic diagram of the first synchronous wheel of an aircraft engine dual-rotor complete machine simulation tester considering foundation impact according to the present invention;

[0034] Fig.14 It is a three-dimensional structural schematic diagram of the second synchronous wheel of an aircraft engine dual-rotor whole machine simulation tester considering foundation impact according to the present invention;

[0035] Fig.15 It is a structural schematic diagram of a thrust rod of an aero-engine dual-rotor whole machine simulation tester taking into account foundation impact of the present invention;

[0036] Fig.16 It is a three-dimensional structural schematic diagram of the second platform of an aero-engine dual-rotor complete machine simulation tester taking into account foundation impact of the present invention;

[0037] Fig.17 It is a three-dimensional structural schematic diagram of the first platform of an aero-engine dual-rotor complete machine simulation tester taking foundation impact into consideration according to the present invention.

[0038] Reference numerals

[0039] 1. Drop vibration platform; 2. First DC brushless motor; 3. Second DC brushless motor; 4. Elastic coupling; 5. Auxiliary installation section base; 6. Sensor bracket; 7. Motor support; 8. Rear bearing casing; 801. First spoke; 802. First bearing seat; 803. Squirrel cage elastic support; 804. Auxiliary installation section; 9. Turbine casing; 10. Combustion chamber casing; 11. Intermediate casing; 1101. Second spoke; 1102. First bearing cover; 1103. Second bearing seat; 1104. Second bearing cover; 1105. Main installation section; 12. Intake bearing casing; 1201. Third spoke; 1202. Third bearing seat; 13. Main installation section base; 14. First platform; 15 , inner rotor shaft; 1501, first separate fixing ring; 1502, fan turntable; 1503, second separate fixing ring; 1504, turbine turntable; 16, outer rotor shaft; 1601, third separate fixing ring; 1602, high pressure turntable; 1701, first positioning ring; 1702, first bearing; 1703, second positioning ring; 1704, second bearing; 1705, third bearing; 1706, third positioning ring; 1707, fourth bearing; 1708, fourth positioning ring; 1709, fifth bearing; 1710, fifth positioning ring; 1801, first pulley; 1802, second pulley; 1901, fixing nut; 1902, thrust rod; 20, second platform. DETAILED DESCRIPTION

[0040] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0041] Unless otherwise defined, the technical terms or scientific terms used in the present invention should be understood by people with ordinary skills in the field to which the present invention belongs. The words "first", "second" and similar words used in the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0042] Embodiment 1

[0043] like Figures 1 to 17As shown, the present invention provides an aircraft engine dual-rotor whole machine simulation tester taking into account foundation impact, comprising a drop vibration platform 1, a basic platform is provided on the drop vibration platform 1, a support assembly is installed on the basic platform, a load-bearing structure is installed on the support assembly, the support assembly is supported by the load-bearing structure, the basic platform comprises a first platform 14 and a second platform 20, the first platform 14 is horizontally arranged, and the second platform 20 is vertically arranged, which can meet the exploration of the vibration characteristics of the whole machine under axial and vertical impacts and the transmission law of impact energy in the dual rotor-support-casing system.

[0044] The load-bearing structure includes a rear load-bearing casing 8, one side of the rear load-bearing casing 8 is connected to a turbine casing 9, one side of the turbine casing 9 is connected to a combustion chamber casing 10, one side of the combustion chamber casing 10 is connected to an intermediate casing 11, and one side of the intermediate casing 11 is connected to an intake load-bearing casing 12. The rear load-bearing casing 8 is connected to the turbine casing 9 by bolts, the turbine casing 9 is connected to the combustion chamber casing 10 by bolts, the combustion chamber casing 10 is connected to the intermediate casing 11 by bolts, and the intermediate casing 11 is connected to the intake load-bearing casing 12 by bolts. The bolt connection surface structure acts as a reinforcement rib of the casing, which can effectively transmit vibration loads and is conducive to studying and analyzing the transmission path.

[0045] The rear bearing casing 8, turbine casing 9 and air intake bearing casing 12 are all provided with sensor brackets 6, on which are mounted acceleration sensors for testing casing surface acceleration, speed sensors for testing shaft speed, and displacement sensors for measuring horizontal and vertical vibration displacements of the turntable. The rear bearing casing 8, turbine casing 9 and air intake bearing casing 12 are provided with square grooves for convenient monitoring by acceleration sensors, speed sensors and displacement sensors. The rear bearing casing 8 is connected to two auxiliary mounting sections 804, the intermediate casing 11 is connected to two main mounting sections 1105, the two auxiliary mounting sections 804 are connected to the auxiliary mounting section base 5 through thrust rods 1902, the two main mounting sections 1105 are connected to the main mounting section base 13, and the auxiliary mounting section base 5 and the main mounting section base 13 are both connected to the base platform.

[0046] The bottom of the thrust rod 1902 is provided with a circular through hole, and the top is provided with a fixing nut 1901, and the fixing nut 1901 is connected to the thrust rod 1902 by threads. The auxiliary installation section 804 is connected to the auxiliary installation section base 5 through the thrust rod 1902. The upper end of the thrust rod 1902 is threaded, which cooperates with the fixing nut 1901 to fix the thrust rod 1902 so that it cannot move up and down; the circular opening at the lower end has the same inner diameter as the "ear" of the auxiliary installation section 804, and is connected by a pin.

[0047] A first spoke 801 is fixedly connected inside the rear bearing casing 8, and the first spoke 801 is fixedly connected to the first bearing seat 802, and a squirrel cage elastic support 803 is installed inside the first bearing seat 802. A second spoke 1101 is fixedly connected inside the intermediate casing 11, and the second spoke 1101 is fixedly connected to the second bearing seat 1103. The first bearing cover 1102 and the second bearing cover 1104 are respectively installed on both sides of the second bearing seat 1103, which mainly serve as an extension of the second bearing seat 1103, and the inner ring shoulder can provide axial positioning of the bearing. A third spoke 1201 is fixedly connected inside the intake bearing casing 12, and the third spoke 1201 is fixedly connected to the third bearing seat 1202.

[0048] The load-bearing structure is internally installed with a rotor structure, which includes an outer rotor shaft 16, a high-pressure rotary disc 1602 is sleeved on the outer side of the outer rotor shaft 16, a third separate fixing ring 1601 is sleeved on the outer rotor shaft 16 on one side of the high-pressure rotary disc 1602, and the outer rotor shaft 16 is connected to the inner rotor shaft 15 through a fourth bearing 1707, the fourth bearing 1707 serves as an intermediate bearing, and a shoulder is provided on the inner ring of the outer rotor to complete axial positioning in cooperation with a fourth positioning ring 1708. A fan rotary disc 1502 and a turbine rotary disc 1504 are sleeved on both sides of the inner rotor shaft 15, respectively, a first separate fixing ring 1501 is sleeved on the inner rotor shaft 15 on one side of the fan rotary disc 1502, and a second separate fixing ring 1503 is sleeved on the inner rotor shaft 15 on one side of the turbine rotary disc 1504. The turbine turntable 1504 , the fan turntable 1502 and the high-pressure turntable 1602 are provided with clamping structures. The fan turntable 1502 and the turbine turntable 1504 can be tightened by the first detachable fixing ring 1501 and the second detachable fixing ring 1503 , and the high-pressure turntable 1602 can be tightened and fixed by the third detachable fixing ring 1601 .

[0049] A first bearing 1702 is installed between the inner rotor shaft 15 and the third bearing seat 1202. The first bearing 1702 cooperates with the shoulder on the third bearing seat 1202 and the first positioning ring 1701 to complete axial positioning. A second bearing 1704 is installed between the inner rotor shaft 15 and the third bearing seat 1202. One side of the second bearing 1704 contacts the first bearing cover 1102. The second bearing 1704 is located inside the first bearing cover 1102. The first bearing cover 1102 is connected to the second bearing seat 1103. The shoulder structure on the first bearing cover 1102 and the second positioning ring 1703 complete axial positioning. A third bearing 1705 is installed between the outer rotor shaft 16 and the second bearing cover 1104. The second bearing cover 1104 is connected to the second bearing seat 1103. The shoulder structure on the second bearing cover 1104 and the third positioning ring 1706 complete axial positioning. A fifth bearing 1709 is installed between the inner rotor shaft 15 and the squirrel cage elastic support 803 . The squirrel cage elastic support 803 is connected to the first bearing seat 802 , and axial positioning is completed by the shoulder of the inner ring of the squirrel cage elastic support 803 and the fifth positioning ring 1710 .

[0050] The first DC brushless motor 2 is connected to the inner rotor shaft 15 through a plum blossom-shaped elastic coupling 4. The first DC brushless motor 2 is coaxially arranged with the inner rotor shaft 15. The bottom of the first DC brushless motor 2 is connected to the motor support 7, and the motor support 7 is connected to the base platform, so as to facilitate the fixed support of the motor. The second DC brushless motor 3 is connected to the first pulley 1801, and the first pulley 1801 is connected to the second pulley 1802 through a belt, and the second pulley 1802 is tightly connected to the outer rotor shaft 16. An opening is provided on the combustion chamber casing 10, so as to facilitate the first pulley 1801 to drive the second pulley 1802 to rotate through the belt. The diameter ratio of the first pulley 1801 to the second pulley 1802 is 2:1. The inner ring of the first pulley 1801 is provided with a keyway for connecting with the shaft of the second DC brushless motor 3, and the second pulley 1802 is tightly connected to the outer rotor shaft 16.

[0051] When using the dual-rotor whole-machine simulation tester for an aero-engine that takes into account the foundation impact provided by the present invention, first ensure that the positions and connection relationships of all components are correct, then test the critical speed on flat ground, determine the subcritical speed and supercritical speed of the test, determine the impact speed by adjusting the height of the drop shock platform 1, and determine the direction of the impact load by adjusting the placement direction of the tester. The first DC brushless motor 2 and the second DC brushless motor 3 control the speeds of the inner rotor shaft 15 and the outer rotor shaft 16 respectively (the test speed is adjusted according to the critical speed). Under different working conditions, preliminary test data are obtained by an acceleration sensor for testing the surface acceleration of the casing, a speed sensor for testing the rotation speed of the shaft, and a displacement sensor for measuring the horizontal and vertical vibration displacements of the turntable, and the test data are processed. Finally, the structural dynamic characteristics, load transfer mechanism, and rotor dynamic response characteristics of the dual-rotor-support-casing system are studied and analyzed.

[0052] Therefore, the present invention adopts the above-mentioned dual-rotor whole-machine simulation tester for an aircraft engine that takes foundation impact into consideration, adopts a segmented design, has thin-wall characteristics, uses circumferential bolt connections, and the connection surface structure acts as a reinforcing rib, which can effectively transmit vibration loads and is conducive to studying and analyzing the transmission path. Squirrel cage elastic supports are used to reduce the support stiffness at the mass concentrated turntable to adjust the critical speed to a safe range.

[0053] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. An aircraft engine dual-rotor complete machine simulation tester considering foundation impact, characterized in that: It includes a drop vibration platform, which is provided with a basic platform, which includes a first platform and a second platform, a supporting assembly is installed on the basic platform, a load-bearing structure is installed on the supporting assembly, and the load-bearing structure includes a rear load-bearing casing, one side of the rear load-bearing casing is connected to a turbine casing, one side of the turbine casing is connected to a combustion chamber casing, one side of the combustion chamber casing is connected to an intermediate casing, and one side of the intermediate casing is connected to an intake load-bearing casing.

2. The dual-rotor whole-machine simulation tester for an aircraft engine taking into account foundation impact according to claim 1, characterized in that: A first spoke is fixedly connected inside the rear bearing casing, the first spoke is fixedly connected to the first bearing seat, and a squirrel cage elastic support is installed inside the first bearing seat.

3. The dual-rotor whole-machine simulation tester for an aircraft engine taking into account foundation impact according to claim 1, characterized in that: A second spoke is fixedly connected inside the intermediate casing, the second spoke is fixedly connected to the second bearing seat, and a first bearing cover and a second bearing cover are respectively installed on both sides of the second bearing seat.

4. The dual-rotor whole-machine simulation tester for an aero-engine considering foundation impact according to claim 1, characterized in that: A third spoke is fixedly connected inside the air intake bearing casing, and the third spoke is fixedly connected to the third bearing seat.

5. The aircraft engine dual-rotor whole machine simulation tester considering foundation impact according to claim 1, characterized in that: A rotor structure is installed inside the load-bearing structure, and the rotor structure includes an outer rotor shaft, a high-pressure turntable is sleeved on the outer side of the outer rotor shaft, a third separate fixing ring is sleeved on the outer rotor shaft on one side of the high-pressure turntable, the outer rotor shaft is connected to the inner rotor shaft through a fourth bearing, a fan turntable and a turbine turntable are sleeved on both sides of the inner rotor shaft, a first separate fixing ring is sleeved on the inner rotor shaft on one side of the fan turntable, and a second separate fixing ring is sleeved on the inner rotor shaft on one side of the turbine turntable.

6. The aircraft engine dual-rotor whole machine simulation tester considering foundation impact according to claim 5, characterized in that: A first bearing is installed between the inner rotor shaft and the third bearing seat, a second bearing is installed between the inner rotor shaft and the third bearing seat, one side of the second bearing is in contact with the first bearing cover, a third bearing is installed between the outer rotor shaft and the second bearing cover, and a fifth bearing is installed between the inner rotor shaft and the squirrel cage elastic support.

7. The aircraft engine dual-rotor whole machine simulation tester considering foundation impact according to claim 5, characterized in that: The first brushless DC motor is connected to the inner rotor shaft, the first brushless DC motor and the inner rotor shaft are coaxially arranged, the bottom of the first brushless DC motor is connected to the motor support, the motor support is connected to the base platform, the second brushless DC motor is connected to the first pulley, the first pulley is connected to the second pulley through a belt, and the second pulley is fixedly connected to the outer rotor shaft.

8. The aircraft engine dual-rotor whole machine simulation tester considering foundation impact according to claim 1, characterized in that: The rear load-bearing casing is connected to two auxiliary mounting sections, the rear load-bearing casing is connected to the turbine casing by bolts, the turbine casing is connected to the combustion chamber casing by bolts, the combustion chamber casing is connected to the intermediate casing by bolts, the intermediate casing is connected to the intake load-bearing casing by bolts, the intermediate casing is connected to two main mounting sections, the two auxiliary mounting sections are connected to the auxiliary mounting section base through thrust rods, the two main mounting sections are connected to the main mounting section base, and the auxiliary mounting section base and the main mounting section base are both connected to the base platform.

9. The aircraft engine dual-rotor whole machine simulation tester considering foundation impact according to claim 8, characterized in that: A circular through hole is arranged at the bottom of the thrust rod, and a fixing nut is arranged at the top. The fixing nut is connected to the thrust rod through threads.

10. The aircraft engine dual-rotor whole machine simulation tester considering foundation impact according to claim 1, characterized in that: Sensor brackets are provided at the rear bearing casing, turbine casing and air intake bearing casing.

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