CN116907807A - Aeroengine main shaft composite load loading test device - Google Patents

Aeroengine main shaft composite load loading test device Download PDF

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Publication number
CN116907807A
CN116907807A CN202310686007.2A CN202310686007A CN116907807A CN 116907807 A CN116907807 A CN 116907807A CN 202310686007 A CN202310686007 A CN 202310686007A CN 116907807 A CN116907807 A CN 116907807A
Authority
CN
China
Prior art keywords
platform
main shaft
bearing
stewart
composite load
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202310686007.2A
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Chinese (zh)
Inventor
苏瀚生
郭建英
王金红
王明明
魏家军
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AECC Sichuan Gas Turbine Research Institute
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AECC Sichuan Gas Turbine Research Institute
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Publication date
Application filed by AECC Sichuan Gas Turbine Research Institute filed Critical AECC Sichuan Gas Turbine Research Institute
Priority to CN202310686007.2A priority Critical patent/CN116907807A/en
Publication of CN116907807A publication Critical patent/CN116907807A/en
Pending legal-status Critical Current

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00—Testing of machine parts
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/16—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/02—Details
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/22—Investigating strength properties of solid materials by application of mechanical stress by applying steady torsional forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The invention relates to the technical field of aero-engine structural strength tests, and discloses an aero-engine main shaft composite load loading test device which comprises a fixed platform, wherein a first Stewart platform is arranged at the bottom of the fixed platform, a guide support column is vertically arranged on the fixed platform, a movable platform is arranged on the guide support column, and an adjusting and locking mechanism and a first bearing are further arranged on the fixed platform; the movable platform is provided with a counter-force seat, and a six-component force sensor is arranged between the main shaft and the first Stewart platform. According to the invention, six-degree-of-freedom motion in a certain range of a space rectangular coordinate system can be realized, and a composite load is applied to the main shaft through the first Stewart platform, so that the loading requirement of the space composite load is met; and the installation environment of the main shaft on the bearing is simulated in the loading process, and the fatigue life test of the main shaft of the aeroengine under the axial force, the lateral force, the vertical force or the torsional rigidity of the main shaft under the installation condition of the bearing can be simulated.

Description

Aeroengine main shaft composite load loading test device
Technical Field
The invention relates to the technical field of aero-engine structural strength tests, and discloses an aero-engine main shaft composite load loading test device.
Background
The main shaft structural strength test of the aeroengine is a test for testing the bearing load of a structural member without breaking capacity, and needs to be widely developed in the development process of aeroengine products. The main subjects of the main shaft structural strength test are a static strength test, a rigidity test, a pressure test, a fatigue life test and the like.
The Stewart parallel mechanism (namely the Stewart platform) has the advantages of six degrees of freedom, compact structure, high rigidity, high bearing capacity and the like, and is widely applied to the fields of mechanical assembly, motion simulation, forming devices and the like. The Stewart parallel mechanism consists of a servo loading actuator, a static coil and a moving coil. The types of the servo loading actuators include an electric servo actuator, a hydraulic servo actuator and a pneumatic servo actuator. For high frequency response applications, hydraulic servo actuators may be used; when high-speed requirements exist, a pneumatic servo actuator can be adopted; other applications may employ electric servo actuators. A Stewart parallel mechanism contains 6 servo-loaded actuators. The two ends of the servo loading actuator are connected with the static ring and the moving ring through universal hinges. The static ring is connected with the fixed platform or the movable platform through a flange.
The main shaft load and working condition of the aero-engine are very complex, and the space multidimensional composite load consisting of axial direction, lateral direction, bending moment, torque and the like is required to be loaded simultaneously in the testing process of the main shaft, so that the existing composite loading device has a complex structure, or only one or a few composite loads can be loaded.
Disclosure of Invention
The invention aims to provide an aeroengine main shaft composite load loading test device, wherein a first Stewart platform can realize six-degree-of-freedom motion within a certain range of a space rectangular coordinate system, composite load is applied to a main shaft through the first Stewart platform, and a six-component force sensor is arranged between the main shaft and the first Stewart platform for measurement, so that the loading requirement of the space composite load is met; and the installation environment of the main shaft on the bearing is simulated in the loading process, and the fatigue life test of the main shaft of the aeroengine under the axial force, the lateral force, the vertical force or the torsional rigidity of the main shaft under the installation condition of the bearing can be simulated.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
the composite load loading test device for the main shaft of the aeroengine comprises a fixed platform arranged on a support, wherein a first Stewart platform is arranged at the bottom of the fixed platform, a guide support column is vertically arranged on the fixed platform, and a movable platform is arranged on the guide support column; the fixed platform is also provided with an adjusting and locking mechanism, the adjusting and locking mechanism is in driving connection with the movable platform, and the adjusting and locking mechanism is used for adjusting the movable platform to axially move to a preset position along the guide support column and then carrying out locking and limiting; the fixed platform and the movable platform are provided with openings through which a main shaft of the aero-engine passes; the fixed platform is also provided with a first bearing which is used for fixing the bearing of the main shaft; the movable platform is provided with a counter-force seat, one end of the main shaft is fixedly connected with the first Stewart platform through a flange plate, the other end of the main shaft is fixed on the counter-force seat, and a six-component force sensor is arranged between the main shaft and the first Stewart platform.
Further, the first bearing is mounted on the fixed platform by a first cage ring.
Further, the reaction seat comprises a second Stewart platform, the second Stewart platform is arranged opposite to the first Stewart platform, and the second Stewart platform is fixedly connected with the main shaft.
Further, a six-component force sensor is also arranged between the main shaft and the second Stewart platform.
Further, a second bearing is installed on the movable platform, and the second bearing is used for axially fixing the main shaft.
Further, the second bearing is fixedly connected with the movable platform through a second squirrel cage ring.
Further, the adjusting and locking mechanism is any one or a combination of at least two of a screw rod, a telescopic cylinder and a hydraulic telescopic rod.
Compared with the prior art, the invention has the following beneficial effects: according to the invention, the first Stewart platform can realize six-degree-of-freedom motion within a certain range of a space rectangular coordinate system, a composite load is applied to the main shaft through the first Stewart platform, and a six-component force sensor is arranged between the main shaft and the first Stewart platform for measurement, so that the loading requirement of the space composite load is met; and the installation environment of the main shaft on the bearing is simulated in the loading process, and the fatigue life test of the main shaft of the aeroengine under the axial force, the lateral force, the vertical force or the torsional rigidity of the main shaft under the installation condition of the bearing can be simulated.
Drawings
FIG. 1 is a schematic structural diagram of a composite load loading test device for a main shaft of an aero-engine in an embodiment;
FIG. 2 is a perspective view of an aero-engine main shaft composite load test device in an embodiment;
wherein, 1, a support; 2. a fixed platform; 3. a guide support column; 4. a movable platform; 5. a main shaft; 6. a first squirrel cage ring; 7. a first Stewart platform; 8. a first bearing; 9. adjusting the locking mechanism; 10. a six-component force sensor; 11. a second bearing; 12. a second squirrel cage ring; 13. a second Stewart platform.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Examples
Referring to fig. 1 and 2, an aero-engine main shaft composite load loading test device comprises a fixed platform 2 arranged on a support 1, wherein a first Stewart platform 7 is arranged at the bottom of the fixed platform 2, a guide support column 3 is vertically arranged on the fixed platform 2, and a movable platform 4 is arranged on the guide support column 3; the fixed platform 2 is also provided with an adjusting and locking mechanism 9, the adjusting and locking mechanism 9 is in driving connection with the movable platform 4, and the adjusting and locking mechanism 9 is used for adjusting the movable platform 4 to axially move to a preset position along the guide support column 3 and then locking and limiting; the fixed platform 2 and the movable platform 4 are provided with openings through which the main shaft 5 of the aero-engine passes; the fixed platform 2 is also provided with a first bearing 8, and the first bearing 8 is used for fixing a bearing of the main shaft 5; the movable platform 4 is provided with a counter-force seat, one end of the main shaft 5 is fixedly connected with the first Stewart platform 7 through a flange plate, the other end of the main shaft 5 is fixed on the counter-force seat, and a six-component force sensor 10 is arranged between the main shaft 5 and the first Stewart platform 7.
In this embodiment, when a composite load loading test of the main shaft 5 is required, firstly, one end of the main shaft 5 of the aeroengine with a bearing on a shaft shoulder passes through an opening of the movable platform 4, so that one end of the main shaft 5 is positioned on the first Stewart platform 7, one end of the main shaft 5 is fixedly connected with the first Stewart platform 7 through a flange plate, and the other end of the main shaft 5 is fixed on a reaction seat (for example, the main shaft can be generally fixed through a flange or a bolt); the movable platform 4 is adjusted to axially move along the guide support column 3 through the adjusting and locking mechanism 9, so that the first bearing 8 on the movable platform 4 corresponds to the bearing on the shaft shoulder, and then the position of the movable platform 4 is locked and limited, and the bearing is fixed in the first bearing 8; a conforming load is then applied to the spindle 5 by controlling the first Stewart platform 7. In the embodiment, the first Stewart platform 7 can realize six-degree-of-freedom motion within a certain range of a space rectangular coordinate system, a composite load is applied to the main shaft 5 through the first Stewart platform 7, and a six-component force sensor 10 is arranged between the main shaft 5 and the first Stewart platform 7 for measurement, so that the loading requirement of the space composite load is met; and the installation environment of the main shaft 5 on the bearing is simulated in the loading process, and the fatigue life test of the main shaft 5 of the aeroengine under the axial force, the lateral force, the vertical force or the torsional rigidity of the main shaft 5 under the installation condition of the bearing can be simulated.
The first bearing 8 in this embodiment is installed on the fixed platform 2 through the first squirrel cage ring 6, and the rigidity of the first squirrel cage ring 6 can be adjusted according to the test design, so that the variable rigidity support test of the spindle 5 can be further realized.
The reaction seat in this embodiment includes a second Stewart platform 13, where the second Stewart platform 13 is disposed opposite to the first Stewart platform 7, and the second Stewart platform 13 is fixedly connected with the spindle 5. The second Stewart platform 13 can realize six-degree-of-freedom motion within a certain range of a space rectangular coordinate system; the composite load loading requirements of different loading conditions are realized by matching with the first Stewart platform 7. As during the application of force by the first Stewart platform 7, torque can be applied to the main shaft 5 by the second Stewart platform 13, so that the actual use condition of the aero-engine can be simulated.
The first Stewart platform 7 and the second Stewart platform 13 in this embodiment are each composed of a servo loading actuator, a stationary coil and a moving coil. The types of the servo loading actuators include an electric servo actuator, a hydraulic servo actuator and a pneumatic servo actuator. For high frequency response applications, hydraulic servo actuators may be used; when high-speed requirements exist, a pneumatic servo actuator can be adopted; other applications may employ electric servo actuators. The first Stewart platform 7 and the second Stewart platform 13 each comprise six servo loading actuators. The two ends of the servo loading actuator are connected with the static ring and the moving ring through universal hinges. The static ring is connected with the corresponding support 1 or the counter-force seat through a flange. In this embodiment, the servo loading actuators of the first Stewart platform 7 are divided into three groups and are uniformly distributed along the circumferential direction. Each group of two actuators are distributed in an isosceles triangle. The six-degree-of-freedom motion of the moving coil in a certain range of a space rectangular coordinate system can be realized, and the loading requirement of the space composite load is met.
A six-component force sensor 10 is also arranged between the main shaft 5 and the second Stewart platform 13 in the embodiment, and six-degree-of-freedom load closed-loop control can be realized through a decoupling algorithm by installing one six-component force sensor 10 on each of the first Stewart platform 7 and the second Stewart platform 13.
The movable platform 4 is provided with a second bearing 11, and the second bearing 11 is used for axially fixing the main shaft 5, so that the axial force, the lateral force, the vertical force or the torsional rigidity composite loading of the main shaft 5 under the double-bearing fixing effect can be realized. Likewise, the second bearing 11 in this embodiment is fixedly connected to the movable platform 4 through the second cage ring 12, and the rigidity of the second cage ring 12 can be adjusted according to the test design, so that the variable rigidity support test of the spindle 5 can be further realized.
In this embodiment, the first bearing 8 may be a roller bearing, which only bears radial load. The second bearing 11 can be a ball bearing, can bear axial load and radial load, and can simulate the real working condition of the main shaft of the aero-engine.
The adjusting and locking mechanism 9 in this embodiment is used to implement position adjustment of the movable platform 4, so that the movable platform 4 can be locked and limited after moving to a preset position along the axial direction of the guide support column 3, and the adjusting and locking mechanism 9 may be any one or a combination of at least two of a screw rod, a telescopic cylinder and a hydraulic telescopic rod.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.

Claims (7)

1. The aeroengine main shaft composite load loading test device is characterized by comprising a fixed platform (2) arranged on a support (1), wherein a first Stewart platform (7) is arranged at the bottom of the fixed platform (2), a guide support column (3) is vertically arranged on the fixed platform (2), and a movable platform (4) is arranged on the guide support column (3); the fixed platform (2) is also provided with an adjusting and locking mechanism (9), the adjusting and locking mechanism (9) is in driving connection with the movable platform (4), and the adjusting and locking mechanism (9) is used for adjusting the movable platform (4) to axially move to a preset position along the guide support column (3) and then locking and limiting; openings through which the main shaft (5) of the aeroengine can pass are formed in the fixed platform (2) and the movable platform (4); the fixed platform (2) is also provided with a first bearing (8), and the first bearing (8) is used for fixing the bearing of the main shaft (5); the movable platform (4) is provided with a counter-force seat, one end of the main shaft (5) is fixedly connected with the first Stewart platform (7) through a flange plate, the other end of the main shaft (5) is fixed on the counter-force seat, and a six-component force sensor (10) is arranged between the main shaft (5) and the first Stewart platform (7).
2. An aero-engine spindle composite load test device according to claim 1, wherein the first bearing (8) is mounted on the stationary platform (2) by means of a first squirrel cage ring (6).
3. The aeroengine main shaft composite load loading test device according to claim 1, wherein the reaction seat comprises a second Stewart platform (13), the second Stewart platform (13) is arranged opposite to the first Stewart platform (7), and the second Stewart platform (13) is fixedly connected with the main shaft (5).
4. An aero-engine spindle composite load test device according to claim 3, wherein a six-component force sensor (10) is also provided between the spindle (5) and the second Stewart platform (13).
5. An aero-engine spindle composite load test device according to claim 3, wherein the movable platform (4) is provided with a second bearing (11), and the second bearing (11) is used for axially fixing the spindle (5).
6. The aeroengine main shaft composite load loading test device according to claim 5, wherein the second bearing (11) is fixedly connected with the movable platform (4) through a second squirrel cage ring (12).
7. The aero-engine main shaft composite load loading test device according to claim 1, wherein the adjusting and locking mechanism (9) is any one or a combination of at least two of a screw rod, a telescopic cylinder and a hydraulic telescopic rod.
CN202310686007.2A 2023-06-09 2023-06-09 Aeroengine main shaft composite load loading test device Pending CN116907807A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310686007.2A CN116907807A (en) 2023-06-09 2023-06-09 Aeroengine main shaft composite load loading test device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310686007.2A CN116907807A (en) 2023-06-09 2023-06-09 Aeroengine main shaft composite load loading test device

Publications (1)

Publication Number Publication Date
CN116907807A true CN116907807A (en) 2023-10-20

Family

ID=88365795

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310686007.2A Pending CN116907807A (en) 2023-06-09 2023-06-09 Aeroengine main shaft composite load loading test device

Country Status (1)

Country Link
CN (1) CN116907807A (en)

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