CN112378671B - Sliding pair friction wear test bed and method for stator blade adjusting mechanism of gas compressor - Google Patents
Sliding pair friction wear test bed and method for stator blade adjusting mechanism of gas compressor Download PDFInfo
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- CN112378671B CN112378671B CN202011271048.8A CN202011271048A CN112378671B CN 112378671 B CN112378671 B CN 112378671B CN 202011271048 A CN202011271048 A CN 202011271048A CN 112378671 B CN112378671 B CN 112378671B
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- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The invention belongs to the technical field of aero-engines, and discloses a test bed and a method for friction and wear of a moving pair of a stator blade adjusting mechanism of an air compressor. The test bed mainly comprises a power driving system, a stator blade adjusting system, a sensing test system and a base. The invention considers the working condition of the stator blade adjusting mechanism of the aero-engine compressor and the motion relation of each component, and can reflect the friction and wear rule of the moving pair of the stator blade adjusting mechanism of the engine; the invention can also research the influence of the parameters such as the material of the kinematic pair, the gap, the length of the connecting rod, the quality of the blade and the like on the friction coefficient and the abrasion loss of the kinematic pair of the stator blade adjusting mechanism of the gas compressor; meanwhile, bosses and grooves are respectively processed on the measured kinematic pair and the connecting rod connected with the measured kinematic pair, so that the measured kinematic pair is convenient to disassemble and is convenient for repeatedly replacing the kinematic pair when the research parameters are changed; the invention can simultaneously measure the friction coefficient and the abrasion loss of the moving pair of the stator blade adjusting mechanism of the air compressor, thereby reducing the experiment cost and shortening the experiment period.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and relates to a test bed and a test method for researching friction and abrasion of a kinematic pair of a stator blade adjusting mechanism of an air compressor.
Background
The compressor stator blade adjusting mechanism is an important composition structure of a modern aeroengine, and mainly has the main function of changing the thermodynamic cycle characteristics of the engine by changing the shape, the size and the like of an air flow channel according to the requirements of different working states, so that the engine has good performance and working stability in various working states. The compressor stator blade adjusting mechanism plays an important role in improving the performance and the economy of an engine, the maneuvering flight capability of an aircraft and the like, and is widely used in modern aero-engines.
The stator blade adjusting mechanism of the aero-engine compressor is a complex mechanical system consisting of a plurality of stages of series-parallel mechanisms, and the number of kinematic pairs is far larger than that of other types of kinematic mechanisms. In practical engineering application, in the process of developing and using a plurality of types of aeroengines at home and abroad, the problems of overlarge hysteresis force, clamping stagnation, low adjusting precision and the like of a kinematic pair of a stator blade adjusting mechanism occur, and the safety of the engine is seriously influenced.
The existing friction wear test bed does not consider the working condition of the stator blade adjusting mechanism of the aero-engine compressor and the motion relation of each component, so that the real condition of the kinematic pair of the stator blade adjusting mechanism of the aero-engine compressor cannot be reflected. In order to achieve the above purposes, a friction and wear test bed considering the structural characteristics of an adjusting mechanism of a stator blade of an aircraft engine compressor needs to be designed, and the influence rule of the size, assembly and material parameters on the friction and wear of a kinematic pair needs to be researched so as to avoid the problems of clamping stagnation, low adjusting precision and the like.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a friction and wear test bed for a kinematic pair of a compressor stator blade adjusting mechanism and a test method thereof. In terms of structure, the invention is a simplified model of an aero-engine compressor stator blade adjustment mechanism; the tested kinematic pair and the connecting rod are designed into a matching mode of a boss and a groove, so that the characteristic of convenience in disassembly is realized while the relative rotational freedom degree is restrained; the test bed can simultaneously measure the friction coefficient and the abrasion loss of the kinematic pair; on the basis, the influence of parameters such as the material, the gap, the length of a connecting rod, the quality of the blade and the like of the kinematic pair on the friction coefficient and the abrasion loss of the kinematic pair of the stator blade adjusting mechanism of the air compressor can be analyzed.
In order to achieve the purpose, the invention adopts the following technical scheme:
a friction wear test bed for a kinematic pair of a stator blade adjusting mechanism of an air compressor comprises a power driving system, a stator blade adjusting system, a sensing test system and a base; the power driving system comprises a linear motor, a driver support, a first hydraulic rod and a second hydraulic rod; the stator blade adjusting system comprises a first connecting rod, a second connecting rod, a third connecting rod, a bushing A, a bushing B, a pin shaft A, a pin shaft B, a rocker arm, a stator blade, a blade shaft and a connecting rod slide rail; the test sensing system comprises a force sensor, an encoder and a balance; the base is used for fixing the driver support, the blade shaft and the connecting rod slide rail; wherein the blade shaft can rotate on the base;
the linear motor is fixed on the driver support and used for providing driving force for the stator blade adjusting system; the linear motor sequentially transmits the driving force to the second hydraulic rod, the first connecting rod and the second connecting rod; the second connecting rod is L-shaped; the break point end of the second connecting rod slides on the connecting rod slide rail and drives the third connecting rod and the rocker arm to swing; the rocker arm realizes the rotation of the stator blade through the blade shaft;
the bushing A is fixed on the rocker arm and provided with a groove for matching with a boss processed on the rocker arm and restricting the relative rotation of the bushing A and the rocker arm; the pin shaft A is fixed on the third connecting rod, and a boss is processed on the pin shaft and is used for matching with a groove processed on the third connecting rod; the design of matching the boss and the groove ensures the constraint of the rotational freedom degree and is convenient to disassemble;
the other group of measured kinematic pairs is arranged between the first connecting rod and the second connecting rod, wherein the bush B is fixed on the first connecting rod and is provided with a groove for matching with a boss processed on the first connecting rod and restricting the relative rotation of the first connecting rod and the second connecting rod; the pin shaft B is fixed on the second connecting rod, and a boss is processed on the pin shaft and is used for matching with a groove processed on the second connecting rod; the design of matching the boss and the groove ensures the constraint of the rotational freedom degree and is convenient to disassemble;
the two force sensors are arranged, one force sensor is arranged between the first hydraulic rod and the second hydraulic rod, and the other force sensor is arranged between the second connecting rod and the third connecting rod and is used for measuring the tension and the pressure between the rods; the two encoders are respectively used for measuring the swing angle of the first connecting rod and the swing angle of the rocker arm.
Furthermore, the stator blade adjusting system simulates a first stage in a stator blade adjusting mechanism of an aircraft engine compressor, wherein the stress and the motion mode of the measured kinematic pair simulate the kinematic pair of the stator blade adjusting mechanism of the aircraft engine compressor.
The invention has the beneficial effects that:
compared with the existing friction and wear test bed, the invention takes the working condition of the stator blade adjusting mechanism of the aero-engine compressor and the motion relation of each component into consideration, and can reflect the friction and wear rule of the moving pair of the stator blade adjusting mechanism of the engine; the invention can also research the influence of the parameters such as the material of the kinematic pair, the gap, the length of the connecting rod, the quality of the blade and the like on the friction coefficient and the abrasion loss of the kinematic pair of the stator blade adjusting mechanism of the gas compressor; meanwhile, bosses and grooves are respectively processed on the measured kinematic pair and the connecting rod connected with the measured kinematic pair, so that the measured kinematic pair is convenient to disassemble and is convenient for repeatedly replacing the kinematic pair when the research parameters are changed; the invention can simultaneously measure the friction coefficient and the abrasion loss of the moving pair of the stator blade adjusting mechanism of the air compressor, thereby reducing the experiment cost and shortening the experiment period.
Drawings
FIG. 1 is a system configuration of a laboratory bench according to the present invention;
FIG. 2 is a schematic structural diagram of a friction and wear test bed of a kinematic pair of a stator blade adjusting mechanism of an air compressor;
FIG. 3 is a schematic structural diagram of a measured kinematic pair A according to the present invention;
FIG. 4 is a schematic structural diagram of a measured kinematic pair B according to the present invention;
FIG. 5 is a schematic view of the bushing configuration of the present invention;
FIG. 6 is a schematic view of a first connecting rod structure according to the present invention;
FIG. 7 is a schematic view of the pin structure of the present invention;
FIG. 8 is a schematic view of a second connecting rod according to the present invention;
FIG. 9 is a schematic view of a third connecting rod according to the present invention;
FIG. 10 is a schematic structural view of a rocker arm of the present invention;
FIG. 11 is a schematic view of the friction coefficient testing method of the present invention;
in the figure: a second connecting rod 1; 2, a first connecting rod; a first hydraulic rod; a second hydraulic rod 4; 5, a linear motor; 6 driver support; 7 a force sensor; a connecting rod No. 8; 9 a base; 10 rocker arms; 11 stator blades; 12 a blade shaft; 13, a bush A; 14, a bushing B; 15 connecting rod slide rails; 16, a pin shaft A; and 17, a pin B.
Detailed Description
The following further describes a specific embodiment of the present invention with reference to the drawings and technical solutions.
As shown in fig. 1 and 2, a friction wear test bed for a kinematic pair of a stator blade adjusting mechanism of an air compressor mainly comprises a power driving system, a stator blade adjusting system, a sensing test system and a base 10; the power driving system comprises a linear motor 5, a driver support 6, a first hydraulic rod 3 and a second hydraulic rod 4; the stator blade adjusting system comprises a first connecting rod 2, a second connecting rod 1, a third connecting rod 8, a bushing A13, a bushing B14, a pin shaft A16, a pin shaft B17, a rocker arm 10, a stator blade 11, a blade shaft 12 and a connecting rod slide rail 15; the test sensing system comprises a force sensor 7, an encoder and a balance; the base 9 is used for fixing the driver support 6, the blade shaft 12 and the connecting rod slide rail 15; wherein the blade shaft 12 can rotate on the base 9;
the linear motor 6 is fixed on the driver support 7 and used for providing driving force for the stator blade adjusting system; the linear motor sequentially transmits the driving force to the second hydraulic rod 4, the first hydraulic rod 3, the first connecting rod 2 and the second connecting rod 1; the second connecting rod 1 slides on the connecting rod slide rail 15 and drives the third connecting rod 8 and the rocker arm 10 to swing; the rocker arm 10 realizes rotation of the stator vane 11 through the vane shaft 12;
as shown in fig. 3, the bushing a13, the bushing B14, the pin a16, and the pin B17 form a measured kinematic pair, and there are two sets, one set is installed between the third connecting rod 8 and the rocker arm 10, wherein the bushing a13 is fixed on the rocker arm 10 and is provided with a groove for matching with a boss processed on the rocker arm 10 to restrict the relative rotation of the two, as shown in fig. 3; a pin shaft A16 is fixed on the third connecting rod 8, a boss is processed on the pin shaft A16 and is used for matching with a groove processed on the third connecting rod 8, as shown in figures 5, 7, 9 and 10; the design of matching the boss and the groove ensures the constraint of the rotational freedom degree and is convenient to disassemble;
the other set of measured kinematic pairs is arranged between the first connecting rod 2 and the second connecting rod 1, wherein the bush B14 is fixed on the first connecting rod 2 and is provided with a groove for matching with the groove processed on the first connecting rod 2 and restricting the relative rotation of the first connecting rod and the second connecting rod, as shown in FIG. 4; similarly, the pin B17 is fixed on the second connecting rod 1, and the pin B17 is provided with a boss for matching with a groove processed on the second connecting rod 1, as shown in fig. 5, 6, 7 and 8; the design of matching the boss and the groove ensures the constraint of the rotational freedom degree and is convenient to disassemble;
two force sensors 7 are arranged, and one force sensor is arranged between the first hydraulic rod 3 and the second hydraulic rod 4; the other is arranged between the second connecting rod 1 and the third connecting rod 8; the device is used for measuring the tension and pressure between the rods; the two encoders are respectively used for measuring the swing angles of the first connecting rod 2 and the rocker arm 10;
the method for testing the static and dynamic characteristics of the system after the early-stage preparation is made is used for testing the friction coefficient and the abrasion loss of the moving pair of the stator blade adjusting mechanism of the aero-engine compressor, and comprises the following steps:
1) friction coefficient test for kinematic pair of stator blade adjusting mechanism
One of the two force sensors is arranged between the first hydraulic rod and the second hydraulic rod; the other is arranged between the second connecting rod and the third connecting rod; holes are formed above the first connecting rod and below the rocker arm, the encoder is connected with the pin shaft through the holes, and the encoder can measure the swing angle, the angular velocity and the angular acceleration of the two measured kinematic pairs; the schematic diagram of the friction coefficient calculation of the measured kinematic pair is shown in FIG. 11 and is calculated by the following formula
Wherein J is the moment of inertia of the connecting rod to the pin shaft, and can be obtained through three-dimensional software, l is the length of the connecting rod, F is the driving force measured by the force sensor, m is the mass, theta is the swing angle of the kinematic pair obtained by the encoder, and FShaft、FDiameter of a pipeAs a restraining counter-force of the axis of rotation, MμIs the friction torque.
Further changing the materials and the gaps of the bushing and the pin shaft, changing the length of the connecting rod and the mass of the stator blade, arranging a force sensor at the same position and performing a test in the same way with the encoder, and researching the change rule of the friction coefficient under different parameters;
2) testing of abrasion loss of kinematic pair of stator blade adjusting mechanism
Cleaning the tested kinematic pair, weighing and recording the mass of the kinematic pair before testing by using a balance; and starting the test bed, unloading and cleaning the kinematic pair after the test bed normally works for a period of time, and weighing the mass of the kinematic pair again. The mass difference of the two times of weighing is the abrasion loss.
On the basis, the materials and the gaps of the bushing and the pin shaft are further changed, the length of the connecting rod and the quality of the stator blade are changed, the test is carried out in the same mode, and the change rule of the abrasion loss under different parameters is researched.
Based on the test method, the invention mainly aims to research and study the influence of parameters such as the material, the clearance, the length of the connecting rod, the quality of the blades and the like of the kinematic pair on the friction coefficient and the abrasion loss of the kinematic pair of the stator blade adjusting mechanism of the air compressor, simultaneously, the tested kinematic pair and the connecting rod connected with the tested kinematic pair are respectively provided with a lug boss and a groove, the disassembly is convenient, the study of the kinematic pair which is repeatedly replaced when the parameters are changed is convenient, and the following explains various working conditions which can be realized by the invention:
the main test condition changes are as follows: the materials of a bush and a pin shaft are changed, the material of the prior aeroengine stator blade adjusting mechanism kinematic pair mainly comprises polyimide, polytetrafluoroethylene, titanium alloy, copper alloy, aluminum alloy and the like, and the combination of a matched form of a lug boss and a groove between the measured kinematic pair and a connecting rod is shown in figures 3, 4, 5, 6, 7, 8, 9 and 10, so that the kinematic pair is convenient to repeatedly disassemble, and the influence of different materials on the friction coefficient and the abrasion loss of the compressor stator blade adjusting mechanism kinematic pair can be researched; the radial sizes of different bushings and pin shafts are processed, the fit clearance is changed, and the influence of different fit clearances on the friction coefficient and the abrasion loss of a kinematic pair of the stator blade adjusting mechanism can be researched; the connecting rods with different lengths and the blades with different masses are processed, so that the influence of the structural size of the connecting rods and the load of the output end on the friction coefficient and the abrasion loss of a moving pair of the stator blade adjusting mechanism can be researched; further mastering the influence rule of various parameters on the friction and abrasion of the moving pair of the stator blade adjusting mechanism so as to avoid the problems of clamping stagnation, low adjusting precision and the like.
Claims (3)
1. A friction wear test bed for a kinematic pair of a stator blade adjusting mechanism of an air compressor is characterized by comprising a power driving system, a stator blade adjusting system, a sensing test system and a base (9); the power driving system comprises a linear motor (5), a driver support (6), a first hydraulic rod (3) and a second hydraulic rod (4); the stator blade adjusting system comprises a first connecting rod (2), a second connecting rod (1), a third connecting rod (8), a bushing A (13), a bushing B (14), a pin shaft A (16), a pin shaft B (17), a rocker arm (10), a stator blade (11), a blade shaft (12) and a connecting rod sliding rail (15); the sensing test system comprises a force sensor (7), an encoder and a balance; the base (9) is used for fixing the driver support (6), the blade shaft (12) and the connecting rod slide rail (15); wherein the blade shaft (12) can rotate on the base (9);
the linear motor (5) is fixed on the driver support (6) and used for providing driving force for the stator blade adjusting system; the linear motor sequentially transmits the driving force to the second hydraulic rod (4), the first hydraulic rod (3), the first connecting rod (2) and the second connecting rod (1); the second connecting rod (1) is L-shaped; the break point end of the second connecting rod (1) slides on the connecting rod slide rail (15) and drives the third connecting rod (8) and the rocker arm (10) to swing; the rocker arm (10) realizes the rotation of the stator blade (11) through the blade shaft (12);
the bushing A (13) is fixed on the rocker arm (10) and is provided with a groove for matching with a boss processed on the rocker arm (10) and restricting the relative rotation of the bushing A and the rocker arm (10); a pin shaft A (16) is fixed on the third connecting rod (8), and a boss is processed on the pin shaft A and is used for matching with a groove processed on the third connecting rod (8); the design of matching the boss and the groove ensures the constraint of the rotational freedom degree and is convenient to disassemble;
the other group of measured kinematic pairs is arranged between the first connecting rod (2) and the second connecting rod (1), wherein the bush B (14) is fixed on the first connecting rod and is provided with a groove for matching with a boss processed on the first connecting rod to restrict the relative rotation of the first connecting rod and the second connecting rod; a pin shaft B (17) is fixed on the second connecting rod, and a boss is processed on the pin shaft B (17) and is used for matching with a groove processed on the second connecting rod; the design of matching the boss and the groove ensures the constraint of the rotational freedom degree and is convenient to disassemble;
the two force sensors (7) are arranged, one is arranged between the first hydraulic rod (3) and the second hydraulic rod (4), and the other is arranged between the second connecting rod (1) and the third connecting rod (8) and used for measuring the tension and the pressure between the rods; the two encoders are respectively used for measuring the swing angle of the first connecting rod (2) and the swing angle of the rocker arm (10).
2. The compressor stator blade adjusting mechanism kinematic pair friction wear test bed of claim 1, characterized in that: the stator blade adjusting system simulates one stage of a stator blade adjusting mechanism of an aircraft engine compressor, wherein the stress and the motion mode of a measured kinematic pair simulate the kinematic pair of the stator blade adjusting mechanism of the aircraft engine compressor.
3. The method for testing the friction wear test bed of the moving pair of the compressor stator blade adjusting mechanism of any one of claims 1 or 2 is characterized by comprising the following tests:
1) friction coefficient test for kinematic pair of stator blade adjusting mechanism
One of the two force sensors is arranged between the first hydraulic rod and the second hydraulic rod; the other is arranged between the second connecting rod and the third connecting rod; holes are formed in the upper portion of the first connecting rod and the lower portion of the rocker arm, the encoder is connected with the pin shaft through the holes, and the encoder measures the swing angle, the angular speed and the angular acceleration of the first connecting rod and the rocker arm; the friction coefficient of the measured kinematic pair is calculated by the following formula
Wherein J is the moment of inertia of the connecting rod to the pin shaft, obtained through three-dimensional software, l is the length of the connecting rod, F is the driving force measured by the force sensor, m is the mass, theta is the swing angle obtained by the encoder, and FShaft、FDiameter of a pipeAs a restraining counter-force of the axis of rotation, MμIs a friction torque;
changing the materials and gaps of the bushing and the pin shaft, changing the length of the connecting rod and the mass of the stator blade, arranging a force sensor and an encoder at the same position, performing a test in the same way, and researching the change rule of the friction coefficient under different parameters;
2) testing of abrasion loss of kinematic pair of stator blade adjusting mechanism
Cleaning the tested kinematic pair, weighing and recording the mass of the kinematic pair before testing by using a balance; starting the test bed, unloading and cleaning the kinematic pair after working normally for a period of time, and weighing the mass of the kinematic pair again; the mass difference of the two times of weighing is the abrasion loss;
on the basis, the materials and the gaps of the bushing and the pin shaft are further changed, the length of the connecting rod and the quality of the stator blade are changed, the test is carried out in the same mode, and the change rule of the abrasion loss under different parameters is researched.
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| CN113063689A (en) * | 2021-03-25 | 2021-07-02 | 上海交通大学 | Aeroengine adjustable stationary blade simulation working condition gap hinge pair test device |
| CN114577459B (en) * | 2022-03-15 | 2022-11-25 | 东北大学 | Single-stage stationary blade adjusting mechanism dynamic characteristic simulation test bed and test method |
| CN116104602B (en) * | 2023-02-28 | 2024-04-12 | 中国空气动力研究与发展中心空天技术研究所 | Force transmission mechanism for engine compressor deflation |
| CN118410264A (en) * | 2024-07-02 | 2024-07-30 | 中国航发四川燃气涡轮研究院 | Method and device for evaluating abrasion of components of static blade adjusting mechanism of compressor |
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| JPH09195795A (en) * | 1996-01-16 | 1997-07-29 | Hitachi Ltd | Remaining life evaluation method for gas turbine stationary blade and device thereof |
| JP3893610B2 (en) * | 2001-10-02 | 2007-03-14 | 石川島播磨重工業株式会社 | Turbine stationary blade test equipment |
| WO2016045684A1 (en) * | 2014-09-26 | 2016-03-31 | Vestas Wind Systems A/S | Fatigue testing of a wind turbine blade |
| CN104819164B (en) * | 2015-05-15 | 2017-08-25 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of adjustable stator blade linkage adjusting apparatus |
| CN110162921B (en) * | 2019-05-31 | 2023-02-28 | 东北大学 | Optimization design method for stationary blade joint adjusting mechanism of aircraft engine |
| CN111441994A (en) * | 2020-04-09 | 2020-07-24 | 中国航发沈阳发动机研究所 | Stator blade rotation angle adjusting and measuring structure and calibration method thereof |
| CN111504621A (en) * | 2020-04-21 | 2020-08-07 | 中国航发沈阳发动机研究所 | Durability test structure of stator blade angle adjusting mechanism |
| CN111911461B (en) * | 2020-08-28 | 2022-06-07 | 中国航发沈阳发动机研究所 | Stator blade angle adjusting mechanism and stator casing structure thereof |
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