CN115112515A - Abrasion measurement experiment method and device for graphite sealing structure of shaft of aircraft engine - Google Patents
Abrasion measurement experiment method and device for graphite sealing structure of shaft of aircraft engine Download PDFInfo
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- CN115112515A CN115112515A CN202210734396.7A CN202210734396A CN115112515A CN 115112515 A CN115112515 A CN 115112515A CN 202210734396 A CN202210734396 A CN 202210734396A CN 115112515 A CN115112515 A CN 115112515A
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- 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
- G01N3/56—Investigating resistance to wear or abrasion
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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
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0021—Torsional
Abstract
The invention utilizes the control system to realize the change of the acceleration, the uniform speed and the deceleration process of the friction disc into one period, and carries out the abrasion experiment of the graphite sealing structure of a plurality of periods. The technical scheme adopted by the invention is as follows: the variable rotating speed control of the aircraft engine rotating shaft is realized by utilizing the existing precise control technology, and the pressing force between the graphite sealing structure and the shaft is controlled in real time, so that the constancy of the pressing force is ensured. The abrasion measurement experiment method for the graphite sealing structure of the shaft of the aircraft engine improves an experiment system for the graphite sealing structure of the shaft of the aircraft engine and increases a test method for the abrasion loss of the graphite sealing structure; the practical working condition of the aero-engine is simulated, the experiment of the alternating speed graphite sealing structure of the aero-engine is carried out, and the service life of the graphite sealing structure is more accurately evaluated, so that the stable performance of the aero-engine is ensured, and the experiment of the traditional graphite sealing structure in a constant speed state can be considered.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to an abrasion measurement experiment method and device for a graphite sealing structure of an aero-engine shaft.
Background
At present, the shaft sealing technology of the aero-engine comprises a labyrinth type, a labyrinth type and the like, and the graphite sealing technology is gradually applied to the sealing of the aero-engine along with the development of the technology. The related experiment research of the graphite sealing structure is mostly a friction loss experiment under a constant speed, the friction loss of the graphite sealing structural member under an alternating speed is not considered, the abrasion of the sealing member caused by the start and stop of the aeroengine is usually neglected, and the evaluation error of the service life of the graphite sealing structure of the aeroengine is larger.
Disclosure of Invention
The invention aims to provide an abrasion measurement experiment method for a graphite sealing structure of an aircraft engine shaft, which is used for solving the technical problem that the traditional friction loss experiment of the graphite sealing structure neglects the friction loss of a graphite sealing structural member under the alternating speed, so that the evaluation error of the service life of the graphite sealing structure of the aircraft engine is larger.
In order to achieve the purpose, the invention adopts the technical scheme that: the wear measurement experiment method for the graphite sealing structure of the aero-engine shaft is used for measuring the wear condition of the graphite sealing structure of the aero-engine shaft under the alternating speed, and comprises the following steps:
s1, assembling an experimental device;
s2, calculating physical parameters required by the control program;
s3, calculating parameters of control output required by the control program;
s4, compiling an acquisition control software experiment system according to the calculation parameters and the experiment process;
s5, checking the actual rotating speed change of the friction disc;
s6, carrying out a graphite sealing structure friction experiment;
s7, changing N accelerations a required by the experiment under the determined pressing force and rotating speed 1 For the first experimental acceleration, the corresponding acceleration time is t 11 At constant speed time t 12 The deceleration time is t 13 Calculating to finish an experimental cycle, and according to experimental requirements until a plurality of cycles are finished, removing the graphite sealing structure to carry out electronic weighing and making a difference with an initial value to be used as the abrasion loss under the acceleration cycle; reinstalling graphite sealing structure, and performing second acceleration a 2 Experiment, changing acceleration time, and repeating the step S7 until all acceleration cycle experiments are completed;
s8, changing the pressing force and the rotating speed of the friction disc, and repeating the step S7 to complete the graphite sealing abrasion experiment under all working conditions;
and S9, comprehensively evaluating the service life of the graphite sealing structure by experimental data.
In one embodiment, the graphite seal structure is not in contact with the friction disk in step S1 to try to rotate the friction disk to ensure free rotation of the friction disk.
In one embodiment, step S2 specifically includes: setting the radius of a friction disc as R meters, the rotating speed as n revolutions per minute and the speed rising time as t seconds; the tangential velocity of the circumference of the friction disk is
Acceleration of
According to the acceleration formula, after the experimental rotating speed is fixed, the acceleration is a function of time, the requirement for changing the acceleration of the friction disc can be met only by changing the speed-up time and the speed-down time, and the alternating speed change of the friction disc is realized.
In one embodiment, step S3 specifically includes: selecting the maximum rotating speed of the variable frequency motor as n max The maximum output of the frequency converter is 50HZ, and the corresponding analog quantity is controlled to be 0-5V, so that the maximum signal of the analog quantity output corresponds to the maximum rotating speed of the motor; computer programOutputting corresponding control quantity within a specified time; the pressing force control of the graphite sealing structure depends on the pressure signal fed back by the tension and compression sensor to control the stepping motor, and the control is carried out according to the actual pressing force setting.
In an embodiment, step S5 specifically includes: controlling the graphite sealing structure to be given according to the pressing force required by the experiment, controlling in real time, and checking only one cycle of acceleration, uniform speed and deceleration at a fixed rotating speed; and giving the rotating speed and the speed increasing time, the constant speed time and the speed reducing time of the friction disc, recording a rotating speed curve of the friction disc through a torque meter, comparing the rotating speed curve with the control signal output, checking whether the curve meets the requirement, if so, performing step S6, and if not, repeating step S5.
In one embodiment, step S6 specifically includes: firstly, determining the pressing force of a graphite sealing structure and the rotating speed of a friction disc according to experimental requirements; and the mass of the graphite sealing structure was weighed using an electronic balance as an initial value before the experiment.
In one embodiment, the t 11 And t 12 And t 13 The values are the same.
Another object of the present invention is to provide an abrasion measurement experiment apparatus for an aircraft engine shaft graphite sealing structure, for performing the abrasion measurement experiment method for the aircraft engine shaft graphite sealing structure described in any of the above embodiments, the abrasion measurement experiment apparatus for the aircraft engine shaft graphite sealing structure includes:
a computer system;
the rotating speed adjusting system is electrically connected with the computer system;
the friction disc is arranged at the power output end of the rotating speed adjusting system;
the sliding rail is provided with a transmission rack;
the sliding block is arranged on the sliding rail in a sliding mode;
the stepping motor is arranged on the sliding block and is electrically connected with the computer system;
the gear is arranged at the power output end of the stepping motor and matched with the transmission rack;
the mounting base is arranged on the sliding rail in a sliding mode, the mounting base is connected with the sliding block, a tension and compression sensor is arranged between the mounting base and the sliding block, and the tension and compression sensor is electrically connected with the computer system;
the graphite sealing structure is fixed on the mounting base through a pressing sheet, and the end part of the graphite sealing structure is in contact friction fit with the friction disc.
In one embodiment, the rotational speed adjustment system comprises:
the brake resistor is electrically connected with the computer system;
the frequency converter is electrically connected with the brake resistor and the computer system;
the variable frequency motor is electrically connected with the frequency converter;
the torque meter is connected with a power output shaft of the variable frequency motor through a first coupling;
and one end of the transmission shaft is connected with the torque meter through a second coupler, and the other end of the transmission shaft is connected with the friction disc.
One or more technical solutions described above in the embodiments of the present invention have at least the following technical effects or advantages:
the abrasion measurement experiment method for the graphite sealing structure of the shaft of the aircraft engine, provided by the embodiment of the invention, perfects an experiment system for the graphite sealing structure of the shaft of the aircraft engine and increases a test method for the abrasion loss of the graphite sealing structure. And then the actual working condition of the aircraft engine is simulated, the alternating speed graphite sealing structure experiment of the aircraft engine is carried out, and the service life of the graphite sealing structure is more accurately evaluated, so that the stable performance of the aircraft engine is ensured. In addition, the experimental method can give consideration to the experiment of the traditional graphite sealing structure in a constant speed state, and can also automatically change the shape of a rotating speed trapezoidal graph according to the actual situation to carry out various alternating speed graphite sealing structure experiments. And the actual rotating speed can be checked on line, so that the experiment precision is improved, and the repeatability of the experiment is further improved.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a flow chart of an experiment of a graphite sealing structure according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of an abrasion measurement experiment of a graphite sealing structure of an aircraft engine shaft according to an embodiment of the invention;
fig. 3 is a schematic view of a graphite sealing structure tool and a loading device of a graphite sealing structure abrasion experiment system provided by an embodiment of the invention;
FIG. 4 is a ladder diagram illustrating a cycle of rotational speed variation for checking the rotational speed of a friction disk in accordance with an embodiment of the present invention;
FIG. 5 is a ladder diagram of rotational speeds in an embodiment of the present invention.
Wherein the respective reference numerals are as follows:
1. a computer system; 2. a brake resistor; 3. a frequency converter; 4. a variable frequency motor; 5. a first coupling; 6. a torque meter; 7. a second coupling; 8. a first bearing housing; 9. a second bearing housing; 10. a drive shaft; 11. a friction disk; 12. a graphite sealing structure; 13. positioning pins; 14. tabletting; 15. a screw; 16. installing a base; 17. a slide rail; 18. a tension and compression sensor; 19. a drive rack; 20. a gear; 21. a stepping motor; 22. a slide block.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
An aircraft engine is an engine device used to generate thrust to advance an aircraft. Advanced aircraft require a powerful heart, and aircraft engines are the source of power for the aircraft. The aircraft engine is a very complicated high-end machine, and the working conditions have the characteristics of high temperature, high pressure and high speed: the working temperature is high, and the temperature at each position inside the device is different and constantly changed; the gas pressure is large, and the working load is high; the rotor has high rotating speed and bears various influences on the engine caused by environment and maneuvering flight. In particular, a compressor of an aircraft engine sucks in low-pressure air, and the pressure of the air is increased by an impeller of the compressor. To achieve high performance of an aircraft engine, a typical compressor is divided into multiple stages: the compressor comprises a fan stage, a low-pressure compressor stage and a high-pressure compressor stage. And the compressors of different stages are driven by different rotating shafts, so that the multi-rotor aero-engine is realized. Because the pressure of gas is increased from one atmosphere at the inlet of an aircraft engine to dozens of atmospheres through a compressor, the gas is easy to leak from high pressure to low pressure, and the sealing between compressor stages is important. The current graphite sealing technology is applied to an aircraft engine, and the graphite sealing is sealed by the extrusion principle of a graphite sealing element and an engine rotating shaft, so that the abrasion of graphite is caused by the relative high-speed movement between the graphite and the rotating shaft. The life of the graphite seals must be evaluated.
In addition, the aircraft engine is a power device of the aircraft, the flying process of the aircraft, especially the flying of a fighter aircraft, needs rapid acceleration and deceleration, and the working process determines that the rotating process is a variable-speed working process, so the abrasion experimental study on the graphite sealing structure of the aircraft engine shaft also needs a variable working process instead of a steady-state process with uniform speed. The performance and the service life of the graphite sealing structure can be accurately evaluated only by accurately simulating the working process of the aero-engine. In the experiment, the graphite sealing structure generates abrasion in the relative motion with the shaft, so that the relative pre-pressing force between the graphite sealing structure and the shaft of the aircraft engine can be changed, the experiment system fully considers the slight change, and sets constant pressing force for the system, and the pressing force does not change along with time.
Therefore, referring to fig. 1, an embodiment of the present application provides an abrasion measurement experiment method for a graphite sealing structure of an aircraft engine shaft, which is used for measuring an abrasion condition of the graphite sealing structure of the aircraft engine shaft at an alternating speed, and the abrasion measurement experiment method for the graphite sealing structure of the aircraft engine shaft includes the following steps:
and S1, assembling the experimental device. Optionally, the graphite sealing structure is not in contact with the friction disc at this time so as to try to rotate the friction disc to ensure free rotation of the friction disc.
And S2, calculating physical parameters required by the control program. Step S2 specifically includes: setting the radius of a friction disc as R meters, the rotating speed as n revolutions per minute and the speed rising time as t seconds; the tangential velocity of the circumference of the friction disk is
Acceleration of
According to the acceleration formula, after the experimental rotating speed is fixed, the acceleration is a function of time, the requirement for changing the acceleration of the friction disc can be met only by changing the speed-up time and the speed-down time, and the alternating speed change of the friction disc is realized.
S3, a parameter of the control output required by the control program is calculated. Step S3 specifically includes: selecting the maximum rotating speed of the variable frequency motor as 50HZ as the maximum output of the frequency converter, and controlling the corresponding analog quantity to be 0-5V, so that the maximum signal of the analog quantity output corresponds to the maximum rotating speed of the motor; the computer program only needs to output corresponding control quantity within a specified time; the pressing force control of the graphite sealing structure depends on the pressure signal fed back by the tension and compression sensor to control the stepping motor, and the control is carried out according to the actual pressing force setting.
S4, compiling an acquisition control software experiment system according to the calculation parameters and the experiment process;
and S5, checking the actual rotating speed change of the friction disc. Step S5 specifically includes: controlling the graphite sealing structure to be given according to the pressing force required by the experiment, controlling in real time, and checking only one cycle of acceleration, uniform speed and deceleration at a fixed rotating speed; and giving the rotating speed and the speed increasing time, the constant speed time and the speed reducing time of the friction disc, recording a rotating speed curve of the friction disc through a torque meter, comparing the rotating speed curve with the control signal output, checking whether the curve meets the requirement, if so, performing step S6, and if not, repeating step S5.
And S6, performing a graphite sealing structure friction experiment. Step S6 specifically includes: firstly, determining the pressing force of a graphite sealing structure and the rotating speed of a friction disc according to experimental requirements; and the mass of the graphite sealing structure was weighed using an electronic balance as an initial value before the experiment.
S7, under the determined pressing force and rotation speed, changing N accelerations a required by the experiment 1 For the first experimental acceleration, the corresponding acceleration time is t 11 At constant speed time t 12 The deceleration time is t 13 Calculating to finish an experimental cycle, and according to experimental requirements until a plurality of cycles are finished, removing the graphite sealing structure to carry out electronic weighing and making a difference with an initial value to be used as the abrasion loss under the acceleration cycle; reinstalling graphite sealing structure, and then carrying out second acceleration a 2 Experiment, changing acceleration time, and repeating the step S7 until all acceleration cycle experiments are completed;
s8, changing the pressing force and the rotating speed of the friction disc, and repeating the step S7 to complete the graphite sealing abrasion experiment under all working conditions;
and S9, comprehensively evaluating the service life of the graphite sealing structure by experimental data.
In one embodiment, t 11 And t 12 And t 13 The values are the same.
As shown in fig. 2 to 3, another object of the present invention is to provide an abrasion measurement experiment device for an aircraft engine shaft graphite sealing structure 12, which is used for performing an abrasion measurement experiment method for the aircraft engine shaft graphite sealing structure 12 in any one of the above embodiments, wherein the abrasion measurement experiment device for the aircraft engine shaft graphite sealing structure 12 comprises a computer system 1, a rotation speed adjustment system, a friction disc 11, a slide rail 17, a slide block 22, a stepping motor 21, a gear 20, a mounting base 16, and the graphite sealing structure 12. The rotating speed adjusting system is electrically connected with the computer system 1. The friction disc 11 is arranged at the power output end of the rotating speed adjusting system. The slide rail 17 is provided with a transmission rack 19. The slide block 22 is slidably disposed on the slide rail 17. The stepping motor 21 is disposed on the slider 22, and the stepping motor 21 is electrically connected to the computer system 1. The gear 20 is arranged at the power output end of the stepping motor 21, and the gear 20 is matched with the transmission rack 19. The mounting base 16 is slidably disposed on the slide rail 17, the mounting base 16 is connected to the slider 22, a tension/compression sensor 18 is disposed between the mounting base 16 and the slider 22, and the tension/compression sensor 18 is electrically connected to the computer system 1. The graphite seal structure 12 is fixed to the mounting base 16 by the pressure plate 14, and the end of the graphite seal structure 12 is in contact friction fit with the friction disc 11.
In one embodiment, the speed regulation system comprises a brake resistor 2, a frequency converter 3, a transmission shaft 10, a torque meter 6 and a variable frequency motor 4. The brake resistor 2 is electrically connected with the computer system 1. The frequency converter 3 is electrically connected with the brake resistor 2 and the computer system 1. The variable frequency motor 4 is electrically connected with the frequency converter 3. The torque meter 6 is connected with the power output shaft of the variable frequency motor 4 through a first shaft connector 5. One end of the transmission shaft 10 is connected with the torque meter 6 through the second coupler 7, and the other end of the transmission shaft 10 is connected with the friction disc 11.
The friction disc 11 is used to rub against the graphite sealing structure 12, which causes the graphite sealing structure 12 to wear. The power system of the friction disc 11 is provided by a variable frequency motor 4, the rotating speed of the variable frequency motor 4 is controlled by a frequency converter 3, and the frequency converter 3 is provided with a brake resistor 2 so as to control the deceleration movement of the variable frequency motor. The torque and the rotational speed of the friction disc 11 may be measured by the torque meter 6, so that the computer system 1 may receive signals from the torque meter 6 for signal processing.
The graphite sealing structure 12 ensures the installation accuracy by means of the positioning pin 13, and the contact area with the friction disc 11 is more than 90%. The graphite seal structure 12 is fixed to a mounting base 16, and the mounting base 16 is slidable on a slide rail 17. Therefore, the stepping motor 21 drives the gear 20 to be meshed with the transmission rack 19 to push the mounting base 16, and the graphite sealing device is loaded. The magnitude of the loading force can be uploaded to the computer system 1 through the tension and compression sensor 18, and then the graphite sealing structure 12 is controlled in real time as the feedback of the pressing force, so that the constancy of the pressing force is ensured.
Fig. 3 is a ladder diagram for checking the rotation speed of the friction disc in one period, wherein a is a given rotation speed signal of a computer, and b is an actually measured rotation speed of the friction disc. The experiment may be performed in a plurality of cycles. The acceleration time, the uniform speed time and the deceleration time of the experiment can be set according to the actual needs of the experiment.
Example one:
the invention only lists a specific process of an acceleration experiment; the radius of the friction disc of the experimental system is 150mm, and the rotating speed of the variable frequency motor is 0-6000 rpm. The graphite seal was measured at 158.1250g and installed, at which point the compression force was zero, i.e., disengaged.
1. And calculating acceleration time, constant speed time and deceleration time. Linear acceleration selection
The experimental speed n is 3000rpm, so t is calculated to be 8.2 s;
2. checking the difference between the actual rotating speed and the set rotating speed of the computer system; it can be seen from fig. 5 that the experimental rotation speed ladder diagram adopts an equal time interval experiment, that is, the acceleration time is 8.2s, the uniform speed time is 8.2s, and the deceleration time is 8.2 s. The total experiment period is 24.6s, the line a represents a relation graph of a rotating speed signal sent by a computer and time, the line b represents the actually measured rotating speed of the friction disc, delay lag of 1 second exists, and the actually measured ladder diagram is not different from a set graph diagram, so that the experiment requirement is met, and subsequent experiments can be carried out.
3. The linear acceleration of the friction disc is 5m/s 2 The deceleration linear acceleration is-5 m/s 2 Thus, the time is 8.2s, and the friction disc rotation speed ladder diagram is piecewise equal time. The pressing force of the graphite sealing structure is 200g, and the experiment is set to thirty periods, namely the experiment time is as follows: 24.6 × 30/60 ═ 12.3 minutes. After thirty cycles are completed, the graphite sealing structure is separated, and the measured quality is as follows: 158.1226 g. The wear parameters of the changed state can thus be calculated according to the following table:
the present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. An abrasion measurement experiment method for a graphite sealing structure of an aircraft engine shaft is used for measuring the abrasion condition of the graphite sealing structure of the aircraft engine shaft under the condition of alternating speed, and is characterized by comprising the following steps:
s1, assembling an experimental device;
s2, calculating physical parameters required by the control program;
s3, calculating parameters of control output required by the control program;
s4, compiling an acquisition control software experiment system according to the calculation parameters and the experiment process;
s5, checking actual rotating speed change of the friction disc;
s6, carrying out a graphite sealing structure friction experiment;
s7, changing N accelerations a required by the experiment under the determined pressing force and rotating speed 1 For the first experimental acceleration, the corresponding acceleration time is t 11 At constant speed time t 12 The deceleration time is t 13 Calculating to finish an experimental cycle, and according to experimental requirements until a plurality of cycles are finished, removing the graphite sealing structure to carry out electronic weighing and making a difference with an initial value to be used as the abrasion loss under the acceleration cycle; reinstalling graphite sealing structure, and then carrying out second acceleration a 2 Experiment, changing acceleration time, and repeating the step S7 until all acceleration cycle experiments are completed;
s8, changing the pressing force and the rotating speed of the friction disc, and repeating the step S7 to complete the graphite sealing abrasion experiment under all working conditions;
and S9, comprehensively evaluating the service life of the graphite sealing structure by experimental data.
2. The abrasion measurement experiment method for the graphite sealing structure of the aircraft engine shaft according to claim 1, characterized in that:
in step S1, the graphite seal structure is not in contact with the friction disk so as to try to rotate the friction disk to ensure free rotation of the friction disk.
3. The abrasion measurement experiment method for the graphite sealing structure of the aircraft engine shaft according to claim 1, characterized in that:
step S2 specifically includes: setting the radius of a friction disc as R meters, the rotating speed as n revolutions per minute and the speed rising time as t seconds; the tangential velocity of the circumference of the friction disk is
Acceleration of
According to the acceleration formula, after the experimental rotating speed is fixed, the acceleration is a function of time, the requirement for changing the acceleration of the friction disc can be met only by changing the speed-up time and the speed-down time, and the alternating speed change of the friction disc is realized.
4. The abrasion measurement experiment method for the graphite sealing structure of the aircraft engine shaft according to claim 1, characterized in that:
step S3 specifically includes: selecting the maximum rotating speed of the variable frequency motor as n max The maximum output of the frequency converter is 50HZ, and the corresponding analog quantity is controlled to be 0-5V, so that the maximum signal of the analog quantity output corresponds to the maximum rotating speed of the motor; the computer program only needs to output corresponding control quantity within a specified time; the pressing force control of the graphite sealing structure depends on a pressure signal fed back by a tension and compression sensor to control the stepping motor, and the control is carried out according to the actual pressing force setting.
5. The abrasion measurement experiment method for the graphite sealing structure of the aircraft engine shaft according to claim 1, characterized in that:
step S5 specifically includes: controlling the graphite sealing structure to be given according to the pressing force required by the experiment, controlling in real time, and checking only one cycle of acceleration, constant speed and deceleration at a fixed rotating speed; and giving the rotating speed and the speed increasing time, the constant speed time and the speed reducing time of the friction disc, recording a rotating speed curve of the friction disc through a torque meter, comparing the rotating speed curve with the control signal output, checking whether the curve meets the requirement, if so, performing step S6, and if not, repeating step S5.
6. The abrasion measurement experiment method for the graphite sealing structure of the aircraft engine shaft according to claim 1, characterized in that:
step S6 specifically includes: firstly, determining the pressing force of a graphite sealing structure and the rotating speed of a friction disc according to experimental requirements; and the mass of the graphite sealing structure was weighed using an electronic balance as an initial value before the experiment.
7. The abrasion measurement experiment method for the graphite sealing structure of the aircraft engine shaft according to claim 1, characterized in that:
said t is 11 And t 12 And t 13 The values are the same.
8. An abrasion measurement experiment device for an aero-engine shaft graphite sealing structure, which is used for carrying out the abrasion measurement experiment method for the aero-engine shaft graphite sealing structure according to any one of claims 1 to 7, wherein the abrasion measurement experiment device for the aero-engine shaft graphite sealing structure comprises:
a computer system;
the rotating speed adjusting system is electrically connected with the computer system;
the friction disc is arranged at the power output end of the rotating speed adjusting system;
the sliding rail is provided with a transmission rack;
the sliding block is arranged on the sliding rail in a sliding mode;
the stepping motor is arranged on the sliding block and is electrically connected with the computer system;
the gear is arranged at the power output end of the stepping motor and matched with the transmission rack;
the mounting base is arranged on the sliding rail in a sliding mode, the mounting base is connected with the sliding block, a tension and compression sensor is arranged between the mounting base and the sliding block, and the tension and compression sensor is electrically connected with the computer system;
the graphite sealing structure is fixed on the mounting base through a pressing sheet, and the end part of the graphite sealing structure is in contact friction fit with the friction disc.
9. The abrasion measurement experiment device for the graphite sealing structure of the aircraft engine shaft according to claim 8, wherein the rotating speed adjusting system comprises:
the brake resistor is electrically connected with the computer system;
the frequency converter is electrically connected with the brake resistor and the computer system;
the variable frequency motor is electrically connected with the frequency converter;
the torque meter is connected with a power output shaft of the variable frequency motor through a first coupling;
and one end of the transmission shaft is connected with the torque meter through a second coupler, and the other end of the transmission shaft is connected with the friction disc.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210734396.7A CN115112515A (en) | 2022-06-27 | 2022-06-27 | Abrasion measurement experiment method and device for graphite sealing structure of shaft of aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210734396.7A CN115112515A (en) | 2022-06-27 | 2022-06-27 | Abrasion measurement experiment method and device for graphite sealing structure of shaft of aircraft engine |
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| CN115112515A true CN115112515A (en) | 2022-09-27 |
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| CN202210734396.7A Pending CN115112515A (en) | 2022-06-27 | 2022-06-27 | Abrasion measurement experiment method and device for graphite sealing structure of shaft of aircraft engine |
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2022
- 2022-06-27 CN CN202210734396.7A patent/CN115112515A/en active Pending
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