CN115420511A - Aero-engine scale deposition simulation experiment testing equipment and using method thereof - Google Patents
Aero-engine scale deposition simulation experiment testing equipment and using method thereof Download PDFInfo
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- CN115420511A CN115420511A CN202211092863.7A CN202211092863A CN115420511A CN 115420511 A CN115420511 A CN 115420511A CN 202211092863 A CN202211092863 A CN 202211092863A CN 115420511 A CN115420511 A CN 115420511A
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- 238000004088 simulation Methods 0.000 title claims abstract description 27
- 238000012360 testing method Methods 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title claims abstract description 24
- 230000008021 deposition Effects 0.000 title claims description 10
- 239000000843 powder Substances 0.000 claims abstract description 77
- 238000002474 experimental method Methods 0.000 claims abstract description 43
- 239000002245 particle Substances 0.000 claims abstract description 22
- 239000000523 sample Substances 0.000 claims description 37
- 230000000087 stabilizing effect Effects 0.000 claims description 17
- 238000009792 diffusion process Methods 0.000 claims description 15
- 230000008602 contraction Effects 0.000 claims description 14
- 238000001914 filtration Methods 0.000 claims description 9
- 238000007789 sealing Methods 0.000 claims description 4
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 239000012780 transparent material Substances 0.000 claims description 2
- 238000005259 measurement Methods 0.000 abstract description 13
- 239000008187 granular material Substances 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229920000742 Cotton Polymers 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 238000003915 air pollution Methods 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 238000005137 deposition process Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
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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
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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Abstract
The invention discloses an aeroengine scale deposit simulation experiment test device which comprises a powder feeding system, a measuring system and a wind tunnel system, wherein the powder feeding system is arranged at the top of the air inlet end of the wind tunnel system, a power device is arranged at the tail end of the wind tunnel system, and the measuring system is arranged at the upper end of the middle part of the wind tunnel system; the powder feeding system is used for conveying the scale particles into the wind tunnel system; the measuring system is used for measuring experimental parameters; the power device is used for providing stable airflow required by experiments. The device highly restores the fouling condition of the airplane under the flying environment condition, has high measurement precision, can visually observe the fouling process, has small volume, high automation degree and simple and convenient operation process, can simulate different fouling states, is convenient to analyze the influence of the fouling on the aerodynamic performance of the engine blade, and ensures the safe operation of the aero-engine.
Description
Technical Field
The invention belongs to the technical field of aero-engine experiment tables, and particularly relates to aero-engine scale accumulation simulation experiment testing equipment and a using method thereof.
Background
The aero-engine inner duct gas path component inevitably suffers atmospheric pollution and generates scale on the surface in the working process, particularly in the severe atmospheric pollution and wide salt-rich airspace in China, and the aero-engine gas path component is easier to suffer pollution and scale. The scale deposit increases the boundary layer thickness and the surface roughness of the gas path component, can influence the aerodynamic characteristics of the boundary layer of the blade and the casing, causes the reduction of the exhaust temperature margin, the increase of the fuel consumption rate, the reduction of the propulsion efficiency, the shortening of the service life of the gas path component at the wing, and can cause the surge of the engine and even the air parking when the engine is serious. Therefore, the research on the fouling of the aero-engine has important application value for improving the flight safety.
The airplane sucks pollutant particles in the flying process, deposits on the surfaces of the blades to form scale, and the scale is influenced by a series of parameters such as particle diameter, particle physical properties, inner duct temperature, inner duct environment humidity and airplane flying speed. Therefore, the flying environments of different air routes can cause different fouling states, the influence on the performance of the engine is difficult to accurately judge, and the flying safety is seriously influenced. In order to analyze the influence of the fouling on the aerodynamic performance of the engine blade and ensure the safe operation of the aero-engine, the blade fouling process needs to be deeply researched. Therefore, a set of device capable of simulating the fouling conditions of the aero-engine in different flight environments is needed to perform simulation experiments of fouling in various flight environments.
Disclosure of Invention
The invention provides an aeroengine scale deposition simulation experiment test device and a using method thereof, which aim to solve the problems in the prior art.
The invention provides an aero-engine scale deposition simulation experiment test device which comprises a powder feeding system, a measuring system and a wind tunnel system, wherein the powder feeding system is installed at the top of the air inlet end of the wind tunnel system, a power device is installed at the tail end of the wind tunnel system, and the measuring system is installed at the upper end of the middle part of the wind tunnel system;
the powder feeding system is used for conveying scale particles into the wind tunnel system;
the measuring system is used for measuring experimental parameters;
the power device is used for providing stable airflow required by experiments.
Further, the measuring system comprises a moving component and a probe, wherein the probe is vertically installed on the moving component, and the moving component is used for driving the probe to move and rotate;
the moving part comprises a base, a moving plate, a lifting plate and a rotary table, the base is fixedly arranged on the upper end face of the wind tunnel system, a guide rail is arranged on the base, the moving plate is slidably arranged on the guide rail, the lifting plate is vertically and fixedly arranged on the moving plate, the upper portion and the lower portion of the rotary table are movably arranged on the side face of the lifting plate, and the probe is arranged on the rotary table.
Further, the wind tunnel system comprises a stable section, a contraction section, an experiment section and a diffusion section which are connected in sequence;
the stabilizing section is of a rectangular structure and is used for guiding and uniformly drawing an upstream incoming flow, a support frame is arranged at the bottom of the stabilizing section, and the powder feeding system is arranged at the top of the stabilizing section;
the contraction section is used for connecting the stable section and the experiment section, the cross section area of the contraction section is gradually reduced from large to small, and the contraction section is used for increasing the flow velocity of the airflow so that the airflow of the stable section uniformly accelerates and then enters the experiment section;
the experimental section is internally provided with a plurality of experimental blades which are uniformly arranged at intervals along the diagonal direction of the top opening of the experimental section, the bottom of the experimental section is provided with a support frame, and the top of the experimental section is provided with the measuring system;
the diffusion section is of a conical structure and is used for connecting the experimental section and the power device, and the cross section area of the diffusion section is gradually increased from small to large and is used for reducing the energy loss of airflow.
Further, the powder feeding system comprises a powder cylinder, a box body and a powder feeding pipe; the box body is fixedly arranged at the top of the stabilizing section, the powder cylinder is fixedly arranged at the top of the box body and used for containing scale particles, the bottom of the box body is communicated with and provided with the powder feeding pipe, and the discharge end of the powder feeding pipe extends into the stabilizing section; the powder feeding device is characterized in that an adjusting structure is arranged in the box body, and a powder feeding motor is fixedly installed on one side of the box body and used for controlling the adjusting structure to adjust the powder feeding amount.
Furthermore, the power device comprises a centrifugal fan and a driving motor, the centrifugal fan is installed at the tail end of the wind tunnel system, and the driving motor is fixedly installed at the rear end of the centrifugal fan.
Furthermore, an air outlet of the centrifugal fan is connected with a diffusion chamber, the diffusion chamber is used for reducing the flow velocity of air flow, and a filtering layer is arranged at the top of the diffusion chamber and used for filtering redundant scale particles.
Furthermore, an expansion joint is arranged between the centrifugal fan and the tail end of the wind tunnel system.
Further, the rotary table drives the probe to rotate under the driving of the rotating motor.
Furthermore, the contraction section is of a shift vickers curve structure.
The invention provides a using method of an aero-engine fouling simulation experiment testing device, which comprises the following steps:
step one, simulating an airflow environment
Turning on a driving motor, starting a centrifugal fan to run, forming stable airflow in a wind tunnel system, and simulating the actual flow field condition in the engine in the flying process of the airplane;
step two, starting the powder feeding system
Turning on a powder feeding motor, conveying the scale deposition particles into a wind tunnel system, controlling the powder feeding amount by adjusting the rotating speed of the powder feeding motor, and simulating the scale deposition state of an engine blade in the flying process;
step three, measuring the parameters of the experimental blade
The position and the angle of the probe are adjusted by the moving part, the probe is positioned at a position behind the experimental blade by a chord length distance, the performance parameters of the experimental blade in a fouling state are collected by the probe, and the collected data are transmitted to the acquisition system for analysis.
The invention has the advantages and positive effects that:
1. the aero-engine fouling simulation experiment test equipment forms stable airflow through the wind tunnel system, the powder feeding system sends fouling particles into the wind tunnel system, the fouling particles are fully mixed with the airflow in the wind tunnel system and then are adhered to the surface of an experiment blade, the actual condition of an engine internal actual flow field in the airplane flight process is truly restored, the fouling conditions under different flight environment conditions are simulated, the measurement system is used for collecting state parameters of the experiment blade, the influence of different factors on the engine blade is analyzed and researched, and the guarantee is provided for the safe operation of the aero-engine.
2. In this aeroengine scaling simulation experiment test equipment, measurement system's removal part can realize the nimble removal of probe, and the control probe is measured the different positions of experiment blade, and degree of automation is high, is convenient for operate, measurement of efficiency height.
3. In the aeroengine fouling simulation experiment test equipment, the diameter of the head end of the contraction section of the wind tunnel system is larger than that of the tail end of the contraction section, and a shift vickers curve structure is adopted, so that the uniform acceleration of airflow is realized, the airflow environment in the flying process is well restored, and the experiment precision is greatly improved; the diffusion section of the wind tunnel system adopts a conical structure with the diameter of the head end smaller than that of the tail end, so that the energy loss of airflow is skillfully reduced.
4. In this aeroengine deposits incrustation simulation experiment test equipment, the deposit granule gets into powder feeding system's box 82, adjusts powder feeding volume through powder feeding motor to the deposit granule flow under the different flight environment of simulation realizes the accurate control to the variable.
5. Among this aeroengine scaling simulation experiment test equipment, centrifugal fan air outlet is provided with filtration system, filters the unnecessary scaling granule in the air current through the filter layer, and the air current gets into earlier through the diffusion room diffusion speed reduction before the filter layer, ensures the velocity of flow greatly reduced when the air current reachs the filter layer, ensures more thoroughly to the filtration of scaling granule, effectively avoids having the gas direct discharge air of scaling granule, causes environmental pollution.
6. In this aeroengine scaling simulation experiment test equipment, connect centrifugal fan and wind tunnel system through the expansion joint, can form the buffering between centrifugal fan and wind tunnel system, prevent centrifugal fan's vibration influence measurement, greatly reduced experimental error, improved experiment measurement accuracy, ensure that the experiment goes on smoothly.
7. The device highly restores the fouling condition of the airplane under the flying environment condition, has high measurement precision, can visually observe the fouling process, has small volume, high automation degree and simple and convenient operation process, can simulate different fouling states, is convenient to analyze the influence of the fouling on the aerodynamic performance of the engine blade, and ensures the safe operation of the aero-engine.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention (the sealing cover is not shown in the drawings);
FIG. 2 is a right side view of the present invention;
FIG. 3 is an enlarged view of a portion A of FIG. 1 in accordance with the present invention;
FIG. 4 is an enlarged view of a portion B of FIG. 1 in accordance with the present invention;
FIG. 5 is an enlarged view of a portion C of FIG. 1 in accordance with the present invention;
FIG. 6 is a top view of an experimental section of the present invention;
FIG. 7 is a flow chart of a method of use of the present invention.
In the figure, 1 is a power device, 2 is a filter layer, 3 is a diffusion chamber, 4 is an expansion joint, 5 is a wind tunnel system, 6 is a measurement system, 7 is an experimental blade, 8 is a powder feeding system, 9 is a support frame, 11 is a driving motor, 12 is a centrifugal fan, 51 is a diffusion section, 52 is an experimental section, 53 is a contraction section, 54 is a stabilization section, 61 is a horizontal cylinder, 62 is a lifting motor, 63 is a probe, 64 is a lifting plate, 65 is a rotary table, 66 is a rotating motor, 67 is a base, 68 is a guide rail, 69 is a moving plate, 81 is a powder cylinder, 82 is a box 82, 83 is a powder feeding motor, and 84 is a powder feeding pipe.
Detailed Description
The present invention will be described in more detail with reference to the accompanying drawings.
The invention provides a device for testing an aero-engine scale deposition simulation experiment, which comprises a powder feeding system 8, a measuring system 6, a wind tunnel system 5 and a filtering system. The top of the air inlet end of the wind tunnel system 5 is provided with the powder feeding system 8, the tail end of the wind tunnel system is provided with the power device 1, and the upper end of the middle part of the wind tunnel system 5 is provided with the measuring system 6; the powder feeding system 8 is used for conveying scale deposition particles into the wind tunnel system 5; the measuring system 6 is used for measuring experiment parameters; the power plant 1 is used to provide a steady air flow required for the experiment. The power device 1 comprises a centrifugal fan 12 and a driving motor 11, the centrifugal fan 12 is connected to the tail end of the wind tunnel system 5, the driving motor 11 is fixedly installed at the rear portion of the centrifugal fan 12, the centrifugal fan 12 is driven by the driving motor 11, and the power device 1 is used for providing stable airflow required by an experiment to form a complete direct-current wind tunnel system 5.
The measuring system 6 comprises a probe 63 and a moving part, wherein the probe 63 is vertically arranged on the moving part, and the moving part is used for driving the probe 63 to move and rotate; the moving part comprises a base 67, a moving plate 69, a lifting plate 64 and a rotary table 65, the base 67 is fixedly mounted at the upper end part of the wind tunnel system 5 through bolts, a guide rail 68 is mounted on the base 67, the moving plate 69 is slidably mounted on the guide rail 68, the moving plate 69 moves along the guide rail 68 under the drive of a horizontal cylinder 61, the lifting plate 64 is vertically and fixedly mounted on the moving plate 69, the rotary table 65 is vertically and movably mounted on the side surface of the lifting plate 64 up and down and is driven by a lifting motor 62 fixedly mounted at the top of the lifting plate 64 to move up and down along the lifting plate 64, the probe 63 is fixedly mounted on the rotary table 65, a rotating motor 66 is fixedly mounted on one side of the rotary table 65, and the rotary table 65 is driven by the rotating motor 66 to rotate to drive the probe 63 to rotate; the structure of the turntable 65 is prior art. Preferably, the probe 63 is a five-well probe 63; during the measurement, moving part moves under horizontal cylinder 61 drive to drive probe 63 along experiment blade 7 array direction round trip movement, lift motor 62 drive revolving stage 65 vertical motion, thereby drive probe 63 and reciprocate, rotate motor 66 drive revolving stage 65, drive probe 63 and rotate around self axis. The probe 63 is used for measuring performance parameters such as outlet airflow angle, outlet airflow speed, pressure, temperature and the like at different positions at the rear part of the experimental blade 7, and transmitting experimental data obtained through measurement to an acquisition system for analysis.
The wind tunnel system 5 comprises a stable section 54, a contraction section 53, an experiment section 52 and a diffusion section 51 which are connected in sequence, wherein the stable section 54 is of a rectangular structure and is used for guiding and uniformly drawing an upstream incoming flow, a support frame 9 is arranged at the bottom of the stable section 54, and the powder feeding system 8 is arranged at the top of the stable section; the contracting section 53 is used for connecting the stabilizing section 54 and the experimental section 52, the cross-sectional area of the contracting section is gradually reduced from large to small, and the contracting section is used for increasing the flow velocity of the airflow so that the airflow of the stabilizing section 54 uniformly accelerates and then enters the experimental section 52; the airflow can play a role of uniform acceleration through the contraction section 53, and in order to obtain the best flow field quality, the contraction section 53 adopts a shift vickers curve structure; the air flow is accelerated by the contraction section 53 and then flows into the experiment section 52, the airflow environment of the airplane in a flight state is simulated, a plurality of experiment blades 7 are arranged in the experiment section 52, the experiment blades 7 are uniformly arranged at intervals along the diagonal direction of the top opening of the experiment section 52, the bottom of the experiment section 52 is provided with the support frame 9, and the top of the experiment section 52 is provided with the measuring system 6; the probe 63 extends into the experiment section 52 from the top opening of the experiment section 52 to measure the experiment blades 7, preferably, the height of the experiment section 52 is 3 times of the chord length of the experiment blades 7, 9 experiment blades 7 are placed in the experiment section 52, the installation attack angle of the experiment blades 7 is 0 degree, the distance between the experiment blades 7 is 30mm, the arrangement direction of the experiment blades 7 is 57 degrees, and the experiment blades 7 are all fixed in the experiment section 52 through nuts; during measurement, the probe 63 is positioned at a chord length distance behind the experimental blade 7; the diffuser section 51 is of a conical structure and is used for connecting the experimental section 52 with the power device 11, and the cross section area of the diffuser section is gradually increased from small to large so as to reduce the energy loss of airflow; the tail end of the diffusion section 51 is connected with the centrifugal fan 12 through the expansion joint 4, the centrifugal fan 12 and the wind tunnel system 5 are connected through the expansion joint 4, vibration caused by the centrifugal fan 12 can be isolated, the scale deposition process of the experimental blade 7 is prevented from being influenced, and smooth measurement is ensured. Experiment section 52 open-top position sealing mounting has transparent material's sealed lid, is convenient for observe blade scaling process, the confession has been seted up on the sealed lid the banding through-hole that probe 63 removed, during the test, probe 63 stretches into experiment section 52 from the through-hole that seals on the lid to remove along the through-hole direction, set up sealed lid and can prevent to mix the air current that has the dust and flow from experiment section 52, pollute the laboratory air.
The powder feeding system 8 is fixedly arranged at the top of the stabilizing section 54, and the powder feeding system 8 comprises a powder cylinder 81, a box body 82 and a powder feeding pipe 84; the box body 82 is fixedly arranged at the top of the stabilizing section 54, the powder cylinder 81 is fixedly arranged at the top of the box body 82, the powder cylinder 81 is used for containing scale deposition particles, the powder feeding pipe 84 is communicated and arranged at the bottom of the box body 82, and the discharge end of the powder feeding pipe 84 extends into the stabilizing section 54; an adjusting structure is arranged in the box body 82, a powder feeding motor 83 is fixedly arranged on one side of the box body 82 and used for controlling the adjusting structure to adjust the powder feeding amount so as to simulate the flow of accumulated dirt particles in different flight environments, and the powder feeding motor 83 is a stepping motor. The adjusting structure is the prior art, and is not described herein in detail. The powder feeding speed of the powder feeding system 8 is positively correlated with the rotating speed of the powder feeding motor 83, the larger the rotating speed is, the larger the powder feeding speed is, the powder feeding amount can be accurately controlled by adjusting the rotating speed of the powder feeding motor 83, and the powder feeding amount adjusting range is 0.5-35g/min; during powder feeding, the scale particles are added into the powder cylinder 81, fall into the box 82, and are input into the wind tunnel system 5 through the powder feeding pipe 84 after the flow rate of the scale particles is adjusted.
An air outlet of the centrifugal fan 12 is connected with a pressure expansion chamber 3, a filter layer 2 is arranged at the top of the pressure expansion chamber 3, airflow is discharged into the pressure expansion chamber 3 from the air outlet of the centrifugal fan 12 to perform pressure expansion and speed reduction, the flow speed of the airflow is greatly reduced when the airflow reaches the filter layer 2, and the filter layer 2 is used for filtering out accumulated dirt particles which cannot be adhered to the experimental blade 7, so that the effect of protecting the environment is achieved, and air pollution is avoided; preferably, the filter layer 2 is made of filter cotton.
The using method of the aeroengine fouling simulation experiment testing equipment comprises the following steps:
step one, simulating an airflow environment
The driving motor 11 is turned on, the centrifugal fan 12 starts to operate, stable airflow is formed in the wind tunnel system 5, the air is guided and uniformly drawn through the stabilizing section 54, enters the contracting section 53 for uniform acceleration, enters the experiment section 52, simulates the actual flow field condition in the engine during the flight of the airplane, then enters the centrifugal fan 12 through the diffusing section 51, and is discharged after being filtered from the air outlet of the centrifugal fan 12;
step two, starting the powder feeding system 8
Turning on a powder feeding motor 83, conveying the scale particles into the wind tunnel system 5, controlling the powder feeding amount by adjusting the rotating speed of the powder feeding motor 83, conveying the scale particles from a powder cylinder 81 through a powder feeding pipe 84 into a stable section 54 of the wind tunnel system 5, fully mixing with airflow, and then reaching an experimental blade 7 in an experimental section 52 to simulate the scale state of an engine blade in the flight process;
step three, measuring parameters of experimental blade 7
The moving part adjusts the position and the angle of the probe 63, the probe 63 is located at a position behind the experimental blade 7 by a chord length distance, performance parameters of the experimental blade 7 in a fouling state are collected through the probe 63, and collected data are transmitted to the acquisition system to be analyzed.
The device highly restores the fouling condition of the airplane under the flying environment condition, has high measurement precision, can visually observe the fouling process, has small volume, high automation degree and simple and convenient operation process, can simulate different fouling states, is convenient to analyze the influence of the fouling on the aerodynamic performance of the engine blade, and ensures the safe operation of the aero-engine.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. This need not be, nor should it be exhaustive of all embodiments. And obvious variations or modifications of the invention may be made without departing from the spirit or scope of the invention.
Claims (10)
1. The aircraft engine scale deposition simulation experiment test equipment is characterized by comprising a powder feeding system (8), a measuring system (6) and a wind tunnel system (5), wherein the powder feeding system (8) is installed at the top of the air inlet end of the wind tunnel system (5), a power device (1) is installed at the tail end of the wind tunnel system (5), and the measuring system (6) is installed at the upper end of the middle part of the wind tunnel system (5);
the powder feeding system (8) is used for conveying scale particles into the wind tunnel system (5);
the measuring system (6) is used for measuring experiment parameters;
the power device (1) is used for providing stable airflow required by experiments.
2. The aircraft engine fouling simulation experiment testing equipment of claim 1, wherein the wind tunnel system (5) comprises a stabilizing section (54), a contracting section (53), an experimental section (52) and a diffusing section (51) which are connected in sequence;
the stabilizing section (54) is of a rectangular structure and is used for guiding and uniformly drawing an upstream incoming flow, a support frame is arranged at the bottom of the stabilizing section, and the powder feeding system (8) is arranged at the top of the stabilizing section;
the contraction section (53) is used for connecting the stable section (54) and the experimental section (52), the cross-sectional area of the contraction section is gradually reduced from large to small, the flow velocity of the airflow is increased, and the airflow in the stable section is uniformly accelerated and then enters the experimental section (52);
a plurality of experimental blades (7) are arranged in the experimental section (52), the experimental blades (7) are uniformly arranged at intervals along the diagonal direction of the top opening of the experimental section (52), a support frame is installed at the bottom of the experimental section (52), and the measuring system (6) is installed at the top of the experimental section;
the diffusion section (51) is of a conical structure and is used for connecting the experimental section (52) and the power device (1), and the cross section area of the diffusion section is gradually increased from small to large so as to reduce the energy loss of airflow.
3. The aircraft engine fouling simulation experiment testing equipment of claim 1, wherein the power device (1) comprises a centrifugal fan (12) and a driving motor (11), the centrifugal fan (12) is installed at the tail end of the wind tunnel system (5), and the driving motor (11) is fixedly installed at the rear end of the centrifugal fan (12).
4. An aeroengine fouling simulation experiment testing equipment according to claim 3, wherein the air outlet of the centrifugal fan (12) is connected with a pressure expansion chamber (3), the pressure expansion chamber (3) is used for reducing the flow velocity of the air flow, a filtering layer (2) is arranged on the top of the pressure expansion chamber (3), and the filtering layer (2) is used for filtering out redundant fouling particles.
5. An aircraft engine fouling simulation experiment testing equipment according to claim 3, characterized in that an expansion joint (4) is installed between the centrifugal fan (12) and the tail end of the wind tunnel system (5).
6. The aircraft engine fouling simulation experiment testing equipment of claim 2, wherein a sealing cover made of transparent materials is installed on the top opening of the experiment section (52), and a through hole which is long and is used for the probe (63) to move is formed in the sealing cover.
7. An aircraft engine fouling simulation experiment testing equipment according to claim 1, characterized in that the measuring system (6) comprises a moving part and a probe (63), the probe (63) is vertically mounted on the moving part, and the moving part is used for driving the probe (63) to move and rotate;
the moving part comprises a base (67), a moving plate (69), a lifting plate (64) and a rotary table (65), the base (67) is fixedly mounted on the upper end face of the wind tunnel system (5), a guide rail (68) is mounted on the base (67), the moving plate (69) is slidably mounted on the guide rail (68), the lifting plate (64) is vertically fixedly mounted on the moving plate (69), the rotary table (65) is movably mounted on the side face of the lifting plate (64) up and down, and the probe (63) is mounted on the rotary table (65).
8. An aircraft engine fouling simulation experiment testing equipment according to claim 2, characterized in that the powder feeding system (8) comprises a powder cylinder (81), a box body (82) and a powder feeding pipe (84); the box body (82) is fixedly arranged at the top of the stabilizing section (54), the powder cylinder (81) is fixedly arranged at the top of the box body (82), the powder cylinder (81) is used for containing scale particles, the bottom of the box body (82) is communicated with and provided with the powder feeding pipe (84), and the discharge end of the powder feeding pipe extends into the stabilizing section (54); the powder feeding device is characterized in that an adjusting structure is arranged in the box body (82), and a powder feeding motor (83) is fixedly mounted on one side of the box body (82) and used for controlling the adjusting structure to adjust the powder feeding amount.
9. An aircraft engine fouling simulation experiment testing equipment according to claim 3, characterized in that the constriction section (53) is of a shift vickers curve structure.
10. Use of an aircraft engine fouling simulation test rig according to any of claims 1 to 9, characterized in that it comprises the following steps:
step one, simulating an airflow environment
The driving motor (11) is turned on, the centrifugal fan (12) starts to operate, stable airflow is formed in the wind tunnel system (5), and the actual flow field condition inside the engine in the flight process of the airplane is simulated;
step two, start the powder feeding system (8)
Turning on a powder feeding motor (83), conveying the scale particles into a wind tunnel system (5), controlling the powder feeding amount by adjusting the rotating speed of the powder feeding motor (83), and simulating the scale state of an engine blade in the flight process;
step three, measuring parameters of the experimental blade (7)
The position and the angle of the probe (63) are adjusted by the moving part, the probe (63) is located at a position behind the experimental blade (7) by a chord length distance, the performance parameters of the experimental blade (7) in a fouling state are collected through the probe (63), and the collected data are transmitted to the acquisition system for analysis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211092863.7A CN115420511B (en) | 2022-09-08 | 2022-09-08 | Aeroengine scale simulation experiment test equipment and application method thereof |
Applications Claiming Priority (1)
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| CN103954452A (en) * | 2014-05-04 | 2014-07-30 | 南京航空航天大学 | Aero-engine gas path fault static electricity monitoring and simulating experiment platform and use method |
| US20160363505A1 (en) * | 2015-06-12 | 2016-12-15 | The Boeing Company | Wind tunnel for erosion testing |
| CN113654976A (en) * | 2021-08-13 | 2021-11-16 | 北京航空航天大学 | Aeroengine high pressure rotor blade service environment simulation device |
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| CN103954452A (en) * | 2014-05-04 | 2014-07-30 | 南京航空航天大学 | Aero-engine gas path fault static electricity monitoring and simulating experiment platform and use method |
| US20160363505A1 (en) * | 2015-06-12 | 2016-12-15 | The Boeing Company | Wind tunnel for erosion testing |
| CN113654976A (en) * | 2021-08-13 | 2021-11-16 | 北京航空航天大学 | Aeroengine high pressure rotor blade service environment simulation device |
Non-Patent Citations (1)
| Title |
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| 殷逸冰;左洪福;文振华;蔡景;付宇;: "航空发动机吸入颗粒物静电感应特性的模拟实验及分析", 航空学报, no. 02, 25 February 2015 (2015-02-25) * |
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