CN212110579U - Aero-engine pre-film atomized liquid film measuring device and test system - Google Patents
Aero-engine pre-film atomized liquid film measuring device and test system Download PDFInfo
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- CN212110579U CN212110579U CN202020733782.0U CN202020733782U CN212110579U CN 212110579 U CN212110579 U CN 212110579U CN 202020733782 U CN202020733782 U CN 202020733782U CN 212110579 U CN212110579 U CN 212110579U
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Abstract
The utility model relates to an aeroengine pre-film atomization liquid film measuring device and a test system, wherein the liquid film measuring device comprises a wind tunnel (1), a light-permeable first window (11) is arranged on the bottom surface of the wind tunnel (1), a liquid inlet (13) and an air inlet (14) are arranged on the wind tunnel (1), so that the liquid entering from the liquid inlet (13) is atomized by compressed gas entering from the air inlet (14), a liquid film is formed on the bottom surface of the wind tunnel (1), and the liquid film is provided with fluorescent substances; a laser emitting member (2) provided below the wind tunnel (1) and configured to emit laser light; the lens group (3) is arranged between the laser emitting component (2) and the wind tunnel (1), is configured to modulate the laser emitted by the laser emitting component (2) into sheet laser and irradiates the sheet laser to the first window (11); and an imaging unit (4) disposed below the wind tunnel (1) and configured to image the fluorescence signal so as to measure the liquid film by the spatial distribution of the fluorescence signal.
Description
Technical Field
The utility model relates to an aeroengine tests and measures technical field, especially relates to an aeroengine pre-filming atomizing liquid film measuring device and test system.
Background
Currently, high-speed micron-sized liquid films are widely applied in a series of industrial fields, in particular to key fields such as fuel atomization process in the field of energy and power. In the fuel oil atomization process of the pre-filming atomization test system of the aircraft engine, fuel oil forms a high-speed moving oil film on the venturi under the action of high-speed airflow, and then the oil film forms spray through secondary atomization, so that the process has great influence on combustion organization forms and pollutant generation. Therefore, the development of a method for measuring the thickness and the speed of the thin oil film in a high-speed motion state is urgently needed to meet the requirements of industrial application of energy, power and the like at present.
Currently, liquid film measurement is mainly based on electrical measurement and optical measurement. The electric measurement method uses the principle of capacitance or resistance, uses electrodes to measure the liquid film, and when the thickness of the liquid film changes, the current passing through the electrodes also changes, thereby realizing the measurement of the thickness of the liquid film. The electric measurement method has the advantage of short response time, but the spatial resolution is poor, and meanwhile, the electrodes can generate disturbance on the liquid film, so that the measurement precision is reduced. At present, the optical measurement method uses the properties of light absorption, reflection and the like to measure the liquid film, and although the optical measurement method has no disturbance on the liquid film, the thickness of the liquid film is still difficult to accurately measure due to the influence of refraction at a gas-liquid interface.
SUMMERY OF THE UTILITY MODEL
The embodiment of the disclosure provides a device and a test system for measuring a pre-film atomized liquid film of an aero-engine, which can more accurately measure parameters of the liquid film.
According to an aspect of the present disclosure, there is provided an aircraft engine pre-filming atomized liquid film measuring device, including:
the bottom surface of the wind tunnel is provided with a light-permeable first window, the wind tunnel is provided with a liquid inlet and a gas inlet so as to atomize liquid entering from the liquid inlet through compressed gas entering from the gas inlet and form a liquid film on the bottom surface of the wind tunnel, and the liquid film is provided with fluorescent substances;
the laser emitting component is arranged below the wind tunnel and is configured to emit laser;
the mirror group is arranged between the laser emission component and the wind tunnel, is configured to modulate the laser emitted by the laser emission component into sheet laser and irradiates the sheet laser to the first window; and
and the shooting component is arranged below the wind tunnel and is configured to shoot the fluorescence signal so as to measure the liquid film through the spatial distribution of the fluorescence signal.
In some embodiments, the air inlet is arranged on a first side surface of the wind tunnel, the liquid inlet is arranged at the top of the wind tunnel and close to the first side surface, the wind tunnel is further provided with an air outlet, and the air outlet is arranged on a second side surface opposite to the first side surface.
In some embodiments, the liquid inlet and the gas inlet are configured to allow liquid and gas to enter the wind tunnel in mutually perpendicular directions.
In some embodiments, the first window is elongate and extends in the direction of flow of the liquid film.
In some embodiments, the top of the wind tunnel is provided with a second window which is transparent to light and is configured to enable the laser light which is remained after being absorbed by the fluorescent substance to be emitted, and the projection of the second window on the bottom surface of the wind tunnel covers the first window.
In some embodiments, the laser emitting component includes two lasers, and the lasers emitted by the two lasers are incident from the same position of the first window after being modulated by the lens group.
In some embodiments, the first window extends in a flow direction of the liquid film, the liquid film measuring apparatus further comprising:
and the translation mechanism is configured to drive the laser emission component, the lens group and the shooting component to move along the flow direction of the liquid film so as to measure the parameter distribution of the liquid film along the flow direction.
In some embodiments, the shooting direction of the shooting part intersects with the emitted laser at the liquid film, and the shooting direction is obliquely arranged relative to the bottom surface of the wind tunnel.
In some embodiments, the liquid film measuring device further comprises a filter, which is arranged between the shooting component and the bottom surface of the wind tunnel and is configured to eliminate interference of scattered incident laser light on the intensity of the fluorescence signal.
In some embodiments, the liquid film measuring apparatus further includes a controller, connected to the photographing part, configured to obtain the thickness of the liquid film through a boundary of a fluorescence region in a single picture photographed by the photographing part; and/or obtaining the liquid film speed through two pictures at preset time intervals.
According to another aspect of the present disclosure, there is provided an aircraft engine prefilming atomization testing system, comprising:
the aeroengine pre-film atomized liquid film measuring device of the embodiment;
the liquid supply subsystem is communicated with the liquid inlet and is configured to supply liquid containing fluorescent substances into the wind tunnel through the liquid inlet; and
and the air supply subsystem is communicated with the air inlet and is configured to supply compressed air into the wind tunnel through the air inlet.
In some embodiments, the assay system further comprises:
the first regulating valve is arranged on a pipeline communicated between the liquid supply subsystem and the liquid inlet and is configured to regulate the liquid supply speed; and/or
And a second regulating valve which is arranged on a pipeline communicated between the gas supply subsystem and the gas inlet and is configured to regulate the supply speed of the compressed gas.
In some embodiments, the test system further comprises an exhaust gas treatment subsystem comprising:
an oil mist separator configured to filter liquid droplets in an exhaust gas in the wind tunnel; and
a silencer configured to absorb noise of the exhaust gas in the wind tunnel.
The device for measuring the pre-film atomized liquid film of the aero-engine provided by the embodiment of the disclosure measures the liquid film parameters by using a planar laser induced fluorescence technology, and has the advantages of high spatial and temporal resolution, no interference and the like. Moreover, because the laser irradiates the liquid film from the lower part outside the wind tunnel through the first window and shoots the fluorescence through the shooting component arranged below the wind tunnel, the problems that the fluorescence is refracted at a gas-liquid interface in the process of being transmitted to the shooting component due to the surface fluctuation of the liquid film and the transmission direction of the fluorescence is changed can be solved, a clear fluorescence image can be obtained, the parameter of the plane liquid film can be accurately obtained, and the accuracy and the effectiveness of measurement are improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the disclosure and together with the description serve to explain the disclosure and not to limit the disclosure. In the drawings:
FIG. 1 is a schematic structural diagram of one embodiment of a prefilming atomization testing system for an aircraft engine according to the present disclosure;
FIG. 2 is a schematic view of the working principle of the aero-engine pre-film atomized liquid film measuring device of the present disclosure.
Description of the reference numerals
1. A wind tunnel; 11. a first window; 12. a second window; 13. a liquid inlet; 14. an air inlet; 15. an exhaust port; 2. a laser emitting part; 21. a laser; 3. a lens group; 4. a photographing part; 5. a filter; 6. a controller; 7. a liquid supply subsystem; 71. a first regulating valve; 8. a gas supply subsystem; 81. a second regulating valve; 9. a tail gas treatment subsystem; 91. an oil mist separator; 92. a muffler.
Detailed Description
The present disclosure is described in detail below. In the following paragraphs, different aspects of the embodiments are defined in more detail. Aspects so defined may be combined with any other aspect or aspects unless clearly indicated to the contrary. In particular, any feature considered to be preferred or advantageous may be combined with one or more other features considered to be preferred or advantageous.
The terms "first", "second", and the like in the present disclosure are merely for convenience of description to distinguish different constituent elements having the same name, and do not denote a sequential or primary-secondary relationship.
In the description of the present invention, it is to be understood that the terms "inner", "outer", "upper", "lower", "left" and "right", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention, and do not indicate or imply that the device referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the scope of the present invention.
Based on a great deal of principle thinking and technical research, the inventor finds that the Planar Laser Induced Fluorescence (PLIF) technology has the advantages of high spatial and temporal resolution, no interference and the like, and is applied to liquid film thickness measurement.
However, the premise of utilizing PLIF technology to realize the thickness and speed measurement of the high-speed micron-sized flat liquid film is to solve the problem of refraction at the interface position in the process of transmitting fluorescence to a camera. This is because the liquid film surface has a certain fluctuation under the action of the high-speed gas flow, and the fluorescence is refracted when it is transmitted to the gas-liquid interface, so that the transmission direction of the fluorescence is changed, and it is difficult to obtain a clear liquid film image.
If the PLIF method is applied to the measurement of the liquid film in the circular pipeline, the circular pipeline has a certain curvature, so that the interface refraction phenomenon can be avoided when the curvature is larger than the surface fluctuation curvature of the liquid film, and the measurement of the liquid film is realized. However, for the flat liquid film, since the curvature of the wall surface is 0, the surface of the liquid film is seriously affected during measurement, and an effective measurement result cannot be obtained.
In view of this, the present disclosure provides a device for measuring a liquid film of pre-film atomization of an aircraft engine, and the following "liquid film measuring device" for short is used for carrying out pre-film atomization on fuel oil of the engine. As shown in fig. 1, in some embodiments, a liquid film measuring apparatus includes: the device comprises a wind tunnel 1, a laser emitting component 2, a lens group 3 and a shooting component 4.
The wind tunnel 1 is a component for generating airflow and controlling the airflow in an artificial mode, a light-permeable first window 11 is arranged on the bottom surface of the wind tunnel 1, a liquid inlet 13 and an air inlet 14 are arranged on the wind tunnel 1, so that liquid entering from the liquid inlet 13 is atomized through compressed air entering from the air inlet 14, a high-speed micron-sized motion liquid film is formed on the bottom surface of the wind tunnel 1, fluorescent substances are contained in the liquid film, and the liquid film flows along the direction K in the figure 1.
The laser emitting unit 2 is provided outside the wind tunnel 1 and below the wind tunnel 1, and is configured to emit laser light. The lens group 3 is arranged between the laser emitting component 2 and the wind tunnel 1, and is configured to modulate the laser emitted by the laser emitting component 2 into sheet laser, and irradiate the sheet laser to the first window 11, and the plane where the sheet laser is located is perpendicular to the flow direction K of the liquid film.
The imaging component 4 is disposed outside and below the wind tunnel 1 and is configured to image the fluorescence signal so as to measure the liquid film by the spatial distribution of the fluorescence signal. The method for measuring the liquid film utilizes the principle of plane laser induced fluorescence, namely, fluorescent substances emit fluorescence after absorbing exciting light, laser is modulated into sheet laser to be used for illuminating a plane area vertical to the flow direction K of the liquid film, and the fluorescence signal is captured by using the shooting part 4 to be used for measuring parameters of the liquid film in the plane, such as the thickness, the flow speed and other information of the liquid film.
The liquid film measuring device of the embodiment utilizes the plane laser induced fluorescence technology, and has the advantages of high spatial and temporal resolution, no interference and the like. Moreover, since the laser irradiates the liquid film from the lower part of the outer surface of the wind tunnel 1 through the first window 11 and shoots the fluorescence through the shooting component 4 arranged below the outer surface of the wind tunnel 1, the problems that the fluorescence is refracted at a gas-liquid interface in the process of being transmitted to the shooting component 4 due to the surface fluctuation of the liquid film and the transmission direction of the fluorescence is changed can be solved, a clear fluorescence image can be obtained, so that the parameter of the plane liquid film can be accurately obtained, and the accuracy and the effectiveness of measurement are improved.
In addition, atomized liquid drops are generated above the liquid film when the liquid is atomized, so that a fluorescent image is difficult to clearly shoot, the atomized liquid drops easily pollute the laser emitting component 2 and the shooting component 4, the laser emitting component 2 and the shooting component 4 are arranged at the bottom of the wind tunnel, the laser emitting component 2 and the shooting component 4 can be prevented from being polluted, the service life of the testing equipment can be prolonged, and the accuracy and the effectiveness of measurement can be improved.
As shown in fig. 1, the air inlet 14 is disposed on a first side surface of the wind tunnel 1, the liquid inlet 13 is disposed at a position close to the first side surface on the top of the wind tunnel 1, the wind tunnel 1 is further provided with an air outlet 15, the air outlet 15 is disposed on a second side surface opposite to the first side surface, and the air outlet 15 can be disposed opposite to the air inlet 14. For example, the wind tunnel 1 has a rectangular parallelepiped structure, the cross section perpendicular to the flow direction K of the liquid film may be square, the liquid film flows along the length direction of the wind tunnel 1, and the air inlet 14 and the air outlet 15 are disposed in the middle region of the wind tunnel 1 along the height direction and the width direction, so that the thickness distribution of the liquid film perpendicular to the flow direction K is uniform.
According to the embodiment, liquid can be atomized by high-pressure gas immediately after entering the wind tunnel 1, so that the entering liquid is atomized more sufficiently, and a high-speed micron-sized flat liquid film based on transverse jet flow energy is formed on the bottom surface of the wind tunnel 1, so that a working scene when an engine fuel nozzle atomizes oil is simulated more accurately, and the test is closer to the real working scene of an aircraft engine.
As shown in fig. 1, the liquid inlet 13 and the gas inlet 14 are configured to allow liquid and gas to enter the wind tunnel 1 in mutually perpendicular directions. The structure can improve the impact force of the compressed gas on the liquid entering the wind tunnel 1 to the maximum extent so as to improve the atomization degree of the liquid.
In some embodiments, the first window 11 is elongated and extends in the flow direction K of the liquid film. For example, the first window 11 may be made of glass. The first window 11 may extend along the entire length of the liquid film flow to flexibly select a certain position on the liquid film flow path for parameter measurement, thereby enabling obtaining a parameter distribution of the liquid film in the flow direction K.
In some embodiments, the top of the wind tunnel 1 is provided with a second window 12 which is transparent to light and is configured to emit the laser light remaining after being absorbed by the fluorescent substance, and the projection of the second window 12 on the bottom surface of the wind tunnel 1 covers the first window 11, and this structure enables the laser light which is not absorbed by the fluorescent light to be sufficiently emitted because the laser light travels along a straight line. For example, the second window 12 may be made of glass.
The embodiment can provide a laser incidence channel and a channel for transmitting fluorescence to the shooting component 4 through the first window 11, and can enable laser which is not completely absorbed by fluorescent substances to be emitted through the second window 12, so that the part of the unabsorbed laser is prevented from being reflected in the cavity of the wind tunnel 1 to influence measurement, and the measurement accuracy is improved.
As shown in fig. 1, the laser emitting component 2 includes two lasers 21, and the lasers emitted by the two lasers 21 are modulated by the mirror group 3 and then enter the wind tunnel 1 from the same position of the first window 11. The timing of the two lasers 21 and the camera 4 is controlled by the controller 6. The two lasers 21 have a large adjustable range by using time sequence control, and can be applied to liquid film speed measurement under different flow rates. The incident directions are consistent all the time, and the installation position has no special requirements. For example, two lasers 21 are spaced apart along the flow direction K of the liquid film, and their respective emitted laser beams finally enter in a direction perpendicular to the first window 11 after passing through the mirror group 3. The lens group 3 may include a plano-convex cylindrical lens, a plano-concave cylindrical lens, a beam combiner, and the like.
In some embodiments, the first window 11 extends in the flow direction K of the liquid film, and the liquid film measuring apparatus further comprises: and the translation mechanism is configured to drive the laser emission component 2, the lens group 3 and the shooting component 4 to move along the flow direction K of the liquid film so as to measure the parameter distribution of the liquid film along the flow direction K.
This embodiment enables the laser 21, the mirror group 3 and the photographing part 4 to be moved synchronously by the translation mechanism to obtain the spatial distribution of the liquid film thickness in the flow direction K by measuring the liquid film parameters, such as the liquid film thickness, of a plurality of sections of the liquid film in the flow direction K, so as to more comprehensively obtain the overall information of the liquid film parameters.
As shown in fig. 2, the shooting direction of the shooting component 4 intersects with the laser emitted by the laser emitting component 2 at the liquid film, and the shooting direction is inclined relative to the bottom surface of the wind tunnel 1, that is, the shooting direction of the shooting component 4 forms an included angle a with the bottom surface of the first window 11. For example, the laser light emitted from the laser emitting part 2 is perpendicular to the first window 11, and the photographing part 4 is located at one side of the laser emitting part 2 in the flow direction K of the liquid film so as to photograph the boundary region of the fluorescence in the section where the incident laser light is located to obtain the thickness of the liquid film. In fig. 2, a indicates the direction of the incident laser beam, and B indicates the direction in which the fluorescence propagates to the imaging element 4.
Preferably, the shooting part 4 is arranged at one side of the laser emitting part 2 and is close to the laser emitting part 2, so that when the fluorescence in the section where the incident laser is positioned is transmitted to the shooting part 4, the longer distance of the transmission of the fluorescence in the liquid film in the flowing direction K of the liquid film can be reduced, the degree of refraction is reduced, the shot fluorescence image is clearer, and the measurement precision of the parameters of the liquid film is further improved.
As shown in fig. 1, the liquid film measuring apparatus further includes a filter 5 disposed between the imaging unit 4 and the bottom surface of the wind tunnel 1, and configured to eliminate interference of the scattered incident laser light with the intensity of the fluorescence signal. This embodiment enables the photographing part 4 to obtain a more accurate fluorescence image to improve measurement accuracy.
As shown in fig. 1, the liquid film measuring apparatus further includes a controller 6 connected to the photographing part 4 and configured to obtain a thickness of the liquid film through a boundary of a fluorescence region in a single picture photographed by the photographing part 4; and/or obtaining the liquid film speed through two pictures at preset time intervals. Specifically, the corresponding size of a single pixel in a picture is obtained according to a calibration result before an experiment, the moving distance can be obtained by comparing the moving pixels of the liquid film at the moments t1 and t2, and the liquid film speed can be obtained according to the preset time interval of the distance.
The embodiment can calculate the thickness or speed of the liquid film through the fluorescence image obtained by the shooting part 4, and can improve the accuracy and the automation degree of measurement.
Secondly, this disclosure also provides an aeroengine prefilming atomization test system, in some embodiments, includes: the aeroengine pre-film atomized liquid film measuring device of the embodiment; a liquid supply subsystem 7, which is communicated with the liquid inlet 13 and is configured to supply liquid containing fluorescent substances into the wind tunnel 1 through the liquid inlet 13, for example, the liquid supply subsystem 7 comprises a liquid storage part and a pump; and the air supply subsystem 8 is communicated with the air inlet 14 and is configured to provide compressed air into the wind tunnel 1 through the air inlet 14, for example, the air supply subsystem 8 comprises an air compressor and the like, a porous medium can be arranged at the air inlet 14 to homogenize the air flow so as to form a uniform flow field with a specific speed in the wind tunnel 1, so that the high-pressure air can fully and uniformly atomize the liquid after entering the wind tunnel 1 so as to form a high-speed flat liquid film on the inner bottom surface of the wind tunnel 1.
As shown in fig. 1, the testing system further comprises: a first regulating valve 71 provided on a pipe communicating between the liquid supply subsystem 7 and the liquid inlet 13 and configured to regulate a liquid supply speed; and/or a second regulating valve 81 provided on a conduit communicating between the gas supply subsystem 8 and the gas inlet 14, configured to regulate the supply rate of the compressed gas.
The embodiment can flexibly adjust the liquid supply speed and the air supply speed so as to enable the forming working condition of the liquid film in the wind tunnel 1 to be closer to the working condition of the pre-film atomized liquid film of the aero-engine, thereby enabling the test to be closer to the real condition.
In some embodiments, the test system further comprises an exhaust gas treatment subsystem 9, the exhaust gas treatment subsystem 9 comprising: an oil mist separator 91 configured to filter liquid droplets in the exhaust gas in the wind tunnel 1; and a muffler 92 configured to absorb noise of the exhaust gas in the wind tunnel 1. This embodiment can reduce the environmental pollution caused by the gas exhausted from the test system.
When the test system provided by the embodiment of the disclosure is used for testing, the following steps can be adopted:
step 1: and (5) preparing. Turning on the power supply of the high-pressure gas source in the liquid feeding subsystem 7 and the gas supply subsystem 8, and setting related parameters; the oil mist separator 91 and the muffler 92 are opened. The power of the laser 21 and the photographing part 4 is turned on and relevant parameters are set.
Step 2: and starting a high-pressure air source to form a high-speed uniform flow field in the high-speed wind tunnel.
And step 3: and starting a liquid sample injection pump to inject liquid into the high-speed wind tunnel, and forming a high-speed micron-sized flat liquid film on a first window 11 at the bottom of the wind tunnel 1.
And 4, step 4: the laser 21 and the photographing part 4 are controlled by the controller 6 to photograph a fluorescent image.
After all experiments are finished, the power supplies of the laser 21 and the shooting part 4 are turned off, the liquid sample injection pump is turned off, the high-pressure gas source is turned off when no liquid remains in the pipeline, and then the high-pressure gas source and the liquid sample injection pump power supply are turned off. Finally, the experimental data are saved, and all instruments and equipment are closed.
The device and the test system for measuring the pre-film atomized liquid film of the aero-engine provided by the disclosure are described in detail above. The principles and embodiments of the present disclosure are explained herein using specific examples, which are set forth only to help understand the method and its core ideas of the present disclosure. It should be noted that, for those skilled in the art, it is possible to make several improvements and modifications to the present disclosure without departing from the principle of the present disclosure, and such improvements and modifications also fall within the scope of the claims of the present disclosure.
Claims (13)
1. The utility model provides an aeroengine prefilming atomizing liquid film measuring device which characterized in that includes:
the liquid atomization device comprises a wind tunnel (1), wherein a light-permeable first window (11) is arranged on the bottom surface of the wind tunnel (1), a liquid inlet (13) and an air inlet (14) are formed in the wind tunnel (1), so that liquid entering from the liquid inlet (13) is atomized through compressed gas entering from the air inlet (14), a liquid film is formed on the bottom surface of the wind tunnel (1), and fluorescent substances are contained in the liquid film;
a laser emitting component (2) arranged below the wind tunnel (1) and configured to emit laser;
the mirror group (3) is arranged between the laser emitting component (2) and the wind tunnel (1), is configured to modulate the laser emitted by the laser emitting component (2) into sheet laser and irradiates the first window (11); and
and the shooting component (4) is arranged below the wind tunnel (1) and is configured to shoot the fluorescence signal so as to measure the liquid film through the spatial distribution of the fluorescence signal.
2. The device for measuring the pre-film atomized liquid film of the aircraft engine according to claim 1, wherein the air inlet (14) is arranged on a first side surface of the wind tunnel (1), the liquid inlet (13) is arranged at a position, close to the first side surface, of the top of the wind tunnel (1), an air outlet (15) is further arranged on the wind tunnel (1), and the air outlet (15) is arranged on a second side surface opposite to the first side surface.
3. The aircraft engine prefilming atomized liquid film measurement device according to claim 2, characterized in that the liquid inlet (13) and the gas inlet (14) are configured to let liquid and gas enter the wind tunnel (1) in mutually perpendicular directions.
4. The aircraft engine prefilming atomized liquid film measurement device according to claim 1, characterized in that the first window (11) is elongated and extends in the flow direction (K) of the liquid film.
5. The device for measuring the atomized liquid film of the aircraft engine prefilming according to claim 1, characterized in that a second light-permeable window (12) is arranged at the top of the wind tunnel (1) and is configured to emit the laser light left after being absorbed by the fluorescent substance, and the projection of the second window (12) on the bottom surface of the wind tunnel (1) covers the first window (11).
6. The device for measuring the atomized liquid film of the aircraft engine pre-film according to claim 1, wherein the laser emitting component (2) comprises two lasers (21), and the lasers emitted by the two lasers (21) are modulated by the lens group (3) and then enter from the same position of the first window (11).
7. The aircraft engine prefilming atomized liquid film measuring device according to claim 1, characterized in that the first window (11) extends in the flow direction (K) of the liquid film, the liquid film measuring device further comprising:
the translation mechanism is configured to drive the laser emission component (2), the lens group (3) and the shooting component (4) to move along the flow direction (K) of the liquid film so as to measure the parameter distribution of the liquid film along the flow direction (K).
8. The device for measuring the atomized liquid film of the aircraft engine prefilming according to claim 1, characterized in that the shooting direction of the shooting component (4) intersects with the emitted laser at the liquid film, and the shooting direction is obliquely arranged relative to the bottom surface of the wind tunnel (1).
9. The device for measuring the atomized liquid film of the aircraft engine prefilming according to claim 1, further comprising a filter (5) arranged between the shooting component (4) and the bottom surface of the wind tunnel (1) and configured to eliminate interference of scattered incident laser light on the intensity of the fluorescence signal.
10. The device for measuring the atomized liquid film of the aircraft engine according to claim 1, further comprising a controller (6) connected to the shooting component (4) and configured to obtain the thickness of the liquid film through the boundary of the fluorescence area in a single picture shot by the shooting component (4); and/or obtaining the moving distance of the liquid film through the moving pixels of the liquid film in the two pictures at the preset time interval so as to obtain the speed of the liquid film.
11. The utility model provides an aeroengine prefilming atomization test system which characterized in that includes:
the aircraft engine pre-film atomized liquid film measuring device according to any one of claims 1 to 10;
a liquid supply subsystem (7) in communication with the liquid inlet (13) and configured to supply liquid containing fluorescent substances into the wind tunnel (1) through the liquid inlet (13); and
a gas supply subsystem (8) in communication with the gas inlet (14) configured to provide compressed gas into the wind tunnel (1) through the gas inlet (14).
12. The aircraft engine prefilming atomization testing system of claim 11, further comprising:
a first regulating valve (71) arranged on a pipeline communicated between the liquid supply subsystem (7) and the liquid inlet (13) and configured to regulate the liquid supply speed; and/or
A second regulating valve (72) provided on a line communicating between the gas supply subsystem (8) and the gas inlet (14) and configured to regulate a supply rate of the compressed gas.
13. The aircraft engine prefilming atomization testing system according to claim 11, further comprising an exhaust gas treatment subsystem (9), the exhaust gas treatment subsystem (9) comprising:
an oil mist separator (91) configured to filter liquid droplets in the exhaust gas in the wind tunnel (1); and
a silencer (92) configured to absorb noise of exhaust gases within the wind tunnel (1).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116255279A (en) * | 2023-05-15 | 2023-06-13 | 北京航空航天大学 | Device for measuring jet gas-liquid interface in closed space |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116255279A (en) * | 2023-05-15 | 2023-06-13 | 北京航空航天大学 | Device for measuring jet gas-liquid interface in closed space |
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