CN114061964A - Multifunctional atomization test system - Google Patents
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- CN114061964A CN114061964A CN202111333009.0A CN202111333009A CN114061964A CN 114061964 A CN114061964 A CN 114061964A CN 202111333009 A CN202111333009 A CN 202111333009A CN 114061964 A CN114061964 A CN 114061964A
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- 238000012360 testing method Methods 0.000 title abstract description 15
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- 239000007921 spray Substances 0.000 claims abstract description 86
- 239000003380 propellant Substances 0.000 claims abstract description 40
- 238000002474 experimental method Methods 0.000 claims abstract description 34
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- 238000005507 spraying Methods 0.000 claims abstract description 26
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a multifunctional atomization test system, which comprises a high-pressure atomization test system, a normal-pressure atomization test system and a propellant supply system, wherein the high-pressure atomization test system is connected with the propellant supply system; the high-pressure atomization experiment system comprises a high-pressure atomization cabin and a first spray cone angle measuring device; the normal-pressure atomization experiment system comprises a normal-pressure spraying device, a second spraying cone angle measuring device and a spraying particle size measuring device; the normal pressure spraying device comprises a nozzle and a nozzle height adjusting frame; the spray particle size measuring device comprises a height lifting frame, a sliding rod and a laser particle size analyzer; the propellant supply system can be used for supplying gas-liquid or liquid-liquid two-component propellant to the nozzle in the high-pressure atomizing cabin or the nozzle on the nozzle height adjusting frame. The invention can carry out atomization experiments under various environments, such as normal pressure atomization experiments, high back pressure atomization experiments, atomization experiments under flow pulsation, atomization experiments of various spraying media, and accurate measurement of spray cone angle and liquid film breaking length.
Description
Technical Field
The invention relates to the field of rocket engines, in particular to a multifunctional atomization test system.
Background
The liquid rocket engine plays an important role in various aerospace activities such as spacecraft launching, attitude control, orbit transfer and the like, and widely undertakes various aerospace tasks such as manned lunar landing, Mars exploration, deep space exploration and the like. In order to ensure the smooth operation of the space mission, the high reliability of the liquid rocket engine needs to be ensured, but the unstable high-frequency combustion becomes an important factor for inhibiting the development of the liquid rocket engine.
Because the high-frequency combustion instability test of the full-size liquid rocket engine is high in risk, high in test cost and long in processing period, in order to improve the test efficiency, researchers mostly develop a scale-down simulation test, and atomization is an important sub-process in a combustion chamber and is naturally concerned.
Since the combustion zone is generally concentrated in the spray zone, the spray cone angle is too small, which may result in an insufficient atomization process and thus a low combustion efficiency. Too large a spray cone angle may result in propellant being sprayed directly onto the inner wall of the combustion chamber, causing erosion and burning through the inner wall, and therefore it is highly desirable to measure the spray cone angle.
The method is simple and direct, but has strong subjectivity, and particularly when the image boundary is fuzzy, the research result can be caused to have large errors. In recent years, in order to improve the accuracy of the fog cone angle extraction, an image detection technology based on machine vision is being developed and applied. Among them, the threshold method based on the MATLAB platform has been applied to the study of the atomization cone angle. The basic principle of the thresholding method is to obtain a boundary by performing region segmentation by setting a threshold value of pixel brightness. However, this method still has disadvantages, the biggest drawback being that there is a great subjective randomness in the threshold setting.
In order to simulate the nozzle outlet atomization environment when high-frequency combustion is unstable, a back pressure atomization condition capable of generating high-frequency large-amplitude pulsation needs to be constructed, so that the influence of high-frequency combustion instability on the nozzle atomization characteristic is researched.
The flow pulsation source of the liquid propellant mainly comprises two parts: 1: the liquid rocket engine can generate violent vibration during combustion, and the propellant pipeline and the engine are fixed together, so that the vibration of the engine can cause the propellant pipeline to vibrate, and the liquid flow in the propellant pipeline is pulsed. 2: when the engine is unstable in combustion, the pressure in the combustion chamber fluctuates, the pressure in the combustion chamber is transmitted upstream through the nozzle, and the flow of the propellant is also pulsated.
Because the method for constructing the high-frequency large-amplitude pulsating back pressure atomization condition needs to simultaneously meet two factors of high frequency and large single-pulse energy due to the energy input source, the realization difficulty is high, so related research in the aspect is basically in a blank stage, researchers try to simulate the disturbance source by using a loudspeaker, but because the energy is limited, the frequency reaches the standard, but the amplitude is too low, and the requirement for constructing the high-frequency large-amplitude pulsating back pressure atomization condition is difficult to meet. And the pulsation is generated by a piston type pulsation device, namely liquid enters a piston cavity, and then the flow of the liquid is changed by the rapid compression of the piston, but the motion mode of the piston is linear motion, so that the frequency is limited to be incapable of reaching the frequency required by the experiment.
The non-uniformity of the droplet distribution and the droplet size in the combustion chamber can cause the non-uniformity of the heat release of the combustion, and the non-uniformity of the heat release directly causes the non-uniformity of the spatial pressure distribution in the combustion chamber. Therefore, the spray particle size needs to be measured, and the particle size of liquid drops in space is measured to obtain a distribution rule of the particle size of the liquid drops in space, so that guidance is provided for the design of an engine nozzle. The existing methods for measuring the droplet particle size are mainly classified into three types:
1. the mechanical method comprises the following steps: such as freezing or cooling the droplets into solid particles. Mechanical methods are not suitable due to the need to measure the droplet size in a specific region.
2. The electrical method comprises the following steps: hot wire method and charging wire method. Electrical methods are suitable for measuring the size of a single droplet size and therefore cannot measure spraying a large number of droplets.
3. The optical method comprises the following steps: by using the physical characteristics (light intensity, phase difference, fluorescence, polarization and the like) of the liquid drop to carry out measurement, high-speed photography, laser holography, laser Doppler and laser imaging. The optical measurement method is mostly adopted, and through comparison of various measurement methods, the laser particle analyzer is found to be more suitable for being applied to the spray generated by the liquid rocket nozzle, the laser particle analyzer is convenient and quick to test, multiple groups of data are measured within set time, and more accurate and stable data can be obtained. The output data is rich and visual: the method can dynamically detect the particle size of the liquid drops, and can process various data such as average particle size, Sotel diameter and the like.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide a multifunctional atomization test system, which can perform atomization experiments under various environments, such as normal pressure atomization experiments, high back pressure atomization experiments, atomization experiments under flow pulsation, atomization experiments of various spraying media, and accurate measurement of spray cone angle and liquid film breaking length.
In order to solve the technical problems, the invention adopts the technical scheme that:
a multifunctional atomization experiment system comprises a high-pressure atomization experiment system, a normal-pressure atomization experiment system and a propellant supply system.
The high-pressure atomization experiment system comprises a high-pressure atomization cabin and a first spray cone angle measuring device.
The side wall of the high-pressure atomization cabin is provided with at least two observation windows which are positioned on the same straight line; the spray cone angle measuring device can measure the cone angle of the spray sprayed by the nozzle in the high-pressure atomization cabin through the observation window.
The normal-pressure atomization experiment system comprises a normal-pressure spraying device, a second spraying cone angle measuring device and a spraying particle size measuring device.
The normal pressure spraying device comprises a nozzle and a nozzle height adjusting frame; the nozzle is installed in the center of nozzle height adjustment frame, and nozzle height adjustment frame's height can go up and down.
And the second spray cone angle measuring device can measure the cone angle of the spray sprayed by the nozzles on the nozzle height adjusting frame.
The spray particle size measuring device comprises a height lifting frame, a sliding rod and a laser particle size analyzer.
The height lifting frame covers the periphery of the nozzle on the nozzle height adjusting frame and can lift.
The slide bar is slidably mounted at the top of the height lifting frame and can slide back and forth or left and right.
The laser emission end and the laser receiving end of the laser particle analyzer are symmetrically arranged on two sides of the nozzle on the nozzle height adjusting frame, and the top ends of the laser emission end and the laser receiving end of the laser particle analyzer are both arranged on the sliding rod.
The propellant supply system can be used for supplying gas-liquid or liquid-liquid two-component propellant to the nozzle in the high-pressure atomizing cabin or the nozzle on the nozzle height adjusting frame.
And the observation windows of the high-pressure atomization cabin are provided with hydrophobic films.
The first spray cone angle measuring device and the second spray cone angle measuring device both comprise a background light source, a semitransparent plate and a high-speed camera.
A background light source and a translucent plate in the first spray cone angle measuring device are arranged on one side of the high-pressure atomization cabin and are opposite to the observation window; the high-speed camera is arranged on one side of the high-pressure atomization cabin and is opposite to the observation window.
The translucent plate is a frosted translucent plate.
The propellant supply system comprises a first liquid storage tank, a second liquid storage tank and a gas storage tank; the first liquid storage tank and the second liquid storage tank are both communicated with the first propellant channel in the corresponding nozzle through liquid supply pipelines; flow pulsator are connected to the liquid supply pipelines of the first liquid storage tank and the second liquid storage tank; the air storage tank is communicated with the propellant channel two phases in the corresponding nozzle through an air supply pipeline.
Liquid supply pipelines of the first liquid storage tank and the second liquid storage tank are respectively provided with a liquid supply valve, a liquid supply flowmeter, a liquid supply electromagnetic valve and a pressure sensor; an air supply valve, an air supply flowmeter, an air supply electromagnetic valve and a pressure sensor are arranged on the air supply pipeline.
Pressure gauges are arranged on the first liquid storage tank, the second liquid storage tank and the gas storage tank.
Can be used for calculating the spray cone angle alpha, and the specific calculation method comprises the following steps.
Step 1, picture shooting: the high-speed camera continuously shoots 500 instantaneous conical spray photos according to a set time interval, so that the instability of two-phase flow and the fluctuation of a spray angle can be avoided.
Step 3, gray level processing: and (3) converting the time-averaged processed image obtained in the step (2) into a gray image.
Step 4, boundary extraction: and (3) extracting the image boundary and the image with the extracted boundary by applying an active contour model segmentation technology and carrying out iterative retrieval for a plurality of times.
Step 5, calculating a spray cone angle alpha: and determining the included angle between the image boundary and the vertical line as alpha/2 according to the boundary image extracted in the step 4.
The method for calculating the spray cone angle alpha further comprises a step 6 of calculating the broken length of the liquid film, and specifically comprises the following steps.
Step 6A, determining the pixel length: measuring the measured diameter D1 of the nozzle outlet on the boundary image according to the boundary image extracted in the step 4; in combination with the actual diameter value D of the nozzle outlet, a length value K for each pixel in the boundary image is obtained, K = D1/D.
Step 6B, finding the broken position of the liquid film: measuring the vertical height H of the conical spray in the boundary image according to the boundary image extracted in the step 4; then, taking the outlet of the nozzle as a starting point, the conical spraying position corresponding to 50% H is the found liquid film breaking position.
Step 6C, measuring the length value L1 of the liquid film broken image: at the liquid film breakup position, the diameter of the conical spray parallel to the nozzle exit diameter was measured as a liquid film breakup image length, and the liquid film breakup image length value was L1.
And 6D, calculating the liquid film breaking length L, wherein the specific calculation formula is as follows: l = L1/K.
The invention has the following beneficial effects:
1. the invention can carry out atomization experiments under various environments, such as normal pressure atomization experiments, high back pressure atomization experiments and atomization experiments under flow pulsation. Wherein, the high back pressure atomization experiment can simulate the spraying state of 10 MPa. Because the pressure of a combustion chamber reaches 10MPa when the liquid rocket engine burns, the liquid rocket engine is easy to burn unstably when the liquid rocket engine burns, and one reason of the instability is probably caused by the nonuniformity of the atomization process, the simulation pressure of 10MPa is adopted for simulating the real atomization state of the liquid rocket.
2. The invention can carry out atomization experiments of various spraying media, particularly gas-liquid and liquid-liquid. The gas can be air or nitrogen, and the liquid can be water or kerosene.
3. The invention can accurately measure the spray cone angle, and avoid the problem that the atomization process is insufficient due to the over-small spray cone angle
And low combustion efficiency; and the phenomena that the high-pressure atomization chamber is corroded and burns through the inner wall due to the fact that the propellant is directly sprayed to the inner wall of the combustion chamber due to the fact that the spray cone angle is too large can be avoided.
4. The invention can accurately measure the broken length of the liquid film, and the burning is generally carried out after the liquid is broken into small liquid drops because
The liquid film form is not generally combusted, and the distance between a combustion area and the front end of the combustion chamber can be obtained by measuring the position of the broken liquid film, so that guidance is provided for the heat protection of the front end of the combustion chamber.
5. In the working process of the liquid rocket engine, unstable combustion sometimes occurs, the main reason is probably caused by the non-uniformity of the atomization process of the liquid propellant, so a set of high-pressure atomization cabin suitable for the atomization process of the liquid rocket propellant is necessary to be developed. During operation of liquid engine combustion, the pressure in the combustion chamber is high and it is therefore necessary for the atomization chamber to provide a certain back pressure. The device can flexibly adjust the pressure according to the pressure in the combustion chamber, obtain the atomization process of the engine under the real working condition, and can capture the spray cone angle of the liquid, and the spray cone angle determines the high-temperature combustion area in the combustion chamber, so that the high-temperature distribution can be obtained according to the spray cone angle, the design of the engine nozzle is optimized, and the purpose of thermal protection is achieved.
6. The pulsation device adopts a rotation mode, is directly connected with the motor, can obtain higher pulsation frequency, and can adjust the pulsation amplitude by changing the size of the flow passage hole in the pulsation device.
Drawings
Fig. 1 shows a schematic structural diagram of a high-pressure atomization experimental system in the invention.
FIG. 2 shows a schematic of the atmospheric spray test system of the present invention.
Fig. 3 shows a schematic structure of the atmospheric pressure spraying device of the present invention.
Fig. 4 shows a schematic diagram of the propellant supply of the high pressure atomization experimental system of the present invention.
Figure 5 shows a schematic diagram of the propellant supply for the atmospheric spray test system of the present invention.
Fig. 6 shows a process diagram for measuring cone angle using the spray cone angle measuring device of the present invention.
Fig. 7 shows a diagram of a method of calculating the spray cone angle.
Among them are:
10. a high pressure atomization chamber; 11. an observation window;
20. a spray cone angle measuring device; 21. a background light source; 22. a translucent plate; 23. a high-speed camera;
30. a normal pressure spraying device; 31. a nozzle height adjusting bracket; 311. a vertical plate; 312. a transverse plate; 313. a height adjustment hole;
32. a nozzle platform; 321. an upper top plate; 322. a middle plate; 323. a vertical threaded rod;
33. a nozzle; 331. a nozzle mounting plate; 34. a spray collection station; 341. a drain valve;
41. a height lifting frame; 42. a slide bar; 43. laser granularity is obtained;
51. a flow pulsator; 52. a flow pulsation controller;
60. a propellant supply system;
61. a first liquid storage tank; 611. a first liquid injection valve; 612. a first liquid storage pressure gauge; 613. a first liquid supply valve; 614. a first liquid supply flow meter; 615. a liquid supply electromagnetic valve I; 616. a first pressure sensor;
62. a second liquid storage tank; 621. a second liquid injection valve; 622. a second liquid storage pressure gauge; 623. a second liquid supply valve; 624. a liquid supply flowmeter II; 625. a liquid supply electromagnetic valve II; 626. a second pressure sensor;
63. a gas storage tank;
631. a first air supply valve; 632. a second air supply valve; 633. a gas supply flow meter; 634. an air supply solenoid valve; 635. an air supply pressure gauge;
70. and (4) a computer.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.
As shown in fig. 1 to 5, a multifunctional atomization experiment system includes a high-pressure atomization experiment system, a normal-pressure atomization experiment system, a propellant supply system 60 and a computer 70.
As shown in fig. 1 and 4, the high-pressure atomization experimental system comprises a high-pressure atomization chamber 10 and a first spray cone angle measuring device.
The inner diameter and the total height of the high-pressure atomization cabin are respectively 500 mm and 1700 mm, stainless steel is adopted as the material, and the design pressure is 10 MPa. The side wall of the high-pressure atomization chamber is provided with at least two observation windows 11 which are positioned on the same straight line. In the present embodiment, the number of the observation windows is preferably three, and the three observation windows are arranged along the circumferential direction of the high-pressure atomization chamber, and two of the observation windows are located on the same straight line. The diameter of each observation window is preferably 130mm, and the material of each observation window is preferably quartz glass.
A layer of hydrophobic film is pasted on the quartz glass of each observation window, so that the high-definition high-transparency and durable waterproof effects can be achieved. To improve the optical effect, a gaseous air purge system is used to prevent the accumulation of liquid droplets on the viewing window.
The high-pressure atomization cabin is connected with a high-pressure air source, and the high-pressure air source can provide 10MPa high-pressure air for the high-pressure atomization cabin. In the present invention, the cause of the high pressure of 10MPa is simulated: when the liquid rocket engine burns, the pressure of a combustion chamber reaches 10MPa, the liquid rocket engine is easy to burn unstably during burning, one reason of the instability is probably caused by the nonuniformity of an atomization process, and therefore, the simulation pressure of 10MPa is adopted for simulating the real atomization state of the liquid rocket.
The spray cone angle measuring device can measure the cone angle of the spray sprayed by the nozzle in the high-pressure atomization cabin through the observation window.
As shown in fig. 2 and 5, the atmospheric atomization experimental system comprises an atmospheric spray device 30, a second spray cone angle measuring device and a spray particle size measuring device.
As shown in fig. 3, the atmospheric pressure spray device includes a nozzle 33, a nozzle height adjusting bracket 31, and a spray collecting table 34.
The height of the nozzle height adjusting frame can be raised and lowered, and preferably comprises two vertical plates 311 and a horizontal plate 312.
The two vertical plates are parallel and vertically arranged, and each vertical plate is provided with a plurality of height adjusting holes 313 along the height direction. The two ends of the transverse plate are respectively connected with the corresponding height adjusting holes on the two vertical plates through bolts.
The nozzle is preferably connected to a nozzle height adjustment bracket via a nozzle platform 32. The nozzle platform preferably includes an upper top plate 321, a middle flat plate 322, a nozzle mounting plate 331, and a plurality of vertical threaded rods 323.
The upper top plate 321, the middle flat plate 322 and the nozzle mounting plate 331 are arranged in parallel from top to bottom, and are in threaded connection with the transverse plate through a plurality of vertical threaded rods 323. The nozzle head is preferably coaxially inserted in the center of the nozzle mounting plate and is capable of projecting a cone-shaped spray, also referred to as cone-shaped spray 332, downwardly.
The spray collection table 34 is located directly below the nozzle, and the bottom is preferably provided with a drain valve 341.
And the second spray cone angle measuring device can measure the cone angle of the spray sprayed by the nozzles on the nozzle height adjusting frame.
The spray particle size measuring device comprises a height lifting frame 41, a sliding rod 42 and a laser particle size analyzer 43.
The height lifting frame covers the periphery of the nozzle on the nozzle height adjusting frame and can lift.
The slide bar is slidably mounted at the top of the height lifting frame and can slide back and forth or left and right.
The laser particle analyzer comprises a laser emitting end and a laser receiving end, the laser emitting end and the laser receiving end are symmetrically arranged on two sides of a nozzle on the nozzle height adjusting frame, and the top ends of the laser emitting end and the laser receiving end are both installed on the sliding rod.
Through the high lift of high crane to and the horizontal slip of slide rail, can obtain the particle size distribution rule of different positions department, if the position that removes at every turn is little enough (if be 5 mm), then can obtain the particle size distribution rule of total space position. The laser particle size analyzer measures the common spray particle size before use, and the particle size is calibrated, so that the atomization particle size measured by an experiment is more accurate.
The first spray cone angle measuring device and the second spray cone angle measuring device are collectively referred to as a spray cone angle measuring device 30. High pressure atomizing experimental system, ordinary pressure atomizing experimental system can respectively set up one set of spraying awl angle measuring device, also can share one set of spraying awl angle measuring device, in this embodiment, then for using one set of spraying cone angle measuring device jointly. When the supply is switched between the high-pressure atomization experiment system and the normal-pressure atomization experiment system, only the nozzle connected with the propellant supply system needs to be transferred and arranged.
The spray cone angle measuring device described above preferably comprises a background light source 21, a translucent plate 22 and a high speed camera 23.
A background light source and a translucent plate in the first spray cone angle measuring device are arranged on one side of the high-pressure atomization cabin and are opposite to the observation window; the high-speed camera is arranged on one side of the high-pressure atomization cabin and is opposite to the observation window.
The background light source 21 is preferably 4 rows X4 rows of LED lamps to provide uniform illumination.
The translucent plate is preferably a frosted translucent plate, and more preferably an acrylic plate, and functions to homogenize the light source on the LED.
The high-speed camera 23 is preferably an I-xseed camera, and can perform high-speed shooting to obtain a spray pattern. The method for measuring the spray cone angle alpha by the high-speed camera 23 based on MATLAB software on the shot conical spray picture preferably comprises the following steps:
step 1, picture shooting: the high-speed camera continuously shoots 500 instantaneous conical spray photos according to a set time interval, so that the instability of two-phase flow and the fluctuation of a spray angle can be avoided. One of the original cone spray photographs is shown in fig. 6 (a).
Step 3, gray level processing: the time-averaged processed image obtained in step 2 is converted into a grayscale image, as shown in fig. 6 (c).
Step 4, boundary extraction: by using the active contour model segmentation technique, the image boundary is extracted through several times of iterative search, and the image after the boundary extraction is shown in fig. 6 (d).
Step 5, calculating a spray cone angle alpha: and determining the included angle between the image boundary and the vertical line as alpha/2 according to the boundary image extracted in the step 4.
And 6, calculating the broken length of the liquid film, and specifically comprising the following steps.
Step 6A, determining the pixel length: measuring the measured diameter D1 of the nozzle outlet on the boundary image according to the boundary image extracted in the step 4; in combination with the actual diameter value D of the nozzle outlet, a length value K for each pixel in the boundary image is obtained, K = D1/D.
Step 6B, finding the broken position of the liquid film: measuring the vertical height H of the conical spray in the boundary image according to the boundary image extracted in the step 4; then, taking the outlet of the nozzle as a starting point, the conical spraying position corresponding to 50% H is the found liquid film breaking position.
Step 6C, measuring the length value L1 of the liquid film broken image: at the liquid film breakup position, the diameter of the conical spray parallel to the nozzle exit diameter was measured as a liquid film breakup image length, and the liquid film breakup image length value was L1.
And 6D, calculating the liquid film breaking length L, wherein the specific calculation formula is as follows: l = L1/K.
The propellant supply system can be used for supplying gas-liquid or liquid-liquid two-component propellant to the nozzle in the high-pressure atomizing cabin or the nozzle on the nozzle height adjusting frame.
As shown in fig. 4 and 5, the propellant supply system includes a first reservoir 61, a second reservoir 62 and a gas reservoir 63; the first liquid storage tank and the second liquid storage tank are both communicated with the first propellant channel in the corresponding nozzle through liquid supply pipelines.
The top of the first liquid storage tank is provided with a first liquid injection port and a first liquid storage pressure gauge 612, and the first liquid injection port is provided with a first liquid injection valve 611. The first liquid storage pressure gauge is used for monitoring liquid storage pressure in the first liquid storage tank.
The bottom of the first liquid storage tank is connected with a first liquid supply pipeline, a first liquid supply valve 613, a first liquid supply flow meter 614, a first liquid supply electromagnetic valve 615, a flow pulsator 51 and a first pressure sensor 616 are sequentially arranged on the first liquid supply pipeline, and the tail end of the first liquid supply pipeline is communicated with a first propellant channel of a corresponding nozzle.
And a second liquid injection port and a second liquid storage pressure gauge 622 are arranged at the top of the second liquid storage tank, and a second liquid injection valve 621 is arranged at the second liquid injection port. And the second liquid storage pressure gauge is used for monitoring the liquid storage pressure in the second liquid storage tank.
The bottom of the second liquid storage tank is connected with a second liquid supply pipeline, a second liquid supply valve 623, a second liquid supply flow meter 624, a second liquid supply electromagnetic valve 625, a flow pulsator and a second pressure sensor 626 are sequentially arranged on the second liquid supply pipeline, and the tail end of the second liquid supply pipeline is communicated with a second propellant channel of the corresponding nozzle.
The first pressure sensor and the second pressure sensor are preferably pressure sensors with an accuracy of 0.25% FS, more preferably 4730 diffused silicon pressure sensors, and are capable of measuring pressures of liquid and gas.
The first liquid supply flow meter and the second liquid supply flow meter preferably use turbine flow meters, the model is preferably LWGY, the liquid mass flow can be measured, and the accuracy is 1% FS.
The flow pulsator 51 is connected with a corresponding flow pulsation controller, and is used for providing liquid flow with controllable amplitude and frequency, and simulating the influence of the oscillation of a propellant supply pipeline on the spraying caused by the combustion of an engine in a real environment. When the rocket engine works, the violent vibration of the engine can cause the vibration of the upstream propellant pipeline, the vibration of the pipeline can cause the vibration of the propellant flow, and the flow vibration causes the non-uniformity of the atomization process, so that the device is designed for researching the influence of the upstream vibration frequency and amplitude on the non-uniformity of the atomization process.
An air supply pipeline of the air storage tank is sequentially provided with an air supply valve 631, an air supply valve 632, an air supply flowmeter 633, an air supply electromagnetic valve 634 and a pressure sensor. In this embodiment, the tail end of the air supply pipeline coincides with the tail end of the first liquid supply pipeline, and the air supply pipeline and the first liquid supply pipeline are both communicated with the first propellant channel corresponding to the nozzle. Thus, a set of pressure sensors one 616 is used together.
The feed gas flow meter 633 is preferably a coriolis flow meter, and is preferably an MFC608, and is capable of measuring a gas mass flow rate with an accuracy of 0.5% FS.
Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the details of the embodiments, and various equivalent modifications can be made within the technical spirit of the present invention, and the scope of the present invention is also within the scope of the present invention.
Claims (9)
1. The utility model provides a multi-functional atomizing experimental system which characterized in that: the system comprises a high-pressure atomization experiment system, a normal-pressure atomization experiment system and a propellant supply system;
the high-pressure atomization experiment system comprises a high-pressure atomization cabin and a first spray cone angle measuring device;
the side wall of the high-pressure atomization cabin is provided with at least two observation windows which are positioned on the same straight line; the spray cone angle measuring device I can measure the cone angle of the spray sprayed by the nozzle in the high-pressure atomization cabin through the observation window;
the normal-pressure atomization experiment system comprises a normal-pressure spraying device, a second spraying cone angle measuring device and a spraying particle size measuring device;
the normal pressure spraying device comprises a nozzle and a nozzle height adjusting frame; the nozzle is arranged in the center of the nozzle height adjusting frame, and the height of the nozzle height adjusting frame can be lifted;
the second spray cone angle measuring device can measure the cone angle of the spray sprayed by the nozzles on the nozzle height adjusting frame;
the spray particle size measuring device comprises a height lifting frame, a sliding rod and a laser particle size analyzer;
the height lifting frame covers the periphery of the nozzle on the nozzle height adjusting frame, and the height of the height lifting frame can be lifted;
the sliding rod is slidably arranged at the top of the height lifting frame and can slide back and forth or left and right;
the laser emitting end and the laser receiving end of the laser particle analyzer are symmetrically arranged on two sides of the nozzle on the nozzle height adjusting frame, and the top ends of the laser emitting end and the laser receiving end of the laser particle analyzer are both arranged on the sliding rod;
the propellant supply system can be used for supplying gas-liquid or liquid-liquid two-component propellant to the nozzle in the high-pressure atomizing cabin or the nozzle on the nozzle height adjusting frame.
2. The multifunctional atomization experimental system of claim 1, wherein: and the observation windows of the high-pressure atomization cabin are provided with hydrophobic films.
3. The multifunctional atomization experimental system of claim 1, wherein: the first spray cone angle measuring device and the second spray cone angle measuring device both comprise a background light source, a semitransparent plate and a high-speed camera;
a background light source and a translucent plate in the first spray cone angle measuring device are arranged on one side of the high-pressure atomization cabin and are opposite to the observation window; the high-speed camera is arranged on one side of the high-pressure atomization cabin and is opposite to the observation window.
4. The multifunctional atomization experimental system of claim 3, wherein: the translucent plate is a frosted translucent plate.
5. The multifunctional atomization experimental system of claim 1, wherein: the propellant supply system comprises a first liquid storage tank, a second liquid storage tank and a gas storage tank; the first liquid storage tank and the second liquid storage tank are both communicated with the first propellant channel in the corresponding nozzle through liquid supply pipelines; flow pulsator are connected to the liquid supply pipelines of the first liquid storage tank and the second liquid storage tank; the air storage tank is communicated with the propellant channel two phases in the corresponding nozzle through an air supply pipeline.
6. The multifunctional atomization experimental system of claim 5, wherein: liquid supply pipelines of the first liquid storage tank and the second liquid storage tank are respectively provided with a liquid supply valve, a liquid supply flowmeter, a liquid supply electromagnetic valve and a pressure sensor; an air supply valve, an air supply flowmeter, an air supply electromagnetic valve and a pressure sensor are arranged on the air supply pipeline.
7. The multifunctional atomization experimental system of claim 5, wherein: pressure gauges are arranged on the first liquid storage tank, the second liquid storage tank and the gas storage tank.
8. The multifunctional atomization experimental system of claim 5, wherein: the method can be used for calculating the spray cone angle alpha, and comprises the following steps:
step 1, picture shooting: the high-speed camera continuously shoots 500 instantaneous conical spray photos according to a set time interval, so that the instability of two-phase flow and the fluctuation of a spray angle can be avoided;
step 2, time-averaged treatment: performing time-sharing processing on 500 conical spray photographs shot in the step 1 to obtain time-sharing processed images;
step 3, gray level processing: converting the time-averaged processed image obtained in the step 2 into a gray image;
step 4, boundary extraction: extracting image boundaries and images with the boundaries extracted by applying an active contour model segmentation technology and carrying out iterative retrieval for a plurality of times;
step 5, calculating a spray cone angle alpha: and determining the included angle between the image boundary and the vertical line as alpha/2 according to the boundary image extracted in the step 4.
9. The multifunctional atomization experimental system of claim 8, wherein: the method for calculating the spray cone angle alpha further comprises a step 6 of calculating the broken length of the liquid film, and specifically comprises the following steps:
step 6A, determining the pixel length: measuring the measured diameter D1 of the nozzle outlet on the boundary image according to the boundary image extracted in the step 4; combining the actual diameter value D of the nozzle outlet to obtain a length value K of each pixel in the boundary image, wherein K = D1/D;
step 6B, finding the broken position of the liquid film: measuring the vertical height H of the conical spray in the boundary image according to the boundary image extracted in the step 4; then, taking the outlet of the nozzle as a starting point, and determining the conical spraying position corresponding to 50% H, namely the found liquid film crushing position;
step 6C, measuring the length value L1 of the liquid film broken image: at the liquid film breaking position, taking the diameter of the conical spray parallel to the diameter of the outlet of the nozzle as the length of a liquid film breaking image, and measuring to obtain a liquid film breaking image length value L1;
and 6D, calculating the liquid film breaking length L, wherein the specific calculation formula is as follows: l = L1/K.
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