CN114061964B - Multifunctional atomization test system - Google Patents
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- CN114061964B CN114061964B CN202111333009.0A CN202111333009A CN114061964B CN 114061964 B CN114061964 B CN 114061964B CN 202111333009 A CN202111333009 A CN 202111333009A CN 114061964 B CN114061964 B CN 114061964B
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- 238000000889 atomisation Methods 0.000 title claims abstract description 100
- 238000012360 testing method Methods 0.000 title claims abstract description 22
- 239000007788 liquid Substances 0.000 claims abstract description 147
- 239000007921 spray Substances 0.000 claims abstract description 84
- 239000003380 propellant Substances 0.000 claims abstract description 45
- 238000002474 experimental method Methods 0.000 claims abstract description 34
- 239000002245 particle Substances 0.000 claims abstract description 33
- 238000005507 spraying Methods 0.000 claims abstract description 23
- 238000002485 combustion reaction Methods 0.000 claims description 32
- 238000000034 method Methods 0.000 claims description 26
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- 230000005514 two-phase flow Effects 0.000 claims description 3
- 230000010349 pulsation Effects 0.000 abstract description 15
- 238000002347 injection Methods 0.000 abstract description 11
- 239000007924 injection Substances 0.000 abstract description 11
- 238000005259 measurement Methods 0.000 abstract description 5
- 239000000203 mixture Substances 0.000 abstract description 3
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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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- Combustion & Propulsion (AREA)
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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; 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 spraying cone angle measuring device II and a spraying particle diameter 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 to provide a propellant of both liquid and gas composition for the nozzles in the high pressure atomising chamber or for the nozzles on the nozzle height adjustment shelf. The invention can perform atomization experiments under various environments, such as normal pressure atomization experiments, high back pressure atomization experiments and atomization experiments under flow pulsation, and can also perform atomization experiments of various injection 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 is widely used for carrying out various aerospace tasks such as manned lunar exploration, spark exploration, deep space exploration and the like. In order to ensure the smooth progress of the aerospace task, the liquid rocket engine needs to be ensured to have higher reliability, but the unstable high-frequency combustion becomes an important factor for inhibiting the development of the liquid rocket engine.
Because of the high-risk performance of the high-frequency combustion instability test of the full-size liquid rocket engine, the high-frequency combustion instability test has high test cost and long processing period, researchers develop a reduced scale simulation test for improving test efficiency, and atomization is an important sub-process in a combustion chamber, and natural attention is paid.
Since the combustion zone is generally concentrated in the spray zone, too small a spray cone angle may result in insufficient atomization and low combustion efficiency. Too large a spray cone angle may result in the propellant being sprayed directly onto the inner wall of the combustion chamber, causing corrosion and burning through the inner wall, so that it is highly necessary to measure the spray cone angle.
The method is simple and direct, but has strong subjectivity, and particularly when the boundary of the image is blurred, the research result can be greatly error. In recent years, in order to improve the accuracy of the extraction of the atomization cone angle, an image detection technique based on machine vision has been developed and applied. Among them, the threshold method based on MATLAB platform has been applied to study of the atomizing cone angle. The basic principle of the thresholding method is to obtain boundaries by setting a threshold value of pixel brightness to achieve region segmentation. However, this method still has the disadvantage that the greatest drawback is the great subjective randomness in the threshold setting.
In order to simulate the nozzle outlet atomization environment when high-frequency combustion instability occurs, it is necessary to construct counter-pressure atomization conditions capable of generating high-frequency large-amplitude pulsation, so that the influence of the high-frequency combustion instability on nozzle atomization characteristics is studied.
The source of the flow pulsation of the liquid propellant mainly comprises two parts: 1: when the liquid rocket engine burns, severe vibration is generated, the propellant pipeline and the engine are fixed together, so that the vibration of the engine can cause the vibration of the propellant pipeline, and the liquid flow in the propellant pipeline is caused to pulsate. 2: when the combustion of the engine is unstable, the pressure in the combustion chamber fluctuates, and the pressure in the combustion chamber is transmitted upstream through the nozzle, and the flow rate of the propellant is also caused to pulsate.
Because the method for constructing the high-frequency large-amplitude pulsation back pressure atomization condition needs to meet two factors of high frequency and large single pulsation energy simultaneously due to the energy input source, the implementation difficulty is large, so the related research is basically in a blank stage, researchers try to simulate the disturbance source by using a loudspeaker, but 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 pulsation back pressure atomization condition is difficult to meet. The pulsation is generated by a 'piston' pulsation device, namely liquid enters a cavity of the piston, and then the liquid flow is changed by the rapid compression of the piston, but the frequency which cannot reach the experimental requirement is limited because the movement mode of the piston is linear movement.
The non-uniformity of droplet distribution and droplet size in the combustion chamber can cause non-uniformity of combustion heat release, which directly leads to non-uniformity of spatial pressure distribution in the combustion chamber. Therefore, it is necessary to measure the spray particle size and obtain the distribution rule of the particle size of the liquid drops in the space by measuring the particle sizes at different positions in the space, thereby providing guidance for the design of the engine nozzle. Existing methods for measuring the particle size of liquid drops are mainly divided 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 because of the need to measure the droplet size in a specific area.
2. The electrical method comprises the following steps: hot wire method and charging wire method. The electrical method is suitable for measuring the size of the individual droplet size, and therefore cannot measure the large number of droplets sprayed.
3. The optical method comprises the following steps: by using the physical properties of the droplets (light intensity, phase difference, fluorescence, polarization, etc.) for measurement, high-speed photography, laser holography, laser doppler, laser imaging are performed. The optical measurement method is most adopted, and the comparison of a plurality of measurement methods shows that the laser particle sizer is suitable for being applied to spraying generated by a liquid rocket nozzle, the laser particle sizer is convenient and quick to test, and multiple groups of data are measured within a set time, so that more accurate and stable data can be obtained. The output data is rich and visual: the particle size of the liquid drop can be dynamically detected, and various data such as average particle size, sotel diameter and the like can be obtained through processing.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a multifunctional atomization test system which can perform atomization experiments under various environments, such as normal pressure atomization experiments, high back pressure atomization experiments and atomization experiments under flow pulsation, and can also perform atomization experiments of various injection media and accurate measurement of spray cone angle and liquid film breaking length.
In order to solve the technical problems, the invention adopts the following technical scheme:
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 spraying cone angle measuring device II and a spraying particle diameter 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 adjusting frame, and the height of nozzle height adjusting frame can go up and down.
And the spray cone angle measuring device II can measure the cone angle of the spray sprayed by the nozzle 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 nozzle can be lifted.
The slide bar is slidably arranged 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 arranged on the sliding rod.
The propellant supply system can be used to provide a propellant of both liquid and gas composition for the nozzles in the high pressure atomising chamber or for the nozzles on the nozzle height adjustment shelf.
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 comprise a background light source, a semitransparent plate and a high-speed camera.
In the first spray cone angle measuring device, a background light source and a semitransparent plate 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 liquid storage tank I and the liquid storage tank II are communicated with the propellant channel I in the corresponding nozzle through liquid supply pipelines; the liquid supply pipelines of the liquid storage tank I and the liquid storage tank II are connected with flow pulsers; the air storage tank is communicated with the propellant channel in the corresponding nozzle through an air supply pipeline.
The liquid supply pipelines of the liquid storage tank I and the liquid storage tank II 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.
The first liquid storage tank, the second liquid storage tank and the air storage tank are respectively provided with a pressure gauge.
Can be used for calculating the spray cone angle alpha, and comprises the following steps.
Step 1, shooting pictures: the high-speed camera continuously shoots 500 instantaneous conical spray pictures according to a set time interval, so that instability of two-phase flow and fluctuation of spray angle can be avoided.
Step 2, time-averaged processing: and (3) carrying out time-averaged processing on the 500 cone-shaped spray photos shot in the step (1) to obtain a time-averaged processed image.
Step 3, gray scale processing: and (3) converting the time-averaged processed image obtained in the step (2) into a gray level image.
Step 4, boundary extraction: and extracting image boundaries by using an active contour model segmentation technology and performing iterative search for a plurality of times, wherein the images are obtained after the boundary extraction.
Step 5, calculating a spray cone angle alpha: and (3) 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 crushing length of the liquid film, and specifically comprises the following steps.
Step 6A, determining the pixel length: measuring to obtain a measured diameter D1 of a nozzle outlet on the boundary image according to the boundary image extracted in the step 4; and 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, searching a liquid film breaking position: measuring and obtaining the vertical height H of cone-shaped spray in the boundary image according to the boundary image extracted in the step 4; then, taking the nozzle outlet as a starting point, the conical spraying position corresponding to 50% H is the found liquid film breaking position.
Step 6C, measuring a liquid film broken image length value L1: at the position of liquid film breaking, the diameter of conical spray parallel to the diameter of the nozzle outlet is taken as the length of the liquid film breaking image, and the length value of the liquid film breaking image is measured to be L1.
Step 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 perform atomization experiments under various environments, such as normal pressure atomization experiments, high back pressure atomization experiments and atomization experiments under flow pulsation. Wherein, high back pressure atomization experiments can simulate 10 MPa's spraying state. Because the pressure of the combustion chamber reaches 10MPa when the liquid rocket engine is combusted, the combustion instability of the liquid rocket engine is easy to occur when the liquid rocket engine is combusted, and one of the reasons is probably caused by the non-uniformity of the atomization process, so that the simulation pressure of 10MPa is adopted for simulating the real atomization form of the liquid rocket.
2. The invention can carry out atomization experiments of various injection media, and specifically comprises gas liquid and liquid. Wherein 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 insufficient atomization process caused by too small spray cone angle
The problem of low combustion efficiency; and the phenomenon that the propellant is corroded and burnt through the inner wall of the high-pressure atomization cabin due to the fact that the spray cone angle is too large and the propellant is directly splashed onto the inner wall of the combustion chamber can be avoided.
4. The invention can accurately measure the breaking length of the liquid film, and the combustion is generally carried out after the liquid is broken into small liquid drops, because
The liquid film is not burnt generally, and the distance between the burning area and the front end of the combustion chamber can be obtained by measuring the breaking position of the 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, and the main reasons are possibly caused by the non-uniformity of the liquid propellant atomization process, so that a set of high-pressure atomization cabins suitable for the liquid rocket propellant atomization process are necessary to be developed. During operation of the liquid engine combustion, the pressure in the combustion chamber is high, and it is therefore necessary for the atomizing chamber to provide a specific back pressure. The device can flexibly adjust the pressure according to the pressure in the combustion chamber, obtain the atomization process under the real working condition of the engine, and 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 nozzle of the engine is optimized, and the aim of heat 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 structure of a high-pressure atomization experimental system in the invention.
FIG. 2 shows a schematic structure of an atmospheric pressure spray test system according to the present invention.
Fig. 3 shows a schematic structure of the normal pressure spraying device in the present invention.
Fig. 4 shows a schematic diagram of the propellant supply of the high pressure atomization experimental system of the present invention.
Fig. 5 shows a schematic diagram of the propellant supply of the atmospheric spray test system of the present invention.
Fig. 6 shows a process diagram of cone angle measurement using a spray cone angle measurement device in accordance with the present invention.
Fig. 7 shows a graph of the calculation method of the spray cone angle.
The method comprises the following steps:
10. a high pressure atomizing cabin; 11. an observation window;
20. 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 frame; 311. a vertical plate; 312. a cross plate; 313. a height adjusting hole;
32. a nozzle platform; 321. an upper top plate; 322. an intermediate plate; 323. a vertical threaded rod;
33. a nozzle; 331. a nozzle mounting plate; 34. a spray collection station; 341. a liquid discharge valve;
41. a height lifting frame; 42. a slide bar; 43. laser granularity particles;
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 liquid storage pressure gauge I; 613. a first liquid supply valve; 614. a first fluid supply flow meter; 615. a first liquid supply electromagnetic valve; 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 liquid supply valve II; 624. a second liquid supply flowmeter; 625. a liquid supply electromagnetic valve II; 626. a second pressure sensor;
63. a gas storage tank;
631. an air supply valve I; 632. an air supply valve II; 633. a gas supply flowmeter; 634. a gas supply electromagnetic valve; 635. a gas supply pressure gauge;
70. and a computer.
Detailed Description
The 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 should be understood that the terms "left", "right", "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and "first", "second", etc. do not indicate the importance of the components, and thus are not to be construed as limiting the present invention. The specific dimensions adopted in the present embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.
As shown in fig. 1 to 5, a multifunctional atomization experiment system includes a high-pressure atomization experiment system, an atmospheric atomization experiment system, a propellant supply system 60, and a computer 70.
As shown in fig. 1 and 4, the high-pressure atomization experiment system includes a high-pressure atomization chamber 10 and a spray cone angle measuring device one.
The inner diameter and the total height of the high-pressure atomization cabin are respectively preferably 500 mm and 1700 mm, stainless steel is adopted as the material, and the design pressure is 10MPa. The side wall of the high pressure atomizing cabin is provided with at least two observation windows 11 positioned on the same straight line. In this embodiment, the number of observation windows is preferably three, and the three observation windows are arranged along the circumference of the high-pressure atomization cabin, and two of the three observation windows are positioned 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.
The quartz glass of each observation window is coated with a layer of hydrophobic film, so that the observation window is high-definition and high-permeability and durable in waterproof. To enhance the optical effect, a gaseous air purge system is used to prevent droplet accumulation 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 high-pressure air of 10MPa for the high-pressure atomization cabin. In the invention, the reason for simulating the high pressure of 10 MPa: when the liquid rocket engine burns, the pressure of the combustion chamber reaches 10MPa, and the liquid rocket engine is easy to burn and unstable when burning, one of the reasons is probably caused by the non-uniformity of the atomization process, so that the simulation pressure of 10MPa is adopted for simulating the real atomization form 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 experiment system includes an atmospheric spraying device 30, a spray cone angle measuring device two, and a spray particle diameter measuring device.
As shown in fig. 3, the atmospheric pressure spraying device includes a nozzle 33, a nozzle height adjustment frame 31, and a spray collection stage 34.
The nozzle height adjusting frame is capable of being lifted and lowered, and preferably includes two vertical plates 311 and a horizontal plate 312.
The two upright plates are arranged in parallel and vertically, and each upright 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 by a nozzle platform 32. The nozzle platform preferably includes an upper top plate 321, a middle plate 322, a nozzle mounting plate 331, and a number 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 all in threaded connection with the cross plate through a plurality of vertical threaded rods 323. The nozzle tip 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 stage 34 is located directly below the nozzle and is preferably provided with a drain valve 341 at the bottom.
And the spray cone angle measuring device II can measure the cone angle of the spray sprayed by the nozzle on the nozzle height adjusting frame.
The spray particle diameter measuring device includes a height lifter 41, a slide bar 42, and a laser particle sizer 43.
The height lifting frame covers the periphery of the nozzle on the nozzle height adjusting frame, and the height of the nozzle can be lifted.
The slide bar is slidably arranged 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 emission end and a laser receiving end, wherein the laser emission 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 emission end and the laser receiving end are both arranged on the sliding rod.
Through the height lifting of the height lifting frame and the horizontal sliding of the sliding rail, the particle size distribution rule at different positions can be obtained, and if the position moved each time is small enough (for example, 5 mm), the particle size distribution rule at the whole space position can be obtained. Before the laser particle analyzer is used, the common spray particle size is measured, and the particle size is calibrated, so that the atomization particle size measured by experiments is accurate.
The first and second spray cone angle measuring devices are collectively referred to as a spray cone angle measuring device 30. The high-pressure atomization experiment system and the normal-pressure atomization experiment system can be respectively provided with one set of spray cone angle measuring device, and can also share one set of spray cone angle measuring device. When the supply is switched between the high-pressure atomization experimental system and the normal-pressure atomization experimental system, the nozzle connected with the propellant supply system is only required to be transferred and used.
The spray cone angle measuring device described above preferably includes a background light source 21, a translucent plate 22 and a high speed camera 23.
In the first spray cone angle measuring device, a background light source and a semitransparent plate 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 backlight 21 is preferably 4 rows of LED lamps in X4 rows so as to provide uniform illumination.
The translucent plate is preferably a frosted translucent plate, and more preferably an acrylic plate, and serves to homogenize the light source on the LED.
The high-speed camera 23 is preferably an I-xseed type camera, and can take a high-speed image to obtain a spray pattern. The high-speed camera 23 performs a method for measuring the spray cone angle α based on MATLAB software on the captured cone spray pictures, preferably including the steps of:
step 1, shooting pictures: the high-speed camera continuously shoots 500 instantaneous conical spray pictures according to a set time interval, so that instability of two-phase flow and fluctuation of spray angle can be avoided. One of the original cone spray photographs is shown in fig. 6 (a).
Step 2, time-averaged processing: the 500 cone spray photographs taken in step 1 were subjected to time-averaged processing to obtain time-averaged processed images, as shown in fig. 6 (b).
Step 3, gray scale processing: the time-averaged processed image obtained in step 2 is converted into a gray-scale image, as shown in fig. 6 (c).
Step 4, boundary extraction: and extracting image boundaries by using an active contour model segmentation technology through iterative search for a plurality of times, wherein the image with the boundaries extracted is shown in fig. 6 (d).
Step 5, calculating a spray cone angle alpha: and (3) 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 step 6, calculating the crushing length of the liquid film, which specifically comprises the following steps.
Step 6A, determining the pixel length: measuring to obtain a measured diameter D1 of a nozzle outlet on the boundary image according to the boundary image extracted in the step 4; and 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, searching a liquid film breaking position: measuring and obtaining the vertical height H of cone-shaped spray in the boundary image according to the boundary image extracted in the step 4; then, taking the nozzle outlet as a starting point, the conical spraying position corresponding to 50% H is the found liquid film breaking position.
Step 6C, measuring a liquid film broken image length value L1: at the position of liquid film breaking, the diameter of conical spray parallel to the diameter of the nozzle outlet is taken as the length of the liquid film breaking image, and the length value of the liquid film breaking image is measured to be L1.
Step 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 to provide a propellant of both liquid and gas composition for the nozzles in the high pressure atomising chamber or for the nozzles on the nozzle height adjustment shelf.
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 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 liquid storage pressure gauge is used for monitoring liquid storage pressure in the liquid storage tank I.
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 flowmeter 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 corresponding to the nozzle.
The top of the second liquid storage tank is provided with a second liquid injection port and a second liquid storage pressure gauge 622, and the second liquid injection port is provided with a second liquid injection valve 621. The second liquid storage pressure gauge is used for monitoring liquid storage pressure in the second liquid storage tank.
The bottom of the liquid storage tank II is connected with a liquid supply pipeline II, and a liquid supply valve II 623, a liquid supply flowmeter II 624, a liquid supply electromagnetic valve II 625, a flow pulsator and a pressure sensor II 626 are sequentially arranged on the liquid supply pipeline II, and the tail end of the liquid supply pipeline II is communicated with the propellant channel of the corresponding nozzle.
The first pressure sensor and the second pressure sensor are preferably pressure sensors having an accuracy of 0.25% fs, and more preferably 4730-diffusion silicon pressure sensors, and are capable of measuring the pressures of the liquid and the gas.
The first and second supply flow meters described above preferably use a turbine flow meter, preferably LWGY, capable of measuring liquid mass flow with an accuracy of 1% fs.
The flow pulser 51 is connected to a corresponding flow pulser controller, and is used for providing a liquid flow with controllable amplitude and frequency, and simulating the influence of oscillation of a propellant supply pipeline on spraying caused by engine combustion in a real environment. When the rocket engine works, the engine can cause the oscillation of an upstream propellant pipeline due to the severe vibration of the engine, the oscillation of the pipeline can enable the propellant flow to oscillate, and the flow oscillation causes the non-uniformity of the atomization process, so that the device is designed for researching the influence of the upstream oscillation frequency and amplitude on the non-uniformity of the atomization process.
The air supply pipeline of the air storage tank is sequentially provided with an air supply valve one 631, an air supply valve two 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 is communicated with the first propellant channel of the corresponding nozzle. Thus, a set of pressure sensors 616 is commonly used.
The gas supply flow meter 633 preferably uses a coriolis flow meter, preferably MFC608, capable of measuring gas mass flow with an accuracy of 0.5% fs.
The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the specific details of the above embodiments, and various equivalent changes can be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and all the equivalent changes belong to the protection scope of the present invention.
Claims (8)
1. A multifunctional atomization experiment system is characterized in that: the device comprises a high-pressure atomization experimental system, a normal-pressure atomization experimental 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 cone angle of spray sprayed by the nozzle in the high-pressure atomization cabin through the observation window;
the high-pressure atomization cabin is connected with a high-pressure air source, and the high-pressure air source can provide high-pressure air of 10MPa for the high-pressure atomization cabin, so that the pressure of a combustion chamber of 10MPa, which is reached when the liquid rocket engine burns, can be simulated;
the normal pressure atomization experiment system comprises a normal pressure spraying device, a spraying cone angle measuring device II and a spraying particle diameter 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 spray cone angle measuring device II can measure cone angle of spray sprayed by the nozzle 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 is covered on 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 emission end and the laser receiving end of the laser particle size 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 size analyzer are arranged on the sliding rod;
the propellant supply system can be used for providing gas-liquid or liquid-liquid two-component propellant for the nozzles in the high-pressure atomization cabin or the nozzles on the nozzle height adjusting frame;
the propellant supply system comprises a first liquid storage tank, a second liquid storage tank and a gas storage tank; the liquid storage tank I and the liquid storage tank II are communicated with the propellant channel I in the corresponding nozzle through liquid supply pipelines; the liquid supply pipelines of the liquid storage tank I and the liquid storage tank II are connected with flow pulsers; the air storage tank is communicated with the propellant channel in the corresponding nozzle through an air supply pipeline;
the flow pulser is connected with the corresponding flow pulser controller and is used for providing liquid flow with controllable amplitude and frequency and simulating the influence of propellant supply pipeline oscillation on spraying caused by engine combustion in a real environment; when the rocket engine works, the serious vibration of the engine can cause the oscillation of an upstream propellant pipeline, the oscillation of the pipeline can cause the oscillation of the propellant flow, the flow oscillation causes the non-uniformity of the atomization process,
the flow pulsator enables the amplitude and the frequency of the propellant flow in the supply pipeline to be controllable, and further the influence of the oscillation frequency and the amplitude of the propellant flow on the non-uniformity of the atomization process can be studied.
2. The multi-functional atomization testing system of claim 1, wherein: and the observation windows of the high-pressure atomization cabin are provided with hydrophobic films.
3. The multi-functional atomization testing system of claim 1, wherein: the first spray cone angle measuring device and the second spray cone angle measuring device comprise a background light source, a semitransparent plate and a high-speed camera;
in the first spray cone angle measuring device, a background light source and a semitransparent plate 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. A multi-functional atomization testing system in accordance with claim 3, wherein: the translucent plate is a frosted translucent plate.
5. The multi-functional atomization testing system of claim 1, wherein: the liquid supply pipelines of the liquid storage tank I and the liquid storage tank II 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.
6. The multi-functional atomization testing system of claim 5, wherein: the first liquid storage tank, the second liquid storage tank and the air storage tank are respectively provided with a pressure gauge.
7. The multi-functional atomization testing system of claim 5, wherein: can be used for calculating the spray cone angle alpha, and comprises the following steps:
step 1, shooting pictures: the high-speed camera continuously shoots 500 instantaneous conical spray pictures according to a set time interval, so that instability of two-phase flow and fluctuation of spray angle can be avoided;
step 2, time-averaged processing: carrying out time-averaged processing on 500 cone-shaped spray photos shot in the step 1 to obtain a time-averaged processed image;
step 3, gray scale processing: converting the time-averaged processed image obtained in the step 2 into a gray level image;
step 4, boundary extraction: extracting image boundaries by using an active contour model segmentation technology through iterative retrieval for a plurality of times, wherein the images with the boundaries extracted are obtained;
step 5, calculating a spray cone angle alpha: and (3) 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).
8. The multi-functional atomization testing system of claim 7, wherein: the method for calculating the spray cone angle alpha further comprises a step 6 of calculating the crushing length of the liquid film, and specifically comprises the following steps:
step 6A, determining the pixel length: measuring to obtain a measured diameter D1 of a 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, searching a liquid film breaking position: measuring and obtaining the vertical height H of cone-shaped spray in the boundary image according to the boundary image extracted in the step 4; then, taking the nozzle outlet as a starting point, and obtaining a conical spraying position corresponding to 50% H, namely a found liquid film crushing position;
step 6C, measuring a liquid film broken image length value L1: taking the diameter of the conical spray parallel to the diameter of the outlet of the nozzle at the position of liquid film breaking as the length of a liquid film breaking image, and measuring to obtain the length value of the liquid film breaking image as L1;
step 6D, calculating the liquid film breaking length L, wherein the specific calculation formula is as follows: l=l1/K.
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| CN114544178A (en) * | 2022-03-03 | 2022-05-27 | 北京航空航天大学 | System for measuring pulsating speed of spray field in high back pressure environment |
| CN114798203B (en) * | 2022-04-15 | 2023-01-17 | 江苏大学 | A fan-shaped suction nozzle, a spray system and a test method for observing the gas-liquid mixed flow field |
| CN115855945B (en) * | 2023-02-06 | 2023-05-26 | 北京成立科技有限公司 | Double-oil-way centrifugal nozzle atomized liquid film form detection equipment for combustion chamber |
| CN116255279B (en) * | 2023-05-15 | 2023-08-01 | 北京航空航天大学 | A device for measuring the gas-liquid interface of a jet in a confined space |
| CN116428080B (en) * | 2023-06-14 | 2023-08-08 | 中国人民解放军战略支援部队航天工程大学 | A atomization experimental system that can simulate engine back pressure oscillation |
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