CN115596574B - Time-resolved injector mixing ratio distribution measurement system and method - Google Patents
Time-resolved injector mixing ratio distribution measurement system and method Download PDFInfo
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- 238000002156 mixing Methods 0.000 title claims abstract description 53
- 238000005259 measurement Methods 0.000 title claims abstract description 34
- 238000000034 method Methods 0.000 title description 10
- 239000007788 liquid Substances 0.000 claims abstract description 147
- 239000000446 fuel Substances 0.000 claims abstract description 90
- 239000007800 oxidant agent Substances 0.000 claims abstract description 89
- 230000001590 oxidative effect Effects 0.000 claims abstract description 84
- NLKNQRATVPKPDG-UHFFFAOYSA-M potassium iodide Chemical compound [K+].[I-] NLKNQRATVPKPDG-UHFFFAOYSA-M 0.000 claims abstract description 63
- 239000000243 solution Substances 0.000 claims abstract description 34
- 238000000889 atomisation Methods 0.000 claims abstract description 23
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 19
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims abstract description 15
- 239000007864 aqueous solution Substances 0.000 claims abstract description 7
- 238000000691 measurement method Methods 0.000 claims abstract description 4
- 230000003287 optical effect Effects 0.000 claims description 28
- 238000004088 simulation Methods 0.000 claims description 26
- 238000002347 injection Methods 0.000 claims description 20
- 239000007924 injection Substances 0.000 claims description 20
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 claims description 16
- 238000001914 filtration Methods 0.000 claims description 14
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 claims description 8
- 238000002073 fluorescence micrograph Methods 0.000 claims description 7
- 238000003384 imaging method Methods 0.000 claims description 7
- 239000003380 propellant Substances 0.000 claims description 7
- 239000007921 spray Substances 0.000 claims description 7
- 230000001360 synchronised effect Effects 0.000 claims description 7
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 6
- 229910001218 Gallium arsenide Inorganic materials 0.000 claims description 6
- 239000003350 kerosene Substances 0.000 claims description 6
- 239000000975 dye Substances 0.000 claims description 5
- 238000012545 processing Methods 0.000 claims description 4
- 230000003595 spectral effect Effects 0.000 claims description 4
- 239000000126 substance Substances 0.000 claims description 4
- 230000003321 amplification Effects 0.000 claims description 3
- 238000003199 nucleic acid amplification method Methods 0.000 claims description 3
- 238000012634 optical imaging Methods 0.000 claims description 3
- 238000004043 dyeing Methods 0.000 claims description 2
- 238000001499 laser induced fluorescence spectroscopy Methods 0.000 abstract description 15
- 238000012360 testing method Methods 0.000 abstract description 14
- HEDRZPFGACZZDS-UHFFFAOYSA-N Chloroform Chemical compound ClC(Cl)Cl HEDRZPFGACZZDS-UHFFFAOYSA-N 0.000 description 6
- CVAVMIODJQHEEH-UHFFFAOYSA-O rhodamine B(1+) Chemical compound C=12C=CC(=[N+](CC)CC)C=C2OC2=CC(N(CC)CC)=CC=C2C=1C1=CC=CC=C1C(O)=O CVAVMIODJQHEEH-UHFFFAOYSA-O 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- VYXSBFYARXAAKO-WTKGSRSZSA-N chembl402140 Chemical compound Cl.C1=2C=C(C)C(NCC)=CC=2OC2=C\C(=N/CC)C(C)=CC2=C1C1=CC=CC=C1C(=O)OCC VYXSBFYARXAAKO-WTKGSRSZSA-N 0.000 description 3
- 229910000365 copper sulfate Inorganic materials 0.000 description 3
- ARUVKPQLZAKDPS-UHFFFAOYSA-L copper(II) sulfate Chemical compound [Cu+2].[O-][S+2]([O-])([O-])[O-] ARUVKPQLZAKDPS-UHFFFAOYSA-L 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000007774 longterm Effects 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- 238000004422 calculation algorithm Methods 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 2
- 239000003153 chemical reaction reagent Substances 0.000 description 2
- 238000004737 colorimetric analysis Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 231100000252 nontoxic Toxicity 0.000 description 2
- 230000003000 nontoxic effect Effects 0.000 description 2
- 231100000331 toxic Toxicity 0.000 description 2
- 230000002588 toxic effect Effects 0.000 description 2
- RHUYHJGZWVXEHW-UHFFFAOYSA-N 1,1-Dimethyhydrazine Chemical compound CN(C)N RHUYHJGZWVXEHW-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000002795 fluorescence method Methods 0.000 description 1
- 239000007850 fluorescent dye Substances 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 231100000956 nontoxicity Toxicity 0.000 description 1
- 238000012216 screening Methods 0.000 description 1
- 231100000419 toxicity Toxicity 0.000 description 1
- 230000001988 toxicity Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Investigating, Analyzing Materials By Fluorescence Or Luminescence (AREA)
Abstract
The invention discloses a time-resolved injector mixing ratio distribution measurement system and a time-resolved injector mixing ratio distribution measurement method, and belongs to the technical field of engines. The system comprises a clock delay pulse signal generator component, a high-frequency pulse laser sheet light generation component, an oxidant path high-speed camera, a fuel path high-speed camera, an image processor, a liquid rocket engine typical liquid-liquid injector unit and a data acquisition instrument, and the mixing ratio distribution measurement is carried out on an analog liquid formed by mixing an alcohol aqueous solution or pure water and a potassium iodide solution, so that the technical bottleneck of restricting the highest heavy frequency of a plane laser-induced fluorescence atomization mixing ratio test system is broken through, and the accurate measurement on the liquid rocket engine atomization mixing ratio distribution is realized.
Description
Technical Field
The invention relates to a time-resolved injector mixing ratio distribution measurement system and a time-resolved injector mixing ratio distribution measurement method, and belongs to the technical field of engines.
Background
The atomization combustion process is a key process for the operation of a liquid rocket engine, and the atomization degree mixing ratio level can have obvious influence on the performance of the engine. The high-efficiency atomization test means and the fine measurement level can fully capture the details of the atomization combustion process of the engine injector, and provide basis for optimizing the atomization mixing effect, improving the combustion tissue level and mastering the influence rule of key structural parameters, thereby improving the specific flushing performance and the reliability of the engine.
The main means for measuring the distribution of the atomization mixing ratio of the liquid rocket engine is a plane laser induced fluorescence method, the highest heavy frequency of a plane laser induced fluorescence atomization mixing ratio test system sold by fluid test instrument development and production companies (Dantec, lavision, TSI and the like) in the world is 15kHz, but because the laser single pulse energy of the laser induced fluorescence atomization mixing ratio test is generally 10-15 mJ, the total power of the laser is 100-225W, the method greatly exceeds the power parameter limit (the laser above 40W needs approval by business department of the foreign side) of the foreign side on the outlet control of the Chinese high-power laser, and severely restricts the experimental capability of basic research of the atomization combustion of the liquid rocket engine in China. In addition, the 15kHz laser repetition frequency cannot completely meet the requirement of measuring the distribution of the atomization mixing ratio of the liquid rocket engine in real time. The typical liquid-liquid injector unit of the liquid rocket engine has the injection speed of 20-40 m/s, the light thickness of the laser sheet is generally 0.5-1 mm, and in order to ensure that all liquid drops passing through the flow section are irradiated by laser to generate fluorescence and are shot and recorded, and the laser and shooting weight frequency is up to 40kHz.
The technical bottleneck for restricting the highest repetition frequency of the planar laser-induced fluorescence atomization mixing ratio test system is mainly concentrated on the laser repetition frequency. On the premise of limiting the average power of laser, the requirement of laser-induced fluorescence atomization mixing ratio test on laser single pulse energy is reduced, so that the laser single pulse energy testing system becomes the key for improving the laser repetition frequency of a planar laser-induced fluorescence atomization mixing ratio testing system.
Disclosure of Invention
The invention solves the technical problems that: the system and the method for measuring the spray mixing ratio distribution of the liquid rocket engine are capable of overcoming the defects of the prior art, breaking through the technical bottleneck of restricting the highest heavy frequency of a planar laser-induced fluorescence spray mixing ratio testing system and realizing accurate measurement of spray mixing ratio distribution of the liquid rocket engine. The invention further provides a nontoxic brand new simulation liquid combination which can cover the density ratio of all the current actual working conditions.
The technical scheme of the invention is as follows:
the utility model provides a time-resolved injector mixing ratio distribution measurement system, includes clock time delay pulse signal generator subassembly, high frequency pulse laser piece light generation component, oxidant way high-speed camera, fuel way high-speed camera, image processor, the typical liquid injector unit of liquid rocket engine, data acquisition appearance, high frequency pressure sensor, still includes:
the liquid rocket engine typical liquid-liquid injector unit stores fuel simulated liquid and oxidant simulated liquid which are mixed according to a preset density ratio and dyed with different fluorescence, liquid-liquid mixed spray liquid drops are formed, and the liquid drops are formed into a mixed simulated liquid injection cone through injection atomization; the fuel simulation liquid is pure water or alcohol water solution, the oxidant simulation liquid is potassium iodide solution and is used for simulating a propellant combination used by the liquid rocket engine;
the oxidant path high-speed camera and the fuel path high-speed camera have the same structure and are provided with a post-mirror filter module, and the post-mirror filter module is positioned between the high-speed camera body and the high-speed photographic optical lens and is used for selectively transmitting fluorescence emitted by the mixed simulated liquid injection cone;
The high-frequency pulse laser sheet light generating component emits laser sheet light, the laser sheet light width is 30 mm-50 mm, and the thickness is 0.5 mm-1 mm; and the laser sheet irradiates the mixed simulation liquid injection cone, and excites the mixed simulation liquid injection cone to emit fluorescence.
Preferably, the post-lens filtering module comprises a filter and a mounting groove for placing the filter, and the maximum diameter of the filter is 50mm.
Preferably, the high-speed camera body of the oxidant path high-speed camera and the high-speed camera body of the fuel path high-speed camera both comprise CMOS imaging photosensitive elements and image intensifiers, the image intensifiers adopt GaAs photocathodes, the CMOS imaging photosensitive elements adopt CMOS with pixel size of 28 mu m, the ISO value is not less than 40000, and the background noise control is not more than 1/255 of full scale range.
Preferably, the atomization injection speed of the liquid-liquid injector unit of the liquid rocket engine is 20-40 m/s.
Preferably, the potassium iodide solution with a density of 1.425g/ml and the pure water with a density of 1g/ml simulate liquid oxygen with a density of 1.14g/ml and kerosene with a density of 0.8g/ml respectively, and the density ratio of the potassium iodide solution to the pure water is 1.425.
Preferably, the potassium iodide solution with the density of 1.62g/ml and the alcohol aqueous solution with the density of 0.9g/ml respectively simulate dinitrogen tetroxide with the density of 1.44g/ml, monomethyl hydrazine with the density of 0.8g/ml, and the density ratio of the potassium iodide solution to the alcohol aqueous solution is 1.8.
Preferably, the device further comprises a calibration target disc, wherein the calibration target disc is a three-dimensional calibration target disc, the three-dimensional calibration target disc is placed on a flow section of laser slice light emitted by the high-frequency pulse laser slice light generating assembly, the oxidant path high-speed camera and the fuel path high-speed camera shoot the calibration target disc, and the corresponding relation between the image coordinates and the calibration target disc coordinates is obtained.
Preferably, the device further comprises a spectrometer for performing spectral measurement on fluorescence emitted by the mixed analog liquid injection cone, and the wave band of the light allowed to pass through the optical filter is selected based on the measurement result.
Preferably, the data acquisition instrument acquires the pressure signal of the high-frequency pressure sensor and the clock delay pulse signal of the clock delay pulse signal generator component at the same time, wherein the acquisition frequency of the data acquisition instrument is not less than 2 MB/s.
The time-resolved injector mixing ratio distribution measuring method comprises the following steps:
Preparing potassium iodide solution as a simulation liquid of an oxidant path, preparing alcohol aqueous solution as a simulation liquid of a fuel path, dyeing the simulation liquid of the fuel path and the simulation liquid of the oxidant path by using different fluorescent substances, mixing the dyed simulation liquid of the fuel path and the dyed simulation liquid of the oxidant path through a liquid-liquid injector unit typical of a liquid rocket engine, injecting and atomizing to form a mixed liquid injection cone;
the laser sheet light with the width of 30-50 mm and the thickness of 0.5-1 mm irradiates the flow section of the mixed liquid injection cone to excite the plane fluorescence of different dyes in the oxidant simulated liquid drop and the fuel simulated liquid drop;
Generating a predetermined TTL square wave signal, providing a marking signal of a synchronous clock, and controlling a pulse clock and a shooting shutter clock generated by high-frequency pulse laser light;
Performing optical imaging on the fluorescence, and generating an oxidant simulated liquid drop plane fluorescence image sequence and a fuel simulated liquid drop plane fluorescence image sequence after filtering and image enhancement amplification;
And performing image processing on the fluorescent image sequence, and calculating to obtain the flow intensity of the oxidant simulated liquid drop and the fuel simulated liquid drop and the space-time distribution field of the mixing ratio of the oxidant simulated liquid drop and the fuel simulated liquid drop.
Compared with the prior art, the invention has the advantages that:
(1) The invention creatively provides a design of a high-speed camera, solves the problem that the area of an optical filter arranged outside a lens in the traditional atomizer atomizing high-speed shooting cannot cover the outer surface with a larger diameter of a long-focus large-aperture lens, and fundamentally solves the dilemma that a mixing ratio distribution measurement test requiring long-focus lens shooting cannot be performed. Through the use of a mirror back filtering module, the image intensifier adopts a GaAs photocathode, adopts a CMOS with the pixel size of 28 mu m, and has the excitation light sheet light source thickness of 0.5-1 mm and the excitation light sheet light source width of 30-50 mm, the laser single pulse energy requirement of plane laser induced fluorescence is reduced from tens mJ to 1mJ, when the average power of a high-frequency pulse laser sheet light generating component is only 40W, the laser pulse weight frequency can reach 40kHz, the oxidant path high-speed camera and the fuel path high-speed camera synchronously reach 40kfps, and each atomization injection section with high flow velocity can be fully captured.
(2) The invention provides a new simulated liquid combination for the first time, a nontoxic potassium iodide solution is prepared as a simulated liquid of an oxidant path, an alcohol aqueous solution or pure water is prepared as a simulated liquid of a fuel path, the density ratio range (1-1.8) which can be simulated by using the two simulated liquids can cover the density ratios of the combined propellant of the unsymmetrical dimethylhydrazine/dinitrogen tetraoxide, the monomethyl hydrazine/dinitrogen tetraoxide and the kerosene/liquid oxygen under different working conditions, almost all working medium types of a common liquid rocket engine can be covered, the mass flow ratio and the momentum ratio of the simulated liquid which are measured by the distribution of a cold state mixing ratio are effectively ensured to be the same as those of the real propellant combination, the working medium is easy to obtain, the cost is low, and compared with the existing copper sulfate solution colorimetric method and chloroform fluorescent method, the simulated liquid has the advantages of being not strong in simulation, having toxic and the like, the long-term pain points which are toxic to operators in the research are solved, and the accuracy and the safety of the test are effectively improved.
(3) According to the invention, the corresponding relation between the image coordinates and the coordinates of the calibration target disk is obtained by using the calibration target disk, and the shot fluorescent image is corrected according to the change of the relative positions of the targets on the target disk, so that the problems that the image deformation is caused by different positions of the decoding lens at different distances and different imaging amplification ratios on the high-speed shooting CMOS due to the fact that the shooting direction of the high-speed shooting is not perpendicular to the irradiation plane due to the factors such as the shielding of the injected liquid are solved.
Drawings
FIG. 1 is a schematic diagram of a time-resolved injector mixing ratio distribution measurement system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a mounting position of a close-up camera in an embodiment of a time-resolved injector mix ratio distribution measurement system according to an embodiment of the present invention;
FIG. 3 is a schematic diagram showing clock synchronization of a time-resolved injector mixing ratio distribution measurement method according to an embodiment of the present invention;
FIG. 4 shows fluorescence wavelengths of different dyes according to an embodiment of the present invention.
Detailed Description
The following detailed description of the preferred embodiments of the invention is provided in connection with the accompanying drawings so that the advantages and features of the invention will be readily understood by those skilled in the art.
The invention provides a time-resolved injector mixing ratio distribution measurement system, which is shown in fig. 1, and comprises a clock delay pulse signal generator 1, a high-frequency pulse laser chip light generation assembly, an oxidant path high-speed camera, a fuel path high-speed camera, an oxidant processor 12, a fuel processor 13, a calibration target disk 14, a trigger delay pulse signal generator 15, a liquid rocket engine typical liquid-liquid injector unit 16, a high-frequency pressure sensor 17, a high-speed data acquisition instrument 18 and a spectrometer 19.
The oxidant path high-speed camera and the fuel path high-speed camera have the same structure, and each of the oxidant path high-speed camera and the fuel path high-speed camera comprises a high-speed camera body, a mirror back filter module and a high-speed photographing optical lens as shown in fig. 2. The high-speed camera body is provided with a CMOS imaging photosensitive element and an image intensifier for collecting oxidant or fuel; the optical filtering module behind the lens is positioned between the high-speed photographic machine body and the high-speed photographic optical lens and comprises an optical filter and an optical filter mounting groove.
Based on the above structure, the oxidizer high speed camera includes an oxidizer body 4, an oxidizer image intensifier 5, an oxidizer optical lens 6, and an oxidizer post-mirror filter module 7. The fuel path high speed camera includes a fuel body 8, a fuel image intensifier 9, a fuel optical lens 10, and a fuel mirror post filter module 11.
The oxidant road mirror post-filtering module 7 and the fuel road mirror post-filtering module 11 are positioned between the oxidant road optical lens 6 and the fuel road optical lens 10 and between the oxidant road image intensifier 5 and the fuel road image intensifier 9, and the light entering area of the optical lens cannot be reduced because the size of the optical filter is smaller than the diameter of the large-aperture optical lens. The maximum diameter of the optical filters of the oxidant road mirror post-filtering module 7 and the fuel road mirror post-filtering module 11 is 50mm, and the light inlet quantity of the mirror post-filtering module is 2.37 times (the focal length is 80-200 mm and the diameter of the 2.8f large aperture lens is 77 mm) and 9.7 times (the focal length is 400mm and the diameter of the 2.8f large aperture lens is 156 mm) of the prior art adopting the mirror pre-filtering scheme respectively.
The oxidant road image intensifier 5 and the fuel road image intensifier 9 adopt GaAs photocathodes, the quantum efficiency of the photocathodes aiming at 570-800 nm wave band light can reach more than 30 percent (more than 2 times of other photocathodes), the oxidant road high-speed camera and the fuel road high-speed camera adopt CMOS with the pixel size of 28 mu m, the ISO value is not less than 40000, the background noise is controlled at 1/255 of full range, the laser-induced fluorescence intensity required by shooting is greatly reduced, and the method is about 1/50 of the scheme of a shooting system in the prior art.
The high-frequency pulse laser sheet light generating assembly comprises a laser 2 and a sheet light lens assembly 3, the width of the emitted laser sheet light is 30-50 mm, the thickness of the sheet light is 0.5-1 mm, the irradiation range requirement of the liquid rocket engine typical liquid injector unit atomization field with the maximum width of 20-40 mm is met, the energy of the laser sheet light is concentrated to the maximum extent, the laser pulse repetition frequency reaches 40kHz, and the requirement that liquid drops are completely recorded is just met, namely the time-resolved mixing ratio distribution measurement is achieved.
The clock delay pulse signal generator component generates a preset TTL square wave signal, provides a marking signal of a synchronous clock for the high-speed data acquisition instrument, and controls the pulse clock of the high-frequency pulse laser sheet light generation component, the shooting shutter clock of the oxidant path high-speed camera and the fuel path high-speed camera, the shutter clock of the oxidant path image intensifier and the shutter clock of the fuel path image intensifier.
The calibration target disc is a three-dimensional calibration target disc and is placed on a flow section irradiated by laser sheet light, and the oxidant path high-speed camera and the fuel path high-speed camera shoot the calibration target disc to obtain the corresponding relation between the image coordinates and the calibration target disc coordinates.
The image processor is internally provided with image processing software, and can carry out digital image processing on fluorescent image sequences obtained by shooting by the oxidant path high-speed camera and the fuel path high-speed camera to obtain the flow intensity of oxidant simulated liquid drops and fuel simulated liquid drops and the space-time distribution field of the mixing ratio of the oxidant simulated liquid drops and the fuel simulated liquid drops. Meanwhile, a plane laser-induced fluorescence image processing program is arranged in the image processor, a third-order polynomial fitting algorithm is adopted in the program to perform conversion calculation of an image coordinate system and a three-dimensional physical coordinate system, a liquid drop image cross-correlation algorithm is adopted to perform self-correction calculation of the out-of-plane deviation of laser slice light and a calibration target disk, and binocular parallax caused by the out-of-plane deviation is eliminated.
The high-speed data acquisition instrument has the acquisition frequency not smaller than 2MB/s, can acquire the pressure signal and the clock delay pulse signal of the high-frequency pressure sensor at the same time, and can realize synchronous measurement of the dynamic pressure drop and the time-resolved spray mixing ratio of a typical liquid-liquid injector unit of the liquid rocket engine.
Compared with the existing common simulated liquid combinations of chloroform/alcohol aqueous solution and copper sulfate solution/water, the invention finds out the chemical reagent with proper density, viscosity, innocuity and higher solubility as the simulated liquid through long-term test screening and comparison of the chemical reagent, and successfully proposes a brand-new simulated liquid combination. The fuel simulation liquid is pure water or alcohol water solution, the oxidant simulation liquid is potassium iodide solution, the density ratio of the propellant combination of dinitrogen tetroxide/hydrazine and liquid oxygen/kerosene which are commonly used for liquid rocket engines can be simulated by adjusting the concentration ratio of the solution, and the specific solution combination is as follows: the density of 1.425g/ml of potassium iodide solution and the density of 1g/ml of pure water respectively simulate the density of 1.14g/ml of liquid oxygen and the density of 0.8g/ml of kerosene, the density ratio of the potassium iodide solution to the pure water is 1.425, and the density ratio of the liquid oxygen to the kerosene is 1.425 in the actual working condition; potassium iodide solution with the density of 1.62g/ml and alcohol water solution with the density of 0.9g/ml respectively simulate dinitrogen tetroxide with the density of 1.44g/ml and monomethyl hydrazine with the density of 0.8g/ml, and the density ratio of the potassium iodide solution to the monomethyl hydrazine is 1.8, which is the same as that of the dinitrogen tetroxide to the monomethyl hydrazine in the actual working condition. The brand new simulated liquid combination provided by the invention covers all working medium types of the liquid rocket engine, can effectively ensure that the mass flow ratio and the momentum ratio of the simulated liquid for cold mixing ratio distribution measurement are the same as those of a real propellant combination, is easy to obtain, has low cost, has the advantages of accuracy, no toxicity and the like compared with the existing copper sulfate solution colorimetric method and chloroform fluorescence method, solves the problems of weak simulated liquid in the research, long-term pain points with toxicity to operators and the like, and effectively improves the accuracy and the safety of the test.
The invention provides a time-resolved injector mixing ratio distribution measuring method, which comprises the following steps: the clock delay pulse signal generator component generates a preset TTL square wave signal, provides a marking signal of a synchronous clock for the high-speed data acquisition instrument, and controls the pulse clock of the high-frequency pulse laser sheet light generation component, the shooting shutter clock of the oxidant path high-speed camera and the fuel path high-speed camera, and the shutter clock of the oxidant path image intensifier and the fuel path image intensifier; the liquid rocket engine typical liquid-liquid injector unit is filled with fuel simulation liquid and oxidant simulation liquid which are prepared according to the real propellant density ratio and added with different fluorescent dyes, so as to form liquid-liquid mixed spray liquid drops; the high-frequency pulse laser sheet light generating component emits laser sheet light, irradiates an atomization mixing flow section with a certain distance below a typical liquid-liquid injector unit of the liquid rocket engine, and respectively excites plane fluorescence of different dyes in oxidant simulated liquid drops and fuel simulated liquid drops; the oxidant path large aperture optical lens and the fuel path large aperture optical lens carry out optical imaging on fluorescence, and respectively carry out imaging on the plane fluorescence of the oxidant simulated liquid drop and the plane fluorescence of the fuel simulated liquid drop in the oxidant path image intensifier and the fuel path image intensifier through the back filtering module of the chemical path fluorescent mirror and the back filtering module of the fuel path fluorescent mirror; the oxidant road image intensifier and the fuel road image intensifier amplify the planar fluorescence of the oxidant analog liquid drop and the planar fluorescence of the fuel analog liquid drop respectively, and image the planar fluorescence in the oxidant road high-speed camera and the fuel road high-speed camera; the oxidant path high-speed camera and the fuel path high-speed camera respectively shoot the amplified planar fluorescence of the oxidant simulated liquid drop and the amplified planar fluorescence of the fuel simulated liquid drop, and transmit the planar fluorescence to the image processor; the calibration target disc is placed on a flow section irradiated by the laser sheet, and the oxidant path high-speed camera and the fuel path high-speed camera shoot the calibration target disc to obtain a corresponding relation between an image coordinate and a calibration target disc coordinate; the image processor is internally provided with image processing software, and can carry out digital image processing on fluorescent image sequences obtained by shooting by the oxidant path high-speed camera and the fuel path high-speed camera to obtain the flow intensity of oxidant simulated liquid drops and fuel simulated liquid drops and the space-time distribution field of the mixing ratio of the oxidant simulated liquid drops and the fuel simulated liquid drops.
Examples of injector mixing ratio profile measurements for time-resolved by simulating dinitrogen tetroxide, monomethylhydrazine with potassium iodide solution and aqueous alcohol solution, respectively, are as follows:
Potassium iodide solution with density of 1.62g/ml and alcohol water solution with density of 0.9g/ml respectively simulate dinitrogen tetroxide with density of 1.44g/ml and monomethyl hydrazine with density of 0.8g/ml, and the density ratio is 1.8. Two kinds of fluorescent substances, namely rhodamine 610 and rhodamine 6G, are added to the oxidant path and the fuel path respectively. The oxidant simulated liquid and the fuel simulated liquid are atomized and mixed through a liquid-liquid injector unit typical of the liquid rocket engine to be tested.
The clock delay pulse signal generator 1 generates 3 paths of TTL signals, as shown in fig. 3, delay can be accurately set between the three paths of signals, and pulse clocks of the 532nm high-frequency pulse laser 2, photographing clocks of the oxidant optical lens 6 and the fuel optical lens 10, and shutter clocks of the oxidant image intensifier 5 and the fuel image intensifier 9 are respectively controlled. The trigger delay pulse signal generator 15 generates 3 paths of TTL signals, the delay of the 3 paths of signals is consistent, wherein two paths of signals respectively control shooting trigger of the oxidant machine body 4 and the fuel machine body 8, and the other path of signals enter the high-speed data acquisition instrument 18 to serve as time synchronization signals of images and other measurement data.
532Nm high-frequency pulse laser 2 generates 532nm high-frequency 40KHz pulse laser beams with energy of 1mJ per pulse, 532nm laser sheets with thickness of 1mm and width of 35mm are formed through a sheet optical lens assembly 3, the laser sheets pass through the flow section of an atomization field, respectively irradiate oxidant simulated liquid drops and fuel simulated liquid drops, respectively generate laser-induced fluorescence with rhodamine 610 and rhodamine 6G in the simulated liquid, and as shown in figure 4, rhodamine 610-600 nm fluorescence is induced, and rhodamine 6G-fluorescence is induced to 550-575 nm.
The spectrometer 19 is used for carrying out actual spectral measurement on the laser-induced fluorescence of different dyes, the wave band of the light which is allowed to pass through by the optical filter is selected based on the spectral measurement result, the bandwidth of the wave band which is passed through by the optical filter is determined according to the signal-to-noise ratio requirement, and the signal-to-noise ratio of the two paths of fluorescence shooting results is ensured to meet the shooting requirement.
The diameter of the optical filter module 7 behind the oxidant road mirror is 50mm, and the oxidant road image intensifier 5 adopts a GaAs photocathode. The oxidant path high-speed camera adopts CMOS with the pixel size of 28 mu m, ISO value 40000 and background noise of 1/255 of full scale, and shoots laser-induced fluorescence of oxidant rhodamine 610, wherein an oxidant mirror back filter module 7 is arranged between an oxidant machine body 4 and an oxidant optical lens 6, and shoots fluorescence two-dimensional distribution images at 40KHz on the premise of not influencing total light inlet quantity, and the fluorescence intensity distribution obtained by shooting is proportional to the flow intensity distribution of oxidant atomized liquid drops.
The diameter of the filter of the fuel road mirror back filter module 11 is 50mm, and the fuel road image intensifier 9 adopts a GaAs photocathode. The fuel path high-speed camera adopts CMOS with the pixel size of 28 mu m, ISO value 40000 and background noise controlled at 1/255 of full scale, and performs laser-induced fluorescence shooting on fuel rhodamine 6G, wherein a fuel mirror back filtering module 11 is arranged between a fuel machine body 8 and a fuel optical lens 10, and shoots fluorescence two-dimensional distribution images at 40KHz on the premise of not influencing the total light inlet quantity, and the fluorescence intensity distribution obtained by shooting is proportional to the flow intensity distribution of fuel atomized liquid drops.
Before the fluorescent image is shot, the calibration target disk 14 is placed in a plane irradiated by laser, and two sets of shooting systems respectively shoot the calibration target disk for converting the later fluorescent image from an image coordinate system to a physical coordinate system.
After the experiment shooting is completed, the oxidant fluorescent image is transmitted from the oxidant path high-speed camera through the tera-network cable and stored into the oxidant processor 12, image processing software is installed in the oxidant processor 12, and the software converts the oxidant fluorescent image from an image coordinate system to a physical coordinate system according to the calibration image. The fuel fluorescence image is transmitted from the fuel path high-speed camera through the tera-network cable and stored in the fuel processor 13, and image processing software is installed in the fuel processor 13 and converts the fuel fluorescence image from an image coordinate system to a physical coordinate system according to the calibration image.
The high-speed data acquisition instrument 18 acquires the 3-way clock synchronous TTL signal, the 1-way synchronous trigger TTL signal and the signal of the high-frequency pressure sensor 14 through coaxial cables. The 532nm high-frequency pulse laser 2 outputs a voltage signal representing the power of each pulse and enters a high-speed data acquisition instrument.
Given the total flow of oxidant and fuel, a spatial-temporal distribution field of the flow intensity of the oxidant and the fuel and the mixing ratio of the two can be calculated by using two sets of fluorescence image sequences converted into a physical coordinate system, and the distribution field has the characteristic of time analysis.
The present invention has been described in detail with reference to the drawings and preferred embodiments, and various modifications of the present invention can be made by those skilled in the art from the above description. Accordingly, the details of the preferred embodiments are not to be taken as limiting the invention, which is defined by the appended claims and which is to be construed as broadly as the scope of the invention.
Claims (10)
1. The utility model provides a time-resolved injector mixing ratio distribution measurement system, includes clock delay pulse signal generator subassembly, high frequency pulse laser piece light generation component, oxidant way high-speed camera, fuel way high-speed camera, image processor, the typical liquid injector unit of liquid rocket engine, data acquisition appearance, high frequency pressure sensor, its characterized in that:
The liquid rocket engine typical liquid-liquid injector unit stores fuel simulated liquid and oxidant simulated liquid which are mixed according to a preset density ratio and dyed with different fluorescence, liquid-liquid mixed spray liquid drops are formed, and the liquid drops are formed into a mixed simulated liquid injection cone through injection atomization; the fuel simulation liquid is pure water or alcohol water solution, the oxidant simulation liquid is potassium iodide solution and is used for simulating a propellant combination used by the liquid rocket engine;
the oxidant path high-speed camera and the fuel path high-speed camera have the same structure and are provided with a post-mirror filter module, and the post-mirror filter module is positioned between the high-speed camera body and the high-speed photographic optical lens and is used for selectively transmitting fluorescence emitted by the mixed simulated liquid injection cone;
The high-frequency pulse laser sheet light generating component emits laser sheet light, the laser sheet light width is 30 mm-50 mm, and the thickness is 0.5 mm-1 mm; and the laser sheet irradiates the mixed simulation liquid injection cone, and excites the mixed simulation liquid injection cone to emit fluorescence.
2. A time resolved syringe mixing ratio distribution measurement system according to claim 1, wherein the post-mirror filter module comprises a filter and a mounting groove in which the filter is placed, the filter maximum diameter being 50mm.
3. A time resolved syringe mixing ratio distribution measurement system according to claim 1, wherein: the high-speed camera body of the oxidant path high-speed camera and the high-speed camera body of the fuel path high-speed camera both comprise CMOS imaging photosensitive elements and image intensifiers, the image intensifiers adopt GaAs photocathodes, the CMOS imaging photosensitive elements adopt CMOS with pixel size of 28 mu m, ISO values are not less than 40000, and background noise control is not more than 1/255 of full range.
4. A time resolved syringe mixing ratio distribution measurement system according to claim 1, wherein: the atomization injection speed of the typical liquid-liquid injector unit of the liquid rocket engine is 20-40 m/s.
5. A time resolved syringe mixing ratio distribution measurement system according to claim 1, wherein: a potassium iodide solution having a density of 1.425g/ml and pure water having a density of 1g/ml each simulate liquid oxygen having a density of 1.14g/ml, kerosene having a density of 0.8g/ml, and the ratio of the density of the potassium iodide solution to that of the pure water was 1.425.
6. A time resolved syringe mixing ratio distribution measurement system according to claim 1, wherein: potassium iodide solution with density of 1.62g/ml and alcohol water solution with density of 0.9g/ml respectively simulate dinitrogen tetroxide with density of 1.44g/ml, monomethyl hydrazine with density of 0.8g/ml, and density ratio of potassium iodide solution to alcohol water solution is 1.8.
7. A time resolved syringe mixing ratio distribution measurement system according to claim 1, wherein: the laser chip laser generating device also comprises a calibration target disk which is a three-dimensional calibration target disk and is arranged on the flow section of the laser chip light emitted by the high-frequency pulse laser chip light generating component, and the oxidant path high-speed camera and the fuel path high-speed camera shoot the calibration target disc, and the corresponding relation between the image coordinates and the calibration target disc coordinates is obtained.
8. A time resolved syringe mixing ratio distribution measurement system according to claim 1, wherein: the device also comprises a spectrometer, wherein the spectrometer is used for carrying out spectral measurement on fluorescence emitted by the mixed analog liquid injection cone, and a wave band of light allowed to pass through the optical filter is selected based on the measurement result.
9. A time resolved syringe mixing ratio distribution measurement system according to claim 1, wherein: the data acquisition instrument acquires the pressure signal of the high-frequency pressure sensor and the clock delay pulse signal of the clock delay pulse signal generator component at the same time, wherein the acquisition frequency of the data acquisition instrument is not less than 2 MB/s.
10. A time-resolved syringe mixing ratio distribution measurement method using the time-resolved syringe mixing ratio distribution measurement system of claim 1, characterized in that: comprising the following steps:
Preparing potassium iodide solution as a simulation liquid of an oxidant path, preparing alcohol aqueous solution as a simulation liquid of a fuel path, dyeing the simulation liquid of the fuel path and the simulation liquid of the oxidant path by using different fluorescent substances, mixing the dyed simulation liquid of the fuel path and the dyed simulation liquid of the oxidant path through a liquid-liquid injector unit typical of a liquid rocket engine, injecting and atomizing to form a mixed liquid injection cone;
the laser sheet light with the width of 30-50 mm and the thickness of 0.5-1 mm irradiates the flow section of the mixed liquid injection cone to excite the plane fluorescence of different dyes in the oxidant simulated liquid drop and the fuel simulated liquid drop;
Generating a predetermined TTL square wave signal, providing a marking signal of a synchronous clock, and controlling a pulse clock and a shooting shutter clock generated by high-frequency pulse laser light;
Performing optical imaging on the fluorescence, and generating an oxidant simulated liquid drop plane fluorescence image sequence and a fuel simulated liquid drop plane fluorescence image sequence after filtering and image enhancement amplification;
And performing image processing on the fluorescent image sequence, and calculating to obtain the flow intensity of the oxidant simulated liquid drop and the fuel simulated liquid drop and the space-time distribution field of the mixing ratio of the oxidant simulated liquid drop and the fuel simulated liquid drop.
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