CN104764609A - Comprehensive optical measurement platform of aero-engine main combustion chamber - Google Patents
Comprehensive optical measurement platform of aero-engine main combustion chamber Download PDFInfo
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Abstract
The invention discloses a comprehensive optical measurement platform of an aero-engine main combustion chamber. By means of various optical measurement means, parameters in the aero-engine combustion chamber are comprehensively measured. Airflow enters an equal-diameter pressure-stabilizing section from an air inlet circle rotating square section, a combustion experimental section is fixedly installed between a pressure expander and an outlet square rotating circle section, airflow enters the combustion experimental section after being subjected to speed reducing and pressure expanding through the pressure expander, and glass inspection windows are embedded in the two sides of the combustion experimental section and used for optical measurement; in a cold-state experiment, airflow enters a cold flow tee joint after flowing out of an outlet of a single-head part rectangular experimental piece combustion chamber, a main way outlet is closed, and airflow flows out of a bypass way. For high-temperature pure airflow, on the basis of a combustion experimental device, through a single-head part experimental piece, the atomizing of kerosene in the combustion chamber and the measuring of the speed, temperature and composition can be carried out, the flow field testing experiment in the aero-engine combustion chamber is completed, and the fine measurement of an aero-engine combustion flow field is achieved.
Description
Technical field
The present invention relates to aeromotor field of optical measuring technologies, specifically, relate to a kind of integrated optical measuring table of aeromotor main chamber.
Background technology
For the measurement of temperature, pressure, speed and component, rely on thermopair, piezoelectric sensor, sound pressure pipe, hot-wire anemometer and the various physical probe of gas analyzer or surveying instrument for a long time.Its deficiency existed is that due to the easy interference flowing field of physical probe or be subject to bad interference, result needs careful correction; Owing to being easily subject to environmental limit, usable range is limited; Owing to generally experiencing macroscopical average physical, lack enough room and time resolution etc.
Be different from over to the contact measurement method measuring flow field and can produce certain interference, developing rapidly in recent decades along with science and technology in computing machine and optical correlation field, there is the contactless measurement of many advanced persons, as PIV (Particle Image Velocimetry), CARS (Coherent anti-StokesRaman Scattering) and TDLAS (Tunable Diode Laser Absorption Spectroscopy) etc.; Wherein PIV is widely used in the measurement of cold flow field, and TDLAS and CARS makes to be used less in combustor primary zone temperature survey as laser spectrum temperature sensing means.
External optical measuring system specialty is wide, A wide selection of colours and designs.Domestic before the mid-90, although also there is the theoretical research work of only a few to carry out, until after the mid-90, just the have ready conditions experiment and theoretical research of systematically carrying out optical measurement.Domestic optical measurement platform has a lot, but seldom has comprehensive optical measurement platform.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of integrated optical measuring table of aeromotor main chamber.
The technical solution adopted for the present invention to solve the technical problems is: the integrated optical measuring table of aeromotor main chamber, comprise optical measuring system, be characterized in, also comprise air inlet circle and turn square section, etc. straight pressure-stabilizing section, diffuser, burning test section, cold flow threeway, rear observation window, hot outlets water-cooled section, exporter turns round section, orifice plate, air inlet circle turns a square section and the straight pressure-stabilizing section leading section such as to be arranged on, be fixedly connected with diffuser etc. straight pressure-stabilizing section, combustion experiment section is positioned at diffuser and exporter turns between round section, combustion experiment section two ends by joint flange respectively with diffuser, exporter turns round section and is fixedly connected with, combustion experiment section both sides mosaic glass observation window is used for optical measurement, cold flow threeway and exporter turn round section and are connected, bypass is provided with orifice plate and rear observation window, main road is provided with pressure regulator valve, orifice plate coordinates with pressure regulator valve and regulates internal pressure of combustion chamber, in Cold simulating test, air-flow enters the exhaust of hot outlets water-cooled section through cold flow threeway bypass, in Thermal-state test, air-flow turns round section through the laggard inlet/outlet side of rectangle water-cooled part spray cooling,
Optical measuring system carries out PIV optical measurement to burning test section, turn square section at air inlet circle and spray into particle, the trace particle dispensed in flow field is with air motion, laser beam is expanded optical illumination flow field in blocks through compound lens, digital camera shooting flow field is used to obtain particle picture, the velocity distribution that correlation computations obtains the tangent plane quantification in flow field is carried out to particle picture, and obtains the characteristic parameter of the flow field distributions such as flow field vorticity, streamline and line of equal velocity after process.
Particle diameter is less than 10 microns.
Beneficial effect
The integrated optical measuring table of aeromotor main chamber of the present invention, applied optics measurement means measures concentration and the temperature of oxygen in the flame of aeroengine combustor buring room simultaneously, and multiple spot is measured simultaneously, the phase-matching technique of laser, spectral titration, supersonic combustion be studied.The present invention has carried out kerosene atomization, PIV velocity field, CARS temperature, SVRS component, the research of TDLAS temperature field measurement to firing chamber.Measure and be not subject to external environment restriction, time and space resolution is high.Result of calculation and comparison of test results obviously can find out test model upper and lower primary holes jet almost symmetry, and the low regime in primary zone is evenly distributed, and stream field analog reslt coincide.
The integrated optical measuring table of aeromotor main chamber of the present invention, for the experimental piece that experimental piece is single head portion rectangle, equipment adopts outlet circle to turn square section, waits straight section to connect diffuser after circle turns side through one section, air flows through diffuser deceleration diffusion, enters engine single head portion testpieces; Because optical measurement needs, experimental section both sides have observation window, and in Cold simulating test, air-flow enters cold flow threeway after single head portion rectangle experimental piece combustor exit flows out, and main road outlet is closed, and at glass observation window, place carries out optical measurement, and air-flow is flowed out by bypass.For the pure air incoming flow of high temperature, based on this firing chamber experimental facilities, take single head portion experimental piece, kerosene atomization in firing chamber, speed, temperature and component can be carried out and measure, complete aeroengine combustor buring Indoor Flow Field test experiments, realize the meticulous measurement of aero-turbine Combustion Flow Field.
Accompanying drawing explanation
Be described in further detail below in conjunction with the integrated optical measuring table of drawings and embodiments to a kind of aeromotor main chamber of the present invention.
Fig. 1 is front and back group section schematic diagram under cold flow state of the present invention.
Fig. 2 is front and back group section cut-open view under cold flow state of the present invention.
Fig. 3 is front and back group section schematic diagram under fired state of the present invention.
Fig. 4 is front and back group section cut-open view under fired state of the present invention.
Fig. 5 is burning test section schematic diagram of the present invention.
Fig. 6 is that CFD of the present invention calculates gained motion pattern.
Fig. 7 is PIV optical measurement gained motion pattern of the present invention.
In figure:
1. after air inlet circle turns threeway such as square cold flow such as section 5. such as burning test such as diffuser 4. such as straight pressure-stabilizing section 3. such as section 2. grade 6., observation window 7. hot outlets water-cooled section 8. exporter turns round section 9. orifice plate
Embodiment
The present embodiment is a kind of integrated optical measuring table of aeromotor main chamber.
Consult Fig. 1 ~ Fig. 7, aeromotor main chamber optical measurement platform by air inlet circle turn square section 1, etc. straight pressure-stabilizing section 2, diffuser 3, burning test section 4, cold flow threeway 5, rear observation window 6, hot outlets water-cooled section 7, outlet circle turn square section 8, orifice plate 9 and an optical measuring system and form.Be single head portion rectangle experimental piece for experimental piece, because existing equipment heater outlet is round exit, first designing apparatus air inlet circle is wanted to turn square section, through the diffuser of one section of part such as straight pressure-stabilizing section joint test such as grade behind circle turn side, air flows through diffuser deceleration diffusion, enters engine single head portion testpieces; In Cold simulating test, air-flow enters cold flow threeway after single head portion rectangle experimental piece combustor exit flows out, and main road outlet is closed, and air-flow is flowed out by bypass.For the pure air incoming flow of high temperature, based on this firing chamber experimental facilities, take single head portion experimental piece, kerosene atomization in firing chamber, speed, temperature and component can be carried out and measure, complete aeroengine combustor buring Indoor Flow Field test experiments and measurement.
The design of cold flow threeway section, because optical measurement needs, in Cold simulating test, air-flow enters cold flow threeway 5 after single head portion rectangle experimental piece combustor exit flows out, and main road outlet is closed, and carry out optical measurement with glass observation window, air-flow is flowed out by bypass.Through CFD numerical simulation calculation, the main road whirlpool backflow coverage of cold flow threeway is less, and bypass gas flow flowing is smooth and easy, very little on upstream flow impact, meets the requirement of experiment of firing chamber, single head portion.
The design of hot outlets water-cooled section, because combustor exit temperature is up to more than 1500K, adopts stainless steel material processing need carry out water-cooled to outlet section, shows, meet intensity and heat transfer requirement according to the hot-fluid of wall heat conduction and strength check.
The design of outlet pressure regulation, owing to will debug the firing chamber under different operating mode, need to arrange pressure regulator valve in combustion experiment section downstream, two-way is divided in combustion experiment section downstream, bypass arranges orifice plate, main road arranges high temperature pressure regulator valve, and according to the orifice plate of the operating mode different choice different pore size of firing chamber, and the pressure regulator valve cooperation of main road realizes on a large scale, high-precision internal pressure of combustion chamber regulates.
Experimental facilities heater system can simulate incoming flow stagnation temperature 300 ~ 1000K, stream air 0.1 ~ 4.0MPa, inlet flow rate 0.0 ~ 1.0kg/s, and experimental gas is pure high enthalpy air.
The course of work:
Incoming air directly enters air distribution board after filter, obtains required inlet flow conditions; Air-flow makes air uniform distribution through mixer; Incoming air enters the mixer of heater outlet after 6 electric heaters, and the air through different heating device is mixed again; Mixer outlet connects a threeway, and incoming air is divided into two-way, and a road enters empirical model through equipment jet pipe, and another road is bypath system, after tank cooling outside discharge chamber; Bypath system adopts nonstandard self-control water cooling radiator system to be cooled by high temperature air, and heat eliminating medium is water, and tank put into by heating radiator, adopts tap water supply circulation; Main road system is successively provided with air inlet circle and turns square section 1, and wait straight pressure-stabilizing section 2 and diffuser 3, diffuser 3 makes incoming flow supercharging slow down, and air-flow enters aero-turbine burning test section 4 after diffuser 3; In Cold simulating test, air-flow enters outlet circle turn square section 8 through the bypass of cold flow threeway 5 structural member, is divided into two-way to discharge via cold flow threeway 5, and outlet two-way regulates outlet aperture by orifice plate 9 and solenoid valve respectively; In Thermal-state test, air-flow turns square section 8 through rectangle water-cooled part spray cooling laggard inlet/outlet circle.
PIV optical measuring system comprises laser instrument, synchronizer, high speed camera and image software for calculation.When PIV optical measurement is carried out to empirical model, first turn square section 1 at air inlet circle and spray into particle, make in flow field, to dispense a large amount of trace particle and follow flow field motion; Double-pulse laser instrument is mainly as lighting source, two pulsed lasers are used spatially to overlap on a face through light beam bundling device, shot out by a light path exit radiation, through light-conducting arm and sheet laser system, produce the pulsatile tablets light source in illumination flow field.The trace particle being less than 10 microns owing to dispensing a large amount of particle diameter in flow field follows flow field motion, laser beam is expanded light in blocks through compound lens, sheet light to throw light on flow field through observation window 6 later, use digital camera by the left observation window shooting flow field photo of burning test section 4, the blind plate that right observation window blackening process is crossed does background, with the front and back two frame particle picture obtained, the velocity distribution that correlation computations obtains the tangent plane quantification in flow field is carried out to the particle picture in image.Further process can obtain the characteristic parameter of the flow field distributions such as flow field vorticity, streamline and line of equal velocity.When carrying out TDLAS and CARS optical measurement to empirical model, by beating laser, reasonable Arrangement light path to the both sides observation window of burning test section 4, measure the temperature of testpieces specified point, wherein TDLAS measures around primary holes along the integral temperature on two paths; CARS measures the temperature of each point in primary zone.
High speed camera is primarily of charge coupled device Charge Coupled Device, CCD is as imageing sensor, CCD converts digital signal to image, by external trigger once, in very short time, take two two field pictures is one group, the multiple series of images data of shooting are transferred in calculator memory simultaneously, show the image of shooting on computers.Synchronizer, by producing the pulse triggering signal in cycle time inner, through multiple delay path, produces delay triggering signal, to control laser instrument, high speed camera and computing machine, make they simultaneously, co-ordination.The view data that computing machine provides for storing image acquisition board, can complete the calculating of velocity field, display and storage in real time by PIV system software.Analysis software adopts image processing algorithm to reduce to original image, can obtain the measurement image of test zone, adopt two-dimentional quick Fourier transformation, calculates related function, according to speed definition, measures the displacement of particle in known interval, obtains its speed.Measure multiple particle simultaneously, can Flow Field Distribution figure be obtained.
Claims (2)
1. the integrated optical measuring table of an aeromotor main chamber, comprise optical measuring system, it is characterized in that: also comprise air inlet circle and turn square section, etc. straight pressure-stabilizing section, diffuser, burning test section, cold flow threeway, rear observation window, hot outlets water-cooled section, exporter turns round section, orifice plate, air inlet circle turns a square section and the straight pressure-stabilizing section leading section such as to be arranged on, be fixedly connected with diffuser etc. straight pressure-stabilizing section, combustion experiment section is positioned at diffuser and exporter turns between round section, combustion experiment section two ends by joint flange respectively with diffuser, exporter turns round section and is fixedly connected with, combustion experiment section both sides mosaic glass observation window is used for optical measurement, cold flow threeway and exporter turn round section and are connected, bypass is provided with orifice plate and rear observation window, main road is provided with pressure regulator valve, orifice plate coordinates with pressure regulator valve and regulates internal pressure of combustion chamber, in Cold simulating test, air-flow enters the exhaust of hot outlets water-cooled section through cold flow threeway bypass, in Thermal-state test, air-flow turns round section through the laggard inlet/outlet side of rectangle water-cooled part spray cooling,
Optical measuring system carries out PIV optical measurement to burning test section, turn square section at air inlet circle and spray into particle, the trace particle dispensed in flow field is with air motion, laser beam is expanded optical illumination flow field in blocks through compound lens, digital camera shooting flow field is used to obtain particle picture, the velocity distribution that correlation computations obtains the tangent plane quantification in flow field is carried out to particle picture, and obtains the characteristic parameter of the flow field distributions such as flow field vorticity, streamline and line of equal velocity after process.
2. the integrated optical measuring table of aeromotor main chamber according to claim 1, is characterized in that: particle diameter is less than 10 microns.
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| CN105628384A (en) * | 2015-12-21 | 2016-06-01 | 中国燃气涡轮研究院 | Aircraft engine afterburning monitoring device |
| CN106540824A (en) * | 2016-09-28 | 2017-03-29 | 西安航天动力研究所 | A kind of high frequency amplitude back-pressure vibrates atomization test device |
| CN107356437A (en) * | 2017-06-30 | 2017-11-17 | 同济大学 | A kind of simulation system for vehicle power cabin heat management |
| CN108562440A (en) * | 2017-12-26 | 2018-09-21 | 南京航空航天大学 | The combustor test device and its test method of air mass flow zonal control |
| CN109342070A (en) * | 2018-12-13 | 2019-02-15 | 中科航空动力(株洲)装备制造研究院有限公司 | Fuel nozzle spray cone angle self-operated measuring unit |
| CN109488488A (en) * | 2018-12-18 | 2019-03-19 | 中国人民解放军战略支援部队航天工程大学 | Test section suitable for combustion instability optical measurement longitudinal under high temperature and high pressure environment |
| CN109781420A (en) * | 2019-03-06 | 2019-05-21 | 中北大学 | A kind of visualization engine high pressure tumble flow air inlet experimental provision |
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| CN111703582A (en) * | 2020-06-29 | 2020-09-25 | 中国人民解放军第五七一九工厂 | Repairing method for observation window of high-temperature photosensimeter of aircraft engine |
| CN112763219A (en) * | 2020-12-31 | 2021-05-07 | 北京航天三发高科技有限公司 | Accurate simulation test bed of low discharge inflow parameter |
| CN113945382A (en) * | 2021-10-15 | 2022-01-18 | 中北大学 | Internal combustion power visual test evaluation system |
| CN114136479A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Optical machine structure for measuring outlet temperature distribution of combustion chamber |
| CN116625694A (en) * | 2023-07-21 | 2023-08-22 | 中国空气动力研究与发展中心空天技术研究所 | Quick replacement device for optical observation glass of scramjet engine |
| CN118066570A (en) * | 2024-04-17 | 2024-05-24 | 中国空气动力研究与发展中心空天技术研究所 | Stamping rotary detonation combustion chamber capable of realizing PLIF optical observation of circular section flow passage |
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| CN105628384B (en) * | 2015-12-21 | 2018-02-27 | 中国燃气涡轮研究院 | A kind of aeroengine thrust augmentation combustion monitoring device |
| CN105628384A (en) * | 2015-12-21 | 2016-06-01 | 中国燃气涡轮研究院 | Aircraft engine afterburning monitoring device |
| CN106540824A (en) * | 2016-09-28 | 2017-03-29 | 西安航天动力研究所 | A kind of high frequency amplitude back-pressure vibrates atomization test device |
| CN106540824B (en) * | 2016-09-28 | 2018-11-20 | 西安航天动力研究所 | A kind of high frequency amplitude back-pressure oscillation atomization test device |
| CN107356437B (en) * | 2017-06-30 | 2019-12-27 | 同济大学 | Simulation system for thermal management of vehicle power compartment |
| CN107356437A (en) * | 2017-06-30 | 2017-11-17 | 同济大学 | A kind of simulation system for vehicle power cabin heat management |
| CN108562440B (en) * | 2017-12-26 | 2020-07-07 | 南京航空航天大学 | Combustion chamber test device with air flow zone control and test method thereof |
| CN108562440A (en) * | 2017-12-26 | 2018-09-21 | 南京航空航天大学 | The combustor test device and its test method of air mass flow zonal control |
| CN109342070A (en) * | 2018-12-13 | 2019-02-15 | 中科航空动力(株洲)装备制造研究院有限公司 | Fuel nozzle spray cone angle self-operated measuring unit |
| CN109488488A (en) * | 2018-12-18 | 2019-03-19 | 中国人民解放军战略支援部队航天工程大学 | Test section suitable for combustion instability optical measurement longitudinal under high temperature and high pressure environment |
| CN109781420A (en) * | 2019-03-06 | 2019-05-21 | 中北大学 | A kind of visualization engine high pressure tumble flow air inlet experimental provision |
| CN111703582A (en) * | 2020-06-29 | 2020-09-25 | 中国人民解放军第五七一九工厂 | Repairing method for observation window of high-temperature photosensimeter of aircraft engine |
| CN111649953A (en) * | 2020-07-23 | 2020-09-11 | 中国航发湖南动力机械研究所 | Sand dust deposition test device |
| CN112763219A (en) * | 2020-12-31 | 2021-05-07 | 北京航天三发高科技有限公司 | Accurate simulation test bed of low discharge inflow parameter |
| CN113945382A (en) * | 2021-10-15 | 2022-01-18 | 中北大学 | Internal combustion power visual test evaluation system |
| CN113945382B (en) * | 2021-10-15 | 2023-06-23 | 中北大学 | Visual test evaluation system for internal combustion power |
| CN114136479A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Optical machine structure for measuring outlet temperature distribution of combustion chamber |
| CN114136479B (en) * | 2021-10-20 | 2023-06-13 | 中国航发四川燃气涡轮研究院 | Optical-mechanical structure for measuring outlet temperature distribution of combustion chamber |
| CN116625694A (en) * | 2023-07-21 | 2023-08-22 | 中国空气动力研究与发展中心空天技术研究所 | Quick replacement device for optical observation glass of scramjet engine |
| CN116625694B (en) * | 2023-07-21 | 2023-10-13 | 中国空气动力研究与发展中心空天技术研究所 | Quick replacement device for optical observation glass of scramjet engine |
| CN118066570A (en) * | 2024-04-17 | 2024-05-24 | 中国空气动力研究与发展中心空天技术研究所 | Stamping rotary detonation combustion chamber capable of realizing PLIF optical observation of circular section flow passage |
| CN118066570B (en) * | 2024-04-17 | 2024-07-12 | 中国空气动力研究与发展中心空天技术研究所 | Stamping rotary detonation combustion chamber capable of realizing PLIF optical observation of circular section flow passage |
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Application publication date: 20150708 |
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