CN108414231A - Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research - Google Patents
Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research Download PDFInfo
- Publication number
- CN108414231A CN108414231A CN201810582732.4A CN201810582732A CN108414231A CN 108414231 A CN108414231 A CN 108414231A CN 201810582732 A CN201810582732 A CN 201810582732A CN 108414231 A CN108414231 A CN 108414231A
- Authority
- CN
- China
- Prior art keywords
- air
- fuel
- section
- combustion
- cyclone
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 134
- 230000010355 oscillation Effects 0.000 title claims abstract description 29
- 238000011160 research Methods 0.000 title claims abstract description 24
- 239000000446 fuel Substances 0.000 claims abstract description 114
- 239000007921 spray Substances 0.000 claims abstract description 43
- 238000009792 diffusion process Methods 0.000 claims abstract description 26
- 239000003380 propellant Substances 0.000 claims abstract description 19
- 239000000463 material Substances 0.000 claims description 14
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 8
- 239000007769 metal material Substances 0.000 claims description 8
- 230000008878 coupling Effects 0.000 claims description 5
- 238000010168 coupling process Methods 0.000 claims description 5
- 238000005859 coupling reaction Methods 0.000 claims description 5
- 239000012212 insulator Substances 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 4
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 239000011521 glass Substances 0.000 claims description 2
- 230000005611 electricity Effects 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 15
- 238000012360 testing method Methods 0.000 abstract description 11
- 230000003287 optical effect Effects 0.000 abstract description 10
- 230000009471 action Effects 0.000 abstract description 4
- 238000005259 measurement Methods 0.000 abstract description 3
- 238000003745 diagnosis Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 20
- 238000002474 experimental method Methods 0.000 description 17
- 238000005516 engineering process Methods 0.000 description 13
- 230000032258 transport Effects 0.000 description 13
- 238000010586 diagram Methods 0.000 description 9
- 238000000034 method Methods 0.000 description 6
- 238000002156 mixing Methods 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 5
- 238000005496 tempering Methods 0.000 description 5
- 230000008602 contraction Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 238000010304 firing Methods 0.000 description 3
- 239000003921 oil Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 102100020760 Ferritin heavy chain Human genes 0.000 description 2
- 101001002987 Homo sapiens Ferritin heavy chain Proteins 0.000 description 2
- 238000013475 authorization Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000007084 catalytic combustion reaction Methods 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 238000000041 tunable diode laser absorption spectroscopy Methods 0.000 description 2
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- UHZZMRAGKVHANO-UHFFFAOYSA-M chlormequat chloride Chemical compound [Cl-].C[N+](C)(C)CCCl UHZZMRAGKVHANO-UHFFFAOYSA-M 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 239000004071 soot Substances 0.000 description 1
- 230000003595 spectral effect Effects 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000002834 transmittance Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 239000013598 vector Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Classifications
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M10/00—Hydrodynamic testing; Arrangements in or on ship-testing tanks or water tunnels
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Fluid Mechanics (AREA)
Abstract
The present invention relates to aero-engines and gas turbine basis experimental study field, a kind of Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research is disclosed, is made of respectively loud speaker section, air section in room, cyclone section, windowing burning zone, five part of combustion chamber extension from bottom to top.Air flows through air supply pipe into after entering room, and by the incentive action of loud speaker, cocurrent can get the sound field environment needed and Swirling Flow environment after axial-flow type cyclone.Three tunnel fuel supply pipe may be implemented in the propellant spray of different location, obtain the swirl flow combustions Field Characteristics such as premixed combustion, diffusion combustion and its mixed mode.This experimental rig use modularized design, main function components are detachable, operating condition of test parameter, sound field conditions, spray position can flexible modulation, can prevent flame from returning.Rectangle four sides windowing combustion chamber can be compatible with various advanced optical devices, is obtained convenient for the measurement of combustion diagnosis data.
Description
Technical field
The present invention relates to aero-engines and gas turbine basis experimental study field, are used for more particularly to one kind
The Modular trial device of swirl flow combustion thermal acoustic oscillation characteristic research.
Background technology
The environmental degradation problem of getting worse, watershed management of the countries in the world to pollution are faced in global range at present
Theory has also reached height and has known together.And the mankind are the major reasons for causing current environment to pollute to the overconsumption of fossil energy.
Current field of energy utilization diffusion combustion mode largely uses, and is to generate thermal NO (NOX) one of main contributor.
With gas turbine, aero engine emissions standard it is increasingly strict, great market demand driving advanced low emissions combustion group
Knit the rapid development of technology.Present developing three big combustion with reduced pollutants technology includes lean premixed combustion technology (LPM), fuel-rich
Lean-burn topologies (RQL), catalytic combustion technology are put out soon.Afterwards in the two, RQL technologies are faced with soot and are formed and the difficulty on mixed performance
There is limitation in cost, service life, secure context in topic, catalytic combustion technology.Poor oil firing can be based on existing combustion technology, not right
Existing combustion system structure carries out performance Promotion Transformation, therefore following Combustion System Design under the premise of being significantly alterred
In, it is lean premixed or it is lean premixed be combined with diffusion combustion, will be more for the potentiality of widespread adoption.
However lean premixed burning is also faced with new problem, it is still necessary to the burning to being directed in laboratory conditions
It learns Basic Problems and carries out a large amount of experimental study.Compared to traditional diffusion combustion, lean premixed combustion technology is easier to control
Flame temperature processed can avoid localized high temperature regions and exist and lead to thermal NOXGeneration.But since potential flame returns
The unsteady phenomenon such as biography, self-ignition exists, and there are certain operation risks, especially poor oil firing to easily lead to heat for premixed combustion technology
Sound oscillation, steady operation boundary are narrow.When combustion oscillation occurs, the pressure occurred under specific frequency is substantially pulsed, is burnt
Wild effect can influence the normal work of combustion system, or induce engine surge, and heat transfer deterioration can be caused when serious and is led
It causes structure to destroy, limits the extensive use of poor oil firing's technology.Combustion oscillation is the classical project of kinetics of combustion research,
Inducement mechanism is complicated, and shows certain nonlinear characteristic.Basic research result thinks, the phase mutual coupling between " sound-whirlpool-heat "
Conjunction mechanism is the basic reason that combustion oscillation generates.
It is in a laboratory environment the common research means in the field to simplifying combustion chamber to carry out reduced scale simulation.In order to right
The physical mechanism wherein contained carries out experimental study and verification, needs to develop a kind of basic combustion test platform.Due to aviation
Cyclone mode is largely used to stablize flame, tissue burning in engine and gas-turbine combustion chamber structure design.It is directed to
A large amount of complex flow structure, such as vortex shedding and broken, precession vortex core evolution, the relevant vortex structure of turbulent flow large scale, liquid fuel
Spraying formation etc., the interaction process between these Complex Flows and flame directly affect combustion chamber ignition performance, burning
Various works performance such as efficiency, disposal of pollutants, dynamic characteristic.Have studies have shown that chamber structure, propellant spray mixing side
Formula, fuel premix degree, incoming working condition etc. all may be to Swirling Flow feature, flame characteristics and its combustion oscillations
Generating process has an impact.Therefore, in order to study influence of many kinds of parameters to swirl flow combustion process, need one kind that can join to structure
Number, duty parameter, sound field conditions carry out the experimental rig of flexible modulation and control as research platform, and can be compatible with various elder generations
Into flow field optical diagnostic devices, to obtain the interior details information of combustion process.
In terms of presently disclosed document, carry out the testing equipment of swirl flame research in the presence of having a single function, there are operating mode ginsengs
The characteristics of number can not be flexibly arranged or main function components can not split replacement.Mansions Li Ren in 2014 et al. devise a kind of eddy flow
Combustion chamber experimental provision (Authorization Notice No. CN203849024U), including air-flow feed system, fuel oil supply system, eddy flow are real
Part and test system are tested, for testing different cyclones, oil-gas ratio and air velocity to three dimensional velocity vectors distribution, Temperature Distribution
With the influence of exhaust gas composition, the performance and structure of swirl combustion chamber are judged and improved.But the device is only capable of simulating different oil-gas ratioes
Under swirl flow combustion situation, different combustion modes cannot be simulated, also be not directed to the simulation to thermal acoustic oscillation, function list
One.2017, Yang Yao et al. devises a kind of device measuring turbulent burner thermoacoustic transitive relation, and (Authorization Notice No. was
), including gas distributing chamber, combustion chamber, turbulent burner, sonic vibrator, hot line wind speed probe, photomultiplier and height CN207019906U
Fast camera, for measuring influence of the acoustic excitation to flame forms and exothermic heat of reaction rate, to study turbulent burner thermoacoustic
The thermoacoustic transitive relation of coupling.But the device is only capable of influence of the acoustic excitation to swirl flow combustion under research premixed combustion mode, not
It is related to other combustion modes, premix fuel is passed directly into gas distributing chamber, there are fuel to be tempered risk.Premixing fuel simultaneously may be into
Enter inside the sound field driver in downstream, causes the damage and danger of device.
Invention content
The purpose of the invention is to overcome swirl flow combustion thermal acoustic oscillation experimental rig of the existing technology to have a single function,
Test parameters range is limited, there are problems that premixing fuel tempering risk, provides a kind of for swirl flow combustion thermal acoustic oscillation characteristic
The Modular trial device of research, the device have the premixed combustion state that can simulate, diffusion combustion state and are mixed and burned state
The thermal acoustic oscillation characteristic of lower eddy flow Combustion Flow Field feature and swirl flow combustion, can effectively prevent flame to return, using modularized design,
Replaceable each main function components, can flexible modulation operating condition of test parameter, sound field conditions, spray position.
To achieve the goals above, the present invention provides a kind of modularization examination for swirl flow combustion thermal acoustic oscillation characteristic research
Experiment device, including the loud speaker section, air section in room, cyclone section, windowing burning zone and the combustion chamber that arrange from bottom to top extend
Section and pipe-line system.
The loud speaker intersegmental part is equipped with loud speaker；Air section in the room inner mold face is in contraction-like, is internally provided with rectification
Grid is set in the same level of lower part there are one entrance and symmetrical more than one air intake, and top is equipped with upper
Portion's flange, the upper flange close the annular gap to be formed with air surface cover in chamber outer wall and constitute gas collection ring cavity, the collector ring
Chamber communicated with the air section in room inner cavity by spray orifice and；The cyclone section includes cyclone sleeve and cyclone, institute
It is whole nestable together in being formed in the cyclone sleeve to state cyclone coaxial sleeve, upper part stretches into the windowing burning zone；Institute
It includes windowing combustion-chamber frame, combustion chamber wall surface tablet and windowing cover board to state windowing burning zone, on the combustion chamber wall surface tablet
Equipped with ignitor；Flange is used to fasten between each section successively coaxially connected.
The pipe-line system includes airflow pipe, premix fuel channel, diffused fuel pipeline and windowing burning zone combustion
Expect spray pipeline；The airflow pipe is connected with the air intake；The premix fuel channel and the collector ring
Chamber is connected；The diffused fuel pipeline enters the air section in room by the entrance, is connected to set on described
The diffusion fuel nozzle to open a window in burning zone；The windowing burning zone propellant spray pipeline is set on the combustion chamber wall surface tablet
The spray orifice set is connected.
Preferably, the airflow pipe includes air interface flange, air straight pipeline, air armful ring and air intake
Branch, air straight pipeline one end are connected with the air interface flange, and the lateral wall that one end embraces ring with the air is connected；
It is open annular that the air, which embraces ring, and the symmetric position of the madial wall of ring is connected with four air intake branches respectively；Institute
Air intake branch is stated in symmetrically arranged four air intakes of the air pars infrasegmentalis in room to be connected.
Preferably, the premix fuel channel includes premix fuel conveying pipe, premix fuel armful ring and premix fuel diameter
It constitutes to branch pipe, is connected by welding or screw-threaded coupling tightening seal between pipeline；The premix fuel radial direction branch pipe and the collection
Compression ring chamber connects.
Preferably, the diffused fuel pipeline includes the horizontal transport tube of diffused fuel, diffused fuel vertical transport pipe and expansion
Dissipate fuel nozzle；The horizontal transport tube of diffused fuel passes through the entrance and the diffused fuel vertical transport pipe phase
Even, the horizontal transport tube of diffused fuel is compressed by nut and gasket with the air wall surface in outdoor and is sealed；The diffusion
Fuel vertical transport pipe passes through the center of flow straightening grid and cyclone, is connect with the diffusion fuel nozzle.
Preferably, the cyclone includes cyclone holder, swirl vane and eddy flow wheel hub；The swirl vane is in certain
Oblique angle is distributed, and size, number and the angle of the swirl vane ensure that axial direction is upper opaque.
Preferably, there are two types of the combustion chamber wall surface tablets, respectively quartz glass material and metal material are made；It is described
Quartz glass material combustion chamber wall surface tablet is observed for flame, and the wall surface of the metal material combustion chamber wall surface tablet is equipped with battle array
Hole is arranged, propellant spray hole and ignitor hole are used as.
Preferably, the ignitor includes ignitor needle, ignitor insulator, ignition electrode housing and electrode locking
Nut, the ignitor needle can move axially in the ignitor；The ignitor can be disposed at the combustion chamber
In the different holes of the wall surface array hole of wall surface tablet.
Preferably, it is provided with heat insulating mattress between the loud speaker section and the air section in room.
Preferably, the present invention further includes a bottom for the Modular trial device of swirl flow combustion thermal acoustic oscillation characteristic research
Seat, the loud speaker section, the air section in room, the cyclone section, the windowing burning zone and the combustion chamber extension
Whole right angle setting is on the base.
Through the above technical solutions, main part is installed using vertical mode, using modularized design, adopted between each component
It, can be easy to disassemble with flanged joint.Loud speaker is installed in loud speaker section, applies the acoustics of certain spectral characteristic to primary air
Feature.Air section in room is used to carry out collecting rectification to the air for embracing ring branch inlet.Cyclone section can install different structure spy
The axial-flow type cyclone of sign applies tangential component to air.The burning zone that opens a window is used for the tissue of swirl flow combustion process, using rectangle
Four sides windowing design, is observed convenient for flame.Combustion chamber extension for exhaust emissions or throttles to primary air, control master
Flow velocity degree and chamber pressure.Fixed placement is in mounting seat after the installation of main functionality component combination.Pipe-line system includes sky
Letter shoot road and three classes fuel tube respectively premix fuel supply pipe, diffused fuel supply line, windowing Duan Ran
Burn room supply line.Airflow pipe is used for air conveying in room air and forms flow field, and three classes fuel tube is logical
The selection of different spray positions is crossed, it can be achieved that swirl-flow premixed flame, eddy flow diffusion flame and its burning in composite mode, and is not had
There is tempering risk.Meanwhile, it can be achieved that realizing that the fuel of secondary flame is horizontal in windowing combustion chamber under the cooperation of these swirl flames
To spray and burning.
The experimental rig of the present invention has the following advantages that：
1, using modularized design thinking, major function parts are designed using discrete, can flexibly be dismantled and quickly more
It changes, can adapt to the diversified demand of test function, greatly save experimentation cost and experiment preparatory period.
2, bottom setting loud speaker applies sound field disturbance to incoming air, by control the frequency of sound field, amplitude, waveform,
The parameters such as power modulate different combustion chamber sound field characteristics, can meet combustion chamber acoustic oscillations mechanism, combustion chamber oscillation inhibits
The experimental study of the classes such as method.
3, cyclone component can be dismantled flexibly, and different swirling numbers, different leaves size etc. can be needed replacing according to experiment
The cyclone of structural parameters obtains the flox condition of different eddy flow flow performances with this.
4, multiple propellant spray entrances are set, when experiment by the selection of different spray positions, it can be achieved that premix, diffusion and
Its a variety of swirl flame operating mode in composite mode, without tempering risk under premixed combustion mode.
5, combustion chamber uses segment design, is made of windowing burning zone and combustion chamber extension, between by flanged joint,
The extension of different length and area shrinkage characteristic flexibly can be selected and replace when carrying out experiment according to experiment needs.
6, windowing burning zone, can be real by quartz glass material combustion chamber wall surface tablet using the windowing design of rectangle four sides
The week of existing combustion flame obtains comprehensive flame oscillation characteristic optical flow field diagnostic data to optical measurement.
7, array mounting hole is preset on the metal material combustion chamber wall surface tablet of windowing burning zone, for pressure-measuring-point
The installation of arrangement or ignitor, and can realize the flexible modulation of ignition location.
Description of the drawings
Following drawings is used to provide further understanding of the present invention, and a part for constitution instruction, and following
Specific implementation mode be used to explain the present invention together, but protection scope of the present invention is not limited to following attached drawings and specific real
Apply mode.In the accompanying drawings：
Fig. 1 is the experimental rig appearance diagram of the present invention；
Fig. 2 is the experimental rig diagrammatic cross-section of the present invention；
Fig. 3 is the partial enlarged view of circle part A in Fig. 2；
Fig. 4 is eddy flow section partial appearance stereogram；
Fig. 5 is eddy flow section partial cutaway schematic view；
Fig. 6 is windowing burning zone structural schematic diagram；
Fig. 7 is metal material combustion chamber wall surface tablet schematic diagram；
Fig. 8 is the sectional view along A-A of Fig. 7；
Fig. 9 is airflow pipe structural schematic diagram；
Figure 10 is premix fuel conveying pipe primary structure schematic diagram；
Figure 11 is diffused fuel pipeline and neighbouring primary structure schematic diagram；
Figure 12 is ignitor structural schematic diagram.
Reference sign
1 air section in room, 2 combustion chamber extension
3 windowing 4 cyclone sections of burning zone
5 loud speaker section, 6 pedestal
7 pipe-line system, 8 ignitor
11 air wall surface in outdoor, 12 flow straightening grid
13 entrance, 14 air intake
15 upper flange, 16 gas collection ring cavity
17 spray orifice, 18 heat insulating mattress
19 lower flanges 31 windowing combustion-chamber frame
32 combustion chamber wall surface tablets 33 windowing cover board
311 windowing burning 41 cyclone sleeves of flange
42 cyclone, 421 cyclone holder
422 swirl vane, 423 eddy flow wheel hub
51 loud speaker, 52 loud speaker section outside wall surface
53 separate space, 54 loudspeaker diffuser film surface
61 mounting seat table top, 62 mounting seat supporting leg
63 mounting seat fixed feet, 71 airflow pipe
711 air interface flange, 712 air straight pipeline
713 air embrace 714 air intake branch of ring
72 premix fuel channels 721 premix fuel conveying pipe
722 premix fuel embrace ring 723 and premix fuel radial direction branch pipe
The horizontal transport tube of 73 diffused fuel pipeline, 731 diffused fuel
732 diffused fuel vertical transport pipe, 733 diffusion fuel nozzle
74 windowing burning zone propellant spray pipeline, 81 ignitor needle
82 ignitor insulator, 83 ignition electrode housing
84 electrode locking nuts
Specific implementation mode
The specific implementation mode of the present invention is described in detail below in conjunction with attached drawing, it should be appreciated that retouch in this place
The specific implementation mode stated is merely to illustrate and explain the present invention, and protection scope of the present invention is not limited to following specific realities
Apply mode.
Fig. 1 is the appearance diagram of experimental rig one embodiment of the present invention.Experimental rig main part is using vertical
Mode is installed, and includes loud speaker section 5, air section in room 1, cyclone section 4, windowing burning zone 3, combustion chamber extension from bottom to top
2.Flanged joint is used between each section, can facilitate handling.Each section of various pieces can pre-set mounting hole, and arrangement thermometric is surveyed
The monitoring devices such as pressure, for obtaining internal flow field and sound field information.Experimental rig main part is mounted in mounting seat 6.
The design of homalographic section can be used in combustion chamber extension 2, contraction designs or what cooperation tail gas was drained needs for burning waste gas row
It puts.When being designed using cross-sectional constriction, it is big that the size of shrinkage area can be used for adjusting the flow velocity of air and pressure in windowing burning zone 3
It is small.The pipe-line system 7 of experimental rig includes four class pipelines, respectively airflow pipe 71, premixes fuel channel 72, diffusion combustion
Pipe material 73, windowing burning zone propellant spray pipeline 74.Wherein airflow pipe 71 is for providing required master for test section
Air is flowed, standard flange structure is used between air delivery pipe pipeline joint and air gas source pipe, air mass flow is according to combustion chamber
The size of the flow rates of required air and select, the flow rates of combustion chamber can be adjusted between 0~150m/s.Premix
Fuel channel 72 is for providing the propellant spray service duct formed needed for premixed combustion condition.Diffused fuel pipeline 73 is for carrying
For forming the required propellant spray service duct of diffusion combustion condition.Burning zone fuel channel 74 open a window for burning in windowing
The different location of section provides the service duct of propellant spray.Each fuel channel can need to carry out fuel simultaneously or respectively according to experiment
Supply, fuel flow rate are accurately controlled by equipment such as the flow controller being arranged in upstream or proportioning valves.
Fig. 2 is the diagrammatic cross-section of the present embodiment.For air section in room 1 using shrinkage type channel, it is whole that inside is equipped with air
Flow grid 12 and diffused fuel pipeline 73.Flow straightening grid 12 is detachable, selects different light transmittances in experiment as needed
Grid model.Flow straightening grid is used to large-scale vortex structure being broken into small-scale structure, improves flow field uniformity quality.Air is stayed
Entrance 13 and four air intakes 14 there are one being set in the lower part same level of room section 1, four air intakes 14 are in sky
It is symmetrical on the horizontal plane of gas wall surface in outdoor 11.As shown in figure 3, the upper flange 15 and air of air section in room 1 stay room
The annular gap that 11 fitting of outside wall surface is formed constitutes the gas collection ring cavity 16 of premix fuel, and the inner wall of gas collection ring cavity 16 is provided with premix combustion
The spray orifice 17 of material.As shown in figure 3, the present embodiment uses Integral welded structure.It is needing to carry out more the spray orifice for premixing fuel
In the case of changing, point of flanged joint can also be used between upper flange 15 and the air wall surface in outdoor 11 of air section in room 1
It is designed from formula, and realizes the excellent sealing of the gas collection ring cavity 16 of premix fuel.The spray position of fuel is premixed due to being arranged in sky
The shrinkage type face position of gas section in room 1, flowing velocity is high, is on the one hand conducive to the quick blending of fuel and air, on the other hand
It can effectively prevent the generation of premix fuel tempering phenomenon.
As shown in figure 3, cyclone section 4 is pressed between windowing burning zone 3 and air section in room 1, using fastening bolt according to
The secondary flange hole across air section in room upper flange 15 and the combustion chamber flange 311 that opens a window, alignment locking connection, end face contact site
Seal groove is opened in position, and places seal washer.Cyclone section 4 is combined by 42 sets of cyclone sleeve 41 and cyclone.Such as Fig. 4, Fig. 5
Shown, cyclone 42 includes 423 three parts of cyclone holder 421, swirl vane 422 and eddy flow wheel hub, is used between each section
Welding or overall processing are formed.The form parameter of swirl vane 422 includes swirl angle, number of blade etc., different form parameters
Combination can form different swirling numbers.There is fuel feed passage inside eddy flow wheel hub 423, for transporting for diffused fuel, end connects
Connect diffusion fuel nozzle 733.Diffusion fuel nozzle 733 can flexibly be replaced according to the demand of operating condition of test.
Combustion section 3 open a window using the windowing design of four sides rectangle.As shown in fig. 6, combustion chamber wall surface tablet 32 is fastened on out
On window combustion-chamber frame 31, rectangular swirl flow combustion space is crowded around.The window for the section that opens a window can be according to experiment needs, selection quartz
Glass material combustion chamber wall surface tablet 32 and/or stainless steel combustion chamber wall surface tablet 32.When selecting quartz glass, tested
Optical instrument can be used in journey combustion flame is observed and is measured.Compatible optical measuring apparatus includes but not limited to
The means such as PLIF, PIV, TDLAS, high speed camera imaging combustion.As shown in Figure 7, Figure 8, metal material combustion chamber wall surface tablet 32
Stainless steel etc. can be used to be made, needed that array hole is arranged in different location according to experiment, be used for the peace of ignitor and ejector filler
Dress.As shown in Fig. 2, two opposite faces of combustion chamber wall surface can arrange ignitor pair 8, and the peace of array arrangement on wall surface can be passed through
It fills hole and carries out up and down adjustment, to realize the selection of different ignition locations.Ignitor structure is as shown in figure 12, ignitor needle 81
It is linked in ignition electrode housing 83 after being coated by insulator 82, while being locked by electrode locking nut.Ignitor can be with
Transverse shifting is adjusted.Array hole can also install propellant spray device other than it can install electrode.The position of propellant spray device can
It is adjusted with being needed according to experiment.Propellant spray is carried out in windowing burning zone, two under the cooperation of swirl flame may be implemented
The blending of secondary flame fuel or combustion research.
As shown in Fig. 2, loud speaker section 5 and air section in room 1 between air pars infrasegmentalis in room flange 19 by passing through bolt
Connection is connected and is separated using heat insulating mattress 18 at section, prevents the heat that combustion chamber generates from generating conduction of heat to loud speaker.It raises
Sound device 51 is placed on using product ripe in the market in the vessel for section of raising one's voice, and loudspeaker diffuser film surface 54 is towards air section in room
1.Gap separate space 53 between loud speaker 51 and loud speaker section outside wall surface 52 is filled using sound-proof material or other flexible materials, is prevented
Generate echo reflection.The signal wiring of loud speaker in outside wall surface trepanning with external signal power amplifier by being connected, power
Size is adjustable.Using the acoustic signal of frequency, amplitude and wave character needed for signal generator generation.
Mounting seat 6 is used to prop up the main part of experimental rig.Mounting seat table top 61 and mounting seat fixed feet 63
Between fixed by mounting seat supporting leg 62, between adopt and be bolted connection, the gap between bolt can be used for platform tune
It is whole to horizontal position.
Fig. 9 is airflow pipe structural schematic diagram, and airflow pipe 71 includes sequentially connected air interface flange
711, air straight pipeline 712, air embrace ring 713 and air intake branch 714.It is open annular that air, which embraces ring 713,；Air intake
There are four branches 714, is symmetrically distributed in the inside that air embraces ring 713.Air intake branch 714 is connected in air section in room
Air intake 14, as shown in Fig. 2, air enters air through airflow pipe 71 by air intake 14 stays interior.It is whole through air
Flow the laggard contraction section for entering room of rectified action of grid 12.In the process, the loudspeaker diffuser film surface 54 of the installation of lower part in room
Effect of vibration apply the sound field of certain frequency and amplitude characteristic to air and pulse.After air is rectified through in room contraction section into
Enter cyclone section 4.Air flows through and forms different eddy flows in downstream windowing combustion chamber regions after the cyclones of different swirling number features
The Field Characteristics of flow structure.
As shown in Fig. 2, Figure 11, the horizontal transport tube of the diffused fuel of diffused fuel pipeline 73 731 is horizontally through air and stays room
After entrance 13 in section 1, the axial centerline deviation an angle of 90 degrees of room is stayed in air, and along central axis to cyclone section
4 extend, and form diffused fuel vertical transport pipe 732.Diffused fuel vertical transport pipe 732 passes through center and the rotation of flow straightening grid 12
The center of stream device 42 is connected with diffusion fuel nozzle 733.Ripe business gas nozzle can be selected in diffusion fuel nozzle 733
Or atomizer, using threaded connection, removable and replaceable.Fuel channel is directly compressed using conical seal (contact) face by screw thread close
It seals, detachable between each component, replaceable and repair.Gap between the horizontal transport tube 731 of diffused fuel and entrance 13
Sealing is compressed by nut and gasket.
As shown in Figure 10, premix fuel channel 72 embraces ring 722 and premix by premix fuel conveying pipe 721, premix fuel
Fuel radial direction branch pipe 723 is sequentially connected composition, is connected by welding or screw-threaded coupling tightening seal between pipeline；It is radial to premix fuel
Branch pipe 723 is connected with the gas collection ring cavity 16 on 1 top of air section in room.Fuel enters pre- after premixing fuel conveying pipe 721
Mixed fuel embraces ring 722, then enters gas collection ring cavity 16 through premixing fuel radial direction branch pipe 723, is entered by premix fuel jet orifice 17 empty
Gas section in room 1.
The spray orifice 17 of premix fuel is arranged in a manner of annular circumferential array on the wall surface of room.The quantity root of spray orifice 17
It is designed according to the needs of fuel flow rate and penetration height.The shape of spray orifice 17 can be radial straight hole or beveling hole, and fuel is through spray
Hole 17 quickly blends after entering swirler passages with air and downstream combustion room transports, and forms the premixed flow of fuel and air.
Fuel determines that the premix degree of fuel, the segment distance can refer to air collapsible tubes the distance between from spray point to swirl vane
Flow velocity size in road optimizes.
The operation principle of the present embodiment is as follows：After air enters air section in room 1, in the disturbance of 51 vibrophone of loud speaker
Under effect, the acoustic feature amount of certain spectrum signature is obtained.By the rectified action of flow straightening grid 12, large scale eddy is broken,
Air obtains axial velocity component, and the uniformity quality in the macroscopic view such as flow field velocity, whirlpool scale feature flow field gets a promotion.Rectification
Air afterwards enters cyclone section 4 along contraction section in room, and speed further increases, since the barrier effect of swirl vane 422 changes
It changes direction, primary air is made to obtain a tangential component.Air forms typical swirl flow combustion stream after entering windowing combustion chamber
.The unsteady feature of the permanent feature and eddy flow turbo-charger set of different Swirling Flows will be obtained under different vane cyclone numbers.Combustion
Fuel gas or liquid fuel can be selected in material.The selection of different propellant spray positions means different combustion modes.Pre-
Under mixed combustion mode, fuel is supplied by premixing fuel channel 72, is sprayed in the spray orifice 17 of the collapsed position of air section in room 1
Note, is blended with mainstream, and after certain mixing distance, fuel and air mixed performance is constantly promoted, by eddy flow leaf
More fully pre-mix state is formed after the stirring action of piece 422, and premixed combustion state is formed after igniting.Diffused fuel pipeline
In 733 spray of diffusion fuel nozzle of 423 end of eddy flow wheel hub, fuel is directly carried out with mainstream rotational flow air fuel in 73
Blending, what is formed after igniting is non-premix diffusion flame.The cooperation of two kinds of spray positions is applicable in experiment, can form premix
Mixed firinor fuel burning mode under the conditions of two kinds of diffusion combustion.Fuel in windowing burning zone propellant spray pipeline 74 is in windowing burning zone
, it can be achieved that the diffusion combustion of empir-ical formulation, can be used for carrying out secondary under the cooperation of swirl flame when lateral spray on 3 wall surface
The blending of flame fuel or combustion research.The burning zone 3 that opens a window is designed using full open window, and the optical radiation signal of combustion flame penetrates stone
The combustion chamber wall surface tablet 32 of English glass material can be received by the exploring block of the optical diagnostic systems such as PIV, TDLAS, PLIF.
From the above, it can be seen that the experimental rig of the present invention has the following advantages that：
Using modularized design thinking, major function parts are designed using discrete, can flexibly be dismantled and quick-replaceable,
The diversified demand that can adapt to test function greatlys save experimentation cost and experiment preparatory period.
The loud speaker 51 being arranged by bottom applies sound field disturbance to incoming air, by control the frequency of sound field, amplitude,
The parameters such as waveform, power modulate different combustion chamber sound field characteristics, can meet combustion chamber acoustic oscillations mechanism, combustion chamber shakes
Swing the experimental study of the classes such as suppressing method.
42 component of cyclone can be dismantled flexibly, and different swirling numbers, different leaves size etc. can be needed replacing according to experiment
The cyclone of structural parameters obtains the flox condition of different eddy flow flow performances with this.
Multiple propellant spray entrances are set, when experiment by the selection of different spray positions, it can be achieved that premix, diffusion and its
A variety of swirl flame operating modes in composite mode, without tempering risk under premixed combustion mode.
Burning zone uses segment design, is made of windowing burning zone 3 and combustion chamber extension 2, between by flanged joint,
The extension of different length and area shrinkage characteristic flexibly can be selected and replace when carrying out experiment according to experiment needs.
The burning zone 3 that opens a window is designed using the windowing of rectangle four sides, by replacing quartz glass material combustion chamber wall surface tablet 32,
The week of combustion flame can be achieved to optical measurement, obtain comprehensive flame oscillation characteristic optical flow field diagnostic data.
By the preset array mounting hole on metal material combustion chamber wall surface tablet 32, it to be used for the arrangement of pressure-measuring-point
And/or the installation of ignitor 8, and can realize the flexible modulation of ignition location.
The preferred embodiment of the present invention is described in detail above in association with attached drawing, still, the present invention is not limited thereto.At this
In the range of the technology design of invention, a variety of simple variants, including each particular technique can be carried out to technical scheme of the present invention
Feature is combined in any suitable manner, and in order to avoid unnecessary repetition, the present invention is to various combinations of possible ways
No longer separately illustrate.But it should also be regarded as the disclosure of the present invention for these simple variants and combination, belongs to the present invention
Protection domain.
Claims (9)
1. a kind of Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research, which is characterized in that including from lower and
Loud speaker section (5), air section in room (1), cyclone section (4), windowing burning zone (3) and the combustion chamber extension (2) of upper arrangement
And pipe-line system (7)；
The loud speaker section (5) is internally provided with loud speaker (51)；Air section in room (1) the inner mold face is in contraction-like, and inside is set
There is flow straightening grid (12), sets in the same level of lower part and enter there are one entrance (13) and symmetrical more than one air
Mouth (14), top are equipped with upper flange (15), the ring that the upper flange (15) is formed with air wall surface in outdoor (11) fitting
Shape gap constitutes gas collection ring cavity (16), and the gas collection ring cavity (16) passes through spray orifice (17) and air section in room (1) inner cavity phase
It is logical and；The cyclone section (4) includes cyclone sleeve (41) and cyclone (42), cyclone (42) coaxial sleeve together in
In the cyclone sleeve (41), upper part stretches into the windowing burning zone (3)；The windowing burning zone (3) includes windowing
Combustion-chamber frame (31), combustion chamber wall surface tablet (32) and windowing cover board (33), the combustion chamber wall surface tablet (32) are equipped with
Ignitor (8)；Flange is used to fasten between each section successively coaxially connected；
The pipe-line system (7) includes airflow pipe (71), premix fuel channel (72), diffused fuel pipeline (73) and opens
Window burning zone propellant spray pipeline (74)；The airflow pipe (71) is connected with the air intake (14)；It is described pre-
Mixed fuel channel (72) is connected with the gas collection ring cavity (16)；The diffused fuel pipeline (73) passes through the entrance
(13) the air section in room (1) is entered, the diffusion fuel nozzle (733) being connected in the windowing burning zone (3)；
The windowing burning zone propellant spray pipeline (74) is connected with the spray orifice being arranged on the combustion chamber wall surface tablet (32).
2. the Modular trial device according to claim 1 for swirl flow combustion thermal acoustic oscillation characteristic research, feature
It is, the airflow pipe (71) includes air interface flange (711), air straight pipeline (712), air armful ring (713)
With air intake branch (714), described air straight pipeline (712) one end is connected with the air interface flange (711), one end with
The lateral wall that the air embraces ring (713) is connected；It is open annular, the symmetrical position of the madial wall of ring that the air, which embraces ring (713),
It sets and is connected respectively with four air intake branches (714)；The air intake branch (714) in the air section in room
(1) symmetrically arranged four of the lower part air intake (14) is connected.
3. the Modular trial device according to claim 1 for swirl flow combustion thermal acoustic oscillation characteristic research, feature
It is, the premix fuel channel (72) includes premix fuel conveying pipe (721), premix fuel armful ring (722) and premix combustion
Material diameter is constituted to branch pipe (723), is connected by welding or screw-threaded coupling tightening seal between pipeline；The premix fuel radial direction branch pipe
(723) it is connect with the gas collection ring cavity (16).
4. the Modular trial device according to claim 1 for swirl flow combustion thermal acoustic oscillation characteristic research, feature
It is, the diffused fuel pipeline (73) includes the horizontal transport tube of diffused fuel (731), diffused fuel vertical transport pipe (732)
With diffusion fuel nozzle (733)；The horizontal transport tube of diffused fuel (731) passes through the entrance (13) and the diffusion
Fuel vertical transport pipe (732) is connected, and the horizontal transport tube of diffused fuel (731) is logical with the air wall surface in outdoor (11)
It crosses nut and gasket compresses sealing；The diffused fuel vertical transport pipe (732) passes through flow straightening grid (12) and cyclone (42)
Center, connect with the diffusion fuel nozzle (733).
5. the Modular trial device according to claim 1 for swirl flow combustion thermal acoustic oscillation characteristic research, feature
It is, the cyclone (42) includes cyclone holder (421), swirl vane (422) and eddy flow wheel hub (423)；The eddy flow
Blade (422) is distributed in a fixed inclination, and size, number and the angle of the swirl vane (422) ensure that axial direction is upper opaque.
6. the Modular trial device according to claim 1 for swirl flow combustion thermal acoustic oscillation characteristic research, feature
It is, there are two types of the combustion chamber wall surface tablets (32), and respectively quartz glass material and metal material are made；The quartz glass
Glass material combustion chamber wall surface tablet (32) is observed for flame, and the wall surface of the metal material combustion chamber wall surface tablet (32) is equipped with
Array hole is used as propellant spray hole and ignitor hole.
7. the Modular trial device according to claim 6 for swirl flow combustion thermal acoustic oscillation characteristic research, feature
It is, the ignitor (8) includes ignitor needle (81), ignitor insulator (82), ignition electrode housing (83) and electricity
Pole locking nut (84), the ignitor needle (81) can the axial movements in the ignitor (8)；The ignitor
(8) it can be disposed in the different holes of the wall surface array hole of the combustion chamber wall surface tablet (32).
8. the Modular trial device according to claim 1 for swirl flow combustion thermal acoustic oscillation characteristic research, feature
It is, heat insulating mattress (18) is provided between the loud speaker section (5) and the air section in room (1).
9. the Modular trial device according to claim 1 for swirl flow combustion thermal acoustic oscillation characteristic research, feature
It is, further includes a pedestal (6), it is the loud speaker section (5), the air section in room (1), the cyclone section (4), described
Windowing burning zone (3) and the combustion chamber extension (2) are integrally vertically mounted on the pedestal (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810582732.4A CN108414231A (en) | 2018-06-07 | 2018-06-07 | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810582732.4A CN108414231A (en) | 2018-06-07 | 2018-06-07 | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108414231A true CN108414231A (en) | 2018-08-17 |
Family
ID=63141425
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810582732.4A Pending CN108414231A (en) | 2018-06-07 | 2018-06-07 | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108414231A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109612739A (en) * | 2018-11-15 | 2019-04-12 | 南京航空航天大学 | A kind of eddy flow centrifugal combustion experimental rig |
| CN109724107A (en) * | 2018-12-29 | 2019-05-07 | 哈尔滨工业大学 | A kind of method that high frequency pumping discharge side surface plasma inhibits combustion pressure pulsation |
| CN110907212A (en) * | 2019-12-09 | 2020-03-24 | 中国人民解放军国防科技大学 | Multifunctional test platform for researching interaction of sound waves and flames |
| CN111272947A (en) * | 2020-03-20 | 2020-06-12 | 蓝色火焰能源科技(镇江)有限公司 | Visual combustion test device with sound excitation system |
| CN113049263A (en) * | 2021-05-17 | 2021-06-29 | 南京航空航天大学 | Combustion oscillation tester with continuously variable amplitude and frequency |
| CN113237663A (en) * | 2021-04-15 | 2021-08-10 | 西安航天动力试验技术研究所 | Cold air insertion type rotational flow mixing device and method for high-temperature fuel gas |
| CN113267342A (en) * | 2021-03-12 | 2021-08-17 | 北京航空航天大学 | Embedded series-mounted test platform for gas turbine parts, components and systems |
| CN113932250A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Combustion chamber capable of suppressing oscillatory combustion and control method thereof |
| CN114046874A (en) * | 2022-01-11 | 2022-02-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Test device for measuring supersonic jet near-field noise |
| CN114280219A (en) * | 2021-12-29 | 2022-04-05 | 中国人民解放军战略支援部队航天工程大学 | Multifunctional mixing combustion experimental device |
| CN114458479A (en) * | 2022-02-08 | 2022-05-10 | 北京航空航天大学 | Pulsating gas generating device and unstable combustion experimental equipment |
| CN115143488A (en) * | 2022-07-01 | 2022-10-04 | 中国人民解放军国防科技大学 | Air heater combustion instability control method and system |
| CN115792083A (en) * | 2022-11-05 | 2023-03-14 | 哈尔滨工程大学 | Modular model combustion chamber test device |
| CN116539318A (en) * | 2023-03-20 | 2023-08-04 | 四川箐梅科技有限公司 | High-precision ramjet engine test model device and use method |
| CN116952555A (en) * | 2023-07-07 | 2023-10-27 | 西安交通大学 | Test device for gas turbine impeller component |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102121870A (en) * | 2010-12-17 | 2011-07-13 | 中国人民解放军国防科学技术大学 | Ultrasonic ground experimental wind tunnel used for knocking combustion research |
| CN102226533A (en) * | 2011-05-26 | 2011-10-26 | 中国人民解放军国防科学技术大学 | High-speed premixed flame furnace for supersonic burning research |
| CN105952552A (en) * | 2016-04-29 | 2016-09-21 | 北京航空航天大学 | Rectangular transparent combustion chamber for optical diagnosis of small rocket engine |
| CN207019906U (en) * | 2017-08-04 | 2018-02-16 | 浙江大学 | A kind of device for measuring turbulent burner thermoacoustic transitive relation |
| CN208333872U (en) * | 2018-06-07 | 2019-01-04 | 湖南云顶智能科技有限公司 | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research |
-
2018
- 2018-06-07 CN CN201810582732.4A patent/CN108414231A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102121870A (en) * | 2010-12-17 | 2011-07-13 | 中国人民解放军国防科学技术大学 | Ultrasonic ground experimental wind tunnel used for knocking combustion research |
| CN102226533A (en) * | 2011-05-26 | 2011-10-26 | 中国人民解放军国防科学技术大学 | High-speed premixed flame furnace for supersonic burning research |
| CN105952552A (en) * | 2016-04-29 | 2016-09-21 | 北京航空航天大学 | Rectangular transparent combustion chamber for optical diagnosis of small rocket engine |
| CN207019906U (en) * | 2017-08-04 | 2018-02-16 | 浙江大学 | A kind of device for measuring turbulent burner thermoacoustic transitive relation |
| CN208333872U (en) * | 2018-06-07 | 2019-01-04 | 湖南云顶智能科技有限公司 | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109612739A (en) * | 2018-11-15 | 2019-04-12 | 南京航空航天大学 | A kind of eddy flow centrifugal combustion experimental rig |
| CN109724107A (en) * | 2018-12-29 | 2019-05-07 | 哈尔滨工业大学 | A kind of method that high frequency pumping discharge side surface plasma inhibits combustion pressure pulsation |
| CN110907212A (en) * | 2019-12-09 | 2020-03-24 | 中国人民解放军国防科技大学 | Multifunctional test platform for researching interaction of sound waves and flames |
| CN110907212B (en) * | 2019-12-09 | 2021-04-16 | 中国人民解放军国防科技大学 | Multifunctional test platform for researching interaction of sound waves and flames |
| CN111272947A (en) * | 2020-03-20 | 2020-06-12 | 蓝色火焰能源科技(镇江)有限公司 | Visual combustion test device with sound excitation system |
| CN113932250A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Combustion chamber capable of suppressing oscillatory combustion and control method thereof |
| CN113267342B (en) * | 2021-03-12 | 2022-03-04 | 北京航空航天大学 | Embedded series-mounted test platform for gas turbine parts, components and systems |
| CN113267342A (en) * | 2021-03-12 | 2021-08-17 | 北京航空航天大学 | Embedded series-mounted test platform for gas turbine parts, components and systems |
| CN113237663A (en) * | 2021-04-15 | 2021-08-10 | 西安航天动力试验技术研究所 | Cold air insertion type rotational flow mixing device and method for high-temperature fuel gas |
| CN113237663B (en) * | 2021-04-15 | 2023-07-04 | 西安航天动力试验技术研究所 | Cold air plug-in type rotational flow blending device and method for high-temperature fuel gas |
| CN113049263A (en) * | 2021-05-17 | 2021-06-29 | 南京航空航天大学 | Combustion oscillation tester with continuously variable amplitude and frequency |
| CN114280219A (en) * | 2021-12-29 | 2022-04-05 | 中国人民解放军战略支援部队航天工程大学 | Multifunctional mixing combustion experimental device |
| CN114046874B (en) * | 2022-01-11 | 2022-03-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Test device for measuring supersonic jet near-field noise |
| CN114046874A (en) * | 2022-01-11 | 2022-02-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Test device for measuring supersonic jet near-field noise |
| CN114458479A (en) * | 2022-02-08 | 2022-05-10 | 北京航空航天大学 | Pulsating gas generating device and unstable combustion experimental equipment |
| CN115143488A (en) * | 2022-07-01 | 2022-10-04 | 中国人民解放军国防科技大学 | Air heater combustion instability control method and system |
| CN115143488B (en) * | 2022-07-01 | 2024-06-21 | 中国人民解放军国防科技大学 | Unstable combustion control method and system for air heater |
| CN115792083A (en) * | 2022-11-05 | 2023-03-14 | 哈尔滨工程大学 | Modular model combustion chamber test device |
| CN116539318A (en) * | 2023-03-20 | 2023-08-04 | 四川箐梅科技有限公司 | High-precision ramjet engine test model device and use method |
| CN116539318B (en) * | 2023-03-20 | 2024-06-07 | 四川箐梅科技有限公司 | High-precision ramjet engine test model device and use method |
| CN116952555A (en) * | 2023-07-07 | 2023-10-27 | 西安交通大学 | Test device for gas turbine impeller component |
| CN116952555B (en) * | 2023-07-07 | 2024-05-17 | 西安交通大学 | Test device for gas turbine impeller component |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108414231A (en) | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research | |
| CN208333872U (en) | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research | |
| Johnson et al. | A comparison of the flowfields and emissions of high-swirl injectors and low-swirl injectors for lean premixed gas turbines | |
| Weigand et al. | Investigations of swirl flames in a gas turbine model combustor: I. Flow field, structures, temperature, and species distributions | |
| CN207019906U (en) | A kind of device for measuring turbulent burner thermoacoustic transitive relation | |
| CN103423769A (en) | Fuel nozzle cap | |
| Liu et al. | Study of combustion oscillation mechanism and flame image processing | |
| Liu et al. | Experimental investigation of spray and combustion performances of a fuel-staged low emission combustor: effects of main swirl angle | |
| CN206669733U (en) | A kind of wind fires super blender | |
| Gao et al. | Experimental investigation on the flame propagation pattern of a staged partially premixed annular combustor | |
| Zhao et al. | Experimental investigation on spark ignition of multi-swirl spray flames under sub-atmospheric pressures and low temperatures | |
| Liu et al. | Experimental investigation of spray and combustion performances of a fuel-staged low emission combustor: Part I—Effects of main swirl angle | |
| Mongia et al. | Combustion research needs for helping development of next-generation advanced combustors | |
| CN106568100A (en) | Large-gradient following wake jet flame burner | |
| Qianpeng et al. | Lean blowout characteristics of spray flame in a multi-swirl staged combustor under different fuel decreasing rates | |
| CN111829787B (en) | Visual combustion experiment platform capable of realizing multiple mixing | |
| Liu et al. | Experimental investigation of spray and combustion performances of a fuel-staged low emission combustor: Part II—Effects of venturi angle | |
| Barnes et al. | Effects of unmixedness in piloted-lean premixed gas-turbine combustors | |
| Lee et al. | An experimental investigation of the effects of turbulence generators attached to an axial swirler nozzle on mixing and combustion | |
| Wang et al. | Effects of axial velocity of main stage on the performances of a centrally staged LPP combustor | |
| CN110296435A (en) | A kind of multi-functional adjustable combustion with reduced pollutants visualization device | |
| Andrews et al. | Liquid fuelled low NOx radial swirlers with central pilot combustion | |
| Yang et al. | Investigation of the effect of pilot burner on lean blow out performance of a staged injector | |
| CN201242162Y (en) | Premixing type double-segment fire energy-saving combustion machine spray head | |
| Yan et al. | Investigations of combustion performance in LPP combustor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |