CN207019906U - A kind of device for measuring turbulent burner thermoacoustic transitive relation - Google Patents
A kind of device for measuring turbulent burner thermoacoustic transitive relation Download PDFInfo
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- CN207019906U CN207019906U CN201720969130.5U CN201720969130U CN207019906U CN 207019906 U CN207019906 U CN 207019906U CN 201720969130 U CN201720969130 U CN 201720969130U CN 207019906 U CN207019906 U CN 207019906U
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- transitive relation
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 32
- 230000005284 excitation Effects 0.000 claims abstract description 14
- 238000005259 measurement Methods 0.000 claims abstract description 14
- 239000000523 sample Substances 0.000 claims abstract description 8
- 239000000446 fuel Substances 0.000 claims abstract description 6
- 238000007789 sealing Methods 0.000 claims description 26
- 239000000203 mixture Substances 0.000 claims description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 4
- 239000010453 quartz Substances 0.000 claims description 3
- 238000009826 distribution Methods 0.000 claims description 2
- 239000011148 porous material Substances 0.000 claims description 2
- 241000256844 Apis mellifera Species 0.000 claims 1
- 230000001133 acceleration Effects 0.000 claims 1
- 239000007789 gas Substances 0.000 abstract description 39
- 230000008878 coupling Effects 0.000 abstract description 4
- 238000010168 coupling process Methods 0.000 abstract description 4
- 238000005859 coupling reaction Methods 0.000 abstract description 4
- 239000002737 fuel gas Substances 0.000 abstract description 3
- 238000002347 injection Methods 0.000 abstract description 3
- 239000007924 injection Substances 0.000 abstract description 3
- 230000036632 reaction speed Effects 0.000 abstract 1
- 230000001413 cellular effect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000008246 gaseous mixture Substances 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000005622 photoelectricity Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
Landscapes
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
The utility model discloses a kind of device for measuring turbulent burner thermoacoustic transitive relation, including the major part such as gas distributing chamber, combustion chamber, turbulent burner, sonic vibrator, hot line wind speed probe, photomultiplier and high speed camera.During work, air and fuel enter gas distributing chamber via premix barrel, by the acoustic excitation of bottom sonic vibrator, pass sequentially through honeycomb fairing and shrink nozzle, finally enter turbulent burner nozzle, produce swirl injection；The ignited pin spark ignitor of fuel gas sprayed into by nozzle forms swirl flame；Sonic vibrator excitation makes it have certain velocity fluctuation, its frequency and amplitude can be adjusted, and be measured by hot line wind speed probe into the air-flow of swirl nozzle；The flame forms and rate of heat release of swirl flame are by high speed camera and photomultiplier measurement.The utility model device can effectively measure influence of the acoustic excitation to flame forms and exothermic heat of reaction speed, so as to study the thermoacoustic transitive relation of turbulent burner thermoacoustic coupling.
Description
Technical field
The invention belongs to aero-engine and ground gas turbine technical field, more particularly, to one kind research burning
The instable new measurement of thermoacoustic, particularly a kind of device for measuring turbulent burner thermoacoustic transitive relation.
Background technology
Thermoacoustic unstability is needed for aero-engine and ground gas turbine field low-nitrogen oxide discharging combustion technology
The major issue to be solved, thermoacoustic is unstable be in combustion process heat release pulsation and the pressure fluctuation of combustion chamber occur exciting and
A kind of flame instability phenomenon formed.Thermoacoustic is unstable will to cause gas turbine operating point off-design value, so as to go out current situation
Portion is flame-out, increases pollutant discharge amount etc..Equipment long-term work under thermoacoustic instability condition, fatigue damage will be produced, from
And shorten the life-span of combustion chamber.The deterministic dependence between thermoacoustic coupling how is obtained, is so as to effectively improve combustion stability
One of subject matter solved required for gas turbine design.Its difficult point is swirl flame rate of heat release under the influence of acquisition sound wave
Changing rule, obtain flame, sound wave and the interactional pervasive receptance function of turbulent flow.
Early stage research thermoacoustic unstability phenomenon mainly be model that Rijke thermoacoustics pipe simplifies.Can by that will premix
In the pipe that combustion gas body closes under being filled with out, inside plus a resistance wire or loop coil are carried out as thermal source to flammable premixed gas body
Igniting, thermal acoustic oscillation phenomenon is observed by the position of moving heat source.Rijke thermoacoustics pipe can only qualitatively illustrate thermal acoustic oscillation phenomenon
The origin cause of formation, it is impossible to in engine commonly use turbulent burner carry out quantitative measurment research.
The domestic research to combustion instability, more using Dynamic Pressure Measurement System, to stable burning and unstable combustion
The pressure fluctuation of burning is measured, by the contrast of different duty parameters and boundary condition, to Flow In Model Combustor unstable combustion
Cover half state is analyzed.There is not yet comprehensive use the measurement means such as a variety of photoelectricity, image and acoustics to swirl flow combustion under acoustically-driven
The flame response of device measures.
The content of the invention
Based on the vacancy to swirl flame thermoacoustic unstability research device, it is an object of the invention to provide one kind to measure
Acoustic excitation is special using the burner structure of the swirl nozzle of tangential admission to the device of swirl flame morphology influence, the device
Sign, at the same can be to flammable premixed gas body application acoustic excitation, device of the invention has the following advantage of (but not limited to)：
- acoustic excitation of different frequency and amplitude can be applied to flammable premixed gas body；
- to flammable premixed gas body measured speed flutter component and pressure fluctuation component；
- influence of the sound field to flame forms can be monitored in real time；
- influence of the sound field to heat liberation rate, heat release rate can be measured in real time；
- it can determine that the relation of sound field, temperature field, pressure field and flame forms and heat liberation rate, heat release rate；
To achieve these goals, technical scheme is as follows：
A kind of device for measuring turbulent burner thermoacoustic transitive relation, mainly includes：Gas distributing chamber, combustion chamber, swirl flow combustion
Device, hot line wind speed probe, honeycomb cowling panel and sonic vibrator, gas distributing chamber by top flange dish, upper flange disk, shrink nozzle, in
Portion's ring flange and lower flange disk are fastenedly connected composition successively from top to bottom, and combustion chamber is located above top flange dish, by quartz
Cylindrical drum forms outer wall of combustion chamber, and outer wall of combustion chamber is tightly connected to form combustion chamber cavity, sound and vibration with top flange dish upper surface
Device is located at below lower flange disk and is connected with lower flange disk, air inlet is provided with lower flange disk side wall, in middle part method
The honeycomb cowling panel of three layers of different pore size is provided with blue disk, the spy of hot line wind speed is provided with above distribution indoor cellular cowling panel
Head, turbulent burner, air and fuel premixed gas is set to enter by air inlet in gas distributing chamber upwards in top flange dish
Motion, while uniform flowing gas is formed by honeycomb cowling panel by the acoustic excitation of bottom sonic vibrator, gas, by receiving
After contracting jet pipe accelerates, eddy flow is formed by turbulent burner, into combustion chamber cavity；Ignition electrode perforate from outer wall of combustion chamber is inserted
Enter, for eddy flow mixed gas of igniting.
In above-mentioned technical proposal, further, sealed between each ring flange of gas distributing chamber by sealing ring, on described top
Ring flange, shrink nozzle, central flange disk and lower flange disk upper surface on be provided with annular groove for assembling sealing ring,
The sealing of gas distributing chamber is realized by assembling the sealing ring of correspondingly-sized and carrying out bolt fastening in sequence.Sealing ring thickness is more than
The annular groove depth of ring flange correspondence position, in the combination of outer collar bolt and the fastening of inner ring bolt combination, sealing ring bears larger pressure
Power, be advantageous to sealing effectiveness.
Further, air inlet connects the air and fuel mixture of high pressure at work, and air inlet is along lower flange
Disk side wall circumference isoazimuth is distributed with 2~8.
Advantageously, outer wall of combustion chamber face is suprasil material so that obtains flame characteristic and burning by optical device
State is possibly realized.
Further, the sonic vibrator is connected with being provided with positioning hole on lower flange disk by positioning hole and bolt fastening
Connect, acoustic excitation can be applied to the premixed gas for entering gas distributing chamber.
Further, axial blind hole is provided with described turbulent burner as main burner passage, in axial blind hole end
Several tangent circle hole paths are provided with, tangent circle hole path connects gas distributing chamber with main burner passage.Described turbulent burner
Belong to a kind of tangential cellular type cyclone, its is most important to be characterized as with air inlet axially bored line and radially 60 ° of angles being present so that mixes
Gas tangentially enters in main burner passage.The number of tangent circle hole path is circumferentially distributed 6 along main burner passage.
Further, the honeycomb cowling panel using three apertures be respectively 1mm, 2mm, 3mm aluminium base cellular material from
Top to bottm lamination forms.Due to the presence of honeycomb fairing, the premixed gas that gas distributing chamber is entered from air inlet will be more neat
Equably flow straight up, reduce turbulent flow as far as possible.
Further, the shrink nozzle inwall design uses bicubic curve method, may be such that premixed gas is shrinking
Accelerate flowing in jet pipe, obtain preferable flow quality.
At work, air and fuel enter gas distributing chamber to the device via premix barrel from air inlet, by bottom sonic vibrator
Acoustic excitation, pass sequentially through honeycomb fairing and shrink nozzle, finally enter circumferential symmetrical turbulent burner, production
Raw swirl injection；Sonic vibrator makes the air-flow into swirl nozzle have certain velocity fluctuation；Mouth is tangentially revolved on turbulent burner
For inlet axis with radially angled, the air-flow for making to enter combustion chamber has certain circumferential speed component；Near ignition electrode
Lighted by the fuel gas that nozzle sprays into by spark plug effect and form swirl flame.Hot line wind speed probe can measure entrance velocity
Pulsation, apparatus of the present invention can effectively measure influence of the acoustic excitation to flame forms, so as to study the pass between thermoacoustic coupling
System.
Brief description of the drawings
Fig. 1 is the structure sectional view of the device of present invention measurement turbulent burner thermoacoustic transitive relation；
Fig. 2 is the front view, sectional view and swirl channel schematic diagram of turbulent burner of the present invention；
Fig. 3 is the axonometric drawing of top flange dish structure of the present invention；
Fig. 4 is the axonometric drawing of upper flange dish structure of the present invention；
Fig. 5 is the isometric cutaway view of shrink nozzle structure of the present invention；
Fig. 6 is the isometric cutaway view of central flange dish structure of the present invention；
Fig. 7 is the axonometric drawing of lower flange dish structure of the present invention；
In figure：1st, top flange dish, 2, upper flange disk, 3, shrink nozzle, 4, central flange disk, 5, lower flange disk,
6th, sonic vibrator, 7, outer wall of combustion chamber, 8, hot line wind speed probe, 9, honeycomb rectification version, 10, turbulent burner, 11, air inlet, 12,
Gas distributing chamber, 13, combustion chamber cavity, 14, turbulent burner air admission hole, 15, turbulent burner jet expansion, 16, turbulent burner
Threaded portion, 17, top flange dish screwed hole, 18, upper flange disc-annular shape groove, 19, shrink nozzle annular groove, 20, middle part
Ring flange annular groove, 21, lower flange disc-annular shape groove, 22, central flange disk groove, 23, photomultiplier, 24, high speed camera.
Embodiment
The invention will be further described with specific embodiment below in conjunction with the accompanying drawings.As shown in figs. 1-7, a kind of measurement rotation
Flowing the device of burner thermoacoustic transitive relation mainly includes gas distributing chamber 12 (by top flange dish 1, upper flange disk 2, shrink nozzle
3rd, central flange disk 4, lower flange disk 5 from top to bottom successively be tightly connected form), turbulent burner 10, outer wall of combustion chamber 7,
Sonic vibrator 6.
As shown in figure 1, top flange dish 1, upper flange disk 2, shrink nozzle 3, central flange disk 4 and lower flange disk 5
The gaseous mixture of the agent structure of composition gas distributing chamber 12, air and fuel gas is entered by the circumferentially distributed mixed gas of isoazimuth
Mouth is that air inlet 11 enters in gas distributing chamber 12, can be along week to be threadedly coupled between air inlet 11 and the side wall of lower flange disk 5
To being provided with 4-8 air inlet.
As Figure 1 and Figure 4, outer wall of combustion chamber 7 is made up of the cylindrical drum of quartz material, the upper surface with top flange dish 1
Annular boss structure carries out maximal clearance and coordinated for the gap of millimeter magnitude, and ignition electrode institute's opened hole from outer wall of combustion chamber 7 is inserted
Enter, tiltedly spray eddy flow mixed gas of igniting during work, high-temperature gas forms spiralling liquid form in combustion chamber cavity 13.
As shown in Figure 1 and Figure 2, the air/gas premixed gas being well mixed in gas distributing chamber 12 is burnt by tangential swirl
Device air admission hole 14 (tangent circle hole path) enters main burner passage and forms eddy flow, and eddy flow is vertically penetrated from turbulent burner nozzle head
Enter in combustion chamber 13.Wherein tangential swirl nozzle air admission hole 14 is circumferentially symmetrical.
As shown in Figure 1, Figure 2 and Figure 3, the turbulent burner 10 carries out screw thread cooperation with top flange dish screwed hole 17.
As shown in Figure 1, Figure 2 and Figure 3, the threaded portion 16 of the turbulent burner and the length of top flange dish screwed hole 17
Unanimously, therefore turbulent burner jet expansion 15 is kept in the same plane with the top surface of top flange dish 1 after completing to assemble.
As shown in Fig. 1, Fig. 3, Fig. 4, upper flange disk 2 is provided with the annular groove 18 for assembling sealing ring, passes through assembling pair
Answer the sealing ring of size and carry out dormant bolt fastening with top flange dish 1, and sealing ring thickness is corresponding more than upper flange disk
Annular groove 18 groove depth, when bolt combination fastens, sealing ring bears larger pressure.
As shown in Figure 1, Figure 4, Figure 5, shrink nozzle 3 is provided with the annular groove 19 for assembling sealing ring, corresponding by assembling
The sealing ring of size simultaneously carries out bolt fastening with upper flange disk 2, and sealing ring thickness is more than annular groove corresponding to shrink nozzle 3
19 groove depth, when bolt combination fastens, sealing ring bears larger pressure, and the inwall of shrink nozzle uses bicubic Curve Design.
As shown in Fig. 1, Fig. 5, Fig. 6, central flange disk 4 is provided with the annular groove 20 for assembling sealing ring, passes through assembling pair
Answer the sealing ring of size and carry out bolt fastening with shrink nozzle 3, and sealing ring thickness is more than corresponding to corresponding central flange disk 4
The groove depth of annular groove 20, when bolt combination fastens, sealing ring bears larger pressure.
As shown in Figure 1, Figure 6, Figure 7, lower flange disk 5 is provided with the annular groove 21 for assembling sealing ring, passes through assembling pair
Answer the sealing ring of size and carry out bolt fastening with central flange disk 4, and sealing ring thickness is more than the corresponding correspondence of lower flange disk 5
Annular groove 21 groove depth, when bolt combination fastens, sealing ring bears larger pressure.
As shown in Figure 1, Figure 6, Figure 7, be provided with groove 22 in central flange disk 4, honeycomb cowling panel 9 by with groove 22 and under
The upper surface of portion's ring flange 5, which is realized, to be coordinated.The thickness of the honeycomb cowling panel 9 and the thickness of groove 22 of central flange disk 4
It is consistent with internal diameter, interference fits can be achieved.
During work, air and fuel enter gas distributing chamber via premix barrel, by the acoustic excitation of bottom sonic vibrator, lead to successively
Honeycomb fairing and shrink nozzle are crossed, finally enters turbulent burner nozzle, produces swirl injection；Sprayed into by nozzle flammable
The ignited pin spark ignitor of gas forms swirl flame；Sonic vibrator excitation makes it have certain into the air-flow of swirl nozzle
Velocity fluctuation, its frequency and amplitude can be adjusted, and be measured by hot line wind speed probe；The flame forms of swirl flame and heat release
Speed is by high speed camera and photomultiplier measurement.Apparatus of the present invention can effectively measure acoustic excitation to flame forms and reaction
The influence of rate of heat release, so as to study the thermoacoustic transitive relation of turbulent burner thermoacoustic coupling.
Claims (9)
- A kind of 1. device for measuring turbulent burner thermoacoustic transitive relation, it is characterised in that：The device mainly includes：Gas distributing chamber (12), combustion chamber (13), turbulent burner (10), hot line wind speed probe (8), honeycomb cowling panel (9) and sonic vibrator (6), distribution Room (12) is by top flange dish (1), upper flange disk (2), shrink nozzle (3), central flange disk (4) and lower flange disk (5) It is fastenedly connected composition successively from top to bottom, combustion chamber (13) are located above top flange dish, combustion chamber is formed by quartz cylinder cylinder Outer wall (7), sonic vibrator (6) are located at below lower flange disk and are connected with lower flange disk, opened in lower flange disk (5) side wall There is air inlet (11), the honeycomb cowling panel (9) of three layers of different pore size, the honeybee in gas distributing chamber are provided with central flange disk (4) Hot line wind speed probe (8) is provided with above nest cowling panel, turbulent burner (10) is set in top flange dish (1), air and Fuel premixed gas is entered in gas distributing chamber (12) by air inlet (11) to move upwards, while by the sound of bottom sonic vibrator (6) Excitation is learned, gas forms uniform flowing gas by honeycomb cowling panel (9), passes through eddy flow after shrink nozzle (3) acceleration Burner (10) forms eddy flow, into combustion chamber (13) cavity；Ignition electrode inserts from perforate on outer wall of combustion chamber (7), for drawing Fire eddy flow mixed gas.
- 2. the device of measurement turbulent burner thermoacoustic transitive relation according to claim 1, it is characterised in that：Described rotation Axial blind hole is provided with as main burner passage on stream burner (10), and several tangential circular holes are provided with axial blind hole end and are led to Road, tangent circle hole path connect gas distributing chamber with main burner passage.
- 3. the device of measurement turbulent burner thermoacoustic transitive relation according to claim 1, it is characterised in that：Described rotation Isoazimuth is distributed with 6 to tangent circle hole path vertically on stream burner (10).
- 4. the device of measurement turbulent burner thermoacoustic transitive relation according to claim 1, it is characterised in that：Described three Layer honeycomb cowling panel (9) aperture is 1mm, 2mm, 3mm successively from top to bottom.
- 5. the device of measurement turbulent burner thermoacoustic transitive relation according to claim 1, it is characterised in that：Described rotation Stream burner (10) is used with top flange dish (1) and is threadedly coupled.
- 6. the device of measurement turbulent burner thermoacoustic transitive relation according to claim 1, it is characterised in that：Described receipts The inwall of contracting jet pipe (3) meets bicubic curve.
- 7. the device of measurement turbulent burner thermoacoustic transitive relation according to claim 1, it is characterised in that：Under described Positioning hole is provided with portion's ring flange (5) and sonic vibrator (6), by positioning hole between lower flange disk (5) and sonic vibrator (6) Bolt connection.
- 8. the device of measurement turbulent burner thermoacoustic transitive relation according to claim 1, it is characterised in that：Under described Circumferentially isoazimuth is distributed with 4~8 to portion's ring flange (5) side wall air inlet (11).
- 9. the device of measurement turbulent burner thermoacoustic transitive relation according to claim 1, it is characterised in that：Described is upper Portion's ring flange (2), shrink nozzle (3), central flange disk (4) and lower flange disk (5) upper surface on be provided with for assembling The annular groove (18) (19) (20) (21) of sealing ring, by assembling the sealing ring of correspondingly-sized and carrying out bolt fastening in sequence Realize the sealing of gas distributing chamber (12).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720969130.5U CN207019906U (en) | 2017-08-04 | 2017-08-04 | A kind of device for measuring turbulent burner thermoacoustic transitive relation |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201720969130.5U CN207019906U (en) | 2017-08-04 | 2017-08-04 | A kind of device for measuring turbulent burner thermoacoustic transitive relation |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108414231A (en) * | 2018-06-07 | 2018-08-17 | 湖南云顶智能科技有限公司 | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research |
| 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 |
| CN111751110A (en) * | 2020-07-04 | 2020-10-09 | 西北工业大学 | Carbon fiber heat release sound production device for oscillation combustion of solid propellant |
| CN112523896A (en) * | 2020-11-20 | 2021-03-19 | 西安航天动力研究所 | High-pressure gas flow rapid decompression rectifying device and method |
| CN113960242A (en) * | 2021-09-17 | 2022-01-21 | 江苏大学 | Staged combustor with two radial rotating inflow channels |
| CN114508769A (en) * | 2022-03-15 | 2022-05-17 | 浙江大学 | Ignition mechanism research device of inclined-jet non-premixed annular combustion chamber |
| 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 |
-
2017
- 2017-08-04 CN CN201720969130.5U patent/CN207019906U/en active Active
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108414231A (en) * | 2018-06-07 | 2018-08-17 | 湖南云顶智能科技有限公司 | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research |
| 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 |
| CN111751110A (en) * | 2020-07-04 | 2020-10-09 | 西北工业大学 | Carbon fiber heat release sound production device for oscillation combustion of solid propellant |
| CN111751110B (en) * | 2020-07-04 | 2021-05-14 | 西北工业大学 | Carbon fiber heat release sound production device for oscillation combustion of solid propellant |
| CN112523896A (en) * | 2020-11-20 | 2021-03-19 | 西安航天动力研究所 | High-pressure gas flow rapid decompression rectifying device and method |
| CN112523896B (en) * | 2020-11-20 | 2022-03-04 | 西安航天动力研究所 | High-pressure gas flow rapid decompression rectifying device and method |
| CN113960242A (en) * | 2021-09-17 | 2022-01-21 | 江苏大学 | Staged combustor with two radial rotating inflow channels |
| CN114508769A (en) * | 2022-03-15 | 2022-05-17 | 浙江大学 | Ignition mechanism research device of inclined-jet non-premixed annular combustion chamber |
| CN114508769B (en) * | 2022-03-15 | 2022-11-25 | 浙江大学 | Ignition mechanism research device of inclined-jet non-premixed annular combustion chamber |
| 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 |
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