CN108072053A - A kind of rotational flow atomization device - Google Patents
A kind of rotational flow atomization device Download PDFInfo
- Publication number
- CN108072053A CN108072053A CN201711218133.6A CN201711218133A CN108072053A CN 108072053 A CN108072053 A CN 108072053A CN 201711218133 A CN201711218133 A CN 201711218133A CN 108072053 A CN108072053 A CN 108072053A
- Authority
- CN
- China
- Prior art keywords
- swirler
- flow distribution
- nozzle
- distribution plate
- flow
- 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.)
- Granted
Links
- 238000000889 atomisation Methods 0.000 title claims abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 25
- 238000002156 mixing Methods 0.000 claims abstract description 16
- 239000007921 spray Substances 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 abstract description 45
- 238000002347 injection Methods 0.000 abstract 1
- 239000007924 injection Substances 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 15
- 239000000295 fuel oil Substances 0.000 description 10
- 239000000243 solution Substances 0.000 description 6
- 230000007704 transition Effects 0.000 description 4
- 238000009792 diffusion process Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 230000008520 organization Effects 0.000 description 3
- 230000002269 spontaneous effect Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000005496 tempering Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000013316 zoning Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
- F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention discloses a kind of rotational flow atomization devices.The rotational flow atomization device includes nozzle, inner swirler, outer swirler, flow distribution plate, support plate；Flow distribution plate, which includes housing, housing support plate, split channel, blending air admission hole, cooling air admission hole and the second cooling air admission hole, flow distribution plate, has inner surface and outer surface；Main injection jet and cap jet are provided on nozzle；Inner swirler is located on the outside of flow distribution plate；Outer swirler is located on the outside of inner swirler；Flow distribution plate is connected by support plate with nozzle；Split channel runs through housing in the thickness direction of housing；Outer surface of the air admission hole perpendicular to flow distribution plate is blended, and is evenly distributed；Cooling air admission hole is circumferentially distributed in the inner surface of flow distribution plate；Inner surface is conical surface with outer surface；Second cooling air admission hole is circumferentially distributed in flow distribution plate top.The rotational flow atomization device of the application simply realizes the indoor fractional combustion of aero-engine main burning, without complicated oil circuit cooling pipe is set, reduces structural complexity.
Description
Technical Field
The invention relates to the technical field of main combustion chambers of aircraft engines, in particular to a rotational flow atomization device and a main combustion chamber of an aircraft engine with the same.
Background
With the continuous development of the technology of the aero-engine, the design of the main combustion chamber gradually develops towards high temperature rise and low pollution, the traditional flame tube head swirl atomizing device can not meet the design requirements of the advanced main combustion chamber due to the problems of smoke generation, carbon deposition, low combustion efficiency, high exhaust pollution and the like, and the combustion organization mode of classification and zoning becomes a necessary trend. Through the careful design of the swirl atomizing device at the head of the flame tube, two combustion areas of a pre-combustion stage and a main combustion stage are formed in the flame tube, the pre-combustion stage is generally used for stabilizing flame in a diffusion combustion mode, and the main combustion stage is generally used for burning most of fuel in a diffusion combustion or premixed combustion mode, so that the performance requirements of an engine on a main combustion chamber in different states are met.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a cyclonic atomizing apparatus which overcomes or at least mitigates at least one of the above-mentioned disadvantages of the prior art.
In order to achieve the purpose, the invention provides a rotational flow atomization device which comprises a nozzle, an inner rotational flow device, an outer rotational flow device, a flow distribution plate and a support plate, wherein the inner rotational flow device is arranged in the nozzle; wherein,
the flow distribution plate comprises a shell, a shell support plate, a flow distribution channel, a mixing air inlet, a cooling air inlet and a second cooling air inlet, and the flow distribution plate is provided with an inner side surface and an outer side surface; the nozzle is provided with a main nozzle and an auxiliary nozzle; the inner swirler is positioned outside the splitter plate; the outer swirler is positioned outside the inner swirler; the flow distribution plate is connected with the nozzle through a support plate; the flow dividing channel penetrates through the shell in the thickness direction of the shell; the mixing air inlets are vertical to the outer side surface of the flow distribution plate and are uniformly distributed along the circumferential direction; the cooling air inlets are circumferentially and uniformly distributed on the inner side surface of the flow distribution plate; the inner side surface and the outer side surface are conical surfaces; and the second cooling air inlets are circumferentially and uniformly distributed at the top end of the flow distribution plate.
Preferably, the inner swirler is a radial swirler or an axial swirler, and the swirler vanes are in the form of straight vanes or curved vanes.
Preferably, the outer swirler is a radial swirler or an axial swirler, and the swirler vanes are in the form of straight vanes or curved vanes.
Preferably, the rotational directions of the air flows of the inner cyclone and the outer cyclone are the same direction or opposite directions.
Preferably, the number of the main nozzles may be 4 to 12.
Preferably, the secondary nozzle may be a direct spray nozzle or a centrifugal nozzle.
Preferably, the number of the blending air inlet holes can be 4 to 20.
Preferably, the surface taper angle of the diverter plate may be between 30 ° and 120 °.
The swirl atomization device simply realizes staged combustion in a main combustion chamber of the aero-engine, does not need to be provided with a complex oil way cooling pipeline, and reduces the structural complexity, thereby reducing the processing difficulty and the cost. Through careful pneumatic organization design, the problems of low combustion efficiency and increased CO and UHC emission under the transition working condition can be solved, and the problems of spontaneous combustion, tempering, unstable combustion and the like can be avoided.
Drawings
Fig. 1 is a schematic structural view of a swirling atomization device according to a first embodiment of the present application.
Fig. 2 is another schematic view of the cyclonic atomizing apparatus shown in fig. 1.
Reference numerals:
| 1 | inner swirler | 9 | Flow dividing channel |
| 2 | Outer swirler | 10 | Mixing air inlet |
| 3 | Flow distribution plate | 11 | Cooling air inlet |
| 4 | Supporting plate | 12 | Second cooling air inlet |
| 7 | Shell body | ||
| 8 | Casing support plate |
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
Fig. 1 is a schematic structural view of a swirling atomization device according to a first embodiment of the present application.
Fig. 2 is another schematic view of the cyclonic atomizing apparatus shown in fig. 1.
The swirl atomizing device shown in fig. 1 and 2 includes a nozzle a, an inner swirler 1, an outer swirler 2, a splitter plate 3, and a support plate 4; the flow distribution plate 3 comprises a shell 7, a shell support plate 8, a flow distribution channel 9, a mixing air inlet hole 10, a cooling air inlet hole 11 and a second cooling air inlet hole 12, and the flow distribution plate 3 is provided with an inner side surface C and an outer side surface B; the nozzle is provided with a main nozzle and an auxiliary nozzle; the inner swirler 1 is positioned outside the splitter plate 3; the outer swirler 2 is positioned outside the inner swirler 1; the flow distribution plate 3 is connected with the nozzle through a support plate 4; the flow dividing passage 9 penetrates the housing 7 in the thickness direction of the housing 7; the mixing air inlets 10 are vertical to the outer side surface of the splitter plate 3 and are uniformly distributed along the circumferential direction; the cooling air inlets 11 are circumferentially and uniformly distributed on the inner side surface of the splitter plate 3; the inner side surface and the outer side surface are conical surfaces; the second cooling air inlet holes 12 are circumferentially and uniformly distributed at the top end of the splitter plate 3.
The swirl atomization device simply realizes staged combustion in a main combustion chamber of the aero-engine, does not need to be provided with a complex oil way cooling pipeline, and reduces the structural complexity, thereby reducing the processing difficulty and the cost. Through careful pneumatic organization design, the problems of low combustion efficiency and increased CO and UHC emission under the transition working condition can be solved, and the problems of spontaneous combustion, tempering, unstable combustion and the like can be avoided.
It will be appreciated that the inner swirler 1 may be a radial swirler or an axial swirler, and that the swirler vanes may be in the form of straight vanes or curved vanes.
It will be appreciated that the outer swirler 2 may be a radial swirler or an axial swirler, and that the swirler vanes may be in the form of straight vanes or curved vanes.
It will be appreciated that the direction of rotation of the air streams of the inner and outer cyclones 1, 2 is co-current or counter-current.
It is understood that the number of the main nozzles 5 may be 4 to 12.
It will be appreciated that the secondary jets 6 may be direct atomising nozzles or centrifugal nozzles.
It will be appreciated that the number of dilution air inlets 10 may be from 4 to 20.
It will be appreciated that the surface taper angle of the diverter plate 3 may be from 30 to 120.
The swirl atomizing device divides a combustion area in a flame tube D into a pre-combustion stage and a main combustion stage. The pre-combustion stage backflow area is formed by a sudden expansion area formed by the inner side surface C of the flow distribution plate 3, and the main combustion stage backflow area is mainly formed by the rotational flow generated by the outer swirler 2.
Air entering the head of the flame tube enters the flame tube D from gaps among the inner cyclone 1, the outer cyclone 2, the splitter plate 3 and the support plate 4. A part of air entering from the gap between the support plates 4 enters the pre-combustion stage, and a part of air enters the air outlet flow passage of the inner swirler 1 through the flow dividing passage 9. A part of air entering the splitter plate 3 enters the inner part of the flame tube D through the cooling air inlet hole 11, cools the inner side surface C and then enters the pre-burning stage; one part of the gas enters the inner part of the flame tube D through the second cooling gas inlet hole 12, and enters the pre-burning stage after cooling the top end of the splitter plate 3; and a part of air enters an air flow channel at the outlet of the inner swirler 1 through a mixing air inlet hole 10, is mixed with air entering from the inner swirler 1 and the diversion channel 9 and then enters a main combustion stage, and the part of air in the main combustion stage is further mixed with air entering from the outer swirler 2.
In a small working condition, only the auxiliary nozzle 6 supplies oil, and the fuel oil sprayed by the auxiliary nozzle 6 directly enters the pre-burning stage; under a large working condition, the main nozzle 5 and the auxiliary nozzle 6 supply oil simultaneously, fuel oil sprayed by the main nozzle 5 enters an air flow channel at the outlet of the inner swirler 1 through the flow dividing channel 9, is rapidly mixed with air entering the mixing air inlet 10 and then enters the main combustion stage.
The swirl atomizing device only supplies oil to the auxiliary nozzle 6 under a small working condition, the pre-combustion stage works, the pre-combustion stage adopts a diffusion combustion mode, and the local oil-gas ratio is higher, so that a local oil-rich combustion area is formed, and the swirl atomizing device is favorable for starting and flame stabilization. When the large-working-condition working condition is met, the main nozzle 5 and the auxiliary nozzle 6 can spray oil at the same time, the pre-burning stage and the main burning stage can work at the same time, most of fuel oil can burn through the main burning stage, the fuel oil and the air in the air flow channel at the outlet of the inner swirler 1 are mixed to a certain extent, the atomization quality and the oil-air mixing uniformity of the fuel oil are improved, the fuel oil-air ratio in the channel is higher, the problems of spontaneous combustion, backfire, unstable combustion and the like are solved, after the air enters the mixing air inlet hole 10, the mixing effect of the fuel oil and the air is further enhanced, the oil-air ratio is rapidly reduced after the mixing air enters, the fuel oil is changed from rich oil to lean oil, the main burning stage is.
During the transition period from a small working condition to a large working condition, the rotational flow atomization device has the advantages that the main nozzle 5 just starts to supply oil, the nozzle pressure drop is small, the initial fuel oil kinetic energy is low, the fuel oil cannot pass through the flow dividing channel 9 to enter the main combustion stage, at the moment, most of the fuel oil enters the pre-combustion stage along with the air entering from the gap between the support plates 4, and therefore the problems that the combustion efficiency is low and the emission of CO and UHC is increased due to the fact that the oil-gas ratio of the main combustion stage is too low during the transition period between the large working condition.
The swirl atomizing device has the advantages that the main oil path and the auxiliary oil path are of concentric structures, the pre-burning stage always works under different working conditions, the auxiliary oil path can be used for cooling the main oil path, and a complex oil path cooling structure is not required to be additionally arranged.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (8)
1. A rotational flow atomization device is characterized by comprising a nozzle, an inner rotational flow device (1), an outer rotational flow device (2), a flow distribution plate (3) and a support plate (4); wherein,
the flow distribution plate (3) comprises a shell (7), a shell support plate (8), a flow distribution channel (9), a mixing air inlet hole (10), a cooling air inlet hole (11) and a second cooling air inlet hole (12), and the flow distribution plate (3) is provided with an inner side surface and an outer side surface;
the nozzle is provided with a main nozzle and an auxiliary nozzle;
the inner swirler (1) is positioned on the outer side of the splitter plate (3);
the outer swirler (2) is positioned at the outer side of the inner swirler (1);
the flow distribution plate (3) is connected with the nozzle through a support plate (4);
the flow dividing channel (9) penetrates through the shell (7) in the thickness direction of the shell (7);
the mixing air inlets (10) are vertical to the outer side surface of the flow distribution plate (3) and are uniformly distributed along the circumferential direction;
the cooling air inlets (11) are circumferentially and uniformly distributed on the inner side surface of the flow distribution plate (3);
the inner side surface and the outer side surface are conical surfaces;
the second cooling air inlets (12) are circumferentially and uniformly distributed at the top end of the splitter plate (3).
2. Swirl atomizing apparatus according to claim 1, characterized in that the inner swirler 1 is a radial swirler or an axial swirler, and the swirler vanes are in the form of straight vanes or curved vanes.
3. Swirl atomizing apparatus according to claim 2,
the outer swirler 2 is a radial swirler or an axial swirler, and the swirler vanes are in the form of straight vanes or curved vanes.
4. Swirl atomizing apparatus according to claim 1, characterized in that the direction of rotation of the gas flow of the inner swirler (1) and the outer swirler (2) is co-directional or counter-directional.
5. The swirl atomizing apparatus according to claim 1, characterized in that the number of the main nozzles 5 may be 4 to 12.
6. The cyclonic atomizing apparatus of claim 1, wherein the secondary nozzle 6 is a direct spray nozzle or a centrifugal nozzle.
7. The cyclone atomizing device according to claim 1, wherein the number of the mixing air inlet holes 10 is 4 to 20.
8. A cyclonic atomizing apparatus as claimed in claim 1, wherein the surface taper angle of the splitter plate 3 is in the range of 30 ° to 120 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711218133.6A CN108072053B (en) | 2017-11-28 | 2017-11-28 | Rotational flow atomization device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711218133.6A CN108072053B (en) | 2017-11-28 | 2017-11-28 | Rotational flow atomization device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108072053A true CN108072053A (en) | 2018-05-25 |
| CN108072053B CN108072053B (en) | 2020-12-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711218133.6A Active CN108072053B (en) | 2017-11-28 | 2017-11-28 | Rotational flow atomization device |
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| CN (1) | CN108072053B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110345513A (en) * | 2019-07-12 | 2019-10-18 | 中国航发沈阳发动机研究所 | A kind of rotational flow atomization device of fractional combustion |
| CN111520715A (en) * | 2020-04-03 | 2020-08-11 | 岳阳远东节能设备有限公司 | Biomass gas burning and online ash and coke cleaning low-nitrogen combustor |
| CN111520757A (en) * | 2020-03-31 | 2020-08-11 | 西北工业大学 | Direct injection type concave cavity swirl nozzle |
| CN111649353A (en) * | 2020-06-15 | 2020-09-11 | 江苏科技大学 | Pre-combustion-stage direct injection main combustion-stage pre-mixing and pre-evaporating three-cyclone combustion chamber |
| CN111911960A (en) * | 2020-08-11 | 2020-11-10 | 新奥能源动力科技（上海）有限公司 | Low nitrogen oxide emission combustion chamber for gas turbine and gas turbine |
| CN111981512A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Fuel air atomization device |
| CN113104916A (en) * | 2021-03-23 | 2021-07-13 | 中国能源建设集团广东省电力设计研究院有限公司 | Evaporation treatment system for salt-containing sewage |
| CN113310071A (en) * | 2021-06-16 | 2021-08-27 | 哈尔滨工程大学 | Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine |
| CN114688526A (en) * | 2020-12-31 | 2022-07-01 | 大连理工大学 | Pre-film type gas-assisted atomizing nozzle with petal-shaped outlet |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1034259A (en) * | 1988-01-14 | 1989-07-26 | 通用电气公司 | The bimodal swirler injector that is used for gas-turbine combustion chamber |
| CN1836134A (en) * | 2004-03-03 | 2006-09-20 | 三菱重工业株式会社 | Combustor |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
| CN102506446A (en) * | 2011-10-13 | 2012-06-20 | 中国科学院工程热物理研究所 | Fuel and air mixing device for low-pollution burning chamber of gas turbine |
| JP6012407B2 (en) * | 2012-10-31 | 2016-10-25 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor and gas turbine |
-
2017
- 2017-11-28 CN CN201711218133.6A patent/CN108072053B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1034259A (en) * | 1988-01-14 | 1989-07-26 | 通用电气公司 | The bimodal swirler injector that is used for gas-turbine combustion chamber |
| CN1836134A (en) * | 2004-03-03 | 2006-09-20 | 三菱重工业株式会社 | Combustor |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
| CN102506446A (en) * | 2011-10-13 | 2012-06-20 | 中国科学院工程热物理研究所 | Fuel and air mixing device for low-pollution burning chamber of gas turbine |
| JP6012407B2 (en) * | 2012-10-31 | 2016-10-25 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor and gas turbine |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110345513A (en) * | 2019-07-12 | 2019-10-18 | 中国航发沈阳发动机研究所 | A kind of rotational flow atomization device of fractional combustion |
| CN111520757B (en) * | 2020-03-31 | 2022-06-10 | 西北工业大学 | Direct injection type concave cavity swirl nozzle |
| CN111520757A (en) * | 2020-03-31 | 2020-08-11 | 西北工业大学 | Direct injection type concave cavity swirl nozzle |
| CN111520715A (en) * | 2020-04-03 | 2020-08-11 | 岳阳远东节能设备有限公司 | Biomass gas burning and online ash and coke cleaning low-nitrogen combustor |
| CN111520715B (en) * | 2020-04-03 | 2022-10-25 | 岳阳远东节能设备有限公司 | Biomass gas burning and online ash and coke cleaning low-nitrogen combustor |
| CN111649353A (en) * | 2020-06-15 | 2020-09-11 | 江苏科技大学 | Pre-combustion-stage direct injection main combustion-stage pre-mixing and pre-evaporating three-cyclone combustion chamber |
| CN111649353B (en) * | 2020-06-15 | 2022-03-25 | 江苏科技大学 | Pre-combustion-stage direct injection main combustion-stage pre-mixing and pre-evaporating three-cyclone combustion chamber |
| CN111981512A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Fuel air atomization device |
| CN111981512B (en) * | 2020-07-31 | 2022-09-02 | 中国航发贵阳发动机设计研究所 | Fuel air atomization device |
| CN111911960A (en) * | 2020-08-11 | 2020-11-10 | 新奥能源动力科技（上海）有限公司 | Low nitrogen oxide emission combustion chamber for gas turbine and gas turbine |
| CN114688526A (en) * | 2020-12-31 | 2022-07-01 | 大连理工大学 | Pre-film type gas-assisted atomizing nozzle with petal-shaped outlet |
| CN113104916A (en) * | 2021-03-23 | 2021-07-13 | 中国能源建设集团广东省电力设计研究院有限公司 | Evaporation treatment system for salt-containing sewage |
| CN113104916B (en) * | 2021-03-23 | 2022-08-30 | 中国能源建设集团广东省电力设计研究院有限公司 | Evaporation treatment system for salt-containing sewage |
| CN113310071A (en) * | 2021-06-16 | 2021-08-27 | 哈尔滨工程大学 | Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108072053B (en) | 2020-12-01 |
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