CN108561898A - A kind of coaxial subregion high temperature rise combustor head - Google Patents
A kind of coaxial subregion high temperature rise combustor head Download PDFInfo
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- CN108561898A CN108561898A CN201711454987.4A CN201711454987A CN108561898A CN 108561898 A CN108561898 A CN 108561898A CN 201711454987 A CN201711454987 A CN 201711454987A CN 108561898 A CN108561898 A CN 108561898A
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- main fuel
- coaxial
- high temperature
- temperature rise
- axial swirler
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Classifications
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- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
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- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Abstract
The present invention relates to a kind of coaxial subregion high temperature rise combustor heads, including level-one axial swirler (31), Venturi tube (32), main fuel path (33), two level axial swirler (34), baffle means (35), three-level axial swirler (36) and splash pan (37).Cooling during rolling runner (41) is formed between Venturi tube (32) and main fuel path (33), Venturi tube (32) expansion segment is provided with the cooling aperture (42) of number row, the air part for flowing into cooling during rolling runner (41) is flowed out from Venturi tube (32) expansion segment cooling aperture (42), another part flows through main fuel path (33) end main injection jet (43) periphery, is flowed out from main fuel-oil atmozation channel (44).
Description
Technical field
Patent of the present invention belongs to aero-engine field, is related to a kind of coaxial subregion high temperature rise combustor head.
Background technology
Modern high performance fighter plane generally uses small Bypass Ratio Turbofan Engine, in order to realize high-speed maneuver, to starting
The requirement of machine thrust-weight ratio is higher and higher (increasing to 16~20 by 8~10), and therefore the loop parameter of engine is also continuously improved, total to increase
Pressure ratio has reached 40 or more, and combustion chamber out temperature is increased to 1000~2150K by 800~1650K.Currently, major aviation
Engine manufacturer is just in the research of the military high temperature rise combustor of Efforts To Develop.
The research and development of high temperature rise combustion technology just have begun in the mid 1970s, the research and development of RB-199 engines at
Work(represents 8 first class engine of thrust-weight ratio, has developed 10 first class engine of thrust-weight ratio the nineties, and what is researched and developed now is
The engine of the engine of 12 level-one of thrust-weight ratio, 15~20 level-one of thrust-weight ratio also incorporates in research and development plan, such as temperature
The combustion chamber of 1315K is risen, United States Air Force, which has developed, becomes the combustion chamber geometry (VG), and USN, which then still uses, determines geometry (FG)
The combustion chamber that temperature is upgraded to 1650K has also been inquired into combustion chamber scheme, the same time U.S..
High temperature rise combustor and high oil-gas ratio combustion chamber are same concepts, as High Performance Aeroengine thrust-weight ratio is wanted
The raising asked, combustion chamber gross gas-oil ratio just need to improve, and temperature rises horizontal also higher.Currently, high thrust-weight ratio aero-engine is high
The greatest problem that oil-gas ratio combustion chamber faces how is solved under igniting, low stable conditions and high operating mode efficiently without burning of smoldering
Between contradiction.The military combustion chamber of tradition can be solved since total oil-gas ratio is not high using conventional tissue combustion technology,
I.e. by the control of head air inflow between 10%~25%, even if in combustion chamber operational to big operating mode, the residual air system in primary zone
Number ensure that the efficient low burning of smoldering in primary zone still 1.0 or more.With the increase of combustion chamber gross gas-oil ratio, if pressed
It is designed according to the assignment of traffic scheme of original combustion chamber, that excess air coefficient that may result in primary zone is less than 1, will lead in this way
Cause primary zone smolders and serious carbon distribution, it is seen that and conventional combustion room technology can not ensure the efficient low burning of smoldering in primary zone,
At this moment the combustion method, air of combustion chamber and the assignment of traffic and structure type of fuel oil will change.
Invention content
Goal of the invention
There is provided a kind of can take into account that the igniting of enlarged head charge combustion room, low stable conditions and high operating mode are efficiently low to smolder
High temperature rise combustor head.
Technical solution
The coaxial subregion high temperature rise combustor CDHTRC of patent (Coaxial and Divisional High of the present invention
Temperature Rise Combustor) head is classified using fuel oil and the tissue combustion strategies of burning subregion, auxiliary oil circuit position
In head center, fuel oil is injected directly into primary zone central area by single oil circuit swirl atomizer, passes through level-one axial swirler
Atomizing air realizes that fuel oil well atomization and mixing, working connection are arranged in auxiliary oil circuit periphery, are particularly located at level-one axial swirler
Between two level axial swirler, fuel oil is injected directly into primary zone, working connection fuel oil master by the way that multiple simple nozzles are arranged
The shearing of firsts and seconds axial swirler air-flow is relied on to realize adequately atomization and mixing, in two level axial swirler and three
Grade axial swirler between baffle means are set, the air by three-level axial swirler be not be directly entered primary zone, but
By stepping into primary zone after the turning back of certain distance fuel-air mixture is formed by with firsts and seconds axial swirler
It is mixed.Specific works pattern is：In low operating mode, only pre-burning level work passes through auxiliary oil circuit swirl atomizer and primary axis
Local fuel-rich combustion is realized to cyclone, and for excess air coefficient between 0.3-0.7, combustion stability is preferable, igniting easy in starting up；
When slow train or the above operating mode of slow train, pre-combustion grade and main combustion stage work at the same time, and pre-combustion grade is formed centrally within stable steady burning things which may cause a fire disaster, main combustion
Grade forms rich oil and directly mixes burning, and combustion zone excess air coefficient controls between 0.6~1, to control the generation that head smolders.Using
Above-mentioned operating mode, it can be ensured that under all working conditions, the whole excess air coefficient of combustion zone control it is visible smolder it is remaining
On gas coefficient, while the stability of low operating mode reliable ignition and burning is taken into account.
Concrete structure is：A kind of coaxial subregion high temperature rise combustor head, including the combustion of level-one axial swirler (31), main
Oil circuit (33), two level axial swirler (34), baffle means (35), three-level axial swirler (36) and nozzle (14), nozzle
(14) it is located at head of combustion chamber (15) center, level-one axial swirler (31) is in nozzle (14) periphery, main fuel path (33)
And main injection jet (43) is located between level-one axial swirler (31) and two level axial swirler (34), baffle means (35) are located at two
Between grade axial swirler (34) and grade axial swirler (36)；Secondary grade fuel oil is by nozzle (14) from head of combustion chamber (15)
The heart is fed along X-axis, and main fuel oil is fed by main fuel path (33).
A kind of coaxial subregion high temperature rise combustor head, level-one axial swirler (31), two level axial swirler
(34) and three-level axial swirler (36) common center axis X axis.
A kind of coaxial subregion high temperature rise combustor head, main injection jet (43) are located at main fuel path (33) end
End, and main injection jet (43) end face is stretched into main fuel-oil atmozation channel (44).
A kind of coaxial subregion high temperature rise combustor head, main fuel-oil atmozation channel (44) type face are homalographic
Type, main fuel-oil atmozation channel (44) are equal from import to discharge area.
A kind of coaxial subregion high temperature rise combustor head, main fuel-oil atmozation channel (44) type face are convergence type,
Main fuel-oil atmozation channel (44) is gradually reduced from import to discharge area.
A kind of coaxial subregion high temperature rise combustor head, main fuel-oil atmozation channel (44) type face are to receive expansion type,
Main fuel-oil atmozation channel (44) first reduces from import to discharge area to increase afterwards.
A kind of coaxial subregion high temperature rise combustor head, baffle means (35) expansion angle (45) is at 40 °~70 °
Between, end height (46) is between 25mm~40mm.
A kind of coaxial subregion high temperature rise combustor head further includes Venturi tube (32), Venturi tube (32) and main
Cooling during rolling runner (41) is formed between fuel path (33), Venturi tube (32) expansion segment is provided with the cooling aperture (42) of number row, stream
The air part for entering cooling during rolling runner (41) is flowed out from Venturi tube (32) expansion segment cooling aperture (42), and another part flows through
Main injection jet (43) periphery of main fuel path (33) end, flows out from main fuel-oil atmozation channel (44).
Advantageous effect
Pre-combustion grade uses lean direct injection pattern, can guarantee combustion chamber reliable ignition and steady operation, expansion segment band
The design of cooling aperture can not only solve the problems, such as head carbon distribution and cooling, the step structure between firsts and seconds axial swirler
It also ensures and helps to the oblique recirculating zone of igniting and flame stabilization in pre-combustion grade downstream；Main combustion stage uses multi-point injection rich oil
Directly mixed combustion technology, can well adapt to the acute variation of ordnance engine main chamber operating mode so that combustion chamber has preferably
Response and followability, main fuel-oil atmozation channel is arranged in main injection jet periphery on the one hand can be to avoid main injection jet end area under low operating mode
On the other hand carbon improves fuel-oil atmozation；Baffle means between two level and three-level axial swirler roll over part fresh air
Primary zone is stepped into after turning, a stoichiometric ratio air-fuel mixture annulus is formd in the periphery of flame of centre (steady burning things which may cause a fire disaster),
So that external flame is wrapped in flame of centre in entire primary zone efficient burning, the efficiency of combustion on head is improved, combustion chamber
Outlet temperature field quality is also improved.
Description of the drawings
Fig. 1 is a kind of coaxial subregion high temperature rise combustor schematic diagram；
Fig. 2 is coaxial subregion high temperature rise combustor head detailed structure schematic diagram；
Fig. 3 is coaxial subregion high temperature rise combustor head downstream flame distribution schematic diagram；
Fig. 4 is main fuel-oil atmozation channel homalographic type structural schematic diagram；
Fig. 5 is main fuel-oil atmozation channel convergence type structural schematic diagram；
Fig. 6 is that expansion type structural schematic diagram is received in main fuel-oil atmozation channel；
A kind of coaxial subregion high temperature rise combustors of 10-, 11- diffusers, the outer casings of 12-, casing in 13-, 14- nozzles, 15-
Head, 16- burner inner liners, 17- sparking plugs, 18- primary holes, 19- blending holes, the combustion chambers 20- outer shroud, the combustion chambers 21- inner ring, 22- combustions
Burn room outlet, 31- level-one axial swirlers, 32- Venturi tubes, 33- main fuel paths, 34- two level axial swirlers, 35- foldings
Flow device, 36- three-level axial swirlers, 37- splash pans, 41- cooling during rolling runners, 42- cooling apertures, 43- main injection jets, 44-
Main fuel-oil atmozation channel；
Fig. 1 describes combustor diffuser, outer casing, interior casing, nozzle, head, burner inner liner, sparking plug, primary holes and mixes
The relative position in mixed hole；Fig. 2 describes coaxial subregion high temperature rise combustor head cyclone, Venturi tube, main fuel path, stream
Device, splash pan and their detailed structure；Fig. 3 describes coaxial subregion high temperature rise combustor head downstream flame and substantially divides
Cloth；Fig. 4 describes main fuel-oil atmozation channel homalographic type structure；Fig. 5 describes main fuel-oil atmozation channel convergence type structure；
Fig. 6 describes main fuel-oil atmozation channel and receives expansion type structure.
Specific implementation mode
Below in conjunction with the accompanying drawings and the present invention is discussed in detail in specific embodiment.
Refering to fig. 1, it is a kind of coaxial 10 structural schematic diagram of subregion high temperature rise combustor, including diffuser 11, outer casing 12,
Interior casing 13, nozzle 14, head 15, burner inner liner 16, sparking plug 17 have primary holes 18 and blending hole 19 on burner inner liner as needed,
Or primary holes 18 can be cancelled and retain blending hole 19.The working condition of combustion chamber is：Air enters combustion chamber from diffuser 11,
Air more than 40% enters burner inner liner 16 from head 15, and remaining air is entered by combustion chamber outer shroud 20 and combustion chamber inner ring 21
Burner inner liner 16, fuel oil enters burner inner liner 16 by nozzle 14, and in burner inner liner 16, after sparking plug 17 is lighted a fire, air is mixed with fuel oil
And burn, from 22 discharge high-temperature fuel gas of burner inner liner outlet.
Referring to Fig.2, being 15 CONSTRUCTED SPECIFICATION of coaxial subregion high temperature rise combustor head, including level-one axial swirler 31, text
Family name's pipe 32, main fuel path 33, two level axial swirler 34, baffle means 35, three-level axial swirler 36 and splash pan 37,
Cooling during rolling runner 41 is formed between Venturi tube 32 and main fuel path 33,32 expansion segment of Venturi tube is provided with the cooling aperture of number row
42, the air part for flowing into cooling during rolling runner 41 is flowed out from 32 expansion segment of Venturi tube cooling aperture 42, and another part flows through
33 end main injection jet of main fuel path, 43 periphery, flows out from main fuel-oil atmozation channel 44.Refering to Fig. 3, coaxial subregion high temperature
The flame structure that head of combustion chamber 15 is formed in downstream is risen to be made of flame of centre and external flame.
Further, 15 air inflow of coaxial subregion high temperature rise combustor head accounts about the 40%- of the total tolerance in combustion chamber
80%, the number of specific air inflow is related with the gross gas-oil ratio and cooling air volume of combustion chamber.31 air inlet of level-one axial swirler
Amount accounts about the 5%~15% of the total air inflow in combustion chamber, and specific air inflow is closely related with combustion chamber idling rating oil-gas ratio；Two
Grade 34 air inflow of axial swirler accounts about the 10%~25% of the total air inflow in combustion chamber, and 36 air inflow of three-level axial swirler is big
Account for about the 20%~35% of the total air inflow in combustion chamber, specific air inflow is closely related with Combustion chamber design dotted state oil-gas ratio.
Further, 33 end main injection jet of main fuel path, 43 quantity is between 4~8, spray angle 5 °~30 ° it
Between, 44 quantity of main fuel-oil atmozation channel is corresponded with main injection jet 43.Refering to Fig. 4, Fig. 5 and Fig. 6, main fuel-oil atmozation channel
44 inner mold faces, which are divided into homalographic, convergence and receive, expands three types.
Further, 35 expansion angle 45 of baffle means is between 40 °~70 °, end height 46 25mm~40mm it
Between.
Claims (8)
1. a kind of coaxial subregion high temperature rise combustor head, including level-one axial swirler (31), main fuel path (33), two
Grade axial swirler (34), baffle means (35), three-level axial swirler (36) and nozzle (14), it is characterised in that：Nozzle
(14) it is located at head of combustion chamber (15) center, level-one axial swirler (31) is in nozzle (14) periphery, main fuel path (33)
And main injection jet (43) is located between level-one axial swirler (31) and two level axial swirler (34), baffle means (35) are located at two
Between grade axial swirler (34) and grade axial swirler (36)；Secondary grade fuel oil is by nozzle (14) from head of combustion chamber (15)
The heart is fed along X-axis, and main fuel oil is fed by main fuel path (33).
2. a kind of coaxial subregion high temperature rise combustor head according to claim 1, which is characterized in that level-one axial rotational flow
Device (31), two level axial swirler (34) and three-level axial swirler (36) common center axis X axis.
3. a kind of coaxial subregion high temperature rise combustor head according to claim 1, which is characterized in that main injection jet (43) position
In main fuel path (33) end, and main injection jet (43) end face is stretched into main fuel-oil atmozation channel (44).
4. a kind of coaxial subregion high temperature rise combustor head according to claim 3, which is characterized in that main fuel-oil atmozation
Channel (44) type face is homalographic type, and main fuel-oil atmozation channel (44) is equal from import to discharge area.
5. a kind of coaxial subregion high temperature rise combustor head according to claim 3, which is characterized in that main fuel-oil atmozation
Channel (44) type face is convergence type, and main fuel-oil atmozation channel (44) is gradually reduced from import to discharge area.
6. a kind of coaxial subregion high temperature rise combustor head according to claim 3, which is characterized in that main fuel-oil atmozation
Channel (44) type face is to receive expansion type, and main fuel-oil atmozation channel (44) first reduces from import to discharge area to increase afterwards.
7. a kind of coaxial subregion high temperature rise combustor head according to claim 1, which is characterized in that baffle means (35)
Expansion angle (45) is between 40 °~70 °, and end height (46) is between 25mm~40mm.
8. a kind of coaxial subregion high temperature rise combustor head according to claim 1, which is characterized in that further include Venturi tube
(32), cooling during rolling runner (41) is formed between Venturi tube (32) and main fuel path (33), Venturi tube (32) expansion segment is opened
There are the cooling aperture (42) of number row, the air part for flowing into cooling during rolling runner (41) to cool down aperture from Venturi tube (32) expansion segment
(42) it flows out, another part flows through main injection jet (43) periphery of main fuel path (33) end, from main fuel-oil atmozation channel
(44) it flows out.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711454987.4A CN108561898B (en) | 2017-12-27 | 2017-12-27 | Coaxial partition high-temperature-rise combustion chamber head |
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| CN201711454987.4A CN108561898B (en) | 2017-12-27 | 2017-12-27 | Coaxial partition high-temperature-rise combustion chamber head |
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| CN108561898A true CN108561898A (en) | 2018-09-21 |
| CN108561898B CN108561898B (en) | 2020-09-22 |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109668171A (en) * | 2018-12-20 | 2019-04-23 | 中国航发四川燃气涡轮研究院 | A kind of radial grading subregion high temperature rise combustor head |
| CN109899831A (en) * | 2019-03-11 | 2019-06-18 | 中国航发湖南动力机械研究所 | Combustion chamber |
| CN110822482A (en) * | 2019-11-28 | 2020-02-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Medium-low calorific value gas and liquid dual-fuel nozzle and fuel switching method |
| CN111006243A (en) * | 2019-12-03 | 2020-04-14 | 哈尔滨工程大学 | Anti-backfire fuel flash evaporation and rotational flow integrated nozzle |
| CN111981511A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Fuel nozzle air heat insulation structure |
| CN112902225A (en) * | 2021-02-04 | 2021-06-04 | 厦门大学 | Multistage afterburning chamber with outer ring rotary detonation supercharged combustion chamber |
| CN113431706A (en) * | 2021-06-30 | 2021-09-24 | 湖北航天技术研究院总体设计所 | Venturi tube combination device and system for liquid engine and operation method of venturi tube combination device |
| CN114165811A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Jet sleeve with cooling structure |
| CN114526497A (en) * | 2022-01-07 | 2022-05-24 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
| WO2022193067A1 (en) * | 2021-03-15 | 2022-09-22 | 北京航空航天大学 | Combustion chamber for suppressing combustion oscillation, and combustor |
| CN115218219A (en) * | 2022-07-26 | 2022-10-21 | 中国航发沈阳发动机研究所 | Three-cyclone head structure of combustion chamber of aero-engine |
| CN115234942A (en) * | 2022-06-28 | 2022-10-25 | 北京航空航天大学 | Combustion chamber for injecting fuel by venturi |
| CN115264533A (en) * | 2022-07-24 | 2022-11-01 | 哈尔滨工程大学 | Natural gas coaxial staged combustion chamber adopting center ignition and combustion method |
| CN115254476A (en) * | 2022-09-27 | 2022-11-01 | 成都中科翼能科技有限公司 | Nozzle structure for gas turbine |
| CN115523509A (en) * | 2021-06-24 | 2022-12-27 | 通用电气公司 | Combustor for a gas turbine engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109668171A (en) * | 2018-12-20 | 2019-04-23 | 中国航发四川燃气涡轮研究院 | A kind of radial grading subregion high temperature rise combustor head |
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| CN110822482A (en) * | 2019-11-28 | 2020-02-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Medium-low calorific value gas and liquid dual-fuel nozzle and fuel switching method |
| CN111006243A (en) * | 2019-12-03 | 2020-04-14 | 哈尔滨工程大学 | Anti-backfire fuel flash evaporation and rotational flow integrated nozzle |
| CN111006243B (en) * | 2019-12-03 | 2021-03-30 | 哈尔滨工程大学 | Anti-backfire fuel flash evaporation and rotational flow integrated nozzle |
| CN111981511A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Fuel nozzle air heat insulation structure |
| CN112902225B (en) * | 2021-02-04 | 2022-03-15 | 厦门大学 | Multistage afterburning chamber with outer ring rotary detonation supercharged combustion chamber |
| CN112902225A (en) * | 2021-02-04 | 2021-06-04 | 厦门大学 | Multistage afterburning chamber with outer ring rotary detonation supercharged combustion chamber |
| WO2022193067A1 (en) * | 2021-03-15 | 2022-09-22 | 北京航空航天大学 | Combustion chamber for suppressing combustion oscillation, and combustor |
| CN115523509A (en) * | 2021-06-24 | 2022-12-27 | 通用电气公司 | Combustor for a gas turbine engine |
| CN115523509B (en) * | 2021-06-24 | 2024-05-28 | 通用电气公司 | Combustor for a gas turbine engine |
| CN113431706A (en) * | 2021-06-30 | 2021-09-24 | 湖北航天技术研究院总体设计所 | Venturi tube combination device and system for liquid engine and operation method of venturi tube combination device |
| CN114165811A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Jet sleeve with cooling structure |
| CN114165811B (en) * | 2021-10-20 | 2023-03-21 | 中国航发四川燃气涡轮研究院 | Jet sleeve with cooling structure |
| CN114526497A (en) * | 2022-01-07 | 2022-05-24 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
| CN114526497B (en) * | 2022-01-07 | 2023-02-07 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
| CN115234942A (en) * | 2022-06-28 | 2022-10-25 | 北京航空航天大学 | Combustion chamber for injecting fuel by venturi |
| CN115264533A (en) * | 2022-07-24 | 2022-11-01 | 哈尔滨工程大学 | Natural gas coaxial staged combustion chamber adopting center ignition and combustion method |
| CN115218219A (en) * | 2022-07-26 | 2022-10-21 | 中国航发沈阳发动机研究所 | Three-cyclone head structure of combustion chamber of aero-engine |
| CN115254476B (en) * | 2022-09-27 | 2022-12-13 | 成都中科翼能科技有限公司 | Nozzle structure for gas turbine |
| CN115254476A (en) * | 2022-09-27 | 2022-11-01 | 成都中科翼能科技有限公司 | Nozzle structure for gas turbine |
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| CN108561898B (en) | 2020-09-22 |
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