CN107143880A - A kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine - Google Patents
A kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine Download PDFInfo
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- CN107143880A CN107143880A CN201710343294.1A CN201710343294A CN107143880A CN 107143880 A CN107143880 A CN 107143880A CN 201710343294 A CN201710343294 A CN 201710343294A CN 107143880 A CN107143880 A CN 107143880A
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- Prior art keywords
- swirl
- swirl nozzle
- combustion
- nozzle mould
- mould
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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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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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
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine, constituted using multiple mutually isostructural swirl nozzle moulds, wherein, by the swirl nozzle mould positioned at center and according to Swirl nozzle mould, equidistantly circumferential three uniform swirl nozzle moulds are constituted pair combustion level, main combustion stage positioned at the swirl nozzle mould alternate with secondary three swirl nozzle moulds for firing level by constituting, main combustion stage and secondary combustion level can independent controls, it is ensured that combustion chamber can steady operation under wide working condition.Using oil-poor lean direct injection technology, jet expansion is concordant with rotational flow air outlet, and nozzle mould is worked in non-premixed combustion mode, can avoid spontaneous combustion and the generation of tempering phenomenon, and the risk that reduction hugging occurs；Nozzle die worker makees equivalent proportion between 0.6~0.8, it is ensured that combustion zone temperature is relatively low and flameholding, effectively the generation of reduction thermal NO.Pollutant emission is few, simple in construction, it is adaptable to low-pollution burning chamber of gas turbine.
Description
Technical field
The present invention relates to gas-turbine combustion chamber technical field, specifically, it is related to a kind of for gas turbine low stain
The direct injector head of oil-poor multiple spot of combustion chamber.
Background technology
The source of gas turbine pollutant emission comes from combustion chamber, therefore development combustion with reduced pollutants technology is reduction combustion gas wheel
The key of machine disposal of pollutants.The major pollutants of combustion chamber include nitrogen oxides, carbon monoxide and unburned hydrocarbon, wherein most important
Be reduce nitrogen oxides growing amount.In a combustion chamber, thermal NO formation mechanism plays leading role, therefore drop
Low combustion zone ignition temperature is to reduce one of effective means of formation of nitrogen oxides.Poor oil firing's technology can effectively reduce burning
Area's ignition temperature, so as to reduce the growing amount of nitrogen oxides.
For poor oil firing's technology, foreign study persons propose lean premixed preevaporated combustion technology, and it is carried out
Widely studied, the technology can effectively control primary zone ignition temperature, have very big potentiality in terms of nitrogen oxides is reduced.But
It is that the technology barriers such as spontaneous combustion, tempering and serious combustion instability are run into during the technical research, these problems are seriously made
The about practical application of the technology.The problem of being run into for premixed combustion, has also been proposed oil-poor lean direct injection technology, the skill
Art intermediate fuel oil is without premix but is directly injected in primary zone and quickly mixes and fully burn with air, equally can be effective
The growing amount of nitrogen oxides is reduced, and completely avoid the problem of spontaneous combustion and tempering, while reducing combustion instability
Degree.Therefore oil-poor lean direct injection technology is one of important directions of combustion with reduced pollutants technology development.
Also there are many patent applications on low pollution combustor the country in recent years.Patent 201510673156.0,
201510674145.4 disclose two kinds of low pollution combustors, and wherein pre-combustion grade is pre- using swirl stabilized diffusion combustion and eddy flow
The mixed mode being combined of burning, can reduce pollutant under small state while stable burning；Main combustion stage uses premix and pre-evaporation
Combustion system, homogenous combustion can be realized under big state to reduce NOxDischarge.Patent 201410643105.9 discloses one kind
The layered portion premix low pollution combustor of the poor premix of main combustion stage, level on duty uses diffusion combustion, and main combustion stage is using lean premixed
Burning, in big operating mode, level and main combustion stage on duty work simultaneously, and primary zone is in poor oil condition, can significantly reduce NOxRow
Put.But main combustion stage be possible to by the way of premix and pre-evaporation produce combustion instability phenomenon, adversely affecting its combustion performance, very
To causing structural destruction.Patent CN104791847A proposes " a kind of suitable for the low of low-pollution burning chamber of gas turbine
Eddy flow multiinjector chamber structure ", the burner is made up of six low swirl nozzles in outside and a low swirl nozzle in center, is adopted
With fuel gas and premixed combustion mode, pollutant emission can be effectively reduced.Fuel gas directly can be mixed quickly with air,
But liquid fuel has to pass through good atomization and could simultaneously and after air mixing form flammable mixed gas, therefore the burner is inapplicable
In liquid fuel, it is impossible to solve the problems, such as the combustion with reduced pollutants using liquid fuel gas turbine.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention proposes a kind of for the poor of low-pollution burning chamber of gas turbine
The oily direct injector head of multiple spot, the injector head can make combustion chamber can stability and high efficiency work, effectively suppression combustion within the scope of full working scope
Instable generation is burnt, while reducing pollutant emission.
The technical solution adopted for the present invention to solve the technical problems is:Including head of combustion chamber flange, secondary combustion level eddy flow
Nozzle mould, main combustion stage swirl nozzle mould, air intlet, swirl channel, annular rotational flow air straight channel, annular rotational flow air are received
Passage, rotational flow air outlet, fuel inlet, nozzle, jet expansion are held back, is constituted using multiple mutually isostructural swirl nozzle moulds,
And be fixed on head of combustion chamber flange, the secondary combustion level swirl nozzle mould is by the swirl nozzle Mo Heyi centers rotation positioned at center
Equidistantly circumferential three uniform swirl nozzle moulds are constituted flow nozzle mould, and the main combustion stage swirl nozzle mould positioned at pair by firing level
The alternate swirl nozzle mould composition of three swirl nozzle moulds, main combustion stage swirl nozzle mould and secondary combustion level swirl nozzle mould can be independent
Control；Wherein, air intlet, swirl channel, annular rotational flow air straight channel, annular rotational flow air convergent passage and eddy flow are empty
Gas exports in the air flow circuit to form swirl nozzle mould, the swirl channel and is provided with swirl vane, and air flows through swirl channel
Rotational flow is formed, the annular straight runner of rotational flow air is located at influence of the swirl channel downstream to eliminate blade wake passing,
The annular rotational flow air convergent passage is located at the straight flow paths downstream of rotational flow air and is used for increasing air axial velocity, empty in eddy flow
Gas exports to form the radially high VELOCITY DISTRIBUTION in the low outside in inner side；Fuel inlet, nozzle and jet expansion composition fuel flow path, institute
State that jet expansion is concordant with rotational flow air outlet, the mist of oil sprayed from jet expansion quick crashing under rotational flow air shear action
Form equally distributed droplet and be mixed to form uniform flammable mixed gas with air, and it is anti-in non-premix mode burn
Should.
Swirl nozzle mould combustion equivalent ratio is 0.6~0.8.
Swirl nozzle mould inward eddy blade quantity is 8~16, and swirl vane setting angle is 35 °~45 °.
Swirl nozzle mould and circumferential uniform swirl nozzle mould centre-to-centre spacing S1For 1.5~2.0d.
Circumferentially-adjacent swirl nozzle mould centre-to-centre spacing S2For 1.5~2.0d.
Beneficial effect
A kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine proposed by the present invention and existing skill
Art is compared:
Combustion zone uses oil-poor design, and combustion equivalent ratio is between 0.6~0.8, and now flame temperature is relatively low, can effectively press down
Make the nitrogen oxides generated by heating power type mechanism.Fuel spray is rapid under rotational flow air effect to be atomized and is well mixed with air
Close, it is ensured that combustion even does not produce hot localised points fully.
Combustion chamber is under identical entry condition, for the more conventional combustion chamber single point injection of multi-point injection, each nozzle
Flow reduces, therefore can select the less nozzle of flow number, so as to ensure higher charge oil pressure, reaches more preferable atomized water
It is flat, faster carry out combustion reaction evenly.Meanwhile, multi-point injection results in more uniform outlet temperature compared with single point injection
.
Oil-poor multiple spot is directly sprayed using non-premixed combustion, greatly reduces the probability for occurring combustion instability, and
Interference effect between each nozzle is controlled by adjusting injector spacing, effectively suppresses combustion noise.
Using grading combustion technology, burning is divided into main combustion stage and secondary combustion level by multiple spot directly injection, and its purpose is to open up
Wide combustion chamber steady operation border.Under small-power state, it is only necessary to pair combustion level fuel feeding burning, main combustion stage not fuel feeding, pair combustion level
Combustion equivalent ratio is between 0.6~0.8, it is ensured that combustion chamber steady operation, with the increase of power rating, can be gradually opened main combustion
Level, same main combustion stage combustion equivalent ratio is between 0.6~0.8, under maximum power state, and main combustion stage and secondary combustion level are while work
Make, remain in that combustion equivalent ratio between 0.6~0.8.It can so ensure under all working state, combustion chamber can be steady
Fixed work simultaneously effectively reduces pollutant emission level.
Brief description of the drawings
Below in conjunction with the accompanying drawings with embodiment to a kind of oil-poor multiple spot for low-pollution burning chamber of gas turbine of the invention
Direct injector head is described in further detail.
Fig. 1 is used for the direct injector head schematic diagram of oil-poor multiple spot of low-pollution burning chamber of gas turbine for the present invention.
Fig. 2 is used for the direct injection nozzle structure figure of oil-poor multiple spot of low-pollution burning chamber of gas turbine for the present invention.
Fig. 3 is swirl nozzle mould schematic diagram of the invention.
Fig. 4 is swirl nozzle mould sectional view of the invention.
Fig. 5 is applied to ring-pipe type combustion chamber schematic diagram for the present invention.
In figure:
1. the secondary main combustion stage swirl nozzle mould of combustion level swirl nozzle mould 4. of 2. head of combustion chamber flange of head of combustion chamber 3.
5. the annular eddy flow of rotational flow air convergent passage 9. of the annular rotational flow air straight channel 8. of 6. swirl channel of air intlet 7. is empty
The streamline of gas outlet 10. fuel inlet, 11. nozzle, 12. jet expansion, 13. taper mist of oil 14.
Pair combustion level swirl nozzle mould includes swirl nozzle mould 3a, swirl nozzle mould 3b, swirl nozzle mould 3c, swirl nozzle mould
3d
Main combustion stage swirl nozzle mould includes swirl nozzle mould 4a, swirl nozzle mould 4c, swirl nozzle mould 4h
Embodiment
The present embodiment is a kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine.
Refering to Fig. 1~Fig. 4, the present embodiment is used for the direct injector head of oil-poor multiple spot of low-pollution burning chamber of gas turbine, adopted
Constituted with multiple mutually isostructural swirl nozzle moulds, pair combustion level swirl nozzle mould 3 by the swirl nozzle mould 3a positioned at center and according to
Equidistantly circumferential three uniform swirl nozzle mould 3b, swirl nozzle mould 3c, swirl nozzle mould 3d are constituted Swirl nozzle mould；
Main combustion stage swirl nozzle mould 4 is by positioned at the swirl nozzle mould 4a alternate with secondary three swirl nozzle moulds for firing level, swirl nozzle mould
4c, swirl nozzle mould 4h are constituted, and main combustion stage swirl nozzle mould 4 and secondary combustion level swirl nozzle mould 3 can independent controls, it is ensured that combustion chamber
Can steady operation under wide working condition.Main combustion stage swirl nozzle mould 4 and secondary combustion level swirl nozzle mould 3 are fixedly mounted on combustion chamber
On the head of combustion chamber flange 2 on head 1；Wherein, Swirl nozzle mould and circumferential uniform swirl nozzle mould centre-to-centre spacing S1For
1.5~2.0d.Circumferentially-adjacent swirl nozzle mould centre-to-centre spacing S2For 1.5~2.0d.
In the present embodiment, air intlet 5, swirl channel 6, annular rotational flow air straight channel 7, annular rotational flow air convergence
Passage 8 and rotational flow air outlet 9 form the air flow circuit of swirl nozzle mould；Swirl vane, eddy flow leaf are installed in swirl channel 6
Piece quantity is 8~16, and swirl vane setting angle is 35 °~45 °, and air flows through the formation rotational flow of swirl channel 6.Annular
Rotational flow air is straight, and runner 7 is located at influence of the downstream of swirl channel 6 to eliminate swirl vane tail.Annular rotational flow air convergence
Passage 8 is located at the annular straight downstream of runner 7 of rotational flow air and is used for increasing air axial velocity, and edge is formed in rotational flow air outlet 9
The high VELOCITY DISTRIBUTION in the low outside of radially inner side.Fuel inlet 10, nozzle 11 and the composition fuel flow path of jet expansion 12；Jet expansion
12 is 9 concordant with rotational flow air outlet, and from the mist of oil of the ejection of jet expansion 12, quick crashing is formed under rotational flow air shear action
Equally distributed droplet is simultaneously mixed to form uniform flammable mixed gas, and carry out combustion reaction in non-premix mode with air.
The specific work process of combustion chamber is:
Only secondary combustion level swirl nozzle mould fuel feeding burning during combustion chamber ignition, with the increase of working condition, fuel delivery also by
It is cumulative plus, when reaching the secondary combustion level work upper limit, open main combustion stage swirl nozzle mould, pair combustion level flame ignites rapidly main combustion stage can
The mixed gas of combustion, then keeps main combustion stage and secondary combustion level to work simultaneously.
The specific work process of swirl nozzle mould is:
Air enters the formation eddy flow flowing of swirl channel 6 from air intake 5, then passes through annular rotational flow air straight channel
7, to eliminate the influence of swirl vane tail, again pass through annular rotational flow air convergent passage 8, are formed in rotational flow air outlet 9 along footpath
To the high VELOCITY DISTRIBUTION in the low outside in inner side, the expansion of final cyclone downstream streamline 14 forms recirculating zone.Fuel oil is from fuel inlet 10
Into nozzle 11, spray cone 13 is sprayed from jet expansion 12.Fuel oil spray cone 13 and rotational flow air mixing after downstream with
Oil-poor in stable condition burning.
Fig. 5 is to be applied to ring-pipe type combustion chamber example, in practical application, according to the concrete structure and size of gas turbine
Adjust can burner's quantity.
Claims (5)
1. a kind of direct injector head of oil-poor multiple spot for low-pollution burning chamber of gas turbine, it is characterised in that:Including combustion chamber
Head flanges, secondary combustion level swirl nozzle mould, main combustion stage swirl nozzle mould, air intlet, swirl channel, annular rotational flow air is straight
Passage, annular rotational flow air convergent passage, rotational flow air outlet, fuel inlet, nozzle, jet expansion, using multiple identical knots
The swirl nozzle mould composition of structure, and be fixed on head of combustion chamber flange, the secondary combustion level swirl nozzle mould is by positioned at center
Swirl nozzle mould and equidistantly circumferential three uniform swirl nozzle moulds are constituted according to Swirl nozzle mould, the main combustion stage eddy flow
Nozzle mould positioned at the swirl nozzle mould alternate with secondary three swirl nozzle moulds for firing level by constituting, main combustion stage swirl nozzle mould and pair
Firing level swirl nozzle mould can independent control；Wherein, air intlet, swirl channel, annular rotational flow air straight channel, annular eddy flow
Air convergent passage and rotational flow air export in the air flow circuit to form swirl nozzle mould, the swirl channel and are provided with eddy flow leaf
Piece, air flows through swirl channel formation rotational flow, and the annular straight runner of rotational flow air is used to positioned at swirl channel downstream
The influence of blade wake passing is eliminated, the annular rotational flow air convergent passage is located at the straight flow paths downstream of rotational flow air and is used for increasing sky
Gas axial velocity, exports to form the radially high VELOCITY DISTRIBUTION in the low outside in inner side in rotational flow air；Fuel inlet, nozzle and nozzle
Outlet composition fuel flow path, the jet expansion is concordant with rotational flow air outlet, and the mist of oil sprayed from jet expansion is empty in eddy flow
Quick crashing forms equally distributed droplet and is mixed to form uniform flammable mixed gas with air under gas shear action, and with non-
Premix mode carries out combustion reaction.
2. the oil-poor multiple spot direct injector head according to claim 1 for low-pollution burning chamber of gas turbine, its feature
It is:Swirl nozzle mould combustion equivalent ratio is 0.6~0.8.
3. the oil-poor multiple spot direct injector head according to claim 1 for low-pollution burning chamber of gas turbine, its feature
It is:Swirl nozzle mould inward eddy blade quantity is 8~16, and swirl vane setting angle is 35 °~45 °.
4. the oil-poor multiple spot direct injector head according to claim 1 for low-pollution burning chamber of gas turbine, its feature
It is:Swirl nozzle mould and circumferential uniform swirl nozzle mould centre-to-centre spacing S1For 1.5~2.0d.
5. the oil-poor multiple spot direct injector head according to claim 1 for low-pollution burning chamber of gas turbine, its feature
It is:Circumferentially-adjacent swirl nozzle mould centre-to-centre spacing S2For 1.5~2.0d.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710343294.1A CN107143880B (en) | 2017-05-16 | 2017-05-16 | Lean oil multi-point direct injection head for low-pollution combustion chamber of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710343294.1A CN107143880B (en) | 2017-05-16 | 2017-05-16 | Lean oil multi-point direct injection head for low-pollution combustion chamber of gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN107143880A true CN107143880A (en) | 2017-09-08 |
| CN107143880B CN107143880B (en) | 2020-02-14 |
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| CN201710343294.1A Active CN107143880B (en) | 2017-05-16 | 2017-05-16 | Lean oil multi-point direct injection head for low-pollution combustion chamber of gas turbine |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108626749A (en) * | 2018-03-16 | 2018-10-09 | 南京航空航天大学 | A kind of 7 points of oil-poor direct injection heads for low pollution combustor |
| CN108844097A (en) * | 2018-03-16 | 2018-11-20 | 南京航空航天大学 | A kind of oil-poor low pollution combustor directly sprayed of multiple spot |
| CN108954388A (en) * | 2018-07-09 | 2018-12-07 | 西北工业大学 | A kind of multiple spot unit directly sprays fractional combustion room |
| CN108980893A (en) * | 2018-07-09 | 2018-12-11 | 西北工业大学 | The direct jetstream whirl device of pass multiple spot and pass multiple spot directly spray head construction |
| CN109113895A (en) * | 2018-09-11 | 2019-01-01 | 中国人民解放军国防科技大学 | Flame stabilizing device of ramjet engine |
| CN115127119A (en) * | 2021-03-26 | 2022-09-30 | 中国航发商用航空发动机有限责任公司 | Annular combustion chamber, staged fuel nozzle thereof and method for suppressing oscillatory combustion |
| CN117803950A (en) * | 2024-01-02 | 2024-04-02 | 中国航空发动机研究院 | Oil injection device of central staged combustion chamber |
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| CN204227464U (en) * | 2014-10-28 | 2015-03-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber centerbody fluting swirl nozzle |
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| CN104791847A (en) * | 2015-03-17 | 2015-07-22 | 上海交通大学 | Low-rotational-flow multi-nozzle combustor structure applicable to low-pollution combustion chamber of gas turbine |
| EP2933560A1 (en) * | 2014-04-17 | 2015-10-21 | Alstom Technology Ltd | Method for premixing air with a gaseous fuel and burner arrangement for conducting said method |
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| CN101206029A (en) * | 2006-12-21 | 2008-06-25 | 中国科学院工程热物理研究所 | Nozzle for minisize gas-turbine combustor |
| US9027349B2 (en) * | 2011-01-27 | 2015-05-12 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine gaseous fuel injection system |
| CN203586283U (en) * | 2013-07-10 | 2014-05-07 | 辽宁省燃烧工程技术中心（有限公司） | Dry-type low-nitrogen combustion device of combustion gas turbine employing gas fuel |
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| CN204227464U (en) * | 2014-10-28 | 2015-03-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber centerbody fluting swirl nozzle |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108626749A (en) * | 2018-03-16 | 2018-10-09 | 南京航空航天大学 | A kind of 7 points of oil-poor direct injection heads for low pollution combustor |
| CN108844097A (en) * | 2018-03-16 | 2018-11-20 | 南京航空航天大学 | A kind of oil-poor low pollution combustor directly sprayed of multiple spot |
| CN108626749B (en) * | 2018-03-16 | 2020-02-21 | 南京航空航天大学 | 7-point lean oil direct injection head for low-pollution combustion chamber |
| CN108954388A (en) * | 2018-07-09 | 2018-12-07 | 西北工业大学 | A kind of multiple spot unit directly sprays fractional combustion room |
| CN108980893A (en) * | 2018-07-09 | 2018-12-11 | 西北工业大学 | The direct jetstream whirl device of pass multiple spot and pass multiple spot directly spray head construction |
| CN109113895A (en) * | 2018-09-11 | 2019-01-01 | 中国人民解放军国防科技大学 | Flame stabilizing device of ramjet engine |
| CN115127119A (en) * | 2021-03-26 | 2022-09-30 | 中国航发商用航空发动机有限责任公司 | Annular combustion chamber, staged fuel nozzle thereof and method for suppressing oscillatory combustion |
| CN115127119B (en) * | 2021-03-26 | 2023-11-24 | 中国航发商用航空发动机有限责任公司 | Method for suppressing oscillation combustion of annular combustion chamber |
| CN117803950A (en) * | 2024-01-02 | 2024-04-02 | 中国航空发动机研究院 | Oil injection device of central staged combustion chamber |
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