CN103277811B - Single cavity standing vortex burning chamber - Google Patents
Single cavity standing vortex burning chamber Download PDFInfo
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- CN103277811B CN103277811B CN201310171123.7A CN201310171123A CN103277811B CN 103277811 B CN103277811 B CN 103277811B CN 201310171123 A CN201310171123 A CN 201310171123A CN 103277811 B CN103277811 B CN 103277811B
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- cavity
- burning chamber
- standing vortex
- vortex burning
- prevapourising
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Abstract
A kind of single cavity standing vortex burning chamber, it includes: diffuser, and combustion chamber inlet air flow enters in described combustion chamber by described diffuser; Interior casing; Outer casing; Burner inner liner, described burner inner liner forms single curved cavity, and described interior casing, outer casing and burner inner liner define main duct and the by-pass air duct of described combustion chamber; Guiding device, main flow and by-pass air duct air are separated by described guiding device; Prevapourising device, described air after diffuser deceleration supercharging is divided into four roads and enters main flow, prevapourising device, main duct and by-pass air duct respectively after described guiding device and prevapourising device; Oil supply system; High-energy spark plug, described high-energy spark plug is arranged at the bottom of described cavity, and described single cavity standing vortex burning chamber combustion zone is divided into district in whirlpool and primary zone, and described single cavity standing vortex burning chamber also includes the connection flame support plate described flame being reached main flow by cavity.
Description
Technical field:
The present invention relates to a kind of single cavity standing vortex burning chamber, mainly as the main chamber of aero-engine, belong to new ideas aero-gas turbine field of combustion technology.
Background technology:
Along with aero engine technology further develops, thrust-weight ratio constantly increases, combustor inlet temperature raises, combustion chamber oil-gas ratio, temperature rise raise, the requirement of chamber performance is also progressively improved, but simultaneously to combustion chamber heavily quantitative limitation in further increase, therefore, the development of high oil ratio combustion chamber is faced with many technological challenges: 1, steady operation in broader scope, invisible smoking of the exhaust burning under mainly solving combustion stability in a low-power state and high power state; 2, distribute the condition of minimizing and the decline of cold gas quality in cooling tolerance under, further maintenance even improves the durability of burner inner liner; 3, exhaust pollution is reduced under large state; 4, turbine normally works under the adverse circumstances of excessive temperature, significantly must reduce exit temperature distribution coefficient.The approach solved the problem can be divided into two classes, and a class takes reasonable measure to optimize conventional swirl stabilized combustion room, and feasible measure comprises fuel oil classification, air classification, lean premixed and prevapourising and Multi-stage spiral etc.; Another kind of, be on the basis of grasping general principle, explore brand-new combustion method, development new concept combustion room, such as standing vortex burning chamber (trapped vortex combustor, TVC), ultra-compact combustion chamber (ultra compact combustor, UCC) etc.
On the other hand, along with day by day fierce and environmental requirement constantly strict of the develop rapidly of aero engine technology, market competition, large aircraft engine is lower towards expense, performance is higher and the better future development of environmental protection characteristic.For this reason, at engines such as improvement development GE90, PW4084, TRENT800 with while completely newly developing the engines such as GP7200, TRENT900, GEnx and TRENT1000, the a series of beforehand research plan of the U.S. and European Union member countries' independence or Joint Implementation, exploitation and demonstrate that performance is high, quality is light, reliability is high and discharge and the low large aircraft engine machine technology of following regular circulation of noise, more economical and the advanced person that is environmental protection of exploratory development is circulated large aircraft engine machine technology, and for future, good technical foundation has been laid in the development of large aircraft engine.
Standing vortex burning chamber (TVC) is a kind of new combustion organizational form grown up from the nineties in 20th century.In conventional combustion room, air is by producing recirculating zone after cyclone, and high-temperature fuel gas upstream lights fresh flammable mixed gas at recirculating zone flows by action, and therefore recirculating zone act as the effect of point of safes burning things which may cause a fire disaster.Standing vortex burning chamber then have employed the concept of Grading And Zoning burning, district in whirlpool is level on duty, the air in district in whirlpool is entered by rationalization, stable swirl flow structure is formed in Shi Zhuwo district, feed fuel oil simultaneously, because vortex in level on duty is stayed fixed, therefore level on duty can smooth combustion under various operating mode; Main combustion stage (main flow) air flows into combustion zone by the circumference shunting bluff body/radial direction connection flame board combining structure of head, circumference shunting bluff body plays shunting, strengthening blending and flame stabilization, and radial connection flame plate is mainly used to propagating flame makes main combustion stage (main flow) be lighted by level on duty smoothly.Under little state, only level fuel feeding on duty, main combustion stage (main flow) not fuel feeding; Under large state, level on duty, main combustion stage (main flow) be fuel feeding work simultaneously.Foreign study finds that standing vortex burning chamber can obtain extraordinary performance in real-world conditions: compared with routine techniques, improve 50% at ignition performance, fuel-lean blowout performance, high-altitude ignition aspect of performance; Nitrogen oxide emission reduces 40% ~ 60% than ICAO standard C AEP2 in 1996; The working range that efficiency of combustion meets or exceeds 99% widens more than 40%.USAF, naval, Ministry of Energy, NASA etc. are exploring this technology transplant in possible military little Bypass Ratio Turbofan Engine, commercial large Bypass Ratio Turbofan Engine, industry and Vessel personnel.
The stability of standing vortex burning chamber and efficiency of combustion are subject to the restriction of cavity size, and fuel system more complicated.
Therefore, necessary the deficiency solving prior art is improved to prior art.
Summary of the invention:
The invention provides a kind of single cavity standing vortex burning chamber, it uses single cavity to stabilize the flame, when identical height of head, can bowl volume be increased, increase residence time, raise the efficiency and combustion stability, and can fuel system be simplified, make structure compacter, weight reduction.
The present invention adopts following technical scheme: a kind of single cavity standing vortex burning chamber, and it includes:
Diffuser, combustion chamber inlet air flow enters in described combustion chamber by described diffuser;
Interior casing;
Outer casing;
Burner inner liner, described burner inner liner forms single curved cavity, and described interior casing, outer casing and burner inner liner define main duct and the by-pass air duct of described combustion chamber;
Guiding device, main flow and by-pass air duct air are separated by described guiding device, and described guiding device comprises the import of antetheca cold gas, and described guiding device introduces cavity antetheca cold gas, cools cavity antetheca;
Prevapourising device, described air after diffuser deceleration supercharging is divided into four roads and enters main flow, prevapourising device, main duct and by-pass air duct respectively after described guiding device and prevapourising device;
Oil supply system;
High-energy spark plug, described high-energy spark plug is arranged at the bottom of described cavity, and described single cavity standing vortex burning chamber combustion zone is divided into district in whirlpool and primary zone, and described single cavity standing vortex burning chamber also includes the connection flame support plate described flame being reached main flow by cavity.
Described burner inner liner wall is furnished with some flame tube wall Cooling Holes cooled described burner inner liner wall.
Described single cavity comprises cavity antetheca air inlet and cavity rear wall air inlet, and the distance between described cavity antetheca air inlet and the distance between bottom cavity are less than bottom described cavity rear wall air inlet and cavity is in different radial positions to make described cavity antetheca air inlet and cavity rear wall air inlet.
Described oil supply system comprises main combustion stage (main flow) fuel manifold, level on duty (cavity) fuel manifold and cavity fuel nozzle, and described cavity fuel nozzle is arranged at the center of described cavity antetheca air inlet.
Described main combustion stage (main flow) fuel manifold to be integrated in described prevapourising device and to introduce prevapourising air.
Baffle plate and evaporation cavity is also provided with in described prevapourising device.
Described main combustion stage (main flow) fuel manifold is provided with nozzle opening, and fuel oil sprays from described nozzle opening, gets on baffle plate, and with the flowing of prevapourising air, forms jet and enter main flow, mix with main flow.
Described single cavity standing vortex burning chamber can realize RQL mode of operation, LPP mode of operation and both combination mode of operation.
Described single cavity standing vortex burning chamber is full loop configuration.
The present invention has following beneficial effect:
(1) list cavity standing vortex burning chamber of the present invention is a kind of fractional combustion room, can realize RQL combustion technology, LPP combustion technology or the above-mentioned burning tissues technology that both combine easily, realizes the efficient low-discharging burning under wider operating mode;
(2) list cavity standing vortex burning chamber of the present invention utilizes single cavity to stabilize the flame, and can increase the volume of single cavity, increases residence time, thus improves efficiency of combustion and ignition performance, widens range of flame;
(3) in high thrust-weight ratio or low emission level engine, utilize the organizationally efficient stable burning of single cavity standing vortex burning chamber, and effectively the pollutant emission of smoke and gas state is emitted in reduction;
(4) list cavity standing vortex burning chamber fuel system of the present invention is more simple, and head of combustion chamber is compacter, and combustion chamber weight significantly alleviates.
Accompanying drawing illustrates:
Fig. 1 is the loopful structural representation of list cavity standing vortex burning chamber of the present invention.
Fig. 2 is the partial sectional view of cavity standing vortex burning chamber single shown in Fig. 1.
Fig. 3 is the flame tube structure partial schematic diagram in the single cavity standing vortex burning chamber shown in Fig. 1.
Fig. 4 is list cavity standing vortex burning chamber cavity oil supply system structural representation of the present invention.
Fig. 5 is list cavity standing vortex burning chamber prevapourising device of the present invention and connection flame support plate structural representation.
Fig. 6 is cavity standing vortex burning chamber prevapourising device operation principle schematic diagram single shown in Fig. 5.
Fig. 7 is that list cavity standing vortex burning chamber of the present invention is without the shaft section flowing of connection flame support plate and combustion process schematic diagram.
Fig. 8 is the shaft section flowing of list cavity standing vortex burning chamber of the present invention connection flame support plate place and combustion process schematic diagram.
Wherein:
The mono-cavity standing vortex burning chamber of 1-, 2-diffuser, casing in 3-, the outer casing of 4-, the import of 5-level on duty (cavity) fuel manifold, the import of 6-main combustion stage (main flow) fuel manifold, 7-high-energy spark plug, 8-burner inner liner, 9-level on duty (cavity) fuel manifold, 10-guiding device, the import of 11-antetheca cold gas, 12-level on duty (cavity) fuel nozzle, 13-flame tube wall, 14-flame tube wall Cooling Holes, 15-cavity, 16-cavity antetheca air inlet, 17-cavity rear wall air inlet, 18-prevapourising device, 19-main combustion stage (main flow) fuel manifold, 20-evaporation cavity, 21-baffle plate, 22-nozzle opening, 23-joins flame support plate, 24-prevapourising mixes gas spurt, 25-main flow, 26-prevapourising air, the main whirlpool of 27-cavity, the secondary whirlpool of 28-cavity, 29-primary zone, 30-main duct, 31-by-pass air duct.
Detailed description of the invention:
The present invention is introduced in detail below in conjunction with the drawings and the specific embodiments.
Please refer to shown in Fig. 1 to Fig. 5, list cavity standing vortex burning chamber of the present invention, primarily of the composition such as burner inner liner 8, guiding device 10, prevapourising device 18 of casing 3 in diffuser 2, combustion chamber and outer casing 4, single curved cavity.Single cavity standing vortex burning chamber is full loop configuration, and the whirlpool of staying utilizing burner inner liner inner cavity 15 to be formed stabilizes the flame, and relies on connection flame support plate 23 that flame is reached main flow 25 by cavity 15, realizes efficient low-discharging in conjunction with RQL combustion technology and LPP grading combustion technology.
Arrange diffuser 2 in combustion chamber import, its main function reduces burner inner liner 5 inlet air flow velocity, improves inlet pressure, and this is conducive to reducing loss, tissue burning.Wherein the interior casing 3 of single cavity standing vortex burning chamber, outer casing 4 are main load parts of combustion chamber, and constitute main duct 30 and the by-pass air duct 31 of combustion chamber with burner inner liner 8.
Guiding device 10 cavity format triangular in shape, and contain antetheca cold gas import 11.Main flow 25 and by-pass air duct air are separated by guiding device 10, and introduce cavity antetheca cold gas, cool cavity antetheca.
Cavity 15 comprises cavity antetheca air inlet 16 and cavity rear wall air inlet 17, distance between described cavity antetheca air inlet 16 and the distance between bottom cavity are less than bottom described cavity rear wall air inlet 17 and cavity is in different radial positions to make described cavity antetheca air inlet 16 and cavity rear wall air inlet 17, such structure is conducive to the two whirlpools vortex structures required for formation, is convenient to stabilize the flame.
In combustion chamber main flow 25, place arranges connection flame support plate 23, its role is to the flame in cavity 15 to be passed to main flow 25, lights the flammable mixture in primary zone 29, joins flame support plate 23 in addition and also plays the effect stabilized the flame.Connection flame support plate 23 makes main flow 25 air form the passage shunk, and air-flow is accelerated, can prevent the generation of tempering like this, can increase turbulivity simultaneously, thus strengthen air-fuel mixture.
Prevapourising device 18 is integrated with main combustion stage (main flow) fuel manifold 19.Main combustion stage (main flow) fuel manifold 19 is opened a lot of nozzle opening 22, fuel oil sprays from nozzle opening 22, through the bounce-back of baffle plate 21, rebound, broken, then carry out being atomized, evaporating along with prevapourising air 26 enters evaporation cavity 20 together, finally form the gaseous mixture of equivalent proportion higher than fuel rich limit of flammability, and mix gas spurt 24 from prevapourising and spue, mix with main flow 25, form the gaseous mixture of required equivalent proportion, enter primary zone 29 and burn.
Cavity antetheca air inlet 16 center arranges swirl atomizer and serves as level on duty (cavity) fuel nozzle 12, to fuel feeding in cavity.
Please refer to described in Fig. 7 and Fig. 8, the operation principle of list cavity standing vortex burning chamber of the present invention is: after diffuser 2 slows down supercharging, enter combustion chamber from the air of blower outlet.Four tunnels are divided into enter main flow 25, prevapourising device 18, main duct 30, by-pass air duct 31 respectively by guiding device 10 and prevapourising device 18; Main duct air-flow enters burner inner liner 8 mainly through flame tube wall Cooling Holes 14, cools flame tube wall 13; By-pass air duct air-flow is divided into four parts: (1) enters in the cavity of guiding device 10 from the antetheca cold gas import 11 guiding device 10, then enters cavity 15 from the Cooling Holes of cavity antetheca, cools cavity antetheca; (2) cavity 15 is entered from cavity antetheca air inlet 16; (3) cavity 15 is entered from cavity rear wall air inlet 17; (4) enter burner inner liner 8 from flame tube wall Cooling Holes 14, flame tube wall 13 is cooled.With reference to shown in Fig. 7, at the shaft section without connection flame support plate, i.e. main flow flow area, enters the air of cavity 15 from cavity antetheca air inlet 16 and cavity rear wall air inlet 17, in cavity 15, form stable double vortex structure.Meanwhile, from level on duty (cavity) fuel nozzle 12 ejection fuel oil with enter in cavity 15 from cavity antetheca air inlet 16, formed combustion mixture.Bottom cavity 15, arrange high-energy spark plug 7, when engine start, high-energy spark plug 7 release has the electric spark of several Joule energy, is lighted by combustion mixture, and forms stable flame under the effect in stable two whirlpool.With reference to shown in Fig. 8, at connection flame support plate 23 place shaft section, i.e. main flow stem shaft cross section, under the driving of differential pressure action, the high temperature that fires in cavity 15 mixes air-flow in the tail of connection flame support plate 23, and mixes with main flow 25, or light main flow and mix gas, make it in primary zone combustion.
List cavity standing vortex burning chamber of the present invention is illustrated below in conjunction with several embodiment.
A kind of embodiment in the present invention is the combustion chamber of RQL (fuel-rich combustion/quench/poor oil firing) pattern.Only have fuel feeding in cavity in this pattern, main flow is pure air.Level on duty (cavity) fuel nozzle 12 feeds excessive fuel oil to cavity 15, thus makes formation rich oil in cavity mix gas, lights a fire successfully, will carry out fuel-rich combustion in cavity.Containing unburnt fuel in the combustion gas that burning generates, they have two kinds of approach and main flow to carry out blending, extinguishing, and then realize poor oil firing: on the one hand under the Involving velocity of main flow, combustion gas in cavity will form shear layer and a series of whirlpool with main flow, in the middle of this region, liquid turbulence degree is very large, increase mixing intensity, be conducive to extinguishing; On the other hand, will form low-pressure area in connection flame support plate 23 tail, the combustion gas in cavity to connection flame support plate 23 wake, thus will add the blending area of Fuel-rich gas and primary air under pressure-driven.
Another kind of embodiment of the present invention is the combustion chamber of LPP (lean premixed preevaporated) pattern.Cavity and main flow fuel feeding simultaneously in this pattern.Level on duty (cavity) fuel nozzle 12 feeds appropriate fuel oil to cavity 15, to ensure burning in district in whirlpool near equivalent proportion 0.8, to ensure the stability of burning.Main combustion stage (main flow) feeds a certain amount of fuel oil, makes main flow fuel-air mixture be in oil-poor state (its equivalent proportion is close to oil-poor Flammability limits).Light a fire successfully, in district in whirlpool, form stable flame.The high-temperature fuel gas produced has two kinds of approach and main flow to interact equally: a part enters primary zone 29 from cavity 15 under main flow mixes the Involving velocity of gas, form the very large shear layer of turbulence intensity and a large amount of whirlpools between, main flow with the direct effect of high-temperature fuel gas under lighted, and to main flow more depths propagate; Another part combustion gas flows to connection flame support plate 23 following wake from cavity 15 under pressure differential, thus forms more incendiary source, and main flow is lighted in different positions, makes burning more complete, raises the efficiency.
The third embodiment of the present invention is the combined burning room of RQL pattern and LPP pattern, namely uses RQL pattern when little state, only has cavity fuel feeding; And use LPP pattern when large state, cavity and main flow fuel feeding simultaneously.So just can take into account the stability of little state and the high efficiency of large state and low emission.
From above-described embodiment, list cavity standing vortex burning chamber of the present invention, can realize RQL combustion technology, LPP combustion technology or the above-mentioned burning tissues technology that both combine easily, realizes the efficient low-discharging burning under wider operating mode.
The above is only the preferred embodiment of the present invention, it should be pointed out that for those skilled in the art, can also make some improvement under the premise without departing from the principles of the invention, and these improvement also should be considered as protection scope of the present invention.
Claims (9)
1. a single cavity standing vortex burning chamber, it includes:
Diffuser, combustion chamber inlet air flow enters in described combustion chamber by described diffuser;
Interior casing;
Outer casing;
Burner inner liner, described burner inner liner forms single curved cavity, and described interior casing, outer casing and burner inner liner define main duct and the by-pass air duct of described combustion chamber;
Guiding device, main flow and by-pass air duct air are separated by described guiding device, and described guiding device comprises the import of antetheca cold gas, and described guiding device introduces cavity antetheca cold gas, cools cavity antetheca;
Prevapourising device, described air after diffuser deceleration supercharging is divided into four roads and enters main flow, prevapourising device, main duct and by-pass air duct respectively after described guiding device and prevapourising device;
Oil supply system;
High-energy spark plug, described high-energy spark plug is arranged at the bottom of described cavity, it is characterized in that: described single cavity standing vortex burning chamber combustion zone is divided into district in whirlpool and primary zone, and described single cavity standing vortex burning chamber also includes connection flame support plate flame being reached main flow by cavity.
2. single cavity standing vortex burning chamber as claimed in claim 1, is characterized in that: described burner inner liner wall is furnished with some flame tube wall Cooling Holes cooled described burner inner liner wall.
3. single cavity standing vortex burning chamber as claimed in claim 2, it is characterized in that: described single cavity comprises cavity antetheca air inlet and cavity rear wall air inlet, the distance between described cavity antetheca air inlet and the distance between bottom cavity are less than bottom described cavity rear wall air inlet and cavity is in different radial positions to make described cavity antetheca air inlet and cavity rear wall air inlet.
4. single cavity standing vortex burning chamber as claimed in claim 1, is characterized in that: described oil supply system comprises main combustion stage fuel manifold, level fuel manifold on duty and cavity fuel nozzle, and described cavity fuel nozzle is arranged at the center of described cavity antetheca air inlet.
5. single cavity standing vortex burning chamber as claimed in claim 4, is characterized in that: described main combustion stage fuel manifold to be integrated in described prevapourising device and to introduce prevapourising air.
6. single cavity standing vortex burning chamber as claimed in claim 5, is characterized in that: be also provided with baffle plate and evaporation cavity in described prevapourising device.
7. single cavity standing vortex burning chamber as claimed in claim 6, is characterized in that: described main combustion stage fuel manifold is provided with nozzle opening, and fuel oil sprays from described nozzle opening, get on baffle plate, and with the flowing of prevapourising air, form jet and enter main flow, mix with main flow.
8. single cavity standing vortex burning chamber as claimed in claim 1, is characterized in that: described single cavity standing vortex burning chamber can realize RQL mode of operation, LPP mode of operation and both combination mode of operation.
9. as the single cavity standing vortex burning chamber in claim 1-8 as described in any one, it is characterized in that: described single cavity standing vortex burning chamber is full loop configuration.
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| CN201310171123.7A CN103277811B (en) | 2013-05-10 | 2013-05-10 | Single cavity standing vortex burning chamber |
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| CN201310171123.7A CN103277811B (en) | 2013-05-10 | 2013-05-10 | Single cavity standing vortex burning chamber |
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| CN103277811B true CN103277811B (en) | 2015-10-28 |
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| CN105020744A (en) * | 2015-07-06 | 2015-11-04 | 南京航空航天大学 | Inclined-flow trapped-vortex combustor |
| CN105546579A (en) * | 2015-12-25 | 2016-05-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Fuel-oil spray nozzle |
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| CN106907742B (en) * | 2017-02-08 | 2019-06-04 | 南京航空航天大学 | A kind of fuel feeding blends integrated standing vortex burning chamber head device and its working method |
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| CN111623375B (en) * | 2019-02-28 | 2021-09-10 | 中国航发商用航空发动机有限责任公司 | Device for cooling fuel nozzle and aircraft engine comprising same |
| CN111706879B (en) * | 2020-06-10 | 2023-06-27 | 中国空气动力研究与发展中心 | Flame-stabilizing concave cavity and oil-gas matching device for duty stage of vortex-holding combustion chamber |
| CN112524641A (en) * | 2020-12-02 | 2021-03-19 | 西北工业大学 | Novel turbine interstage combustion chamber |
| CN113405119B (en) * | 2021-05-07 | 2022-04-08 | 南京航空航天大学 | Vortex-flow trapped-vortex partition combustion chamber |
| CN114484505B (en) * | 2022-01-27 | 2023-05-16 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite full-ring flame tube, shaping mold and preparation method thereof |
| CN115076723B (en) * | 2022-06-01 | 2023-04-07 | 南京航空航天大学 | Concave cavity standing vortex stabilizer and working method thereof |
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