CN202032613U - Partial pre-mixing & pre-evaporation combustion chamber - Google Patents
Partial pre-mixing & pre-evaporation combustion chamber Download PDFInfo
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- CN202032613U CN202032613U CN2010207013086U CN201020701308U CN202032613U CN 202032613 U CN202032613 U CN 202032613U CN 2010207013086 U CN2010207013086 U CN 2010207013086U CN 201020701308 U CN201020701308 U CN 201020701308U CN 202032613 U CN202032613 U CN 202032613U
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Abstract
The utility model belongs to the aeroengine field and relates to a partial pre-mixing & pre-evaporation combustion chamber for liquid spray injection in a swirler vane channel. The combustion chamber has a head composed of a secondary combustion stage and a primary combustion stage. The secondary combustion stage is composed of a first-stage axial swirler, a converging section, a throat section, an expanding section and a secondary oil-way nozzle. The primary combustion stage is composed of a first-stage axial swirler, a first-stage radial swirler, a pre-mixing section, a converging throat section and a direct fuel injection nozzle. The combustion chamber with the head having the above-mentioned structure adopts a center-graded DIPME (Rich/Lean Direct Injection and Lean Partial Pre-Mixing & Pre-Evaporation) mixed combustion mode. In small states, the secondary combustion stage adopts a rich direct injection combustion mode. In large states, the secondary combustion stage adopts a lean direct injection combustion mode and the primary combustion stage adopts a lean partial pre-mixing & pre-evaporation combustion mode. In order to ensure that the fuel is atomized, the primary combustion stage adopts a pressure direct fuel injection nozzle. The combustion chamber head can make emission of UHC, NOx, CO and soot particles rather greatly reduced without other performances of the combustion chamber sacrificed.
Description
Technical field
Patent of the present invention belongs to the aero-engine field, relates to the partly-premixed pre-evaporating combustion chamber of liquid mist jet in a kind of swirl vane passage.
Background technology
International Civil Aviation Organization has just issued " environment protectment protection " and " aero-engine discharging " regulations in the eighties, and constantly revises perfectly, has begun to carry out CAEP 6 discharge standards at present.Each big aero-engine company and research institution are all studied the control pollutant emission as important topic, wherein the low emissions combustion technology is the most important research contents of civil aviation engine.Because disposal of pollutants is the Compulsory Feature of seaworthiness evidence obtaining to the civil aircraft engine, American-European international well-known aero-engine company of several families is at more and more severeer emission request, implement advanced civilian reseach of engine plan, grasped the key technology of low emission combustor.Up-to-date dicyclo premixed swirl (TAPS) tissue combustion technology is adopted in the combustion chamber of GE company development, has been used for the Leap-X engine, and its NOx disposal of pollutants is than CAEP 6 low 47.7%.PW company adopts the TALON X combustion chamber of RQL technical development on the PW1000G engine, estimates that the NOx disposal of pollutants is than CAEP 6 low 40%.RR company adopts the LDIS low pollution combustor of ANTLE planned development, and its NOx disposal of pollutants has reduced by 50% than CAEP 2 standards.
NOx is that aeroengine combustor buring chamber designer needs one of pollutant that emphasis considers, in aero-engine, NOx is mainly determined by the combustion zone flame temperature.At present existing low pollution combustor begins to adopt equivalent proportion that lean premixed preevaporated technology guarantees the combustion zone in 0.5～0.65 scope, thereby effectively controls the generation that flame temperature reduces NOx.Adopt common its premix section in combustion chamber of this technology longer, occur spontaneous combustion and tempering easily, owing to burn at oil-poor state in this combustion chamber, mix the fine of evaporation again, make the probability that rough burning occurs double.The rich oil head design is adopted in traditional combustion chamber, the equivalent proportion of combustion zone is about 1, this combustion system can't reduce pollutant, the growing amount of NOx particularly, but this combustion chamber is more stable with respect to the combustion chamber work of adopting lean premixed preevaporated technology, its some combustion chamber key property is higher, such as slow train fuel-lean blowout border (LBO) and oil-poor ignition limit (LLO).
The performance that guarantees the combustion chamber also will reduce pollutant emission simultaneously, need above two kinds of technology combinations, secondary combustion level adopts direct injection, and main combustion stage adopts the mixed combustion mode of oil-poor partly-premixed prevapourising, the performance requirement of combustion chamber can be guaranteed, the requirement of pollutant emission can be guaranteed again.
Summary of the invention
The purpose of patent of the present invention: a kind of partly-premixed pre-evaporating combustion chamber that can guarantee chamber performance and reduce disposal of pollutants is provided.
The technical scheme of patent of the present invention is: the head scheme adopts DIPME (the Rich/Lean Direct Injection and Lean Partial Pre-Mixing ﹠amp of center classification; Pre-Evaporation) mixed combustion mode, promptly when startup and little state, secondary combustion level adopts rich oil direct injection (Rich DirectInjection) combustion mode, this combustion mode is to realize local rich oil by the pair combustion level that auxiliary oil circuit swirl atomizer (or air atomizer spray nozzle) and secondary combustion level axial eddy device constitute, and this combustion system of organizing is between premixed combustion and diffusion combustion; When big state states such as (comprise) taking off, cruise, secondary combustion level adopts oil-poor direct injection (Lean Direct Injection) combustion mode, and main combustion stage adopts oil-poor partly-premixed prevapourising (Lean Partial Pre-Mixing ﹠amp; Pre-Evaporation) combustion mode, make central combustion zone play retention flame effect, the combustion zone is oil-poor partly-premixed prevapourising burning on every side, the combustion zone equivalent proportion is controlled between 0.5～0.65, combustion zone temperature is controlled in 1700K～1900K scope, and the time of staying of control thermal-flame, thereby effectively control the growing amount of NOx and CO.Main combustion stage by primary axis to swirler and one-level radial whirl device, and the direct fuel injection formula nozzle that is positioned at axial eddy device blade path is formed, the inside and outside pressure reduction of fuel oil depending nozzle initially atomizes, rely on the shear action of axial eddy device again, the main combustion stage fuel oil is atomized fully, and carry out good partly-premixed closing with the incoming flow air.Convergence type passage is adopted in the main combustion stage outlet, quickens air-flow and prevents tempering; Main combustion stage axial eddy device adopts strong eddy flow, and the radial whirl device adopts weak eddy flow and opposite with axial eddy device rotation direction, and the main combustion stage fuel oil is fully atomized.
Concrete structure is:
A kind of partly-premixed pre-evaporating combustion chamber, comprise diffuser (11), outer casing (12), interior casing (13), nozzle (14), head of combustion chamber (15), burner inner liner (16) and sparking plug (17), primary holes (18) and blending hole (19) are arranged on the burner inner liner as required, it is characterized in that described head of combustion chamber (15) fires level (30) by pair and main combustion stage (31) is formed, wherein:
1) secondary combustion level (30) is made of to swirler (32), converging portion (33), venturi (34), expansion segment (35) and auxiliary oil circuit nozzle (36) primary axis, primary axis is equipped with axial eddy device blade (37) in swirler (32), primary axis links to each other successively to swirler (32) converging portion (33) and expansion segment (35), auxiliary oil circuit nozzle (36) is positioned at primary axis between swirler (32) outlet and venturi (34), with the distance (61) of primary axis to swirler (32) be about 5mm.
2) main combustion stage (31) is made of to swirler (39), one-level radial whirl device (40), premix section (41), convergence venturi (42) and direct fuel injection formula nozzle (43) primary axis, and direct fuel injection formula nozzle (43) is positioned between main combustion stage axial eddy device (39) blade path.
Described axial eddy device blade (37) setting angle is between 30 °～45 °, and blade quantity is between 10～16, and swirl strength is between 0.45～0.75.
Described axial eddy device expansion segment angle (58) is between 90 °～150 °, and converging portion angle (60) is about 90 °.
Described secondary combustion level axial length (38) is between 25mm～32mm, and main combustion stage axial length (52) is between 22mm～28mm.
Described axial eddy device blade (44) established angle is between 50 °～60 °, blade quantity is 8～12, axial eddy device (39) exports to distance (62) between main combustion stage outlet between 10～15mm, radial whirl device blade (46) established angle is between 0 °～25 °, and the average swirl strength that guarantees the two-stage swirler is about 0.6.
Described axial eddy device (39) is strong eddy flow, and radial whirl device (40) is weak eddy flow, and both are used, and described convergence venturi (42) is used with premix section (41).
The interior convergency (48) of described convergence venturi (42) is between 20 °～45 °, and outer convergency (49) is between 10 °～30 °, and convergence venturi (42) is used with premix section (41).
Described main combustion stage is provided with the cooling aperture (50) of diameter 0.5mm～1mm, and head is provided with the upper cooling aperture of diameter 0.5mm～1.2mm (51).
Described fuel injection hole (45) is 3～8mm to axial eddy device (39) import distance (54), fuel injection hole (45) diameter 0.5mm～0.7mm, and spray-hole quantity is 8～12, spray angle (59) is between 45 °～70 °.
The beneficial effect of patent of the present invention is: the air of combustion chamber 60%～80% enters the combustion zone burning from the head, when reducing disposal of pollutants, takes into account combustion chamber igniting/flame-out and low high efficiency performance requirement of state; Main combustion stage adopt simple nozzle at a certain angle (45 °～70 °) be ejected in the main combustion stage passage, fully effectively fuel oil is atomized and is pre-mixed with air, can obtain good concentration field; Pre-combustion grade can be directly injected to the combustion zone, forms local rich oil, to guarantee the igniting and the extinguishment characteristics of combustion chamber, also can make air and fuel oil carry out part and be pre-mixed by changing nozzle location, to improve the discharging of NOx under the low operating mode.Two contracting and extending ports by pre-combustion grade and main combustion stage effectively prevent tempering, solve the key technology difficult problem of lean premixed preevaporated burning; Primary zone poor oil firing has reduced oil consumption; Adopt the LPP combustion technology to reduce the discharging of pollutants such as NOx, UHC, CO and smoke particle by a relatively large margin.Considered easy-disassembling-assembling problem on the structural design, changed the structure of optimizing when being convenient to test and be convenient to maintain and replace.
Description of drawings
Fig. 1 is a kind of oil-poor partly-premixed prevapourising low emission combustor structural representation;
Fig. 2 is a kind of oil-poor partly-premixed prevapourising low emission combustor head schematic diagram;
Fig. 3 is the local enlarged diagram of main combustion stage among Fig. 2 (31);
Fig. 4 is one of specific embodiment of main combustion stage among Fig. 2 (31), has shown the schematic diagram of radial whirl device (40) being changed into straight channel (55);
Fig. 5 be main combustion stage among Fig. 2 (31) specific embodiment two, shown the schematic diagram of radial whirl device (40) being changed into axial eddy device (56);
Fig. 6 is brace rod (57) schematic diagram between straight channel among Fig. 4 (55) and the main combustion stage swirler (39), has shown the position of four brace rods;
The specific embodiment
Introduce the present invention in detail below in conjunction with drawings and the specific embodiments.See also Fig. 1～Fig. 4.
Fig. 1 is DIPME (the Rich/Lean Direct Injection and Lean PartialPre-Mixing ﹠amp of employing center classification; Pre-Evaporation) the low pollution combustor schematic diagram of mixed combustion mode, combustion chamber (10) comprises diffuser (11), outer casing (12), interior casing (13), nozzle (14), head (15), burner inner liner (16) and sparking plug (17), and primary holes (18) and blending hole (19) are arranged on the burner inner liner as required.The working condition of combustion chamber is that air enters the combustion chamber from diffuser (11), air above 50% (15) from the head enters burner inner liner (16), remaining air enters burner inner liner (16) by combustion chamber outer shroud (20) and interior ring (21), fuel oil enters burner inner liner (16) by nozzle (14), in burner inner liner (16), after sparking plug (17) igniting, air and oil inflame are discharged from burner inner liner outlet (22).
Fig. 2 is DIPME low pollution combustor head (a 15) CONSTRUCTED SPECIFICATION, and head is made up of pair combustion level (30) and main combustion stage (31).Head (15) air inflow accounts for 50%～80% of the total tolerance in combustion chamber (10) greatly, specifically air inflow is how much relevant with cooling air volume with the gross gas-oil ratio of combustion chamber, secondary combustion level (30) air inflow accounts for 5%～20% of the total air inflow in combustion chamber greatly, concrete air inflow is closely related with combustion chamber idling rating oil-gas ratio, main combustion stage (31) air inflow accounts for 40%～65% of the total air inflow in combustion chamber greatly, and concrete air inflow is closely related with combustion chamber takeoff condition oil-gas ratio.
Secondary combustion level (30) is made of to swirler (32), converging portion (33), venturi (34), expansion segment (35) and auxiliary oil circuit nozzle (36) primary axis.Axial eddy device (32) valid circulation area and venturi (34) area determine secondary combustion level (30) air mass flow jointly, general about 90 ° of converging portion angle (60), the design of expansion segment (35) need be considered head carbon deposit and cooling, must guarantee in addition to be formed with the oblique recirculating zone that helps light a fire with flame stabilization in pair combustion level (30) downstream, the too little easy carbon deposit of expansion segment angle (58), the cooling problem appears in angle too conference.Auxiliary oil circuit nozzle (36) is positioned between secondary combustion level swirler (32) outlet and the secondary combustion level venturi (34), distance (61) to the swirler outlet is about 5mm, make the secondary combustion system of level that fires like this between premixed combustion and diffusion combustion, not only help the combustion chamber working stability, also help to reduce the pollutant of little operating mode.In all operating modes of combustion chamber, secondary combustion level (30) all will be worked, and starting and be local fuel-rich combustion here during unskilled labourer's condition, when operating mode greatly, be poor oil firing here.
Main combustion stage (31) is made of to swirler (39), one-level radial whirl device (40), premix section (41), convergence venturi (42) and direct fuel injection formula nozzle (43) primary axis.In order to prevent the appearance of rough burning phenomenon, need to keep the average swirl strength of two-stage swirler about 0.6, for this reason, main combustion stage radial whirl device (40) can be changed into non-eddy flow straight channel (55) or weak eddy flow axial eddy device (56), can also reach same performance requirement.The valid circulation area of two-stage swirler or one-level swirler and straight channel and convergence venturi (42) area determine main combustion stage (31) air mass flow jointly.The total length (47) of premix section and convergence venturi can guarantee effectively that between 10～15mm the main combustion stage fuel oil reaches partly-premixed prevapourising.The convergence venturi is used with the premix section, can effectively prevent the generation of tempering phenomenon, and this external main combustion stage increases the generation that cooling aperture (50) can effectively prevent dieseling.Direct fuel injection formula nozzle (43) is positioned between main combustion stage axial eddy device (39) blade path, fuel oil enters collection chamber (53) from working connection, spray from fuel injection hole (45) again, the inside and outside pressure reduction of depending nozzle carries out primary atomization, rely on the strong cyclonic action of main combustion stage axial eddy device (39) again, make the main combustion stage fuel oil be atomized fully and mix.Main combustion stage (31) is generally being opened a little less than 30% thrust operating mode, and its combustion system belongs to lean premixed burning, forms lift-off flame in main combustion stage (31) downstream, while the premix evaporation of burning is highly beneficial to control NOx pollutant.
Claims (9)
1. partly-premixed pre-evaporating combustion chamber, comprise diffuser (11), outer casing (12), interior casing (13), nozzle (14), head of combustion chamber (15), burner inner liner (16) and sparking plug (17), primary holes (18) and blending hole (19) are arranged on the burner inner liner as required, it is characterized in that described head of combustion chamber (15) fires level (30) by pair and main combustion stage (31) is formed, wherein:
1) secondary combustion level (30) is made of to swirler (32), converging portion (33), venturi (34), expansion segment (35) and auxiliary oil circuit nozzle (36) primary axis, primary axis is equipped with axial eddy device blade (37) in swirler (32), primary axis links to each other successively to swirler (32) converging portion (33) and expansion segment (35), auxiliary oil circuit nozzle (36) is positioned at primary axis between swirler (32) outlet and venturi (34), with the distance (61) of primary axis to swirler (32) be about 5mm;
2) main combustion stage (31) is made of to swirler (39), one-level radial whirl device (40), premix section (41), convergence venturi (42) and direct fuel injection formula nozzle (43) primary axis, and direct fuel injection formula nozzle (43) is positioned between main combustion stage axial eddy device (39) blade path.
2. partly-premixed pre-evaporating combustion chamber according to claim 1 is characterized in that described axial eddy device blade (37) setting angle between 30 °～45 °, and blade quantity is between 10～16, and swirl strength is between 0.45～0.75.
3. partly-premixed pre-evaporating combustion chamber according to claim 1 is characterized in that described axial eddy device expansion segment angle (58) between 90 °～150 °, and converging portion angle (60) is about 90 °.
4. the partly-premixed pre-evaporating combustion chamber of liquid mist jet in a kind of swirl vane passage according to claim 1 is characterized in that described secondary combustion level axial length (38) between 25mm～32mm, and main combustion stage axial length (52) is between 22mm～28mm.
5. partly-premixed pre-evaporating combustion chamber according to claim 1, it is characterized in that described axial eddy device blade (44) established angle is between 50 °～60 °, blade quantity is 8～12, axial eddy device (39) exports to distance (62) between main combustion stage outlet between 10～15mm, radial whirl device blade (46) established angle is between 0 °～25 °, and the average swirl strength that guarantees the two-stage swirler is about 0.6.
6. partly-premixed pre-evaporating combustion chamber according to claim 1 is characterized in that described axial eddy device (39) is strong eddy flow, and radial whirl device (40) is weak eddy flow, and both are used, and described convergence venturi (42) is used with premix section (41).
7. partly-premixed pre-evaporating combustion chamber according to claim 1, the interior convergency (48) that it is characterized in that described convergence venturi (42) is between 20 °～45 °, outer convergency (49) is between 10 °～30 °, and convergence venturi (42) is used with premix section (41).
8. according to the arbitrary described partly-premixed pre-evaporating combustion chamber of claim 1 to 7, it is characterized in that described main combustion stage is provided with the cooling aperture (50) of diameter 0.5mm～1mm, head is provided with the upper cooling aperture of diameter 0.5mm～1.2mm (51).
9. partly-premixed pre-evaporating combustion chamber according to claim 8, it is characterized in that described fuel injection hole (45) is 3～8mm to axial eddy device (39) import distance (54), fuel injection hole (45) diameter 0.5mm～0.7mm, spray-hole quantity is 8～12, and spray angle (59) is between 45 °～70 °.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010207013086U CN202032613U (en) | 2010-12-31 | 2010-12-31 | Partial pre-mixing & pre-evaporation combustion chamber |
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| CN2010207013086U CN202032613U (en) | 2010-12-31 | 2010-12-31 | Partial pre-mixing & pre-evaporation combustion chamber |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103123122A (en) * | 2012-12-31 | 2013-05-29 | 南京航空航天大学 | Lean oil pre-mixing and pre-evaporating low-pollution combustion chamber capable of ejecting main-stage fuel oil directly |
| CN105240847A (en) * | 2015-11-19 | 2016-01-13 | 哈尔滨东安发动机（集团）有限公司 | Anti-backfire structure of combustion chamber |
-
2010
- 2010-12-31 CN CN2010207013086U patent/CN202032613U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103123122A (en) * | 2012-12-31 | 2013-05-29 | 南京航空航天大学 | Lean oil pre-mixing and pre-evaporating low-pollution combustion chamber capable of ejecting main-stage fuel oil directly |
| CN103123122B (en) * | 2012-12-31 | 2015-08-12 | 南京航空航天大学 | The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays |
| CN105240847A (en) * | 2015-11-19 | 2016-01-13 | 哈尔滨东安发动机（集团）有限公司 | Anti-backfire structure of combustion chamber |
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Granted publication date: 20111109 |