CN203757766U - Rich oil direct-mixing partitioning combustion chamber - Google Patents
Rich oil direct-mixing partitioning combustion chamber Download PDFInfo
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- CN203757766U CN203757766U CN201320809412.0U CN201320809412U CN203757766U CN 203757766 U CN203757766 U CN 203757766U CN 201320809412 U CN201320809412 U CN 201320809412U CN 203757766 U CN203757766 U CN 203757766U
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 194
- 238000002156 mixing Methods 0.000 title claims abstract description 18
- 238000000638 solvent extraction Methods 0.000 title abstract 4
- 238000002347 injection Methods 0.000 claims description 18
- 239000007924 injection Substances 0.000 claims description 18
- 239000000446 fuel Substances 0.000 claims description 15
- 238000001816 cooling Methods 0.000 claims description 10
- 230000004323 axial length Effects 0.000 claims description 6
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims description 4
- 238000007664 blowing Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 8
- 238000000889 atomisation Methods 0.000 abstract description 7
- 238000005496 tempering Methods 0.000 abstract description 3
- 230000002269 spontaneous effect Effects 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 22
- 239000007789 gas Substances 0.000 description 16
- 238000005516 engineering process Methods 0.000 description 7
- 239000000295 fuel oil Substances 0.000 description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910052799 carbon Inorganic materials 0.000 description 4
- 238000007789 sealing Methods 0.000 description 4
- 230000001276 controlling effect Effects 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 102100038238 Aromatic-L-amino-acid decarboxylase Human genes 0.000 description 2
- 101710151768 Aromatic-L-amino-acid decarboxylase Proteins 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000003134 recirculating effect Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 244000126211 Hericium coralloides Species 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
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- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 238000002663 nebulization Methods 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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Abstract
The utility model relates to the field of aircraft engine, and mainly relates to a rich oil direct-mixing partitioning combustion chamber. The rich oil direct-mixing partitioning combustion chamber comprises a diffuser (11), an outer cartridge receiver (12), an inner cartridge receiver (13), a nozzle (14), a combustion chamber head (15), a flame tube (16), a splashing disc (17) and a sparking plug (18), wherein main combustion holes (19) and mixing holes (20) are formed in the flame tube (16) according to requirements. The rich oil direct-mixing partitioning combustion chamber is characterized in that the combustion chamber head (15) consists of a precombustion stage (31) and a main combustion stage (30). A staged head manner is adopted, high uniformity and good atomization for local gas-oil ratio inside the combustion zone under any working condition can be ensured, so that the quality of outlet temperature field of the combustion chamber is improved. Through the design of a convergence throat passage, spontaneous combustion and tempering can be effectively prevented.
Description
Technical field
The utility model patent relates to aero-engine field, relates generally to directly mixed minute area combustion of a kind of rich oil.
Background technology
It is main application that aero-gas turbine just be take military from birth, along with fighter plane is more and more higher to the requirement of thrust-weight ratio by little Bypass Ratio Turbofan Engine, improving loop parameter is an important approach, so Ge great aero-engine manufacturer has carried out the research of military high oil-gas ratio main chamber.
It is benchmark that thrust-weight ratio 8 one-level fanjet main chambers be take in the works at IHPTET in the U.S., and the first rank main chamber outlet stagnation temperature improves 170K, and combustion chamber adjustable range increases by 20%, and burner inner liner volumetric heat intensity increases by 10%, OTDF and is not more than 0.25; Second stage combustor exit stagnation temperature improves 340K, and combustion chamber adjustable range increases by 100%, and burner inner liner volumetric heat intensity increases by 20%, OTDF and is not more than 0.15; Phase III combustor exit stagnation temperature improves 500K, and combustion chamber adjustable range increases by 150%, and burner inner liner volumetric heat intensity increases by 30%, OTDF and is not more than 0.10.The U.S. has completed the IHPTET requirement of three phases in the works at present, starts to carry out VAATE plan, the higher military turbofan engine of development thrust-weight ratio.For reply IHPTET plan and VAATE plan, the large main aero-engine company of the U.S. three: P & W, GE, AADC have carried out a series of high temperature rise combustor research for above-mentioned requirements.
P & W company mainly adopts RQL combustion technology, GE company mainly adopts standing vortex burning chamber technology, AADC company mainly adopts multiple cyclonic to organize combustion technology, by current analysis, the combustion technology of each company all can be applied to high temperature rise combustor design, but also has some problems.
The greatest problem that the high oil-gas ratio of high thrust-weight ratio aero-engine combustion chamber faces is how to solve the efficient contradiction without smoldering between burning under igniting, low operating mode stability and high operating mode.The military combustion chamber of tradition, because total oil-gas ratio is not high, can be controlled at head air inflow between 10%～25%, even when the extremely large operating mode of combustion chamber work, the excess air coefficient in primary zone, still more than 1.0, has guaranteed the efficient low burning of smoldering in primary zone.Along with the increase of combustion chamber gross gas-oil ratio, if designed according to the assignment of traffic scheme of former combuster, that will cause the excess air coefficient in primary zone to be less than 1, will cause like this primary zone to smolder and serious carbon distribution.For guarantee primary zone under high oil-gas ratio condition excess air coefficient more than 1, there are two methods, first can increase the air inflow of head, whole primary zone air inflow is guaranteed, or can keep under the condition of original head air inflow, increase primary zone air inlet, what the utility model adopted is the first string.The utility model adopts: rich oil is mixed grading combustion technology directly, the use of burning gas major part feeds from the head of combustion chamber, another fraction enters from primary holes, by controlling the excess air coefficient of head, guarantee that primary zone excess air coefficient is not less than the excess air coefficient on the border that smolders as seen, thereby guarantee the efficient low burning of smoldering in primary zone under high oil-gas ratio condition.Blending hole on burner inner liner is for regulating the outlet temperature field of combustion chamber.Head of combustion chamber is divided into pre-combustion grade and main combustion stage two-stage, adopts the combination of two kinds of different fuel injection modes and two kinds of combustion modes, to solve the contradiction between enlarged head air inflow and igniting and low operating mode stability.Pre-combustion grade starts when igniting, and while keeping little state, pre-combustion grade excess air coefficient, between 0.3-0.7, makes the good stability of burning, easily starting ignition.When engine operation during at large state two-stage oil circuit work simultaneously, the oil-poor lean direct injection pattern of pre-combustion grade, no matter guarantee how combustion chamber operating mode acutely changes, and it can form stable steady burning things which may cause a fire disaster; Main combustion stage is directly mixed pattern of rich oil, adopts rich oil directly to mix the acute variation that Combustion Energy adapts to ordnance engine main chamber operating mode preferably, makes combustion chamber have good response and followability; Adopt the head type of classification can guarantee under any operating mode in combustion zone that Local Oil-gas is than the high good atomization of the uniformity, thereby the outlet temperature field quality of assurance combustion chamber is improved.Adopt above-mentioned high temperature rise combustor, can guarantee under all duties in aeroengine combustor buring chamber, the whole excess air coefficient of combustion zone is all controlled on the excess air coefficient of smoldering as seen, by controlling pre-combustion grade, guarantee the smooth combustion of combustion chamber under each operating mode with mating of main combustion stage simultaneously, also can be by controlling the main combustion stage mist of oil uniformity, degree of mixing carry out the oil-gas ratio uniformity in control combustion district, thereby reach the performance requirement of wide stable operation range, exhaust is not smoldered, combustor exit temperature field quality is high aero-engine high temperature rise combustor.
Utility model content
The object of the utility model patent: provide a kind of rich oil that can take into account high oil-gas ratio main chamber igniting and low operating mode stability and the efficient low combustibility of smoldering of high operating mode directly to mix a minute area combustion.
The technical scheme of the utility model patent is:
A kind of rich oil is mixed minute area combustion directly, comprise diffuser 11, outer casing 12, interior casing 13, nozzle 14, head of combustion chamber 15, burner inner liner 16, splash pan 17 and sparking plug 18, on burner inner liner 16, there are as required primary holes 19 and blending hole 20, described head of combustion chamber 15 is comprised of pre-combustion grade 31 and main combustion stage 30, wherein:
Pre-combustion grade 31 consists of one-level axial swirler 32, converging portion 33, venturi 34, expansion segment 35 and auxiliary oil circuit nozzle 36, axial swirler blade 37 is installed in one-level axial swirler 32, one-level axial swirler 32, converging portion 33 and expansion segment 35 are connected successively, auxiliary oil circuit nozzle 36 is between 32 outlets of one-level axial swirler and venturi 34, apart from venturi 4010mm～15mm.
Main combustion stage 30 consists of the main combustion stage first order 43, the main combustion stage second level 52 and direct fuel injection formula nozzle 48, and the venturi that the main combustion stage first order 43 is formed by the inner edge 47 of one-level axial swirler 41, changeover portion 45, converging portion 46, pre-combustion grade expansion segment outer rim 44 and direct fuel injection formula nozzle 48 forms.In the main combustion stage first order 43 axial swirlers 41, axial swirler blade 42 is installed.The venturi that the main combustion stage second level 52 is formed by the inner edge 49 of one-level axial swirler 50, converging portion 53, converging portion inner edge 54 and axial swirler 50 forms.In 52 axial swirlers 50 of the main combustion stage second level, axial swirler blade 51 is installed.
Described axial swirler blade 37 setting angles are between 30 °～45 °, and blade quantity is between 10～16, and swirl strength is between 0.45～0.75.
The concentricity line X of described converging portion 33 angle is at 25 °～45 °, and line X angle that expansion segment 35 is concentricity is between 45 °～75 °.
Described pre-combustion grade axial length 39 is between 25mm～30mm, and main combustion stage axial length 60 is between 25mm～35mm.
Between 40 °～55 ° of described axial swirler blade 41 established angles, 18～24 of blade quantity sheets, swirl strength is between 0.6～0.8, between 40 °-55 ° of axial swirler blade 51 established angles, 18～32 of blade quantity sheets, swirl strength is between 0.5～0.8, and the average swirl strength of two-stage cyclones is between 0.6～0.8.
Described converging portion 46, the angle of direct fuel injection formula nozzle 48 and center line X is between 15 °～30 °.
The interior convergency of described converging portion 53 is between 30 °～45 °.
Described pre-combustion grade is provided with the cooling of diameter 0.5mm～1mm and blows down boundary-layer aperture 59, and head is provided with diameter 0.8mm～1.2mm and impacts cooling aperture 55.
Described blowing boundary-layer annular groove 57, groove width 1mm～1.5mm, groove depth 2.5mm～4mm; Boundary-layer annular groove bleed hole 56, aperture 0.8mm～1.2mm, 40～60 of hole counts.
Wide 1.5mm～the 2mm of contact boss 66 of annular groove pneumostop structure 61,2～4 of quantity; Expansion step-down annular groove 65 wide 2mm～3mm, groove depth 0.7mm～1.2mm, 2～4 of groove numbers.
The beneficial effect of the utility model patent is: pre-combustion grade of the present invention adopts lean direct injection pattern, can guarantee combustion chamber steady operation, can improve the efficiency of combustion of head again, its expansion segment design can not only solve head carbon deposit and cooling problem, can also guarantee to be formed with in pre-combustion grade downstream the oblique recirculating zone that helps igniting and flame stabilization; Main combustion stage adopts directly mixed combustion technology of multi-point injection rich oil, adapts to preferably the acute variation of ordnance engine main chamber operating mode, makes combustion chamber have good response and followability; Adopt the head type of classification can guarantee under any operating mode in combustion zone that Local Oil-gas is than the high good atomization of the uniformity, thereby the outlet temperature field quality of assurance combustion chamber is improved.The design of its convergence venturi can effectively prevent the appearance of spontaneous combustion and tempering phenomenon.
Accompanying drawing explanation
Fig. 1 is high temperature rise combustor schematic diagram;
Fig. 2 is the directly head construction scheme of mixed subregion of a kind of multi-point injection rich oil;
Fig. 3 is axial air ring slot sealing arrangement scheme;
Fig. 1 has described the relative position of combustion chamber diffuser, outer casing, interior casing, head, burner inner liner, splash pan, sparking plug, primary holes and blending hole; Fig. 2 has described the relative position of pre-combustion grade and main combustion stage and their detailed structure; Fig. 3 has described axial pneumatic annular groove sealing detailed structure, comprises contact boss, expansion step-down annular groove.
The specific embodiment
Below in conjunction with drawings and the specific embodiments, introduce in detail the utility model.
The utility model patent head scheme adopts two-stage oil circuit TAMDIM (the Twin Annular Multi-point Direct Injection Mixing) mixed combustion mode of center classification, when low operating mode, pre-combustion grade adopts rich oil directly to spray (Rich Direct Injection) combustion mode, this combustion mode is that the pre-combustion grade consisting of auxiliary oil circuit swirl atomizer or air atomizer spray nozzle and pre-combustion grade axial swirler realizes local rich oil, and this combustion system of organizing is between premixed combustion and diffusion combustion; When slow train or the above operating mode of slow train, main combustion stage adopts rich oil multi-point injection directly to mix (Multi-point Direct Injection Mixing) combustion mode, cause like this central combustion zone to work the effect of stabilizing the flame, around combustion zone is directly mixed combustion zone of rich oil, combustion zone excess air coefficient is controlled between 0.6～1, thereby controls the generation that head is smoldered.Main combustion stage is by two-stage axial swirler, and the composition of the simple nozzle between two-stage cyclones, relies on the air-flow shear action of two-stage cyclones, can make main combustion stage fuel oil obtain sufficient atomization and mixing.
Combustion chamber 10 comprises diffuser 11, outer casing 12, interior casing 13, nozzle 14, head 15, burner inner liner 16 splash pans 17 and sparking plug 18, has as required primary holes 19 and blending hole 20 on burner inner liner, or can cancel primary holes 19 retains blending hole 20.The working condition of combustion chamber is: air enters combustion chamber from diffuser 11, air over 40% 15 enters burner inner liner 16 from the head, 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 18 igniting, air and fuel oil mix combining combustion, from burner inner liner outlet 22, discharge high-temperature fuel gas.
Fig. 2 is TAMDIM high temperature rise combustor head 15 CONSTRUCTED SPECIFICATIONs, and head is comprised of pre-combustion grade 31 and main combustion stage 30.Head 15 air inflows account for greatly 50%～80% of combustion chamber 10 total tolerance, concrete air inflow number relevant with cooling air volume with the gross gas-oil ratio of combustion chamber, pre-combustion grade 31 air inflows account for greatly 5%～15% of the total air inflow in combustion chamber, and concrete air inflow is closely related with combustion chamber idling rating oil-gas ratio; Main combustion stage 30 air inflows account for greatly 30%～40% of the total air inflow in combustion chamber, and concrete air inflow is closely related with Combustion chamber design dotted state oil-gas ratio.If head air inflow is less, can retain as required burner inner liner 16 primary holes 19 and blending hole 20, if head air inflow is more, can remove primary holes 19 and blending hole 20, or only retain blending hole 20.
Pre-combustion grade 31 consists of one-level axial swirler 32, converging portion 33, pre-combustion grade expansion segment 35 and pre-combustion grade nozzle 36.Axial swirler 32 valid circulation area and venturi 34 areas determine pre-combustion grade 31 air mass flows jointly, axial swirler blade 37 setting angles are between 30 °～45 °, blade quantity is between 10～16, swirl strength is between 0.45～0.75, 45 ° of left and right of converging portion 33 angle, coaxial cyclone 32 valid circulation area of venturi 34 size are relevant, their common pre-combustion grade 31 air mass flows that determine, head carbon deposit and cooling problem have been considered in expansion segment 35 designs, can also guarantee to be formed with in pre-combustion grade 31 downstreams the oblique recirculating zone that helps igniting and flame stabilization, line X angle that expansion segment 35 is concentricity is between 45 °～75 °, the too little easy carbon deposit of angle, angle there will be too greatly cooling problem.So be designed with, blow down boundary-layer and Cooling Holes 59 on expansion segment 35.Pre-combustion grade nozzle 36 end faces and converging portion 33 exit end face distances 40 remain on OK range, make like this combustion system of pre-combustion grade between premixed combustion and diffusion combustion, form good secondary pneumatic nebulization, not only contribute to combustion chamber working stability, also contribute to reduce the pollutant of little operating mode.During design, also need to consider that pre-combustion grade venturi 34 diameters can not interfere by the fuel spray cone angle 38 under maximum duty mutually with pre-combustion grade nozzle 36.In all operating modes in combustion chamber, pre-combustion grade 31 all will be worked, and when starting and little state, pre-combustion grade is local pole fuel-rich combustion, and when large state, pre-combustion grade is fuel-rich combustion.。Pre-combustion grade axial length 39, between 25mm～30mm, on pre-combustion grade expansion segment, for preventing that thermic load is too high herein, has cooling aperture 59, aperture 0.5mm～1mm.It is short that pre-combustion grade cyclone axial length 39 will be tried one's best in the situation that meeting above-mentioned designing requirement, so that the dismounting of nozzle.
The main combustion stage first order 43 is comprised of with the venturi forming the inner edge 47 of one-level axial swirler 41, changeover portion 45, converging portion 46, pre-combustion grade expansion segment 35 outer rims 44 and direct fuel injection formula nozzle 48.The swirl strength of the main combustion stage first order 43 is in 0.6 left and right.The valid circulation area of axial swirler 41 has determined the air mass flow of the main combustion stage first order 43.Between 40 °～55 ° of axial swirler blade 41 established angles, 18～24 of blade quantities, swirl strength is between 0.6～0.8.Converging portion 46, the angle of direct fuel injection formula nozzle 48 and center line X, between 15 °～30 °, has guaranteed that main combustion stage first order exhaust stream is to consistent with the injection direction of direct projection fuel nozzle 48, improves combustion oil atomization.
The venturi that the main combustion stage second level 52 is formed by the inner edge 49 of one-level axial swirler 51, converging portion 53, converging portion inner edge 54 and axial swirler 51 forms.The swirl strength of the main combustion stage second level 52 is in 0.6～1 left and right.The valid circulation area of axial swirler 50 has determined the air mass flow of the main combustion stage second level 52.The valid circulation area of axial swirler 50 has determined the air mass flow of the main combustion stage second level 52.Between 40 °-55 ° of axial swirler blade 51 established angles, 18～32 of blade quantities, swirl strength is between 0.5～0.8.
The direction of rotation of the main combustion stage first order 43 cyclones 41 and the main combustion stage second level 52 cyclones 50 according to different designs can rotating Vortex also can counter-rotating.
The fuel oil of main combustion stage 30 feeds in main combustion stage 30 by simple nozzle 48 between the main combustion stage first order 43 and the main combustion stage second level 52.Simple nozzle 48 is the ratio of 1:1 or 2:1 at the quantity making progress in week and main combustion stage first order cyclone 41 blade quantities.The fuel oil of main combustion stage 30 feeds in simple nozzle 48 by fuel feeding ring cavity 58.
The inside and outside pressure reduction of simple nozzle 48 depending nozzles carries out primary atomization, the swirling eddy shear action that relies on again the cyclone 41 of the main combustion stage first order 43 and the cyclone of the main combustion stage second level 52 50 to produce, makes main combustion stage fuel oil obtain sufficient atomization and directly mixes with main combustion stage air.Main combustion stage 30 is just started working at slow train or the above operating mode of slow train, and its combustion system belongs to direct mixed combustion, in main combustion stage 30 downstreams, forms lift-off flame, and to improving head air-fuel mixture, improving head burning uniformity has very large effect.In order to prevent, in 52 downstreams, main combustion stage 30 second level, tempering occurs, in the outside of main combustion stage 30 second level 52 converging portion outer rims 54, have the blowing annular groove 57 that blows down boundary-layer and backrush whirlpool, the air inlet of annular groove enters by radial air inlet hole 56, and the air admission hole in hole 56 is entered by the impact opening 55 that impacts splash pan 17.Blow down annular groove 57 groove width 1mm～1.5mm, groove depth 2.5mm～4mm; Boundary-layer annular groove bleed hole 56, aperture 0.8mm～1.2mm, 40～60 of hole counts.
For improving the maintainability of head, pre-combustion grade 31 is integrated structures with the main combustion stage first order 43, main combustion stage nozzle 48, and 52 of the main combustion stage second level are independent structures, and both coaxially install.For guaranteeing both centering installations, reduce gas leakage and has adopted annular groove pneumostop structure 61.Annular groove pneumostop structure 61 consists of with annular groove 65 the contact boss 66, the expansion step-down that are positioned at working connection outside.The inner ring surface of the main combustion stage second level 52 (63) contacts with working connection outer ring surface 64 is concentric, for meeting the needs of assembling, adopt matched in clearance, can produce gas leakage herein, therefore adopt the principle of comb tooth sealing, the gas of axial flow, through the process of diffusion repeatedly of annular groove 65, by reducing axial pressure reduction, forms sealing.For guaranteeing that pre-combustion grade 31 and the main combustion stage first order 43, auxiliary jet 36, main combustion stage nozzle 48 are assemblings of integral structure, designed the guiding conical surface 62.
Wide 1.5mm～the 2mm of contact boss 66 of annular groove pneumostop structure 61,2～4 of quantity; Expansion step-down annular groove 65 wide 2mm～3mm, groove depth 0.7mm～1.2mm, 2～4 of groove numbers.
Claims (10)
1. a rich oil directly mixes a minute area combustion, comprise diffuser (11), outer casing (12), interior casing (13), nozzle (14), head of combustion chamber (15), burner inner liner (16), splash pan (17) and sparking plug (18), on burner inner liner (16), there are as required primary holes (19) and blending hole (20), it is characterized in that described head of combustion chamber (15) is comprised of pre-combustion grade (31) and main combustion stage (30), wherein:
Pre-combustion grade (31) consists of one-level axial swirler (32), converging portion (33), venturi (34), expansion segment (35) and auxiliary oil circuit nozzle (36), axial swirler blade (37) is installed in one-level axial swirler (32), one-level axial swirler (32), converging portion (33) and expansion segment (35) are connected successively, auxiliary oil circuit nozzle (36) is positioned between one-level axial swirler (32) outlet and venturi (34), apart from venturi (40) 10mm～15mm;
Main combustion stage (30) consists of the main combustion stage first order (43), the main combustion stage second level (52) and direct fuel injection formula nozzle (48), and the venturi that the main combustion stage first order (43) is formed by the inner edge (47) of one-level axial swirler (41), changeover portion (45), converging portion (46), pre-combustion grade expansion segment outer rim (44) and direct fuel injection formula nozzle (48) forms; Axial swirler blade (42) is installed in the main combustion stage first order (43) axial swirler (41); The venturi that the main combustion stage second level (52) is formed by the inner edge (49) of one-level axial swirler (50), converging portion (53), converging portion inner edge (54) and axial swirler (50) forms; Axial swirler blade (51) is installed in the main combustion stage second level (52) axial swirler (50).
2. a kind of rich oil according to claim 1 directly mixes a minute area combustion, it is characterized in that, described axial swirler blade (37) setting angle is between 30 °～45 °, and blade quantity is between 10～16, and swirl strength is between 0.45～0.75.
3. a kind of rich oil according to claim 1 directly mixes a minute area combustion, it is characterized in that, the concentricity line of described converging portion (33) (X) angle is at 25 °～45 °, and the concentricity line of expansion segment (35) (X) angle is between 45 °～75 °.
4. a kind of rich oil according to claim 1 directly mixes a minute area combustion, it is characterized in that, described pre-combustion grade axial length (39) is between 25mm～30mm, and main combustion stage axial length (60) is between 25mm～35mm.
5. a kind of rich oil according to claim 1 directly mixes a minute area combustion, it is characterized in that, between 40 °～55 ° of described axial swirler blade (41) established angles, 18～24 of blade quantity sheets, swirl strength between 0.6～0.8, between 40 °-55 ° of axial swirler blade (51) established angles, 18～32 of blade quantity sheets, swirl strength is between 0.5～0.8, and the average swirl strength of two-stage cyclones is between 0.6～0.8.
6. a kind of rich oil according to claim 1 directly mixes a minute area combustion, it is characterized in that, and described converging portion (46), the angle of direct fuel injection formula nozzle (48) and center line (X) is between 15 °～30 °.
7. a kind of rich oil according to claim 1 directly mixes a minute area combustion, it is characterized in that, the interior convergency of described converging portion (53) is between 30 °～45 °.
8. according to a kind of rich oil one of claim 1～7 Suo Shu, directly mix a minute area combustion, it is characterized in that, described pre-combustion grade is provided with the cooling of diameter 0.5mm～1mm and blows down boundary-layer aperture (59), and head is provided with diameter 0.8mm～1.2mm and impacts cooling aperture (55).
9. a kind of rich oil according to claim 8 directly mixes a minute area combustion, it is characterized in that described blowing boundary-layer annular groove (57), groove width 1mm～1.5mm, groove depth 2.5mm～4mm; Boundary-layer annular groove bleed hole (56), aperture 0.8mm～1.2mm, 40～60 of hole counts.
10. a kind of rich oil according to claim 9 directly mixes a minute area combustion, it is characterized in that the wide 1.5mm～2mm of contact boss (66) of annular groove pneumostop structure (61), 2～4 of quantity; Wide 2mm～the 3mm of expansion step-down annular groove (65), groove depth 0.7mm～1.2mm, 2～4 of groove numbers.
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| CN201320809412.0U CN203757766U (en) | 2013-12-10 | 2013-12-10 | Rich oil direct-mixing partitioning combustion chamber |
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| CN108561898A (en) * | 2017-12-27 | 2018-09-21 | 中国航发四川燃气涡轮研究院 | A kind of coaxial subregion high temperature rise combustor head |
| CN111780161A (en) * | 2019-04-04 | 2020-10-16 | 中国航发湖南动力机械研究所 | Turbine engine combustion chamber |
| CN111878849A (en) * | 2020-07-08 | 2020-11-03 | 西北工业大学 | Double-vortex-control graded-partition combustion chamber head |
| CN112503572A (en) * | 2020-12-01 | 2021-03-16 | 中国航发沈阳发动机研究所 | Combustion chamber with oscillating combustion detection and inhibition functions |
| CN113027615A (en) * | 2021-04-14 | 2021-06-25 | 中国航空发动机研究院 | Engine using axial electrode to control combustion |
| CN114076324A (en) * | 2022-01-19 | 2022-02-22 | 中国航发四川燃气涡轮研究院 | Combustion chamber capable of automatically adjusting mixed air intake |
| CN114151826A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Variable geometry combustion chamber |
| CN115355526A (en) * | 2022-08-25 | 2022-11-18 | 江西中发天信航空发动机科技有限公司 | Semi-closed precombustion chamber structure of aero-engine and combustion chamber thereof |
-
2013
- 2013-12-10 CN CN201320809412.0U patent/CN203757766U/en not_active Expired - Lifetime
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| CN104949152A (en) * | 2015-05-25 | 2015-09-30 | 沈阳航空航天大学 | LNG and aviation kerosene dual fuel combustor of aero-gas turbine |
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| CN111878849A (en) * | 2020-07-08 | 2020-11-03 | 西北工业大学 | Double-vortex-control graded-partition combustion chamber head |
| CN111878849B (en) * | 2020-07-08 | 2023-09-26 | 西北工业大学 | Double-vortex control grading partition combustion chamber head |
| CN112503572A (en) * | 2020-12-01 | 2021-03-16 | 中国航发沈阳发动机研究所 | Combustion chamber with oscillating combustion detection and inhibition functions |
| CN113027615A (en) * | 2021-04-14 | 2021-06-25 | 中国航空发动机研究院 | Engine using axial electrode to control combustion |
| CN113027615B (en) * | 2021-04-14 | 2022-11-04 | 中国航空发动机研究院 | Engine using axial electrode to control combustion |
| CN114151826A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Variable geometry combustion chamber |
| CN114076324A (en) * | 2022-01-19 | 2022-02-22 | 中国航发四川燃气涡轮研究院 | Combustion chamber capable of automatically adjusting mixed air intake |
| CN115355526A (en) * | 2022-08-25 | 2022-11-18 | 江西中发天信航空发动机科技有限公司 | Semi-closed precombustion chamber structure of aero-engine and combustion chamber thereof |
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Address after: No. 999, Xuefu Road, Xindu, Chengdu, Sichuan 610500 Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 operation monitoring department, Jiangyou 305 mailbox, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |
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