CN111174233B - Central-grading lean-oil premixed low-pollution combustion chamber - Google Patents
Central-grading lean-oil premixed low-pollution combustion chamber Download PDFInfo
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- CN111174233B CN111174233B CN202010034769.0A CN202010034769A CN111174233B CN 111174233 B CN111174233 B CN 111174233B CN 202010034769 A CN202010034769 A CN 202010034769A CN 111174233 B CN111174233 B CN 111174233B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 166
- 239000003921 oil Substances 0.000 claims description 54
- 238000002347 injection Methods 0.000 claims description 43
- 239000007924 injection Substances 0.000 claims description 43
- 239000000446 fuel Substances 0.000 claims description 24
- 238000001816 cooling Methods 0.000 claims description 21
- 239000000295 fuel oil Substances 0.000 claims description 17
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims description 13
- 239000007788 liquid Substances 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 4
- 238000000889 atomisation Methods 0.000 abstract description 12
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- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 2
- 229910002091 carbon monoxide Inorganic materials 0.000 description 2
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
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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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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Abstract
本发明涉及一种中心分级贫油预混低污染燃烧室，值班级位于中心，由成膜式空气雾化喷嘴和两级旋流器组成，两级旋流器在下游形成合理的中心回流区，另外油膜在两级旋流的剪切作用下改善了雾化效果，有效改善了小工况下的火焰稳定特性，并拓宽了值班级的工作边界。主燃级由多个带环形空气的直射式喷嘴和主燃级旋流器组成，环形空气有效的控制了射流在全工况范围内具有合理的穿透深度，旋流空气与多个射流在主燃级平直通道和收敛通道中进行预先混和，形成的均匀可燃混气在燃烧室内进行预混燃烧，能显著降低燃烧室大工况下的污染排放，并有效避免自燃问题。因此，本发明专利能有效解决小工况下火焰稳定和大工况下污染排放问题。
The invention relates to a centrally graded lean-oil premixed low-polluting combustion chamber. The duty stage is located in the center and is composed of a film-forming air atomizing nozzle and a two-stage cyclone. The two-stage cyclone forms a reasonable central recirculation zone downstream. In addition, the oil film improves the atomization effect under the shearing action of the two-stage swirl, effectively improves the flame stability characteristics under small working conditions, and broadens the working boundary of the duty class. The main combustion stage is composed of multiple direct jet nozzles with annular air and main combustion stage swirlers. The annular air effectively controls the jet to have a reasonable penetration depth in the full range of working conditions. The main combustion stage is pre-mixed in the straight channel and the convergent channel, and the formed uniform combustible gas mixture is pre-mixed and burned in the combustion chamber, which can significantly reduce the pollution emission under large working conditions of the combustion chamber and effectively avoid the problem of spontaneous combustion. Therefore, the patent of the present invention can effectively solve the problems of flame stability under small working conditions and pollution emission under large working conditions.
Description
Technical Field
The invention belongs to the field of low-pollution combustors of gas turbines, and relates to a center-graded lean oil premixed low-pollution combustor.
Background
Compared with the ground pollution emission, the pollution emission of the aircraft engine mainly has two characteristics: the method has the characteristics of concentration and locality, and is mainly concentrated on large airports, test beds of aviation factories, laboratories of research units and nearby areas. The aeroengine has large flow, so the concentration of pollutants in local areas is very high; and the civil aviation engine is the main cause of high-altitude air pollution. Therefore, the CAEP (environmental protection agency) of the national civil aviation organization formulated a series of emission standards from 1980 to the beginning for carbon monoxide CO, unburned hydrocarbons UHC and nitrogen oxides NO of civil aviation enginesXStrict regulations are made on the emission of micro-particles and soot, and the civil aviation engine has to meet the pollution emission requirement of the international civil aviation organization ICAO to obtain airworthiness certification. In order to meet the increasingly strict requirements on pollutant emission, the development of environment-friendly low-pollution engines becomes the development trend of civil aircraft engines,the source of the engine pollutants is in the combustion chamber, so the development of low-pollution combustion technology is very critical.
At present, the common low-pollution combustion technology of the aero-engine is mainly divided into three types: rich combustion-rapid quenching-lean combustion RQL, lean premixed pre-evaporative combustion LPP and lean direct injection combustion LDI. The LPP and LDI combustion technologies have greater potential than RQL in reducing pollutant emissions due to the lean mode of combustion. Aiming at the LPP combustion organization technology, main combustion stages of the schemes such as patents US8607575, US8171735 and US6363726 applied by foreign GE companies all adopt lean oil premixing and pre-evaporation technology, and the domestic units such as North aviation and industry and Heat institute also provide low-pollution combustion chamber schemes with main combustion stages adopting lean oil premixing. The schemes are greatly improved in the aspect of reducing emission, and have some defects, on one hand, the duty stage adopts a single-oil-way centrifugal nozzle to match single-stage rotational flow, so that the duty stage working condition range is narrow, the main combustion stage is opened earlier, and the combustion efficiency is lower; on the other hand, the main combustion level fuel oil is injected by adopting a single-phase direct-injection air atomizing nozzle, the sensitivity of jet flow depth along with the change of working conditions is too large, the penetration depth is too small under small working conditions, atomization is easy to wet the side wall surface of the injection, the atomization is poor, the penetration depth is too large under large working conditions, the outer wall surface of the premixing section is easy to wet, the spontaneous combustion phenomenon is easy to generate in the premixing section under large working conditions, and the problems of pollution emission increase and the like exist. Therefore, a patent CN201710608804.3 applied by the northwest industrial university combustion team in 2017 designs a low-emission combustion chamber based on an LDI concept, wherein a duty stage adopts a single-stage cyclone matched with a single-oil-way centrifugal nozzle to realize duty diffusion combustion, a main combustion stage adopts a single-stage cyclone matched with a plurality of coaxial downstream air atomizing nozzles with annular air to realize main combustion stage diffusion combustion, and compared with premixed combustion, the diffusion combustion has the advantages that the problems of spontaneous combustion, tempering and the like can be effectively avoided.
Disclosure of Invention
Technical problem to be solved
In order to avoid the defects of the prior art, the invention provides a center-graded lean premixed low-pollution combustion chamber, wherein a film-forming air atomizing nozzle is matched with a two-stage swirler in an on-duty stage, and a direct injection nozzle with annular air is matched with a single-stage swirler in a main combustion stage. On one hand, the flame stability under small working conditions is improved, and the working boundary of a class is widened; and on the other hand, the problem that the sensitivity of the penetration depth of the main oil along with the working condition is too large is solved.
The invention adopts the center grading and zoning combustion technology, and effectively solves the problems of flame stability under small working conditions and pollution discharge under large working conditions. Under a small working condition, only the duty level works, the duty level adopts the film-forming type air atomizing nozzle to be matched with the two-stage swirler to realize diffusion combustion, the flame stability under the small working condition is improved by enhancing the fuel oil atomization under the small working condition, and the working boundary of the duty level is effectively widened. Under the big operating mode, the class and the main level of burning work simultaneously, the main level of burning adopts the direct injection formula air atomizing nozzle of a plurality of band ring shape air to match single-stage swirler and realizes that lean oil mixes the burning in advance, can effectively solve the too big problem of main oil penetration depth along with the operating mode change sensitivity in the traditional combustion chamber that mixes in advance, guarantees that the main level of burning has good atomizing and oil-gas mixture characteristic in the full operating mode within range, can show the pollution emission volume that reduces under the big operating mode to avoid the production of spontaneous combustion problem.
Technical scheme
A central grading lean oil premixing low pollution combustion chamber comprises a diffuser, a combustion chamber head, a head mounting end wall, a flame tube and a combustion chamber casing; the head part of the combustion chamber consists of an on-duty stage and a main combustion stage and adopts a concentric circle type arrangement mode; the method is characterized in that: the device comprises a main combustion stage 9, an overtime stage 8, a main oil injection device and a main combustion stage swirler, wherein the overtime stage 8 and the main combustion stage 9 are of an integrated structure and comprise film-forming air atomizing nozzles and two-stage swirlers of the overtime stage 8 and the main combustion stage swirler; the primary swirler of class 8 is positioned at the center, the outer ring of the primary swirler is an on-duty oil collecting ring 25, the outer ring of the oil collecting ring 25 is a secondary swirler of class 8, the outer ring of the secondary swirler of class 8 is a main combustion oil collecting ring 41, and the outer ring of the main combustion oil collecting ring 41 is a main combustion swirler; the duty oil collecting ring 25 is provided with a duty progressive oil pipe 15; the main combustion stage fuel oil pipe 31 is arranged on the main combustion stage oil collecting ring 41; a plurality of direct injection nozzles 37 are arranged between the main combustion stage oil collecting ring 41 and the main combustion stage swirler; the direct nozzle 37 includes an annular atomizing air channel support rib 48, an annular air channel 51 and a direct nozzle inner channel 52; a direct injection type nozzle inner channel 52 is arranged at the center of the cylindrical structure, one end of the direct injection type nozzle inner channel is a direct injection type nozzle inlet 50, and the other end of the direct injection type nozzle inner channel is a fuel injection hole 49; circular steps are arranged at the two ends, and annular atomizing air channel supporting ribs 48 are arranged between the circular steps; an annular air channel 51 is arranged on a step at one end of the fuel injection hole 49; the outlet of the main combustion stage swirler is provided with a cooling air and fuel oil atomization air channel baffle 39, and the baffle is provided with a plurality of tangential cooling small holes 38; outlets of the two-stage swirler of the class 8 and the main combustion stage swirler are flush, and an air outlet channel is an annular convergent channel; the vane rotating directions of the on-duty 8-stage cyclones are opposite, and the rotating directions of the main combustion stage cyclones and the on-duty two-stage cyclones are the same.
The first-stage swirler vane 11 of class 8 adopts axial flow type straight vanes, the swirl angle is 20-50 degrees, and the number of the vanes is 6-20.
The blades 20 of class 8 adopt axial flow straight blades, the rotational flow angle is 30-60 degrees, and the number of the blades is 6-20.
The air flow ratio of the two-stage cyclone of the class 8 is 0.5-1.2.
The included angle between the convergent side of the inner wall 14 of the film-forming air atomizing nozzle and the convergent side of the secondary cyclone outlet baffle 21 and the axis is 30-60 degrees.
The ring height of the film-forming air atomizing nozzle channel 26 is 0.05-0.5 mm, and the length is 0.5-25 mm.
The swirl angle of the blades 35 of the main combustion stage swirler is 40-75 degrees, and the number of the blades is 6-20.
The included angle between the convergent side of the outer wall 36 of the main combustion stage swirler and the axis is 0-45 degrees.
The included angle between the fuel oil jet hole 49 in the direct injection type nozzle 37 and the axial direction is-75 degrees, the diameter of the nozzle is 0.1-0.8 mm, and the length of the internal channel 52 of the direct injection type nozzle is 10-40 times of the diameter of the nozzle.
The ratio of the flow rates of annular air and fuel oil in the direct injection nozzle 37, i.e., the gas-liquid ratio, is 1 to 5.
Advantageous effects
The invention provides a center-graded lean oil premixed low-pollution combustion chamber, wherein the head part of the combustion chamber consists of an on-duty stage and a main combustion stage and adopts a concentric circle type arrangement mode; the on-duty and main combustion stages are integrated structures and comprise an on-duty film-forming air atomizing nozzle, a two-stage swirler, a main fuel injection device and a main combustion stage swirler; the vane rotating directions of the two-stage cyclones on duty are opposite, and the main combustion stage cyclones and the two-stage cyclones on duty have the same rotating direction. The duty level is positioned in the center and consists of a film-forming air atomizing nozzle and two stages of cyclones, the two stages of cyclones form a reasonable central reflux area at the downstream, and in addition, an oil film improves the atomizing effect under the shearing action of the two stages of cyclones. Under a small working condition, the duty stage works independently, the duty stage adopts a film-forming air atomizing nozzle to match with the two-stage swirler to realize non-premixed combustion, and the reasonable backflow region structure and the richer local equivalence ratio are favorable for widening the flame stabilization boundary of the combustion chamber; effectively improves the flame stability under small working conditions and widens the working boundary of duty level. The main combustion stage is composed of a plurality of direct injection nozzles with annular air and a main combustion stage swirler, the annular air effectively controls the jet flow to have reasonable penetration depth in the full working condition range, the swirl air and the jet flows are premixed in a straight channel and a convergent channel of the main combustion stage, and formed uniform combustible mixed gas is premixed and combusted in the combustion chamber. Along with the increase of operating mode, the class and the main stage of burning work simultaneously, the main stage of burning adopts the direct injection formula air atomizing nozzle of a plurality of band ring air to match single-stage swirler and realizes lean oil and mixes burning in advance, and the penetration depth of main oil in mixing the ring cavity in advance can effectively be controlled to the ring air to improve and mix the effect in advance, even oil-gas mixture is favorable to eliminating the high temperature hot spot in the combustion chamber this moment, can show the pollution emission volume under the big operating mode of reduction.
Compared with the prior art, the invention has the following advantages:
1) the combustion concept of grading and partitioning is adopted, the head part of the combustion chamber is an on-duty stage and a main combustion stage, the on-duty stage adopts double-cyclone diffusion combustion, the main combustion stage adopts premixed combustion, the stable working boundary of the combustion chamber can be effectively widened, and the pollution emission under large working conditions is remarkably reduced.
2) The film-forming air atomizing nozzle is matched with the two-stage swirler in class, fuel is atomized and oil-gas mixed under the shearing action of two-stage swirling air with opposite swirling directions, and the flame stabilization boundary is effectively widened in a diffusion combustion mode.
3) The main combustion grade fuel adopts the direct injection type nozzle with annular air, can ensure that the main fuel has reasonable penetration depth in a wide working condition range, effectively solves the problems of insufficient penetration depth under small working conditions and overlarge penetration depth under large working conditions of the traditional direct injection type nozzle, and avoids the problem of spontaneous combustion caused by wetting the inner side and the outer side of the premixing section.
The reasonable main combustion stage convergence channel enables combustible mixed gas to flow at the outlet of the main combustion stage in an accelerated manner, and backfire can be effectively avoided.
Drawings
FIG. 1 is a three-dimensional isometric view of an all-annular combustor of the present invention.
FIG. 2 is a cross-sectional view of the full-ring combustor configuration of the present invention.
FIG. 3 is a sectional view showing the structure of a head part of a combustion chamber according to the present invention.
FIG. 4 is a front view and a cross-sectional view of a combustor head class configuration of the present invention.
FIG. 5 is a front view and a cross-sectional view of a combustor head main stage configuration of the present invention.
FIG. 6 is a schematic view and sectional view of a direct injection nozzle for a combustor head primary stage of the present invention.
In the figure: 1-diffuser, 2-combustion chamber outer casing, 3-combustion chamber inner casing, 4-flame tube outer wall, 5-flame tube inner wall, 6-combustion chamber head, 7-head installation end wall, 8-duty stage, 9-main combustion stage, 10-primary cyclone inner hub, 11-primary cyclone blade, 12-duty oil collecting ring inner wall, 13-central cone, 14-film forming type air atomizing nozzle inner wall, 15-duty progressive oil pipe, 16-duty fuel inlet, 17-film forming type air atomizing nozzle outer wall, 18-duty cyclone oil collecting ring outer wall, 19-secondary cyclone blade, 20-secondary cyclone outer wall, 21-secondary cyclone outlet baffle, 22-primary cyclone air inlet, 23-primary cyclone air channel, 24-a first-stage cyclone air annular convergent channel, 25-an on-duty stage oil collecting ring, 26-a film-forming air atomizing nozzle channel, 27-a second-stage cyclone air inlet, 28-a second-stage cyclone air channel, 29-a second-stage cyclone air annular straight channel, 30-a second-stage cyclone air annular convergent channel, 31-a main combustion stage fuel pipe, 32-a main combustion stage fuel inlet, 33-a main combustion stage oil collecting ring outer wall, 34-a main combustion stage swirler inner wall, 35-a main combustion stage swirler vane, 36-a main combustion stage swirler outer wall, 37-a direct injection nozzle, 38-a tangential cooling pore, 39-a cooling air and fuel oil atomizing air channel baffle, 40-a cooling air and fuel oil atomizing air channel support rib, 41-a main combustion stage oil collecting ring, 42-a cooling air and fuel oil atomizing air inlet, 43-cooling air and fuel atomizing air channel, 44-main combustion stage swirl air inlet, 45-main combustion stage swirl air channel, 46-main combustion stage air annular straight channel, 47-main combustion stage air annular convergent channel, 48-annular atomizing air channel support rib, 49-fuel injection hole, 50-direct injection nozzle inlet, 51-annular air channel, 52-direct injection nozzle internal channel.
Detailed Description
The invention will now be further described with reference to the following examples and drawings:
as shown in fig. 1-2, the central staged lean premixed low pollution combustor of the present embodiment mainly includes a diffuser 1, an outer casing 2 of a combustor, an inner casing 3 of the combustor, an outer wall 4 of a liner, an inner wall 5 of the liner, a head 6 of the combustor, and a head-mounted end wall 7. The combustion chamber head 6 is uniformly arranged on the head mounting end wall 7 along the circumferential direction; the combustor head 6 consists of an on-duty stage 8 and a main combustion stage 9, the on-duty stage 8 and the main combustion stage 9 are arranged in a concentric circle mode, the on-duty stage 8 is located in the center, and the main combustion stage 9 is located on the periphery.
The outer casing 2 and the inner casing 3 of the combustion chamber are fixed with the diffuser 1 through welding, the outer wall 4 and the inner wall 5 of the flame tube are connected with the head mounting end wall 7, and the head 6 of the combustion chamber is mounted on the head mounting end wall 7 through welding. The diffuser 1 divides the high-speed airflow flowing out of the compressor into three paths after speed reduction and diffusion, one path enters a combustion area formed by the outer wall 4 of the flame tube and the inner wall 5 of the flame tube through the head of the combustion chamber, the other path flows to an outer annular cavity formed by the outer casing 2 of the combustion chamber and the outer wall 4 of the flame tube, and the other path flows to an inner annular cavity formed by the inner casing 3 of the combustion chamber and the inner wall 5 of the flame tube. For an advanced gas turbine combustor, combustion air completely enters from the head of the combustor and accounts for 65% -80% of the total air quantity, air flowing into inner and outer annular cavities is mainly used for cooling and mixing of a flame tube, cooling air accounts for 20% -25% of the total air quantity, and mixed air accounts for 0% -10%.
As shown in FIG. 3, the embodiment of the invention adopts a central staged combustion organization mode to divide the head part of the combustion chamber into an on-duty stage 8 and a main combustion stage 9, wherein the on-duty stage 8 is positioned at the center, the main combustion stage 9 is positioned at the periphery, and the on-duty air amount accounts for 20-40% of the total combustion air amount. Under a small working condition, the duty class works independently, the local equivalence ratio of the time class 8 is 1-1.5, and flame stability under the small working condition is guaranteed by rich oil combustion. Along with the continuous improvement of operating mode, the class 8 of on-duty and the main grade 9 of burning work simultaneously, the average equivalence ratio of whole head is 0.5 ~ 1 this moment, guarantees when the class flame on-duty is stable, and whole combustion chamber has very low polluting emission.
As shown in fig. 4, the class 8 is composed of a primary swirler inner hub 10, primary swirler vanes 11, a duty oil collecting ring inner wall 12, a center cone 13, a film-forming air atomizing nozzle inner wall 14, a duty progressive oil pipe 15, a film-forming air atomizing nozzle outer wall 17, a duty oil collecting ring outer wall 18, secondary swirler vanes 19, a secondary swirler outer wall 20 and a secondary swirler outlet baffle 21, which are all connected by welding. Class 8 air is divided into two paths, one path enters a primary swirl air channel 23 through a primary swirl air inlet 22 and generates rotational motion, and then develops sufficiently in a primary swirl air annular converging channel 24 to eliminate wakes generated by the primary swirler vanes 11. The other path enters the secondary swirl air passage 28 via the secondary swirl air inlet 27 and imparts a swirling motion which then develops sufficiently in the secondary swirl air annular flat passage 29 and the secondary swirl air annular converging passage 30 to smooth out the wake created by the secondary swirler vanes 19. The fuel enters the duty oil collecting ring 25 from the duty fuel inlet 16 through the duty progressive oil pipe 15, then fully develops in the film-forming air atomizing nozzle channel 26, and finally forms an annular oil film at the outlet. The oil film is atomized and mixed under the shearing action of the two-stage swirling flow, and then the swirling air forms a central backflow zone at the downstream for stabilizing the flame. The blades 11 of the primary cyclone adopt axial flow straight blades, the rotational flow angle is 20-50 degrees, and the number of the blades is 6-20. The secondary cyclone blades 19 adopt axial flow straight blades, the rotational flow angle is 30-60 degrees, and the number of the blades is 6-20. The two-stage cyclones have opposite rotation directions, and the air flow ratio of the two-stage cyclones is 0.5-1.2. The included angle between the convergent side of the inner wall 14 of the film-forming air atomizing nozzle and the convergent side of the outlet baffle 21 of the secondary cyclone and the axis is 30-60 degrees. The ring height of the film-forming air atomizing nozzle channel 26 is 0.05-0.5 mm, and the length is 0.5-25 mm.
As shown in FIGS. 5-6, the main stage 9 is comprised of a main stage fuel pipe 31, a main stage oil collection ring outer wall 33, a main stage swirler inner wall 34, main stage swirler vanes 35, a main stage swirler outer wall 36, a direct injection nozzle 37, tangential cooling apertures 38, a cooling air and fuel atomization air passage baffle 39, and cooling air and fuel atomization air passage support ribs 40. The direct injection nozzle 37 is composed of a fuel injection hole 49 and an annular atomizing air passage support rib 48. The inner primary stage swirler wall 34, the primary stage swirler vanes 35, the outer primary stage swirler wall 36, and the cooling air and fuel atomization air passage baffle 39 are connected by welding. The inner primary stage swirler wall 34 is connected to the outer primary stage oil collector ring wall 33 by cooling air and fuel atomization air passage support ribs 40. The majority of the air from the main stage 9 enters the main stage swirl air passage 45 through the main stage swirl air inlet 44 and imparts a swirling motion that then develops sufficiently in the main stage annular flat passage 46 and the main stage annular converging passage 47 to smooth the wake created by the main stage swirler vanes 35. A small portion of the air in the main combustion stage 9 enters the cooling air and fuel atomization air passage 43 through the cooling air and fuel atomization air inlet 42. The main combustion stage fuel oil atomized air enters the annular air channel 51 and is coated with liquid column jet flow to be sprayed out together, and the reasonable penetration depth of main oil in a wide working condition range is guaranteed. Cooling air enters the cooling apertures 38 and this air portion is used to cool the cooling air and fuel atomization air passage baffle 39 and prevent hot gases from burning off the combustion chamber head. The main combustion level fuel oil enters the main combustion level oil collecting ring 41 through the main combustion level oil pipe 31, then enters the direct injection nozzle inner channel 52 from the direct injection nozzle inlet 50, finally forms liquid column jet flow with annular air to be injected into the main combustion level rotational flow air channel 45, the liquid column jet flow is pre-mixed in the main combustion level air annular straight channel 46 and the main combustion level air annular convergent channel 47 under the action of rotational flow air, and uniformly mixed combustible mixed gas flows at the main combustion level outlet in an accelerated mode, so that the occurrence of backfire is effectively avoided. The main combustion stage swirler and the duty stage secondary swirler have the same rotating direction. The main combustion stage swirler vanes 35 are axial flow straight vanes, the swirl angle is 40-75 degrees, and the number of the vanes is 6-20. The included angle between the convergent side of the outer wall 36 of the main combustion stage swirler and the axis is 0-45 degrees. The included angle between the fuel oil jet hole 49 in the direct injection type nozzle 37 and the axial direction is-75 degrees, the diameter of the nozzle is 0.1-0.8 mm, and the length of the internal channel of the nozzle is 10-40 times of the diameter of the nozzle. The ratio of the flow rates of the annular air and the fuel oil (gas-liquid ratio) in the direct injection nozzle 37 is 1 to 5.
The working process of the invention is as follows:
the invention designs a central grading lean oil premixing low-pollution combustion chamber which can effectively inhibit the generation of pollutants (carbon monoxide, unburned hydrocarbon, nitrogen oxide, micro-particles and carbon smoke) and realize low-emission combustion. In the combustion chamber, high-speed airflow flowing out of the compressor is subjected to speed reduction and diffusion by the diffuser and then is divided into three paths, the three paths enter the inner ring cavity, the outer ring cavity and the head of the combustion chamber respectively, and combustion air completely enters from the head. Based on the concept of central staged zoned combustion, the head of the combustion chamber is divided into a value class and a main combustion class. Under a small working condition, only the duty stage works, the duty stage adopts the film-forming air atomizing nozzle to match with the two-stage swirler to realize non-premixed combustion, and the richer local equivalence ratio is favorable for the flame stability of the combustion chamber. Along with the increase of operating mode, the class and the main stage of burning work simultaneously, the main stage of burning adopts the direct injection formula air atomizing nozzle of a plurality of band ring air to match single-stage swirler and realizes lean oil and mixes burning in advance, and annular air can effectively control the penetration depth of main oil in mixing the ring cavity in advance, improves and mixes the effect in advance, and even oil-gas mixture is favorable to eliminating the high temperature hot spot in the combustion chamber this moment, can show the pollution emission volume under the big operating mode of reduction.
The head structure of the central grading lean oil premixing combustion chamber effectively solves the contradiction between flame stability and pollution emission under the wide working condition, ensures that the combustion chamber has a wide stable working boundary, and can obviously reduce the pollution emission.
Claims (8)
1. A central grading lean oil premixing low pollution combustion chamber comprises a diffuser, a combustion chamber head, a head mounting end wall, a flame tube and a combustion chamber casing; the head part of the combustion chamber consists of an on-duty stage and a main combustion stage and adopts a concentric circle type arrangement mode; the method is characterized in that: the device comprises a main combustion stage (9), an overtime stage (8), a secondary combustion stage (8), a film-forming air atomizing nozzle, a primary oil injection device and a primary combustion stage swirler, wherein the overtime stage (8) and the primary combustion stage (9) are of an integrated structure and comprise film-forming air atomizing nozzles and two-stage swirlers of the overtime stage (8); the primary swirler of the class (8) is positioned at the center, the outer circle of the primary swirler is an on-duty oil collecting ring (25), the outer circle of the on-duty oil collecting ring (25) is a secondary swirler of the class (8), the outer circle of the secondary swirler of the class (8) is a main combustion oil collecting ring (41), and the outer circle of the main combustion oil collecting ring (41) is a main combustion swirler; the duty grade oil collecting ring (25) is provided with a duty grade oil pipe (15); the main combustion stage fuel oil pipe (31) is arranged on the main combustion stage oil collecting ring (41); a plurality of direct injection nozzles (37) are arranged between the main combustion stage oil collecting ring (41) and the main combustion stage swirler; the direct nozzle (37) comprising an annular atomizing air channel support rib (48), an annular air channel (51) and a direct nozzle inner channel (52); a direct injection type nozzle inner channel (52) is arranged at the center of the cylindrical structure, one end of the cylindrical structure is a direct injection type nozzle inlet (50), and the other end of the cylindrical structure is a fuel injection hole (49); circular steps are arranged at the two ends, and annular atomizing air channel supporting ribs 48 are arranged between the circular steps; an annular air channel (51) is arranged on a step at one end of the fuel injection hole (49); a cooling air and fuel oil atomizing air channel baffle plate (39) is arranged between the secondary cyclone outlet baffle plate (21) and the inner wall (34) of the main combustion stage cyclone, and a plurality of tangential cooling small holes (38) are formed in the baffle plate; outlets of the two-stage cyclone of the overtime stage (8) and the main combustion stage cyclone are flush, and an air outlet channel is an annular convergent channel; the vane rotating directions of the two stages of cyclones on duty (8) are opposite, and the rotating directions of the main combustion stage cyclone and the two stages of cyclones on duty are the same;
axial flow type straight blades are adopted as the first-stage swirler blades (11) of the class (8), the swirling angle is 20-50 degrees, and the number of the blades is 6-20;
the secondary cyclone blades of the class (8) adopt axial flow straight blades, the rotational flow angle is 30-60 degrees, and the number of the blades is 6-20.
2. The center staged lean premixed low pollution combustor as claimed in claim 1, wherein: the air flow ratio of the two-stage cyclone of the overtime (8) is 0.5-1.2.
3. The center staged lean premixed low pollution combustor as claimed in claim 1, wherein: the included angle between the convergent side of the inner wall (14) of the film-forming air atomizing nozzle and the convergent side of the secondary cyclone outlet baffle (21) and the axis is 30-60 degrees.
4. The center staged lean premixed low pollution combustor as claimed in claim 1, wherein: the ring height of the channel (26) of the film-forming air atomizing nozzle is 0.05-0.5 mm, and the length of the channel is 0.5-25 mm.
5. The center staged lean premixed low pollution combustor as claimed in claim 1, wherein: the swirl angle of the blades (35) of the main combustion stage swirler is 40-75 degrees, and the number of the blades is 6-20.
6. The center staged lean premixed low pollution combustor as claimed in claim 1, wherein: the included angle between the convergent side of the outer wall (36) of the main combustion stage swirler and the axis is 0-45 degrees.
7. The center staged lean premixed low pollution combustor as claimed in claim 1, wherein: an included angle between a fuel oil jet hole (49) in the direct injection type nozzle (37) and the axial direction is-75 degrees, the diameter of the nozzle is 0.1-0.8 mm, and the length of an internal channel (52) of the direct injection type nozzle is 10-40 times of the diameter of the nozzle.
8. The center staged lean premixed low pollution combustor as claimed in claim 1, wherein: the ratio of the flow rates of annular air and fuel oil in the direct injection nozzle (37), namely the gas-liquid ratio, is 1-5.
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| CN111928295B (en) * | 2020-09-08 | 2024-05-14 | 中国科学院工程热物理研究所 | Micro-premixing on-duty nozzle assembly and gas turbine micro-premixing combustion chamber |
| CN113464981B (en) * | 2021-07-09 | 2022-12-23 | 成立航空股份有限公司 | Air atomizing nozzle for enhancing atomizing effect |
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| CN114165814B (en) * | 2021-10-29 | 2023-02-10 | 南京航空航天大学 | A Multipoint Array Synergistic Direct Injection Lean Oil Staged Swirl Combustor |
| CN115899771B (en) * | 2022-12-19 | 2024-08-09 | 南京航空航天大学 | Concentric annular swirl combustion chamber for high temperature rise |
| CN116293808B (en) * | 2023-02-28 | 2024-10-29 | 南京航空航天大学 | Full-cyclone grading combustion chamber |
| CN116358000B (en) * | 2023-04-10 | 2025-03-28 | 西安热工研究院有限公司 | A double swirl premixing nozzle and single tube combustion chamber structure for injecting fuel from blades |
| CN116358003B (en) * | 2023-04-10 | 2025-03-28 | 西安热工研究院有限公司 | Fuel staged single swirl nozzle and single tube combustion chamber structure |
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