CN108844097B - Low-pollution combustion chamber for multi-point lean oil direct injection - Google Patents
Low-pollution combustion chamber for multi-point lean oil direct injection Download PDFInfo
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- CN108844097B CN108844097B CN201810219175.XA CN201810219175A CN108844097B CN 108844097 B CN108844097 B CN 108844097B CN 201810219175 A CN201810219175 A CN 201810219175A CN 108844097 B CN108844097 B CN 108844097B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 243
- 238000002347 injection Methods 0.000 title claims abstract description 71
- 239000007924 injection Substances 0.000 title claims abstract description 71
- 239000000446 fuel Substances 0.000 claims abstract description 26
- 238000002156 mixing Methods 0.000 claims description 8
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims description 8
- 230000001133 acceleration Effects 0.000 claims description 4
- 239000003344 environmental pollutant Substances 0.000 abstract description 12
- 231100000719 pollutant Toxicity 0.000 abstract description 12
- 238000009792 diffusion process Methods 0.000 abstract description 8
- 239000003921 oil Substances 0.000 description 33
- 239000007789 gas Substances 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 230000002269 spontaneous effect Effects 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 238000005496 tempering Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000003197 catalytic effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000003466 welding Methods 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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Of Fluid Fuel (AREA)
Abstract
The invention discloses a multipoint lean oil direct injection low-pollution combustion chamber, which consists of a diffuser, a combustion chamber casing, a combustion chamber head, a flame tube and a combustion chamber outlet; the staged combustion strategy is adopted, the head part of the combustion chamber is divided into an on-duty stage, a first main combustion stage and a second main combustion stage, the on-duty stage adopts a centrifugal nozzle to form a diffusion combustion mode, the main combustion stage adopts a lean oil direct injection combustion mode, and fuel nozzles in the on-duty stage, the first main combustion stage and the second main combustion stage can be independently controlled. And in the working condition of 7% thrust, only the duty class works, in the working condition of 30% thrust, the duty class and the first main combustion class work simultaneously, and in the working condition of 85% thrust and 100% thrust, the duty class, the first main combustion class and the second main combustion class work simultaneously. The design of the invention can better reduce pollutant emission, combustion efficiency and pollutant emission under low working conditions, and combustion efficiency under various working conditions under LTO circulation is considered.
Description
Technical Field
The invention belongs to the field of low-pollution combustion chambers, and particularly relates to a low-pollution combustion chamber with multipoint lean oil direct injection.
Background
In recent years, with more and more attention paid to environmental protection, the environmental protection of aircraft engines is more and more prominent in the research and development requirements, and the main development targets of reducing pollution and prolonging service life of gas turbine engines are.
Therefore, the low-pollution combustion technology is widely researched in all countries of the world, and different types of low-pollution combustion chambers are developed. For example, staged combustion technology, lean premixed pre-evaporative combustors (LPP), rich burn-quench-lean combustion technology (RQL), catalytic combustors, and Variable Geometry Combustors (VGC) have been developed in the united states as early as the 70 th century, with the primary objective being to substantially reduce nox formation. However, these techniques have their disadvantages, and the RQL combustion technique has difficulty in ensuring rapid and thorough mixing in the intermediate zone, thereby reducing combustion efficiency; the LPP combustion technology has the problems of tempering, spontaneous combustion, poor combustion stability and the like.
Therefore, attention is paid to a Lean Direct Injection (LDI) technique, in which fuel is directly injected into a combustion chamber to be mixed with air for combustion, and since the fuel is not premixed with air, the LDI technique does not have problems of spontaneous combustion, flashback, and the like. Research of a plurality of research organizations shows that the graded LDI combustion scheme can effectively reduce the emission of nitrogen oxides, and NO of the graded LDI combustion schemeXThe emissions are more than 80% lower than the CAEP/6 regulation.
However, the design of the low-pollution combustion chamber aiming at various working conditions is always a technical problem to be solved by the technical personnel in the field. Therefore, the combustion chamber can better reduce the pollutant discharge and has the combustion efficiency under various working conditions under the LTO circulation.
Disclosure of Invention
The invention discloses a low-pollution combustion chamber with multipoint lean oil direct injection, which aims at the problems in the prior art, adopts a staged combustion strategy, and enables the head part of the combustion chamber to be an on-duty stage, a first main combustion stage and a second main combustion stage, wherein the on-duty stage adopts a centrifugal nozzle to form a diffusion combustion mode, and the main combustion stage adopts a lean oil direct injection combustion mode, so that the problems in the prior art are solved.
The invention is realized by the following steps:
a low-pollution combustion chamber for directly jetting multipoint lean oil comprises a diffuser, a combustion chamber casing connected with the diffuser, a flame tube arranged in the combustion chamber casing, and a combustion chamber head connected with the flame tube, wherein a class on the combustion chamber head is a central swirler and is connected with an oil injection rod;
two first main combustion stage cyclones are arranged on two sides of the duty stage center, and a second main combustion stage four cyclones are arranged on an outer ring and an inner ring close to the duty stage center, and the structure of the second main combustion stage four cyclones is a 7-point lean oil direct injection head;
in the class, only four cyclones of the second main combustion stage are arranged on the outer ring and the inner ring, and the structure is a 5-point lean oil direct injection head;
the on-duty stage is a centrifugal nozzle, and the on-duty stage arranged at the centers of the 7-point lean oil direct injection head and the 5-point lean oil direct injection head can be used for oil injection and combustion under all working conditions, so that stable on-duty diffusion combustion flame can be provided for the low-pollution combustion chamber of the gas turbine; the first main combustion stage and the second main combustion stage are direct injection nozzles;
the head of the combustion chamber is uniformly arranged by adopting a 7-point lean oil direct injection head and a 5-point lean oil direct injection head in a mutually staggered mode in the circumferential direction. Namely, the head parts of the lean oil direct injection cyclones are 7 points and the 5 points are evenly arranged in the circumferential direction of the combustion chamber head part in a staggered mode. The structure of the 5-point lean oil direct injection head is similar to that of the 7-point lean oil direct injection head, and the difference is that direct injection nozzles are not arranged on two sides of the duty stage of the 5-point lean oil direct injection head structure.
Furthermore, the duty level comprises a duty level expansion channel, a bevel hole on the duty level expansion channel and a duty level centrifugal nozzle outlet circular table connected with the duty level expansion channel; an on-duty centrifugal nozzle outlet and an on-duty centrifugal nozzle outlet inner channel connected with the on-duty centrifugal nozzle outlet are sequentially arranged behind the on-duty centrifugal nozzle outlet circular truncated cone.
Furthermore, each unit lean oil injection head in the first main combustion stage and the second main combustion stage has the same structure and comprises a main combustion stage expansion channel and a two-stage axial swirler, wherein the main combustion stage second-stage swirler and the main combustion stage first-stage swirler are respectively connected with the main combustion stage expansion channel and the main combustion stage first-stage swirler and are internally connected with the main combustion stage second-stage swirler, and the main combustion stage first-stage swirler is connected with a main combustion stage central axial air acceleration channel.
Furthermore, the wall surface of the flame tube is provided with mixing holes.
Furthermore, the on-duty stage expansion channel is flush with the outlet of the main combustion stage expansion channel.
Furthermore, a main combustion grade secondary cyclone convergence section is formed on the outer side of the main combustion grade secondary cyclone, and a main combustion grade primary cyclone convergence section is formed between the main combustion grade primary cyclone and the main combustion grade secondary cyclone.
Furthermore, the main combustion level central axial air acceleration channel, the main combustion level primary cyclone and the main combustion level secondary cyclone are connected with the outlet of the main combustion level fuel nozzle through the main combustion level fuel nozzle outer channel in a three-stage air inlet mode.
Further, the duty-level outlet equivalence ratio is 0.6-1.6, and is slightly changed according to the working condition of the combustion chamber.
Further, the outlet equivalence ratio of the 7-point lean oil direct injection head to the 5-point lean oil direct injection head is 0.4-0.9, and the outlet equivalence ratio is changed according to the working condition of the low-pollution combustion chamber of the gas turbine; the number of the 7-point lean oil direct injection head and the number of the 5-point lean oil direct injection head are respectively 4-15, and the specific number is determined according to the diameter of the low-pollution combustion chamber of the gas turbine.
Furthermore, only the duty stage works under the working condition of 7% thrust; under the working condition of 30% thrust, the class and the first main combustion class work simultaneously; and under the working conditions of 85% thrust and 100% thrust, the class, the first main combustion stage and the second main combustion stage work simultaneously.
Compared with the prior art, the invention has the beneficial effects that:
1) the staged combustion strategy is adopted, the head part of the combustion chamber is divided into an on-duty stage, a first main combustion stage and a second main combustion stage, and the main combustion stages realize two-stage combustion, so that the problem of low combustion efficiency of the lean oil combustion chamber under a small working condition (particularly 30% working condition) is effectively solved, the working range of the combustion chamber is expanded, and the pollutant emission is reduced;
2) the first main combustion stage and the second main combustion stage adopt a direct fuel injection mode, so that the problems of tempering, spontaneous combustion and the like are avoided, and the risk of burning the head of the combustion chamber is reduced; the main combustion stage adopts a multipoint lean oil direct injection mode, the two-stage axial swirler of the main combustion stage ensures that fuel oil and air are quickly and uniformly mixed, the combustion efficiency is improved, the average equivalence ratio in the main combustion stage is 0.4-0.9, and the average temperature of the main combustion stage of the combustion chamber is reduced, so that pollutants NO are reducedXDischarging;
3) the centrifugal nozzle is adopted to form a diffusion combustion mode in class, so that reliable and stable combustion can be guaranteed under various working conditions; the main combustion stage adopts a lean oil direct injection combustion mode, so that the problems of spontaneous combustion, tempering and the like are effectively avoided; aiming at different working conditions: in the working condition of 7% thrust, only working on duty; under the working condition of 30% thrust, the class number and the first main combustion stage work simultaneously, so that the pollutant emission and the combustion efficiency under the working condition are considered; under the working conditions of 85% thrust and 100% thrust, the class, the first main combustion stage and the second main combustion stage work simultaneously; under each working condition, the average equivalence ratio in the main combustion stage of the combustion chamber is 0.4-0.9, and the average temperature of the main combustion stage of the combustion chamber is lower, so that pollutant emission is effectively reduced, and combustion efficiency is considered.
Drawings
FIG. 1 is a general schematic view of a multi-point lean direct injection low-pollution combustor of the present invention;
FIG. 2 is a cross-sectional view of a multi-point lean direct injection low-pollution combustor of the present invention
FIG. 3 is a front elevational view of the head of a multi-point lean direct injection low pollution combustor of the present invention;
FIG. 4 is a front view of a 7-point lean direct injection head of a multi-point lean direct injection, low pollution combustion chamber of the present invention;
FIG. 5 is an enlarged cross-sectional view of a 7-point lean direct injection head of a multi-point lean direct injection low fouling combustor of the present invention;
FIG. 6 is a front view of a 5-point lean direct injection head of a multi-point lean direct injection, low pollution combustion chamber of the present invention;
wherein, 1-diffuser, 2-combustor casing, 3-combustor head, 4-flame tube, 5-7 point lean oil direct injection head, 6-5 point lean oil direct injection head, 7-duty stage, 8-first main combustion stage, 9-second main combustion stage, 10-mixing hole, 11-fuel spray rod, 12-duty centrifugal nozzle outlet inner channel, 13-duty centrifugal nozzle outlet, 14-oblique cutting hole, 15-duty centrifugal nozzle outlet circular table, 16-duty expansion channel, 17-main combustion stage expansion channel, 18-main combustion stage fuel nozzle outlet, 19-main combustion stage fuel nozzle outer channel, 20-main combustion stage central axial air acceleration channel, 21-main combustion stage primary swirler, 22-main combustion stage secondary swirler, 23-a main combustion stage first-stage swirler convergence section and 24-a main combustion stage second-stage swirler convergence section.
Detailed Description
In order to make the objects, technical solutions and effects of the present invention clearer, the present invention is further described in detail below with reference to the accompanying drawings and examples. It should be noted that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1-2, the invention provides a low-pollution combustion chamber based on multi-point lean oil direct injection, which comprises a diffuser 1, a combustion chamber casing 2, a combustion chamber head 3 and a flame tube 4. The high-speed airflow compressed by the compressor is subjected to speed reduction and diffusion by the diffuser 1 and then is divided into two flows, one flow enters an inner annular channel and an outer annular channel formed by the casing 2 of the combustion chamber and the wall surface of the flame tube 4, and the other flow enters the flame tube 4 through the head 3 of the combustion chamber to participate in combustion. One part of the airflow flowing into the inner and outer ring channels is used for cooling the flame tube, and the other part of the airflow enters the flame tube from the mixing hole 10 to adjust the temperature distribution of the outlet of the combustion chamber. The air flow entering the combustion chamber head 3 accounts for 60-85% of the total air flow, the cooling air amount accounts for 15-20%, and the air amount entering the mixing holes accounts for 0-20% of the air volume.
As shown in fig. 3, the combustion chamber head 3 is arranged with 7-point lean direct injection heads and 5-point lean direct injection heads staggered uniformly in the circumferential direction. As shown in fig. 4, when two swirlers of the first main combustion stage 8 are disposed on both sides of the center of class 7, and four swirlers of the second main combustion stage 9 are disposed on the outer and inner rings of class 7, the structure is a 7-point lean direct injection head 5; as shown in fig. 6, the configuration of the four swirlers of the second main combustion stage 9 when only the outer and inner rings of the duty stage 7 are provided is a 5-point lean direct injection head 6.
The invention adopts a staged combustion technology, the combustion chamber head part 3 is divided into an executive stage 7, a first main combustion stage 8 and a second main combustion stage 9, wherein the main combustion stages are also subjected to staged combustion. The first main combustion stage 8 and the second main combustion stage 9 are uniformly and circumferentially distributed outside the duty stage 7, and the main combustion stage expansion channel 17 is flush with the outlet of the duty stage expansion channel 16 and is connected in a welding mode and the like. Under the working condition of 7% thrust, the fuel is only worked on class 7, a local rich oil combustion mode is adopted, the head outlet equivalence ratio of the class on duty is 0.6-1.6, and stable and reliable combustion is guaranteed; under the working condition of 30% thrust, the duty stage 7 and the first main combustion stage 8 work simultaneously, and the combustion efficiency and pollutant emission under the working condition are considered; the duty stage 7 and the first and second main combustion stages 8 and 9 operate simultaneously at 85% and 100% thrust conditions. Under large working conditions, the average equivalence ratio in the main combustion stage of the combustion chamber is lean, the average equivalence ratio is 0.4-0.9, and the average temperature in the main combustion stage of the combustion chamber is low, so that the pollutant emission is effectively reduced.
As shown in fig. 4 to 5, the duty 7 mainly includes an on-duty centrifugal nozzle outlet inner channel 12, an on-duty centrifugal nozzle outlet 13, an on-duty centrifugal nozzle outlet circular truncated cone 15, an on-duty expansion channel 16, and a chamfered hole 14 in the on-duty expansion channel. The fuel nozzle of the class adopts a centrifugal nozzle, so that good fuel atomization effect is ensured.
The duty air flow enters the duty expansion channel 16 through the bevel hole 14 on the duty expansion channel, a rotational flow is formed in the channel, a backflow area is formed at the downstream, the duty fuel oil is sprayed out from the duty centrifugal nozzle outlet 13 through the duty centrifugal nozzle outlet inner channel 12, and then the duty expansion channel 16 and the rotating air are quickly and uniformly mixed to form combustible gas, so that duty diffusion combustion flame is formed, and a stable high-temperature ignition source under various working conditions is provided.
The lean oil injection head structures of the units in the first main combustion stage 8 and the second main combustion stage 9 are the same, and the lean oil injection head structures are composed of a main combustion stage expanding channel 17, a main combustion stage fuel nozzle outlet 18, a main combustion stage fuel nozzle outer channel 19, a main combustion stage central axial air accelerating channel 20, a main combustion stage primary swirler 21, a main combustion stage secondary swirler 22, a main combustion stage primary swirler converging section 23 and a main combustion stage secondary swirler converging section 24. The airflow entering the main combustion stage is three, one of the three flows passes through the central axial air accelerating channel 20 of the main combustion stage to form a strong air axial speed, the other flow passes through the primary cyclone 21 of the main combustion stage and generates rotary motion after passing through the swirl blades, the other flow passes through the secondary cyclone 22 of the main combustion stage and generates rotary motion after passing through the swirl blades, and the three flows all enter the main combustion stage expanding channel 17 and form a backflow zone at the downstream. The fuel is sprayed out from the outlet 18 of the main combustion level fuel nozzle through the direct injection type nozzle, enters the outer channel 19 of the main combustion level fuel nozzle and then enters the main combustion level primary swirler 21, a rotary oil film layer is formed on the main combustion level primary swirler 21, the fuel is crushed and atomized under the mutual shearing action of the air inlet of the main combustion level primary swirler 21 and the air inlet of the main combustion level secondary swirler 22, and the fuel is rapidly and uniformly mixed with the air to form combustible gas. The fuel nozzles in the class 7, the first main combustion stage 8 and the second main combustion stage 9 can be independently controlled, the duty fuel nozzle adopts a centrifugal nozzle, the fuel nozzles in the first main combustion stage 8 and the second main combustion stage 9 adopt a direct injection type nozzle, and the main combustion stage fuel enters the main combustion stage inner vortex passage through the main combustion stage fuel nozzle outer passage 19.
The principle of the invention is as follows:
the temperature distribution and the average temperature of a combustion area are controlled by reasonably controlling the local equivalence ratio in the combustion chamber, the average equivalence ratio of the combustion chamber and the uniform degree of oil-gas mixing, so that the pollutant emission is effectively reduced, the aim of low emission is fulfilled, and the combustion efficiency of each working condition is considered. The high-speed airflow from the compressor is subjected to speed reduction and diffusion by a diffuser 1 and then is divided into two parts, one part enters an inner annular channel and an outer annular channel which are formed by a combustion chamber casing 2 and the wall surface of a flame tube 4 and used for cooling an air film on the wall surface of the flame tube 4 and introducing air into a mixing hole 10 to adjust the temperature distribution of the outlet of the combustion chamber; the other strand passes through the head part 3 of the combustion chamber and enters the flame tube 4 to participate in combustion, and the air inflow of the head part 3 of the combustion chamber accounts for 60-85% of the air inflow of the diffuser 1. Under the working condition of 7% thrust, only the on-duty nozzle works, and a local rich oil diffusion combustion mode is adopted to ensure stable and reliable combustion; under the working condition of 30% thrust, the duty stage 7 and the first main combustion stage 8 work simultaneously, and meanwhile, the combustion efficiency and pollutant discharge under the working condition are considered; under the working conditions of 85% thrust and 100% thrust, the duty stage 7, the first main combustion stage 8 and the second main combustion stage 9 work simultaneously; under large working conditions, the average equivalence ratio in the main combustion stage of the combustion chamber is lean, and the average temperature in the main combustion stage of the combustion chamber is lower, so that the pollutant emission is effectively reduced. Therefore, the multi-point lean direct injection low-pollution combustion chamber disclosed by the invention can be used for stably combusting and has the advantages of low emission and high combustion efficiency.
Claims (9)
1. A low-pollution combustion chamber with multipoint direct lean oil injection comprises a diffuser (1), a combustion chamber casing (2) connected with the diffuser (1), a flame tube (4) arranged in the combustion chamber casing (2), and a combustion chamber head (3) connected with the flame tube (4), and is characterized in that a spangle (7) on the combustion chamber head (3) is a central swirler and is connected with an oil injection rod (11);
two sides of the center of the class (7) are provided with two cyclones of a first main combustion stage (8), and four cyclones of a second main combustion stage (9) are arranged on the outer ring and the inner ring of the class (7) and are structurally provided with 7-point lean oil direct injection heads (5);
the structure of four cyclones of a second main combustion stage (9) arranged on an outer ring and an inner ring of the overtime stage (7) is a 5-point lean oil direct injection head (6);
the number class (7) is a centrifugal nozzle, and the first main combustion stage (8) and the second main combustion stage (9) are direct injection nozzles;
the combustor head (3) is uniformly arranged by adopting 7-point lean oil direct injection heads (5) and 5-point lean oil direct injection heads (6) in a mutually staggered mode in the circumferential direction.
2. The multi-point lean direct injection low pollution combustor of claim 1 wherein said class (7) comprises a class expansion channel (16), a chamfered hole (14) in said class expansion channel (16), and a class centrifugal nozzle cone (15) connected to said class expansion channel (16); an on-duty centrifugal nozzle (13) and an on-duty centrifugal nozzle inner channel (12) connected with the on-duty centrifugal nozzle (13) are sequentially arranged behind the on-duty centrifugal nozzle circular truncated cone (15).
3. The low-pollution combustion chamber with multipoint lean direct injection is characterized in that the unit lean injection heads of the first main combustion stage (8) and the second main combustion stage (9) are identical in structure and comprise a main combustion stage expanding channel (17), two-stage axial swirlers, a main combustion stage secondary swirler (22) connected with the main combustion stage expanding channel (17), a main combustion stage primary swirler (21) connected with the inside of the main combustion stage secondary swirler (22), and a main combustion stage central axial air accelerating channel (20) connected with the main combustion stage primary swirler (21).
4. The low-pollution multi-point lean direct injection combustor according to claim 1, wherein the flame tube (4) is provided with mixing holes (10) in the wall surface.
5. The low-pollution combustor with multipoint lean direct injection according to claim 3, wherein a main combustion stage secondary cyclone channel converging section (24) is formed outside the main combustion stage secondary cyclone (22), and a main combustion stage primary cyclone channel converging section (23) is formed between the main combustion stage primary cyclone (21) and the main combustion stage secondary cyclone (22).
6. The low-pollution multi-point lean direct injection combustor of claim 3, wherein the main stage central axial air acceleration passage (20), the main stage primary swirler (21) and the main stage secondary swirler (22) are connected with the main stage fuel nozzle outlet (18) through the main stage fuel nozzle outer passage (19) in a three-stage air intake mode.
7. The multi-point lean direct injection low pollution combustor of claim 1, wherein the value class (7) outlet equivalence ratio is 0.6-1.6.
8. The low-pollution combustor with multi-point lean direct injection according to claim 1, wherein the outlet equivalence ratio of the 7-point lean direct injection head (5) to the 5-point lean direct injection head (6) is 0.4-0.9; the number of the 7-point lean oil direct injection head parts (5) and the number of the 5-point lean oil direct injection head parts (6) are respectively 4-15.
9. A multipoint lean direct injection low pollution combustor according to claim 1, characterized in that at 7% thrust condition, only class (7) is active; under the working condition of 30% thrust, the class (7) and the first main combustion stage (8) work simultaneously; and under the working conditions of 85% thrust and 100% thrust, the value class (7), the first main combustion stage (8) and the second main combustion stage (9) work simultaneously.
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| CN201810219175.XA CN108844097B (en) | 2018-03-16 | 2018-03-16 | Low-pollution combustion chamber for multi-point lean oil direct injection |
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| CN110953603B (en) * | 2019-12-05 | 2021-08-03 | 中国航发四川燃气涡轮研究院 | Multi-oil-path fuel oil spraying device suitable for radial grading main combustion chamber |
| CN111829008B (en) * | 2020-07-06 | 2021-04-23 | 南京航空航天大学 | Rotary detonation combustion chamber based on integration of shearing airflow and fuel injection |
| CN115095885B (en) * | 2022-06-06 | 2024-02-09 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI inclined combustion chamber |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5321947A (en) * | 1992-11-10 | 1994-06-21 | Solar Turbines Incorporated | Lean premix combustion system having reduced combustion pressure oscillation |
| US5437158A (en) * | 1993-06-24 | 1995-08-01 | General Electric Company | Low-emission combustor having perforated plate for lean direct injection |
| US6986255B2 (en) * | 2002-10-24 | 2006-01-17 | Rolls-Royce Plc | Piloted airblast lean direct fuel injector with modified air splitter |
| DE102007043626A1 (en) * | 2007-09-13 | 2009-03-19 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine lean burn burner with fuel nozzle with controlled fuel inhomogeneity |
| CN102242939B (en) * | 2011-07-29 | 2013-12-11 | 北京航空航天大学 | Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor |
| 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 |
| CN203671653U (en) * | 2013-12-12 | 2014-06-25 | 中航商用航空发动机有限责任公司 | Combustor for gas turbine |
| CN106482154A (en) * | 2016-10-31 | 2017-03-08 | 南京航空航天大学 | The lean premixed preevaporated low contamination combustion chamber that a kind of main is atomized with splashing type |
| CN107143880B (en) * | 2017-05-16 | 2020-02-14 | 西北工业大学 | Lean oil multi-point direct injection head for low-pollution combustion chamber of gas turbine |
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