CN111207413A - Multistage swirl miniature gas turbine combustor - Google Patents
Multistage swirl miniature gas turbine combustor Download PDFInfo
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- CN111207413A CN111207413A CN202010131114.5A CN202010131114A CN111207413A CN 111207413 A CN111207413 A CN 111207413A CN 202010131114 A CN202010131114 A CN 202010131114A CN 111207413 A CN111207413 A CN 111207413A
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- 239000000446 fuel Substances 0.000 claims abstract description 79
- 238000002485 combustion reaction Methods 0.000 claims abstract description 57
- 238000005192 partition Methods 0.000 claims abstract description 32
- 238000000889 atomisation Methods 0.000 claims abstract description 28
- 230000004323 axial length Effects 0.000 claims description 7
- 125000003158 alcohol group Chemical group 0.000 abstract description 6
- 230000002349 favourable effect Effects 0.000 abstract description 4
- 238000009826 distribution Methods 0.000 abstract description 3
- 239000000203 mixture Substances 0.000 abstract description 3
- 238000010304 firing Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 121
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 24
- 239000007789 gas Substances 0.000 description 17
- 230000000694 effects Effects 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 5
- 230000003111 delayed effect Effects 0.000 description 4
- 238000002156 mixing Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000018109 developmental process Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 239000003208 petroleum Substances 0.000 description 2
- 238000009834 vaporization Methods 0.000 description 2
- 230000008016 vaporization Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000009827 uniform distribution 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
A multi-stage rotational flow micro gas turbine combustor belongs to the technical field of gas turbine combustion. The invention solves the problems of difficult cold start, easy occurrence of the condition of incapability of firing and low combustion efficiency of the traditional double-oil-way centrifugal atomizing nozzle. A multi-stage rotational flow micro gas turbine combustor comprises an ignition plug, an atomization net, a reference piece, a main oil way partition plate and a shell which are coaxially arranged, wherein the ignition plug is a variable-diameter cylindrical section, the reference piece is sleeved on the ignition plug, an annular cavity is formed between the middle part of the reference piece and the ignition plug, and a plurality of axial guide vanes are processed on the outer surface of the reference piece. Adopt multistage whirl hole structure to divide into root wind and two-stage whirl wind with whole air and strengthen the hierarchical mixture of alcohol group fuel and air for alcohol group fuel and air misce bene are favorable to the stability of combustion process, export temperature distribution is even and NOx discharges and reduce.
Description
Technical Field
The invention relates to a multistage rotational flow micro gas turbine combustor, and belongs to the technical field of gas turbine combustion.
Background
In recent years, due to rapid development of global economy, the demand for energy in various countries has been increasing. In order to solve the current energy crisis, concepts of smart grids and distributed energy resources are developed. The Micro-Turbine (Micro-Turbine) is used as a core device of a new energy technology, and the maturity of the technology plays an important role in promoting the development of smart grids and distributed energy systems. The micro gas turbine has the advantages of portability, wide range of fuel types, extremely low pollution, safety, reliability and the like, and has great influence on the life and production of people in the 21 st century. However, as the international petroleum market price is unstable and China lacks enough petroleum resources to support long-term development, the search of alternative energy sources of the gas turbine becomes an important task which is imperative in China. Alcohol-based fuels are highly efficient, clean, economical and widely available. Alcohol-based fuels have many advantages over conventional fuels, such as low viscosity for easy atomization, high ignition point for improved safety, low emissions for reduced environmental pollution, etc., and tests and studies have shown that alcohol-based fuels are entirely feasible for use in gas turbines.
The atomizing nozzle is a key device of the micro gas turbine, and the fuel atomizing quality of the atomizing nozzle directly influences ignition, mixing, burning and burnout of a combustion chamber; the better the atomization dispersion effect, the more uniform the atomization particle size, the more favorable the mixing, ignition and combustion of the particles. Therefore, a good nozzle structure is essential to improve the combustion efficiency of the gas turbine combustor. The centrifugal atomizing nozzle with double oil channels is an improved single-channel pressure atomizing nozzle, and has the outstanding advantages of wide oil quantity adjusting range and capability of ensuring that better atomizing quality can be obtained under low working conditions, so that the centrifugal atomizing nozzle with double oil channels is widely applied to gas turbines. However, if the conventional dual-oil nozzle and alcohol-based fuel are directly applied to the micro gas turbine, the following problems may be caused:
1. the main oil circuit of the double-oil circuit centrifugal atomizing nozzle has small oil supply pressure when starting to work, and cannot meet the atomizing performance of a micro gas turbine unit under the starting working condition, so that the combustion efficiency is not ideal.
2. Because the latent heat of vaporization of the alcohol-based fuel is very large compared with the common fuel, the absorbed heat is much during vaporization, the temperature of a combustion area is low, and the combustion efficiency is poor. The traditional double oil ways have the problems of poor atomization effect, difficult cold start and the like under the condition of no preheating measure or improvement.
3. Because the fuel concentration at the front end of the spray hole of the atomizing nozzle is high, the oxygen content of the fuel which is fully combusted is insufficient, so that the phenomena of low combustion efficiency, exhaust and smoke generation of a combustion chamber and the like can be caused.
4. When the atomizing nozzle burns, air is fed once, so that the ignition heat of liquid fuel is increased, and the problems of incapability of igniting or oil dripping, carbon precipitation and the like are caused.
Therefore, it is necessary to further improve various aspects of the atomizing nozzle, so that the combustion chamber of the micro gas turbine can obtain good atomizing effect under various working conditions while effectively applying alcohol-based fuel or other liquid fuel, and the whole combustion chamber can meet the requirements of high-efficiency low-pollution combustion technology.
Disclosure of Invention
The invention aims to solve the problems of difficult cold start, easy occurrence of condition of incapability of firing and low combustion efficiency of the existing double-oil-way centrifugal atomizing nozzle, and further provides a multi-stage rotational flow micro gas turbine combustor.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a multi-stage rotational flow micro gas turbine combustor comprises an ignition plug, an atomization net, a reference piece, a main oil way partition plate and a shell which are coaxially arranged, wherein the ignition plug is a variable-diameter cylindrical section, the reference piece is sleeved on the ignition plug, an annular cavity is formed between the middle part of the reference piece and the ignition plug, and a plurality of axial guide vanes are processed on the outer surface of the reference piece;
the atomization net is of a hollow cylindrical structure and is arranged in an annular cavity between the reference part and the ignition plug, an annular gap is formed between the inner surface of the atomization net and the ignition plug,
the main oil way partition plate comprises a partition plate main body and a coil pipe coaxially arranged on the partition plate main body in a coiling manner, the partition plate main body is of a hollow cylindrical structure and is sleeved on the reference piece, one end part, far away from the combustion chamber, of the shell is coaxially sleeved on the main oil way partition plate, and a plurality of axial guide vanes are positioned between the partition plate main body and the reference piece to form a root part air flow channel;
one end part of the reference piece close to the combustion chamber is a tapered section, an auxiliary oil path convergence channel is formed between the tapered section and the ignition plug, one end of the auxiliary oil path convergence channel close to the combustion chamber is an auxiliary oil path fuel nozzle,
a main oil path convergence channel is formed between the inner surface of the middle part of the shell and the outer surface of the tapered section of the reference part, one end of the main oil path convergence channel close to the combustion chamber is a main oil path fuel nozzle,
one end of the coil pipe is a main oil path inlet end and extends to the outside of the shell, the other end of the coil pipe is an outlet end and is arranged close to a main oil path convergence channel, an auxiliary oil path pipe section is inserted on the reference piece, the auxiliary oil path pipe section is arranged far away from the combustion chamber, the end part of the auxiliary oil path pipe section is communicated with an annular cavity where the atomizing net is located,
a plurality of primary swirl holes are circumferentially processed at positions, close to the reducing section, on the reference part, the middle part of the shell is a reducing section, a plurality of secondary swirl holes and a plurality of tertiary swirl holes are processed on the shell, the plurality of secondary swirl holes are arranged close to the main oil way partition plate, and the plurality of tertiary swirl holes are arranged close to the combustion chamber.
Furthermore, one end part of the reference piece far away from the combustion chamber is in threaded connection with the ignition plug, and the outer surface of the atomization net is in close contact with the inner surface of the reference piece, and one end of the atomization net is in close contact with a shaft shoulder on the ignition plug.
Further, the number of circles of the coil pipe is 4 to 10 circles, the inner diameter and the outer diameter of the coil pipe are 1 to 3mm, and the rotational direction of the rotational flow in the coil pipe is the same as the rotational direction of the air entering the primary rotational flow hole.
Furthermore, the number of the axial guide vanes is 4-8, the axial guide vanes are uniformly distributed along the circumferential direction of the reference piece, and the axial length of each axial guide vane is smaller than or equal to 2/3 of the axial length of the partition plate main body.
Further, the quantity of one-level whirl hole is 8 ~ 12, and along benchmark piece circumference equipartition, and one-level whirl hole is 1 ~ 3 mm's of length of side rectangular hole, and the projection of the contained angle on the section between the axis of every one-level whirl hole and the benchmark piece axis is 30 ~ 60.
Further, the quantity of second grade whirl hole is 8 ~ 16, and along shell circumference equipartition, and second grade whirl hole is diameter 1 ~ 3 mm's round hole.
Further, the quantity of tertiary whirl hole is 16 ~ 24, and along shell circumference equipartition, and tertiary whirl hole is 1 ~ 3mm rectangular hole of length of side, and the projection of the contained angle on the section between the axis of every tertiary whirl hole and the casing axis is 30 ~ 60.
Furthermore, the central axes of the primary swirl hole, the secondary swirl hole and the tertiary swirl hole are arranged in the same direction.
Furthermore, the inner diameter and the outer diameter of the inlet end of the main oil way are both 1-3 mm, and the inner diameter and the outer diameter of the auxiliary oil way pipe section are both 0.5-1.5 mm.
Furthermore, the diameter distance between the inner ring and the outer ring of the fuel nozzle of the main oil way and the diameter distance between the inner ring and the outer ring of the fuel nozzle of the auxiliary oil way are both 0.25-1 mm.
Compared with the prior art, the invention has the following effects:
the dual-oil-way oil supply mode that the main oil way and the auxiliary oil way are separated is adopted, the ignition plug is adopted to preheat and ignite the alcohol-based fuel of the auxiliary oil way, so that the alcohol-based fuel can effectively absorb heat to evaporate and ignite in the atomization net, and an ignition heat source of the fuel of the main oil way is provided, so that the problem of difficult cold start of the alcohol-based fuel is effectively solved;
the main oil way fuel realizes tangential oil supply through a coil pipe surrounding structure on the main oil way partition plate through a plurality of times of rotational flows, so that on one hand, the main oil way fuel is fed in a delayed manner, and on the other hand, the main oil way fuel is preheated to a certain degree, which is beneficial to ignition and combustion of the main oil way fuel;
adopt multistage whirl hole structure to divide into root wind and two-stage whirl wind with whole air and strengthen the hierarchical mixture of alcohol group fuel and air for alcohol group fuel and air misce bene are favorable to the stability of combustion process, export temperature distribution is even and NOx discharges and reduce.
Drawings
Fig. 1 is a schematic perspective view (partially in section) of the present application;
FIG. 2 is a schematic front view of the present application;
FIG. 3 is a schematic cross-sectional view taken along line C-C of FIG. 2;
FIG. 4 is a schematic structural view of the coil;
fig. 5 is a schematic perspective view of the present application (the housing and the main oil passage partition are not shown).
Detailed Description
The first embodiment is as follows: the embodiment is described with reference to fig. 1 to 5, and a multistage swirl micro gas turbine combustor comprises an ignition plug 1, an atomization net 2, a reference piece 3, a main oil way partition plate 4 and a shell 5 which are coaxially arranged, wherein the ignition plug 1 is a cylindrical section with a variable diameter, the reference piece 3 is sleeved on the ignition plug 1, an annular cavity is formed between the middle part of the reference piece 3 and the ignition plug 1, and a plurality of axial guide vanes 17 are processed on the outer surface of the reference piece 3;
the atomization net 2 is a hollow cylindrical structure and is arranged in an annular cavity between the reference piece 3 and the ignition plug 1, an annular gap is formed between the inner surface of the atomization net 2 and the ignition plug 1,
the main oil way partition plate 4 comprises a partition plate main body 10 and a coil pipe 9 coaxially coiled on the partition plate main body 10, the partition plate main body 10 is of a hollow cylindrical structure and is sleeved on the reference piece 3, one end part, far away from a combustion chamber, of the shell 5 is coaxially sleeved on the main oil way partition plate 4, and a plurality of axial flow guide blades 17 are positioned between the partition plate main body 10 and the reference piece 3 to form a root part air flow channel;
one end part of the reference piece 3 close to the combustion chamber is a tapered section, an auxiliary oil path convergence channel 7 is formed between the tapered section and the ignition plug 1, one end of the auxiliary oil path convergence channel 7 close to the combustion chamber is an auxiliary oil path fuel nozzle 6,
a main oil path convergence channel 12 is formed between the inner surface of the middle part of the shell 5 and the outer surface of the tapered section of the reference part 3, one end of the main oil path convergence channel 12 close to the combustion chamber is provided with a main oil path fuel nozzle 13,
one end of the coil pipe 9 is a main oil path inlet end 11 and extends to the outside of the shell 5, the other end of the coil pipe 9 is an outlet end and is arranged close to a main oil path convergence channel 12, an auxiliary oil path pipe section 14 is inserted on the reference piece 3, the auxiliary oil path pipe section 14 is arranged far away from the combustion chamber, the end part of the auxiliary oil path pipe section 14 is communicated with an annular cavity where the atomization net 2 is positioned,
a plurality of primary swirl holes 8 are circumferentially processed at positions, close to the reducing section, on the reference part 3, the middle part of the shell 5 is a reducing section 18, a plurality of secondary swirl holes 15 and a plurality of tertiary swirl holes 16 are processed on the shell, wherein the plurality of secondary swirl holes 15 are arranged close to the main oil way partition plate 4, and the plurality of tertiary swirl holes 16 are arranged close to the combustion chamber.
The coil pipe 9 is welded on the outer surface of the clapboard main body 10, and the coil pipe 9 is coiled in an annular cavity formed between the shell 5 and the clapboard main body 10. The coil pipe 9 is a spiral tubular structure, and a rectangular thread, a trapezoidal thread or an external thread with other cross-section types can be used instead of the coil pipe 9. Said coil 9 is tightly coiled in the annular chamber formed between the casing 5 and the main body 10 of the baffle.
The fuel oil passing through the main oil path in the coil pipe 9 rotates along the circumferential direction, passes through a main oil path channel 19 enclosed by the clapboard main body 10 and the shell 5, then flows through a main oil path convergent channel 12, and is sprayed into a combustion chamber from a main oil path fuel nozzle 13. The outlet end of the coil 9 is in close contact with the inner wall surface of the housing 5. The inlet end of the coil pipe 9 is not in the coverage range of the main oil channel 19 to ensure the oil channel connection, the fuel oil is sprayed into the main oil channel convergence channel 12 through the rotation of the outlet end of the coil pipe, and the rotational direction of the fuel oil is the same as the rotational direction of the air entering the primary rotational hole 8.
The atomizing net 2 is a hollow cylindrical metal wire net or a sintered hollow cylindrical structure, the tail end position of the atomizing net cannot exceed the central line of the primary swirl hole 8 on the reference piece 3, and the tail end position is one end close to the combustion chamber.
The auxiliary oil path pipe section 14 is a straight section of a steel pipe, is inserted into the position close to the front end of the ignition plug 1 along the tangential direction of the inner circle of the auxiliary oil path channel 20 and directly abuts against the atomization net 2, and is welded after an opening is formed in the reference part 3 during installation; the auxiliary oil passage 20 is an annular cavity where the atomizing net 2 is located.
The secondary oil path pipe section 14 is a secondary oil path inlet end, and the primary oil path inlet end 11 and the secondary oil path inlet end are arranged in parallel.
The axial guide vanes 17 are uniformly distributed along the circumferential direction of the reference part 3 to form annular air passages 21. First-stage air tangentially enters the auxiliary oil path channel 20 from the first-stage swirl hole 8 through the annular air path 21, and atomization and ignition of the alcohol-based fuel are enhanced under the action of tangential shearing force of the air.
An annular cavity is formed between the middle part of the reference part 3 and the ignition plug 1 and is used as an installation space of the auxiliary oil path fuel atomization net 2 and a space for evaporation atomization and ignition combustion; the reference member 3 is arranged along the same axis as the ignition plug 1;
the auxiliary oil path fuel nozzle 6 is positioned in an annular gap between the reference part 3 and the ignition plug 1, the front side of the auxiliary oil path fuel nozzle is an auxiliary oil path convergent channel 7, and the center of the auxiliary oil path fuel nozzle 6 and the center of the main oil path fuel nozzle 13 are both positioned on the axis of the combustor; under the starting working condition, an ignition plug 1 is adopted to preheat and ignite the alcohol-based fuel tangentially supplied from the inlet end of the auxiliary oil path, so that the alcohol-based fuel effectively absorbs heat in the atomizing net 2, evaporates and ignites, then flows through an auxiliary oil path convergence channel 7 and is sprayed out from an auxiliary oil path fuel nozzle 6;
the primary circuit fuel jets 13 are located at the end of the datum 3, flush with the secondary circuit fuel jets 6.
The ignition plug 1 evaporates and atomizes the fuel of the auxiliary oil way in the atomizing net 2 and provides an ignition heat source for the atomized fuel; the tail end of the auxiliary oil way is directed to one side of the combustion chamber and is flush with the end surface of the fuel nozzle 6 of the auxiliary oil way or is exposed for a certain length;
the primary swirl hole 8 is an inlet of root wind, and a root wind flow channel is formed between the partition plate main body 10 and the reference part 3, so that the primary air entering the channel can rotate along the tangential inlet to enter an annular cavity where the ignition plug 1 is located;
the secondary swirl holes 15 and the tertiary swirl holes 16 are used as inlet channels of residual air to realize the staged swirl combustion of fuel oil; the secondary swirl holes 15 and the tertiary swirl holes 16 may be selected from only one or two stages, and the opening pattern may be circular holes, rectangular holes or other types of rotating blades with the same flow area.
The main oil path converging channel 12 is a tapered annular cavity structure formed by the reference piece 3, a tapered section and the inner surface of the shell 5.
One end part of the shell 5 close to the combustion chamber is a straight section, and the machining precision of the outer surface of the straight section can ensure the sealing and the fixing when the straight section is installed with the circular inlet of the combustion chamber.
The application is applied to the micro gas turbine combustor burning alcohol-based fuel and other liquid fuels, and has the characteristics of high efficiency, stability and low pollution.
The method adopts a double-oil-way oil supply mode that a main oil way and an auxiliary oil way are separated, adopts the ignition plug 1 to preheat and ignite the alcohol-based fuel of the auxiliary oil way, so that the alcohol-based fuel effectively absorbs heat in the atomizing net 2 to evaporate and ignite, and provides an ignition heat source for the fuel of the main oil way, thereby effectively solving the problem of difficult cold start of the alcohol-based fuel;
the fuel of the main oil way passes through a coil pipe 9 surrounding structure on the partition plate 4 of the main oil way, and tangential oil supply is realized through multiple times of rotational flow, so that on one hand, the fuel of the main oil way is fed in a delayed manner, and on the other hand, the fuel of the main oil way is preheated to a certain degree, thereby being beneficial to ignition and combustion of the fuel of the main oil way;
adopt multistage whirl hole structure to divide into root wind and two-stage whirl wind with whole air and strengthen the hierarchical mixture of alcohol group fuel and air for alcohol group fuel and air misce bene are favorable to the stability of combustion process, export temperature distribution is even and NOx discharges and reduce.
One end part of the reference piece 3 far away from the combustion chamber is in threaded connection with the ignition plug 1, and the outer surface of the atomization net 2 is in close contact with the inner surface of the reference piece 3, and one end of the atomization net 2 is in close contact with a shaft shoulder on the ignition plug 1. The close contact is achieved by an interference fit.
The number of circles of the coil pipe 9 is 4-10 circles, the inner diameter and the outer diameter of the coil pipe are 1-3 mm, and the rotational direction of the coil pipe 9 is the same as the rotational direction of the air entering the primary rotational flow hole 8. I.e. the smallest inner diameter of the coil is 1mm and the largest outer diameter is 3 mm.
The number of the axial guide vanes 17 is 4-8, the axial guide vanes 17 are uniformly distributed along the circumferential direction of the reference piece 3, the axial length of each axial guide vane 17 is smaller than or equal to 2/3 of the axial length of the partition plate main body 10, the axial length of each axial guide vane 17 is the extending distance of the tail end of one side, pointing to the combustion chamber, of each axial guide vane 17, as shown in fig. 5, the projection of the included angle between a thread line and an axis in each axial guide vane on the upper view reference plane is α, the α value is 30-60 degrees, and the size of any cross section on the spiral line is a rectangle of 1-3 mm.
The quantity of one-level whirl hole 8 is 8 ~ 12, and along 3 circumference equipartitions of benchmark piece, and one-level whirl hole 8 is 1 ~ 3 mm's of length of side rectangular hole, and the projection of the contained angle on the section between the axis of every one-level whirl hole 8 and the 3 axis of benchmark piece is 30 ~ 60.
The number of second grade whirl hole 15 is 8 ~ 16, and along 5 circumference equipartitions of shell, and second grade whirl hole 15 is diameter 1 ~ 3 mm's round hole. The circular holes are arranged tangentially according to a certain eccentricity and form a certain angle with the axis of the burner, and the rotational flow direction of the circular holes is the same as that of the primary rotational flow hole 8 for the atomized gas to enter.
The quantity of tertiary whirl hole 16 is 16 ~ 24, and along 5 circumference equipartitions of shell, tertiary whirl hole 16 is 1 ~ 3mm rectangular hole of length of side, and the projection of the contained angle on the section between every tertiary whirl hole 16's axis and the casing axis is 30 ~ 60. The atomizing air enters tangentially into the tertiary swirl holes 16.
The central axes of the primary swirl holes 8, the secondary swirl holes 15 and the tertiary swirl holes 16 are arranged in the same direction. Namely, the central axes of the primary swirl hole 8, the secondary swirl hole 15 and the tertiary swirl hole 16 form the same included angle with the central axis of the ignition plug 1. Feeding of swirl holes at different positions or different time points is realized by controlling different included angles between the swirl holes and the axis of the ignition plug 1, so that accurately controlled staged combustion is achieved.
The inner diameter and the outer diameter of the main oil path inlet end 11 are both 1-3 mm, and the inner diameter and the outer diameter of the auxiliary oil path pipe section 14 are both 0.5-1.5 mm. By the design, the flow of oil supplied by the oil pump can be distributed according to a selected proportion; the axes of the inlet ends of the main oil passage and the auxiliary oil passage are parallel but are at a certain distance.
The diameter distance between the inner ring and the outer ring of the main oil path fuel nozzle 13 and the diameter distance between the inner ring and the outer ring of the auxiliary oil path fuel nozzle 6 are both 0.25-1 mm.
The working principle is as follows:
under the starting working condition, the ignition plug 1 is started firstly, then the oil pump is started to supply oil to the buffer tank, and the fuel oil or the alcohol-based fuel is distributed to the inlet ends of the main oil passage and the auxiliary oil passage. Because the strokes of the auxiliary oil way and the main oil way are greatly different, firstly, the alcohol-based fuel in the inlet end of the auxiliary oil way enters the burner reference part 3 along the tangential direction and is quickly diffused in the atomizing net 2, and under the action of heat provided by the ignition plug 1, the alcohol-based fuel diffused in the atomizing net 2 quickly absorbs the heat and is quickly evaporated in the auxiliary oil way channel 20; meanwhile, first-stage air tangentially enters the auxiliary oil path channel 20 from the first-stage swirl hole 8 through the annular air path 21 to perform auxiliary atomization and combustion supporting on alcohol-based fuel, and the alcohol-based fuel in the auxiliary oil path channel 20 is atomized and ignited under the action of tangential shear force of the air to form a rotating flame sprayed out through the auxiliary oil path fuel nozzle 6, so that the pilot flame can be turned on duty when the fuel in the main oil path is ignited. The alcohol-based fuel at the inlet end 11 of the main oil way flows in the coil pipe 9 for a plurality of times in a rotational flow mode, flows into the main oil way convergence channel 12 in a delayed mode, is sprayed out from the main oil way fuel nozzle 13, at the moment, the alcohol-based fuel of the coil pipe 9 is fed in a delayed mode, so that stable flame is formed at the auxiliary oil way fuel nozzle 6 and then is sprayed out, preheating and ignition of the flame of the auxiliary oil way are received, and the stability of combustion of the fuel of the main oil way can be. A secondary swirl hole 15 and a tertiary swirl hole 16 are processed on the burner shell 5, residual air flows through the secondary swirl hole 15 and the tertiary swirl hole 16 to respectively support the combustion of alcohol-based fuel sprayed from the primary and secondary oil circuit fuel nozzles 6, and a backflow area can be formed to ensure the combustion stability of primary flame due to the combustion stabilizing principle of swirl combustion; through the graded feeding of air, the effect of the mixing process is better, the mixing is more uniform, thereby being beneficial to the stability of the combustion process, the uniform distribution of the outlet temperature and the reduction of NOx emission.
Claims (10)
1. The utility model provides a miniature gas turbine combustor of multistage whirl which characterized in that: the ignition device comprises an ignition plug (1), an atomization net (2), a reference piece (3), a main oil way partition plate (4) and a shell (5) which are coaxially arranged, wherein the ignition plug (1) is a variable-diameter cylindrical section, the reference piece (3) is sleeved on the ignition plug (1), an annular cavity is formed between the middle part of the reference piece (3) and the ignition plug (1), and a plurality of axial guide vanes (17) are processed on the outer surface of the reference piece (3);
the atomization net (2) is of a hollow cylindrical structure and is arranged in an annular cavity between the reference piece (3) and the ignition plug (1), an annular gap is formed between the inner surface of the atomization net (2) and the ignition plug (1),
the main oil way partition plate (4) comprises a partition plate main body (10) and a coil pipe (9) coaxially coiled on the partition plate main body (10), the partition plate main body (10) is of a hollow cylindrical structure and is sleeved on the reference piece (3), one end part, far away from a combustion chamber, of the shell (5) is coaxially sleeved on the main oil way partition plate (4), and a plurality of axial guide vanes (17) are positioned between the partition plate main body (10) and the reference piece (3) to form a root air flow channel;
one end part of the reference piece (3) close to the combustion chamber is a tapered section, an auxiliary oil path convergence channel (7) is formed between the tapered section and the ignition plug (1), one end of the auxiliary oil path convergence channel (7) close to the combustion chamber is an auxiliary oil path fuel nozzle (6),
a main oil path convergence channel (12) is formed between the inner surface of the middle part of the shell (5) and the outer surface of the tapered section of the reference part (3), a main oil path fuel nozzle (13) is arranged at one end of the main oil path convergence channel (12) close to the combustion chamber,
one end of the coil pipe (9) is a main oil way inlet end (11) and extends to the outside of the shell (5), the other end of the coil pipe (9) is an outlet end and is arranged close to a main oil way convergence channel (12), an auxiliary oil way pipe section (14) is inserted on the reference part (3), the auxiliary oil way pipe section (14) is far away from the combustion chamber and the end part of the auxiliary oil way pipe section (14) is communicated with an annular cavity where the atomization net (2) is positioned,
a plurality of primary swirl holes (8) are circumferentially processed at positions, close to the reducing section, on the reference part (3), the middle part of the shell (5) is a reducing section (18), a plurality of secondary swirl holes (15) and a plurality of tertiary swirl holes (16) are processed on the shell, the secondary swirl holes (15) are arranged close to the main oil way partition plate (4), and the tertiary swirl holes (16) are arranged close to the combustion chamber.
2. The multi-stage cyclonic micro gas turbine combustor as claimed in claim 1, wherein: one end part of the reference piece (3) far away from the combustion chamber is in threaded connection with the ignition plug (1), and the outer surface of the atomization net (2) is in close contact with the inner surface of the reference piece (3) and one end of the atomization net (2) is in close contact with a shaft shoulder on the ignition plug (1).
3. The multi-stage swirling micro gas turbine combustor of claim 1 or 2, wherein: the number of circles of coil pipe (9) is 4 ~ 10 circles, and the internal diameter and the external diameter of coil pipe are 1 ~ 3mm, and the whirl direction is the same with the direction of rotation that air got into one-level whirl hole (8) in coil pipe (9).
4. The multi-stage cyclonic micro gas turbine combustor as claimed in claim 3, wherein: the number of the axial guide vanes (17) is 4-8, the axial guide vanes are uniformly distributed along the circumferential direction of the reference piece (3), and the axial length of each axial guide vane (17) is smaller than or equal to 2/3 of the axial length of the partition plate main body (10).
5. The multi-stage cyclonic micro gas turbine combustor as claimed in claim 4, wherein: the quantity of one-level whirl hole (8) is 8 ~ 12, and along benchmark piece (3) circumference equipartition, and one-level whirl hole (8) are 1 ~ 3 mm's of length of side rectangular hole, and the projection of the contained angle on the section between the axis of every one-level whirl hole (8) and benchmark piece (3) axis is 30 ~ 60.
6. The multi-stage cyclonic micro gas turbine combustor as claimed in claim 5, wherein: the number of second grade whirl hole (15) is 8 ~ 16, and along shell (5) circumference equipartition, and second grade whirl hole (15) are diameter 1 ~ 3 mm's round hole.
7. The multi-stage cyclonic micro gas turbine combustor as claimed in claim 6, wherein: the quantity of tertiary whirl hole (16) is 16 ~ 24, and along shell (5) circumference equipartition, and tertiary whirl hole (16) are 1 ~ 3mm rectangular hole of length of side, and the projection of the contained angle between the axis of every tertiary whirl hole (16) and the casing axis on the section is 30 ~ 60.
8. The multi-stage cyclonic micro gas turbine combustor as claimed in claim 4, 5, 6 or 7, wherein: the central axes of the primary swirl hole (8), the secondary swirl hole (15) and the tertiary swirl hole (16) are arranged in the same direction.
9. The multi-stage cyclonic micro gas turbine combustor of claim 8, wherein: the inner diameter and the outer diameter of the main oil way inlet end (11) are both 1-3 mm, and the inner diameter and the outer diameter of the auxiliary oil way pipe section (14) are both 0.5-1.5 mm.
10. The multi-stage cyclonic micro gas turbine combustor as claimed in claim 1, 2, 4, 5, 6, 7 or 9, wherein: the diameter distance between the inner ring and the outer ring of the main oil path fuel nozzle (13) and the diameter distance between the inner ring and the outer ring of the auxiliary oil path fuel nozzle (6) are both 0.25-1 mm.
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| CN111207413B (en) | 2024-04-26 |
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