CN112923395A - Double-rotational-flow multipoint injection head structure with non-rotation function - Google Patents
Double-rotational-flow multipoint injection head structure with non-rotation function Download PDFInfo
- Publication number
- CN112923395A CN112923395A CN202110201295.9A CN202110201295A CN112923395A CN 112923395 A CN112923395 A CN 112923395A CN 202110201295 A CN202110201295 A CN 202110201295A CN 112923395 A CN112923395 A CN 112923395A
- Authority
- CN
- China
- Prior art keywords
- wall
- swirl
- air
- supply part
- swirler
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Images
Classifications
-
- 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
-
- 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
-
- 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
Abstract
The invention relates to a double-rotational flow multipoint injection head structure with non-rotation, belonging to the field of combustion chambers of gas turbines; the device comprises four parts which are arranged in a concentric circle manner, namely an inner side oil supply part, an inner side air supply part, an outer side oil supply part and an outer side air supply part from inside to outside in sequence; the outer gas supply part comprises outer swirler vanes and the outer wall of the combustion chamber head; the outer wall of the head part of the combustion chamber is coaxially arranged at the periphery of the outer wall of the cooling atomization air channel to form an outer side rotational flow non-rotational mixing cavity; the outer cyclone blades are coaxially fixed on the outer wall of the cooling atomization air channel, and the inlet is an outer cyclone air inlet; the outer peripheral surface of the outer swirler vane is connected with the outer wall of the combustion chamber head to form an outermost non-swirl air channel. The swirling flow of the air supply part at the outer side is combined with the non-swirling air, the two air flows shear the fuel oil at the same time, further crushing is carried out to form smaller liquid drops, the fuel oil SMD is reduced, and the fuel oil atomization effect is better than that of the non-swirling air.
Description
Technical Field
The invention belongs to the field of combustion chambers of gas turbines, and particularly relates to a double-cyclone multipoint injection head structure with non-cyclone.
Background
In recent years, with the continuous development of the air transportation industry, people have higher requirements on an aircraft engine, and the requirements on higher thrust-weight ratio, lower oil consumption rate and less pollution emission are met. For military aircraft engines, better maneuverability is required, so that the military aircraft engines have more advantages in combat, and therefore the military engines mainly seek high temperature rise; for Civil engines, as the demand for environmental protection is increasing, the pollution emission of the aircraft engine by International Civil Aviation Organization (ICAO for short) is becoming stricter, and the requirements for the generation of carbon monoxide (CO), Unburned Hydrocarbon (UHC), nitrogen oxide (NOx) and smoke are becoming higher, so that the Civil engines need to reduce the emission continuously and realize low pollution.
The design of the conventional combustion chamber can not meet the requirements of people on the performance of the aircraft engine at present, so that a novel combustion organization needs to be developed. At present, staged combustion, lean oil premixing and pre-evaporation (LPP), lean oil direct injection (LDI), rich oil combustion-quenching-lean oil combustion (RQL), variable geometry combustion technology, low oxygen combustion technology and the like are mainly used in the combustion technology, lean oil premixing and pre-evaporation technology is adopted in main combustion stages of patents US8607575, US8171735, US6363726 and the like applied by foreign GE companies aiming at LPP combustion organization technology, and low pollution combustion chamber schemes that lean oil premixing is adopted in main combustion stages are also proposed in units such as domestic North aviation and industry and Heat institute. The staged combustion technology in the schemes can well solve the problem of mixing of fuel and air, the structure can solve the basic contradiction that a high-temperature combustion chamber is in lean flameout under a slow vehicle state and invisible exhaust and smoke are generated under a large working condition, and the structure has the advantages of high temperature rise, high heat capacity, high efficiency, compact structure, low pollution emission and the like, and has a very wide application prospect.
The central staged combustion chamber mainly meets the requirements of high temperature rise and low pollution through staged oil supply and zoned combustion, a patent CN201710608804.3 applied by a combustion team of northwest university in 2017 designs a low-emission combustion chamber based on an LDI concept, a duty stage adopts a single-stage swirler to match a single-oil-way centrifugal nozzle to realize the diffusion combustion of the duty stage, and a main combustion stage adopts a swirler and a coaxial downstream air atomizing nozzle to perform the diffusion combustion. Compared with the combustion chamber, the multi-point jet combustion chamber with the non-cyclone, disclosed by the invention, has the advantages that the direct-injection diffusion combustion technology is utilized, and the non-cyclone flow is added at the outermost side, so that the problem of higher temperature of the flame cylinder wall is effectively solved, the main combustion grade oil gas is completely and uniformly mixed due to the non-cyclone flow, the hot point index is reduced, and the combustion efficiency is improved.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides a double-rotational-flow multipoint injection head structure with non-rotation, which applies a direct injection diffusion combustion technology and takes aviation kerosene as fuel. The technology of combining rotational flow and non-rotational air flow and carrying out diffusion combustion by a plurality of nozzles is adopted, so that not only is stable combustion facilitated, but also the strength of the rotational flow at the head part can be effectively changed, the shearing action of the rotational flow on an oil film is changed, the atomization effect is improved, and the performance of a combustion chamber is improved to a certain extent; on the other hand, the non-cyclone air at the outermost side of the head can solve the problem of higher temperature of the flame tube wall, an air film is formed between the central high-temperature area and the wall surface of the flame tube, and the temperature of the wall surface is effectively reduced, so that the service life of the flame tube is prolonged.
The technical scheme of the invention is as follows: the utility model provides a take non-swirl's double-swirl multi-point to spray head structure which characterized in that: the device comprises an inner side gas supply part 1, an inner side oil supply part 2, an outer side gas supply part 3 and an outer side oil supply part 4, wherein the four parts are arranged in a concentric circle manner and sequentially form the inner side oil supply part 2, the inner side gas supply part 1, the outer side oil supply part 4 and the outer side gas supply part 3 from inside to outside;
the inner oil supply part 2 comprises a central swirler 11;
the inner side air supply part 1 comprises an inner side rotational flow air inlet 5, inner side swirler vanes 6, an inner side swirler inner wall 7 and an inner side swirler outer wall 8; the inner swirler vanes 6 are coaxially arranged between an inner swirler wall 7 and an inner swirler outer wall 8, an inner air channel is formed between the inner swirler wall 7 and the inner swirler outer wall 8, one end of the central centrifugal nozzle is a convergent section, the other end of the central centrifugal nozzle is a straight section, and an outer port of the straight section is an inner swirling air inlet 5;
the outer oil supply part comprises an oil collecting ring inlet 13, an oil collecting ring cavity 14, an oil collecting ring outer wall 15, an oil collecting ring inner wall 16, an oil collecting ring support rib 17 and a direct injection nozzle 18; the outer wall 15 of the oil collecting ring is coaxially fixed on the periphery of the outer wall 8 of the inner swirler through an oil collecting ring support rib 17, the outer peripheral surface of the outer wall 8 of the inner swirler serves as an inner wall 16 of the oil collecting ring, and an oil collecting ring cavity 14 is formed between the outer wall and the inner wall; the outer side port of the oil collecting ring cavity 14 is an oil collecting ring inlet 13, and a plurality of direct injection nozzles 18 are uniformly distributed at the outlet of the oil collecting ring cavity along the circumferential direction;
the outer wall 21 of the cooling atomizing air channel is coaxially fixed on the periphery of the outer wall 15 of the oil collecting ring through a cooling atomizing air channel supporting rib to form a cooling atomizing air channel, so that cooling gas is provided for the head part, and meanwhile, the atomization and evaporation of fuel oil are promoted;
the outer air supply part 3 comprises an outer rotational flow air inlet 23, outer rotational flow blades 25, a combustion chamber head outer wall 30 and an outermost non-rotational flow air inlet 27; the outer wall 30 of the head part of the combustion chamber is coaxially arranged at the periphery of the outer wall 21 of the cooling atomization air channel to form an outer rotational flow non-rotational mixing cavity 31, one end of the outer rotational flow non-rotational mixing cavity 31, which is positioned at the central centrifugal nozzle, is a convergent section, the other end of the outer rotational flow non-rotational mixing cavity is a straight section, and the port at the outer side of the straight section is an air inlet; the outer swirler vanes 25 are coaxially fixed on the outer wall 21 of the cooling atomization air channel near the air inlet, and the inlet is an outer swirling air inlet 23; the outer peripheral surface of the outer swirler vane 25 is connected to the combustor head outer wall 30 via an outer non-swirl passage support rib 36 to form an outermost non-swirl air passage, the inlet of which is the outermost non-swirl air inlet 27.
The further technical scheme of the invention is as follows: the inner swirler vanes 6 adopt axial flow straight vanes, the swirling angle is 30-60 degrees, and the number of the vanes is 6-20.
The further technical scheme of the invention is as follows: the ratio of the amount of swirling air flowing in from the outer swirling air inlet 23 to the amount of non-swirling air flowing in from the outer non-swirling air inlet 27 is 2: 1.
The further technical scheme of the invention is as follows: the outermost non-swirl air inlet 27 is located outermost of the flame barrel head.
The further technical scheme of the invention is as follows: the number of the direct nozzles 18 of the outer oil supply part is integral multiple of the outer swirler vanes 25.
The further technical scheme of the invention is as follows: the number of the direct injection nozzles 18 is even.
The further technical scheme of the invention is as follows: the head structure has a combustion equivalence ratio of 0.6 to 0.8.
Advantageous effects
The invention has the beneficial effects that: the invention relates to a double-rotational flow multipoint injection head scheme with non-rotation, which mainly comprises an inner side gas supply part, an inner side oil supply part, an outer side gas supply part and an outer side oil supply part. A part of airflow enters from the inner side rotational flow channel, is directly mixed with fuel injected by the centrifugal nozzle positioned in the center, and forms a stable central backflow area at the downstream of the head part; a part of air current gets into and mixes from the non-passageway of revolving the passageway in outside whirl passageway and the outside respectively, gets into the flame tube from mixing section export and participates in the burning, and the existence of non-revolving the passageway can make whirl intensity change to can change the shearing effect of whirl to the oil film, and then change the atomization effect of nozzle, make combustion performance obtain promoting, the size that the existence of non-revolving the passageway can effective control backward flow district simultaneously makes high temperature zone and flame tube wall have a certain distance, reduces flame tube wall temperature. Therefore, the invention can effectively improve the performance of the combustion chamber and reduce the temperature of the flame tube wall to a certain extent, thereby prolonging the service life of the combustion chamber of the gas turbine.
Compared with the prior art, the invention has the following advantages:
1. the outside air supply part adopts a mode of combining swirl and non-swirl air to control the swirl strength. Two air currents shear the fuel oil simultaneously, and liquid forms liquid mass, liquid silk under the combined action of aerodynamic force, liquid surface tension and viscous force to further the breakage forms littleer liquid droplet, and fuel oil SMD reduces, and fuel oil atomization effect is better than not having nonrotating air.
2. The non-cyclone air is positioned at the outermost side of the outer air supply part, the problem that the temperature of the flame tube wall is too high is mainly solved, a layer of gas barrier is formed between the flame tube and the main combustion area by a part of air flow, and the flame tube on the wall surface is in high temperature for a long time to protect the flame tube.
3. The number of the direct injection nozzles is integral multiple of the outer swirler vanes, each direct injection nozzle corresponds to each outer swirler vane, fuel sprayed by a certain nozzle, namely a certain part of swirling air, corresponds to form a shearing action to carry out an atomization process, the air and the fuel are uniformly mixed, and the outlet temperature distribution is improved.
4. The equivalence ratio of the whole head combustion area is lean oil, so that the discharge of pollutants at an outlet is reduced while flame stability is ensured.
Drawings
FIG. 1 is a schematic view of a combustor head configuration of the present invention;
FIG. 2 is a schematic view and a sectional view of the inner side structure of the head of the combustion chamber of the present invention;
FIG. 3 is a schematic view and a sectional view of the outer side structure of the head of the combustion chamber of the present invention;
description of reference numerals: 1-an inner air supply section, 2-an inner oil supply section, 3-an outer air supply section, 4-an outer oil supply section, 5-an inner swirl air inlet, 6-inner swirler vanes, 7-an inner air channel wall, 8-an inner air channel outer wall, 9-an inner air channel flat section, 10-an inner air channel converging section, 11-a central centrifugal nozzle, 12-a centrifugal nozzle outlet, 13-an oil collecting ring inlet, 14-an oil collecting ring cavity, 15-an oil collecting ring outer wall, 16-an oil collecting ring inner wall, 17-an oil collecting ring support rib, 18-a direct spray nozzle, 19-a cooling atomizing air inlet, 20-a cooling atomizing air channel inner wall, 21-a cooling atomizing air channel outer wall, 22-a cooling atomizing air channel support rib, 23-outer swirl air inlet, 24-outer swirl air channel inner wall, 25-outer swirl vane, 26-outer swirl air channel outer wall, 27-outermost non-swirl air inlet, 28-outermost non-swirl air channel inner wall, 29-outermost non-swirl air channel outer wall, 30-combustion chamber head outer wall, 31-outer swirl non-swirl mixing chamber, 32-outer swirl non-swirl mixing straight section, 33-outer swirl non-swirl mixing convergent section, 34-cooling atomizing air outlet baffle, 35-cooling atomizing air outlet baffle cooling hole, 36-outer non-swirl channel support rib.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 1, the embodiment of the present invention provides a non-swirl double-swirl multi-point injection head solution using aviation kerosene as fuel, comprising an inner gas supply part 1, an inner gas supply part 2, an outer gas supply part 3, and an outer gas supply part 4, wherein the inner gas supply part 1 is swirl gas, the gas generates a larger backflow zone through an axial flow swirler to stabilize flame, and the inner gas supply part 2 is a centrifugal nozzle; the outer air supply part 3 is divided into outer swirling air and non-swirling air, and the outer swirling air and the non-swirling air are mixed and then meet fuel oil sprayed from a plurality of direct injection nozzles of the outer oil supply part 4 to be stably combusted.
The inner air accounts for about 20-40% of the total combustion air amount, flows in from the inner side of the head of the combustion chamber, only the inner part works under the working condition of slow vehicle, the local equivalence ratio is 1-3 at the moment, the combustion is rich, and the flame stability and lean flameout under the working condition of slow vehicle can be ensured; along with the continuous increase of working conditions, the thrust required by the engine is also increased, the required fuel flow and gas flow are increased, so that the inner part and the outer part need to work simultaneously, the average equivalence ratio of the whole head is 0.6-0.8, the flame stability is ensured, and the pollution emission of the whole combustion chamber is low.
As shown in fig. 2, the inside air supply part 1 is composed of an inside swirling air inlet 5, inside swirler vanes 6, an inside air passage inner wall 7, an inside air passage outer wall 8, an inside air passage straight section 9, and an inside air passage converging section 10. The inner side air channel inner wall 7 and the inner side swirler outer wall 8 form an inner side air channel, and the inner side swirler vanes 6 are coaxially arranged between the inner side swirler inner wall 7 and the inner side swirler outer wall 8; one end of the central centrifugal nozzle installed in the inner side air channel is a convergent section, the other end of the central centrifugal nozzle is a straight section, and an outer side port of the straight section is an inner side rotational flow air inlet 5; the gas enters from the axial swirl air inlet 5 and flows downstream along the swirl vanes, after which a relatively large stable central recirculation zone is created. The inner oil supply part 4 consists of a centrifugal nozzle 11 positioned in the center, when the centrifugal force is greater than the surface tension of the liquid, the kerosene is gradually broken into smaller liquid threads and liquid drops under the action of the centrifugal force, and the diameters of the liquid drops are gradually reduced, so that the evaporation and the atomization of the fuel oil are facilitated. The gas with rotational flow coming out of the cyclone directly contacts with the fuel oil sprayed from the nozzle, the kerosene is further crushed by the shearing action of the gas, the particle size is further reduced, the gas and liquid drops are stably and efficiently combusted in a backflow area, and the formed central backflow area is an area with higher oil gas in the flame tube and is also a high-temperature area in the flame tube, so that if the backflow area is too large, the temperature of the flame tube wall is too high, the high-temperature limit of the material is reached, the service life of the whole combustion chamber is shortened, axial flow type straight blades are adopted as the blades 6 of the cyclone, the rotational flow angle is 30-60 degrees, and the number of the blades is 6-20.
As shown in FIG. 2, the outer oil supply part is composed of an oil collecting ring inlet 13, an oil collecting ring cavity 14, an oil collecting ring inner wall 15, an oil collecting ring outer wall 16, an oil collecting ring support rib 17 and a direct injection nozzle 18. The inner and outer walls 15 and 16 of the oil collecting ring form an oil collecting ring chamber 14 through which oil is supplied by the oil supply rod and further supplied to the direct injection nozzles 18, and oil collecting ring support ribs 17 for the fixed mounting of the oil collecting ring.
As shown in fig. 2, the outer wall 16 of the oil collecting ring as the cooling atomization air inner wall 20 and the cooling atomization air channel outer wall 21 form a head cooling atomization air channel, and air enters from the cooling atomization air inlet 19 and flows out from the cooling holes 35 of the cooling atomization air outlet baffle plate to provide cooling air for the head and promote atomization and evaporation of fuel oil.
As shown in FIG. 3, the outer air supply section 3 is composed of an outer swirl air inlet 23, an outer swirl air passage inner wall 24, outer swirler vanes 25, an outer swirl air passage outer wall 26, an outermost non-swirl air inlet 27, an outermost non-swirl air passage inner wall 28, an outermost non-swirl air passage outer wall 29, a combustor head outer wall 30, an outer swirl non-swirl mixing chamber 31, an outer swirl non-swirl air mixing straight section 32, an outer swirl non-swirl air mixing converging section 33, and outer non-swirl passage support ribs 36. The outer peripheral surface of the outer wall 21 of the cooling atomizing air channel is used as the inner wall 24 of the outer rotational flow air channel, the outer wall 30 of the head part of the combustion chamber is coaxially arranged at the periphery of the outer wall 21 of the cooling atomizing air channel to form an outer rotational flow non-rotational mixing cavity 31, one end of the outer rotational flow non-rotational mixing cavity 31, which is positioned at the central centrifugal nozzle, is a outer rotational flow non-rotational flow air mixing convergent section 33, the other end of the outer rotational flow non-rotational flow air mixing straight section 32, and the outer port of the straight section is an air inlet; the outer swirler vanes 25 are coaxially fixed on the outer wall 21 of the cooling atomization air channel near the air inlet, and the inlet is an outer swirling air inlet 23; the outer peripheral surface of the outer swirler vane 25 serves as an outermost non-swirl air passage inner wall 28, and is connected to the combustion chamber head outer wall 30 by an outer non-swirl passage support rib 36, and the inner peripheral surface of the combustion chamber head outer wall 30 serves as an outermost non-swirl air passage outer wall 29. The inner wall 24 and the outer wall 26 of the outer rotational flow air channel form an outer rotational flow channel, the inner wall 28 and the outer wall 29 of the non-rotational flow air channel form an outer non-rotational flow channel, air flows respectively flow through the outer rotational flow air inlet 23 and the non-rotational flow air inlet 27, the air ratio of the outer rotational flow air inlet to the non-rotational flow air inlet is 2:1, then mixing is carried out in the rotational flow non-rotational flow mixing cavity 31 to eliminate the tail track generated by the blades 25, the rotational flow non-rotational flow mixing section is divided into a straight section 32 and a convergent section 33, and the convergent section can effectively achieve flame tempering and spontaneous combustion on. And the airflow flows out of the mixing section, enters the flame tube and participates in combustion. The existence of the non-cyclone gas flow in the outside gas flow can control the strength of the cyclone flow at the position, thereby controlling the breaking strength of liquid drops, achieving the effective control of combustion performance, and the existence of the outside non-cyclone gas can lead a gas layer to be arranged between a central reflux area, namely a high-temperature area, and the wall surface of the flame tube, thereby reducing the wall temperature, prolonging the service life of the flame tube, also improving the service life of the combustion chamber, leading the material requirement of the flame tube to be less strict, and further reducing the manufacturing cost. The outer swirler and the central swirler have the same rotating direction, so that the interaction and the mutual influence of the outer swirler and the central swirler can be reduced. The outer swirler vanes 25 adopt axial flow straight vanes, the swirl angle is 40-75 degrees, and the number of the vanes is 6-20.
The working process of the invention is as follows:
the invention designs a double-rotational-flow multipoint injection head scheme with non-rotation. Part of the airflow enters from the inner side rotational flow channel, is directly mixed with the fuel injected by the nozzle, and forms a stable central backflow area at the downstream of the head part; and a part of airflow enters the flame tube from the outer swirl channel and the outermost non-swirl channel respectively and participates in combustion. The structure can ensure stable combustion and lean blowout under various working conditions, and can reduce pollution emission, and the existence of non-cyclone gas can lead a layer of gas separation to be arranged between the central combustion area and the flame tube, thereby avoiding the flame tube from being in a high-temperature combustion area for a long time.
The scheme of the double-rotational-flow multi-point injection head with the non-rotation function can improve the combustion performance, effectively control the expansion size of the backflow area, enable the high-temperature area to have a certain distance with the wall surface of the flame tube, and effectively reduce the wall temperature of the flame tube, thereby prolonging the service life of the flame tube and reducing the material requirements on the flame tube.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (7)
1. The utility model provides a take non-swirl's double-swirl multi-point to spray head structure which characterized in that: the oil supply device comprises an inner side air supply part (1), an inner side oil supply part (2), an outer side air supply part (3) and an outer side oil supply part (4), wherein the four parts are arranged in a concentric circle manner and sequentially form the inner side oil supply part (2), the inner side air supply part (1), the outer side oil supply part (4) and the outer side air supply part (3) from inside to outside;
the inner oil supply portion (2) comprises a central swirler (11);
the inner side air supply part (1) comprises an inner side rotational flow air inlet (5), inner side swirler vanes (6), an inner side swirler inner wall (7) and an inner side swirler outer wall (8); the inner swirler vanes (6) are coaxially arranged between the inner swirler wall (7) and the outer swirler wall (8), an inner air channel is formed between the inner swirler wall (7) and the outer swirler wall (8), one end of the central centrifugal nozzle is a convergent section, the other end of the central centrifugal nozzle is a straight section, and the outer port of the straight section is an inner swirling air inlet (5);
the outer oil supply part comprises an oil collecting ring inlet (13), an oil collecting ring cavity (14), an oil collecting ring outer wall (15), an oil collecting ring inner wall (16), an oil collecting ring support rib (17) and a direct injection nozzle (18); the outer wall (15) of the oil collecting ring is coaxially fixed on the periphery of the outer wall (8) of the inner swirler through an oil collecting ring support rib (17), the outer peripheral surface of the outer wall (8) of the inner swirler serves as the inner wall (16) of the oil collecting ring, and an oil collecting ring cavity (14) is formed between the outer wall and the inner wall; the outer end opening of the oil collecting ring cavity (14) is an oil collecting ring inlet (13), and a plurality of direct nozzles (18) are uniformly distributed at the outlet along the circumferential direction;
the periphery of the outer wall (15) of the oil collecting ring is coaxially fixed with a cooling atomization air channel outer wall (21) through a cooling atomization air channel supporting rib to form a cooling atomization air channel, so that cooling gas is provided for the head part, and meanwhile, the atomization and evaporation of fuel oil are promoted;
the outer air supply part (3) comprises an outer rotational flow air inlet (23), outer rotational flow blades (25), a combustion chamber head outer wall (30) and an outermost non-rotational flow air inlet (27); the outer wall (30) of the head part of the combustion chamber is coaxially arranged at the periphery of the outer wall (21) of the cooling atomization air channel to form an outer rotational flow non-rotational mixing cavity (31), one end, positioned on the central centrifugal nozzle, of the outer rotational flow non-rotational mixing cavity (31) is a convergent section, the other end of the outer rotational flow non-rotational mixing cavity is a straight section, and an outer port of the straight section is an air inlet; the outer swirler vanes (25) are coaxially fixed on the outer wall (21) of the cooling atomization air channel close to the air inlet, and the inlet of the outer swirler vanes is an outer swirler air inlet (23); the outer peripheral surface of the outer swirler vane (25) is connected with the outer wall (30) of the combustion chamber head through an outer non-swirl channel supporting rib (36) to form an outermost non-swirl air channel, and the inlet of the outermost non-swirl air channel is an outermost non-swirl air inlet (27).
2. The dual swirl multi-point injection head structure with non-swirl of claim 1, wherein: the inner swirler vanes (6) adopt axial flow straight vanes, the swirling angle is 30-60 degrees, and the number of the vanes is 6-20.
3. The dual swirl multi-point injection head structure with non-swirl of claim 1, wherein: the ratio of the amount of swirling air flowing in from the outer swirling air inlet (23) to the amount of non-swirling air flowing in from the outer non-swirling air inlet (27) is 2: 1.
4. The dual swirl multi-point injection head structure with non-swirl of claim 1, wherein: the outermost non-swirl air inlet (27) is located outermost of the flame tube head.
5. The dual swirl multi-point injection head structure with non-swirl of claim 1, wherein: the number of the direct nozzles (18) of the outer oil supply part is integral multiple of the number of the outer swirler vanes (25).
6. The dual swirl multi-point injection head structure with non-swirl of claim 1, wherein: the number of the direct injection nozzles (18) is even.
7. The dual swirl multi-point injection head structure with non-swirl of claim 1, wherein: the head structure has a combustion equivalence ratio of 0.6 to 0.8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110201295.9A CN112923395A (en) | 2021-02-23 | 2021-02-23 | Double-rotational-flow multipoint injection head structure with non-rotation function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110201295.9A CN112923395A (en) | 2021-02-23 | 2021-02-23 | Double-rotational-flow multipoint injection head structure with non-rotation function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112923395A true CN112923395A (en) | 2021-06-08 |
Family
ID=76170469
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110201295.9A Withdrawn CN112923395A (en) | 2021-02-23 | 2021-02-23 | Double-rotational-flow multipoint injection head structure with non-rotation function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112923395A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114646077A (en) * | 2022-03-23 | 2022-06-21 | 西北工业大学 | Air atomizing nozzle with annular cavity opening |
| CN115218217A (en) * | 2022-06-16 | 2022-10-21 | 北京航空航天大学 | Main combustion stage head of central staged combustion chamber adopting porous multi-angle oil injection ring structure |
-
2021
- 2021-02-23 CN CN202110201295.9A patent/CN112923395A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114646077A (en) * | 2022-03-23 | 2022-06-21 | 西北工业大学 | Air atomizing nozzle with annular cavity opening |
| CN114646077B (en) * | 2022-03-23 | 2023-08-11 | 西北工业大学 | Air atomizing nozzle with holes in annular cavity |
| CN115218217A (en) * | 2022-06-16 | 2022-10-21 | 北京航空航天大学 | Main combustion stage head of central staged combustion chamber adopting porous multi-angle oil injection ring structure |
| CN115218217B (en) * | 2022-06-16 | 2023-06-16 | 北京航空航天大学 | Main combustion stage head of central staged combustion chamber adopting porous multi-angle oil injection ring structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102032598B (en) | Circumferentially graded low-pollution combustion chamber with multiple middle spiral-flow flame stabilizing stages | |
| CN110657452B (en) | Low-pollution combustion chamber and combustion control method thereof | |
| CN206281000U (en) | Pre-combustion grade uses the low emission combustor of double-deck axial swirler | |
| CN108561897B (en) | Partial premixing and pre-evaporating ultralow emission combustion chamber for enhancing oil-gas mixing | |
| CN111059574B (en) | Swirl cup type dual-fuel air atomizing nozzle structure | |
| CN103017203B (en) | The fractional combustion chamber of a kind of main combustion stage loopful air inlet | |
| CN102889617B (en) | Premixing and pre-evaporation combustor for main combustion stage using radial film formation | |
| CN108253455B (en) | Premixing and pre-evaporating ultra-low emission combustion chamber head and combustion chamber thereof | |
| CN107726364B (en) | Evaporation tube combustion chamber | |
| CN102200291A (en) | Pneumatic primary level graded low-pollution combustion chamber | |
| CN107143880B (en) | Lean oil multi-point direct injection head for low-pollution combustion chamber of gas turbine | |
| CN113324262B (en) | Coaxial staged gas fuel combustor head for low emission gas turbine | |
| CN109084330A (en) | The loopful combustion chamber that a kind of pass cyclone and pass eddy flow type are constituted | |
| CN108626749B (en) | 7-point lean oil direct injection head for low-pollution combustion chamber | |
| CN108954388A (en) | A kind of multiple spot unit directly sprays fractional combustion room | |
| CN112923395A (en) | Double-rotational-flow multipoint injection head structure with non-rotation function | |
| CN102242940A (en) | Three-stage structured pre-mixing and pre-evaporating low-pollution combustor | |
| CN111174233B (en) | Central-grading lean-oil premixed low-pollution combustion chamber | |
| CN109059045A (en) | A kind of poor premixed swirl nozzle of gaseous fuel low pollution combustor and loopful combustion chamber | |
| CN114608032B (en) | Combustor with widened stability boundary | |
| CN108844097B (en) | Low-pollution combustion chamber for multi-point lean oil direct injection | |
| CN109708148B (en) | Gas turbine combustor doublestage radial swirler | |
| CN107676816B (en) | Evaporating pipe with built-in swirler at outlet, combustion chamber and engine | |
| CN215336468U (en) | Double-rotational-flow multipoint injection head with non-rotation function | |
| CN113048513B (en) | Multistage oil spout hole center cone integration afterburner |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20210608 |