CN110925794A - Discrete multi-point rotational flow pressure atomizing nozzle, combustion chamber head and combustion chamber - Google Patents
Discrete multi-point rotational flow pressure atomizing nozzle, combustion chamber head and combustion chamber Download PDFInfo
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- CN110925794A CN110925794A CN201911234823.XA CN201911234823A CN110925794A CN 110925794 A CN110925794 A CN 110925794A CN 201911234823 A CN201911234823 A CN 201911234823A CN 110925794 A CN110925794 A CN 110925794A
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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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- 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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- 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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
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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
Abstract
The invention relates to a discrete multipoint rotational flow pressure atomizing nozzle which comprises an oil collecting cavity (45), a rotational flow core (47) and a nozzle spray hole (52), wherein a tangential groove (50) is formed in the rotational flow core (47), and oil flows into the cavity of the rotational flow core (47) and flows out of the tangential groove (50); the combustor head is characterized in that a main combustion stage tongue piece (44) is arranged between a main combustion stage first-stage axial swirler (34) and a main combustion stage second-stage inclined radial swirler (37); the main combustion stage adopts a lean oil partially premixed and pre-evaporated combustion technology, fuel oil is sprayed out in a rotational flow mode through the main nozzle, mixing with air is enhanced, meanwhile, the inclined V-shaped slotted tongue piece is arranged, airflow turbulence is increased, oil-gas mixing is enhanced, uniform premixed gas is obtained, and emission of pollutants such as NOx, UHC, CO and smoke particles can be greatly reduced.
Description
Technical Field
The invention belongs to the field of aero-engines, and relates to a discrete multipoint swirl pressure atomizing nozzle, a combustion chamber head and a combustion chamber.
Background
The international civil aviation organization promulgates the regulations of 'environmental protection standard' and 'aeroengine emission' in the 80 s, is continuously revised and perfected, and currently, the CAEP/8 emission standard is started to be executed. Various large aircraft engine companies and research institutions research on controlling pollutant emissions as an important topic, and low-emission combustion technology is one of the most important research contents for civil aircraft engines. As the pollution emission is the mandatory requirement of the airworthiness evidence obtaining on the civil engine, a plurality of international famous aviation engine companies in Europe and America implement the advanced civil engine development plan aiming at the increasingly strict emission requirement, and master the key technology of the low-emission combustion chamber. The combustion chamber developed by GE company adopts the latest double ring premixed swirl (TAPS) organization combustion technology, and is used for the low-emission combustion chamber of the GEnx engine, and the NOx pollution emission is about 50 percent lower than CAEP/8; the TALON X combustion chamber developed by adopting RQL technology by the PW company is applied to a PW1100G engine, and the NOx pollution emission is about 43 percent lower than CAEP/8; RR company adopts LDIS low pollution combustion chamber developed by ANTLE plan, and NOx pollution emission of the LDIS low pollution combustion chamber is reduced by about 33% compared with CAEP/8 standard.
The TAPS combustion technology of GE company has applied for a plurality of U.S. patents, and the low-emission combustor head patents with the patent numbers of US006354072B1, US006381964B1, US006389815B1 and the like propose the technical proposal that: the pre-combustion stage consists of a centrifugal nozzle, two-stage axial swirlers, a venturi tube and a sleeve, and the main combustion stage consists of a simple direct-injection nozzle and one-stage or two-stage radial swirlers; the air inflow directions of the radial swirlers are all from outside to inside, and the main combustion stage nozzle is a simple direct injection type nozzle. The Beijing university of aerospace also applies for several patents of lean oil premixing and pre-evaporation combustion chambers, most pre-combustion stages adopt two-stage radial swirlers, the main combustion stage adopts an axial or radial swirler, and no radial swirler for guiding air to flow from inside to outside is adopted; the primary combustion stage nozzle is also a simple direct injection nozzle. The chinese gas turbine institute has applied for several patents of lean oil partially premixed pre-evaporation combustors, such as ZL201020701303.3, ZL201020701305.2, ZL201020701308.6, ZL201220733515.9, etc., which propose the following technical solutions: the head scheme adopts a center-graded two-stage oil-way DIPME mixed combustion mode, and a pre-combustion stage consists of a centrifugal nozzle, a first-stage axial swirler and a contraction and expansion section; the main combustion stage is composed of a direct-injection nozzle and a first-stage axial (radial) or first-stage axial and first-stage radial swirler, has good combustion performance and pollution emission characteristics in a large state, but has poor combustion efficiency under working conditions such as a return field and the like, has limited potential of reducing pollution emission under the same head air inlet condition, and is mainly caused by a diffusion combustion mode of a pre-combustion stage centrifugal nozzle, and the main combustion stage is not good in oil-gas mixing. In order to realize ultralow emission, the pre-combustion stage and the main combustion stage both need to adopt a lean oil partial premixing and pre-evaporation combustion mode, and the main combustion stage and the pre-combustion stage both need to achieve good fuel oil atomization and strengthen oil-gas mixing.
NOx is one of the pollutants that needs to be considered heavily by aircraft engine combustor designers, where NOx is primarily determined by combustion zone flame temperature and gas residence time. At present, lean oil premixing and pre-evaporation technology is adopted in the low-pollution combustion chamber to ensure that the equivalence ratio of a combustion area is within the range of 0.5-0.65, and the flame temperature is effectively controlled so as to reduce the generation of NOx. The combustion chamber adopting the technology has a long premixing section, is easy to generate spontaneous combustion and backfire, and has good mixing and evaporation due to the combustion in a lean oil state, so that the probability of generating unstable combustion is multiplied. The conventional combustor adopts a rich head design, the equivalence ratio of a combustion zone is about 1.0, the combustion mode cannot reduce the generation amount of pollutants, particularly NOx, but the combustor works more stably relative to the combustor adopting a lean premixed pre-evaporation technology, and the basic performance of certain combustors is higher, such as a slow train lean blowout boundary (LBO) and a lean ignition boundary (LLO).
The performance of a combustion chamber is ensured, meanwhile, pollutant emission is reduced, the two technologies are combined, a direct injection diffusion combustion mode is adopted in a pre-combustion stage, a lean oil partial premixing and pre-evaporation combustion mode is adopted in a main combustion stage, and a mixed combustion mode formed by combining the two combustion modes in one combustion chamber head can meet the performance requirement of the combustion chamber and certain pollutant emission requirement. However, for the ultra-low emission combustion chamber, the pre-combustion stage and the main combustion stage both adopt a partial pre-mixing and pre-evaporation combustion technology, so that the pollutant emission is further reduced, and the potential of the pollutant emission is improved. Therefore, the pre-combustion stage of the ultra-low emission combustion technology adopts a partial premixing and pre-evaporation combustion mode, so that the diffusion combustion is weakened, the premixing combustion is enhanced, and in order to ensure the combustion stability, the pre-combustion stage diffusion combustion and the premixing combustion need to be considered in a compromise way; the main combustion stage is a discrete multi-point rotational flow pressure atomizing nozzle, and an air atomizing mode of multi-layer air shearing is also adopted, so that atomization and premixing are enhanced, high-temperature hot spots in a combustion zone are reduced, and NOx emission is reduced. In order to meet the maintainability of the civil aircraft engine, the head nozzle is easy to replace, the head nozzle is convenient to assemble and disassemble, and the realization on engineering is easy.
Disclosure of Invention
The purpose of the invention is as follows: the head of the lean oil partially premixed and pre-evaporated combustor can ensure the performance of the combustor, realize ultralow emission and facilitate the assembly and disassembly of the head.
The technical scheme of the invention is as follows:
one aspect of the invention provides a discrete multipoint swirl pressure atomizing nozzle, which comprises an oil collecting cavity 45, a swirl core 47 and nozzle spray holes 52, wherein the swirl core 47 is arranged in the oil collecting cavity 45, the nozzle spray holes 52 are arranged on the wall of the oil collecting cavity 45, the swirl core 47 is coaxial with the nozzle spray holes 52, tangential grooves 50 are formed in the swirl core 47, and oil flows into the cavity of the swirl core 47 and flows out of the tangential grooves 50.
Preferably, in the discrete multi-point swirl pressure atomizing nozzle, the oil collecting cavity 45 is provided with a plurality of nozzle spray holes 52, and each nozzle spray hole 52 corresponds to one swirl core 47.
Preferably, 2-5 tangential grooves 50 are formed in the swirling core 47 of the discrete multipoint swirling pressure atomizing nozzle, and the swirling angle 49 of each tangential groove 50 is 40-50 degrees.
In another aspect of the present invention, a combustor head is provided for enhanced oil and gas mixing in the main combustion stage, using a discrete multi-point swirl pressure atomizing nozzle as described above in the main combustion stage discrete multi-point swirl pressure atomizing nozzle 56.
Preferably, in the combustion chamber head for enhancing oil-gas mixing of the main combustion stage, the main combustion stage 32 is composed of a main combustion stage first-stage axial swirler 34, a main combustion stage second-stage inclined radial swirler 37 and a main combustion stage discrete multi-point swirl pressure atomizing nozzle 56, and the main combustion stage discrete multi-point swirl pressure atomizing nozzle 56 is located between the main combustion stage first-stage axial swirler 34 and the main combustion stage second-stage inclined radial swirler 37.
Preferably, in the combustion chamber head for enhancing oil-gas mixing of the main combustion stage, a main combustion stage tongue piece 44 is arranged between the main combustion stage first-stage axial swirler 34 and the main combustion stage second-stage inclined radial swirler 37.
Preferably, in the combustion chamber head for enhancing oil-gas mixing of the main combustion stage, the tongue piece 44 of the main combustion stage is provided with an inclined V-shaped slot 61.
Preferably, in the combustion chamber head for enhancing oil-gas mixing of the main combustion stage, the angle 53 of the inclined V-shaped slot 61 is consistent with the installation angle of the main combustion stage secondary inclined radial swirler vane 60, and the opening direction of the inclined V-shaped slot 61 is consistent with the rotation direction of the main combustion stage secondary inclined radial swirler vane 60.
Preferably, in the combustion chamber head for enhancing oil-gas mixing of the main combustion stage, the number of the inclined V-shaped slot 61 is an integral multiple of the number of the discrete multi-point swirl pressure atomizing nozzles 56 of the main combustion stage.
In another aspect of the present invention, a combustion chamber for enhancing fuel-air mixing in a main combustion stage is provided, which employs a combustion chamber head for enhancing fuel-air mixing in a main combustion stage as described above.
The invention has the beneficial effects that: the main combustion stage adopts a lean oil partially premixed and pre-evaporated combustion technology, fuel oil is sprayed out in a rotational flow mode through the main nozzle, mixing with air is enhanced, meanwhile, the inclined V-shaped slotted tongue piece is arranged, airflow turbulence is increased, oil-gas mixing is enhanced, uniform premixed gas is obtained, and emission of pollutants such as NOx, UHC, CO and smoke particles can be greatly reduced. By adopting different head air intake, the NOx emission can reach 50% -70% lower than CAEP/8.
Drawings
FIG. 1 is a schematic view of a low emission combustor;
FIG. 2 is a schematic view of a lean partially premixed pre-evaporative combustor head with enhanced fuel-air mixing for the main combustion stage;
FIG. 3 is a schematic structural view of a discrete multi-point swirl pressure atomizing nozzle;
FIG. 4 is a schematic view of a cyclone core structure;
FIG. 5 is a schematic view of cooling fins disposed inboard of the primary combustion stage throat exit;
FIG. 6 is a schematic view of a main combustion stage inclined V-shaped slotted tongue;
wherein: 10-combustion chamber, 11-diffuser, 12-outer casing, 13-inner casing, 14-nozzle, 15-head, 16-flame tube, 17-electric nozzle, 18-main combustion hole, 19-mixing hole, 20-combustion chamber outer ring, 21-combustion chamber inner ring, 22-flame tube outlet, 30-big nozzle, 31-precombustion stage, 32-main combustion stage, 33-precombustion stage first-stage axial swirler, 34-main combustion stage first-stage axial swirler, 35-precombustion stage nozzle, 37-main combustion stage second-stage oblique radial swirler, 38-main combustion stage premixing cavity, 41-precombustion stage first-stage axial swirler vane, 42-main combustion stage first-stage axial swirler vane, 43-contraction and expansion section, 44-main combustion stage oblique V-shaped slot tongue piece, 45-main combustion stage oil collecting cavity, 46-distance between the inner wall surface of an outlet of the main combustion stage and a cooling tongue piece, 47-swirl core, 48-swirl core groove width, 49-rotation angle of the swirl core groove, 50-swirl core groove, 51-cooling tongue piece, 52-main combustion stage nozzle spray hole, 53-main combustion stage inclined V-shaped slot angle, 54-main combustion stage discrete multi-point swirl pressure atomizing nozzle spray direction, 55-inner wall surface of the outlet of the main combustion stage, 56-splash baffle, 57-main combustion stage premix section length, 58-contraction and expansion section contraction angle, 59-contraction and expansion section expansion angle, 60-main combustion stage inclined radial swirler vane, 61-main combustion stage inclined V-shaped slot, 62-head switching section, 63-head switching section cooling small hole and 64-main combustion stage fuel jet angle.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to specific embodiments and the accompanying drawings.
The discrete multipoint rotational flow pressure atomizing nozzle comprises an oil collecting cavity 45, a rotational flow core 47 and nozzle spray holes 52, wherein the rotational flow core 47 is arranged in the oil collecting cavity 45, the nozzle spray holes 52 are formed in the wall of the oil collecting cavity 45, the rotational flow core 47 is coaxial with the nozzle spray holes 52, a tangential groove 50 is formed in the rotational flow core 47, oil flows into the cavity of the rotational flow core 47 and flows out of the tangential groove 50, and an oil mist cone with a certain expansion angle and good atomization is formed.
The head scheme of the combustion chamber adopts a two-stage oil way lean oil partially premixed and pre-evaporated combustion mode with central classification, namely, the pre-combustion stage adopts a rich oil diffusion combustion mode at the time of starting and in a small state, so that reliable ignition, stable flame and high-efficiency combustion are ensured; the combustion mode is realized by a precombustion stage consisting of an auxiliary oil way centrifugal nozzle, a primary axial swirler and a contraction and expansion section; in a large state (including take-off, climbing, cruising and the like), the pre-combustion stage and the main combustion stage both adopt a lean oil part premixing and pre-evaporating combustion mode with a lower equivalence ratio, but the premixing degree of the pre-combustion stage is not higher than that of the main combustion stage, so that the central combustion zone plays a role in stabilizing flame, the peripheral combustion zone is premixed and pre-evaporated for the lean oil part, the local equivalence ratio of the combustion zone is controlled to be about 0.5, the temperature of the combustion zone is controlled to be within the range of 1700K-1900K, and the residence time of high-temperature flame is controlled, so that the generation amount of NOx and CO/UHC is effectively controlled. The main combustion stage consists of a primary axial swirler, a primary radial swirler and a discrete multi-point rotational flow pressure atomizing nozzle, primary atomization is carried out by means of pressure difference between the inside and the outside of the nozzle to form a hollow atomizing cone similar to a centrifugal nozzle, and fuel oil can be fully atomized and evaporated by means of shearing action of rotating airflow in the swirler and (rotating) airflow in an outer ring channel, and mixing with incoming flow air is strengthened; meanwhile, an inclined V-shaped slotted tongue piece is added between the two stages of vortex devices, so that the turbulence degree of the rotating airflow is enhanced, and the oil-gas mixing is enhanced.
The concrete structure is as follows: a main combustion stage enhanced fuel-air mixed lean partially premixed pre-evaporative combustor head, the head 15 comprising a turn-around stage 62, splash plate 56, pre-combustion stage 31 main combustion stage 32;
the pre-combustion stage 31 comprises a pre-combustion stage one-stage axial swirler 33, a contraction and expansion section 43 and a pre-combustion stage nozzle 35; the effective flow area of the axial swirler 33 of the pre-combustion stage and the throat area of the contraction and expansion section 43 jointly determine the air flow of the pre-combustion stage. The distance between the nozzle 35 of the pre-combustion stage and the throat of the convergent-divergent section 43 is in a proper range to ensure good atomization, achieve the desired mixing of fuel and air and ensure reliable ignition.
The main combustion stage 32 comprises a main combustion stage first-stage axial swirler 34, a main combustion stage second-stage inclined radial swirler 37, an inclined V-shaped slotted tongue 44 and a discrete multi-point swirl pressure atomizing nozzle 56; the discrete multi-point swirl pressure atomizing nozzles 56 are uniformly distributed between the first-stage and second-stage swirlers of the main combustion stage, and the distance 57 between the spray holes 52 of the discrete multi-point swirl pressure atomizing nozzles and the outlet of the main combustion stage is not more than 30 mm.
Further, the installation angle of blades 41 of the pre-combustion stage first-stage axial swirler is 30-35 degrees, the number of the blades is 8-16, and the rotational flow strength is 0.45-0.6.
Furthermore, the contraction section angle 58 of the contraction and expansion section 43 of the pre-combustion stage is 80-90 degrees, and the expansion section angle 59 is 100-120 degrees.
Further, the air inlet of the primary axial swirler 34 of the main combustion stage and the air inlet of the secondary inclined radial swirler 37 of the main combustion stage are substantially perpendicular to each other, and the air flow direction is opposite; the two-stage swirler of the main combustion stage acts together to enable the air swirl strength of the main combustion stage to be 0.6-0.7.
Further, the lean oil partially premixed and pre-evaporated ultra-low emission combustor for enhancing the oil-gas mixture comprises a diffuser 11, an outer casing 12, an inner casing 13, a nozzle 14, the combustor head 15, a flame tube 16 and an electric nozzle 17.
8-12 swirl cores 47 are arranged in the oil collecting cavity 45 of the main combustion stage discrete multipoint swirl pressure atomizing nozzle 56, 2-3 tangential grooves 50 with the groove widths and the groove depths of 0.4-0.5 mm are formed in the swirl cores 47, and the swirl angle 49 of the tangential grooves 50 is 40-50 degrees; the fuel swirling strength formed by the tangential grooves 50 is about 0.6, so that a certain hollow fog cone is formed after the fuel flows out of the spray holes 52, good atomization is achieved, and oil-gas mixing is enhanced. The diameter of the spray hole 52 of the discrete multi-point swirl pressure atomizing nozzle is 0.45 mm-0.6 mm, and the jet angle 64 is between 10-60 degrees.
An inclined V-shaped slotted tongue piece 44 is arranged between the two-stage swirlers of the main combustion stage. The main combustion level fuel is sprayed out, under the action of the secondary inclined radial swirler 37, the oil-gas mixture flows to the inclined V-shaped slot tongue piece 44, part of the oil-gas mixture forms an oil film on the tongue piece, and the oil film is crushed and atomized under the common shearing action of the air flow of the primary axial swirler 34; the other part of the fuel flows through the inclined V-shaped slotted tongue piece 44 to be mixed with the airflow of the primary axial swirler 34, so that the air-fuel mixture is enhanced.
Further, the number of the inclined V-shaped slotted tongue pieces 44 of the main combustion stage is multiple of that of the discrete multi-point swirl pressure atomizing nozzle 56 of the main combustion stage nozzle; the angle 53 of the oblique V-shaped slot 61 is substantially consistent with the mounting angle of the main combustion stage secondary oblique radial swirler vane 60, and the opening direction is also consistent with the rotation direction of the main combustion stage secondary oblique radial swirler vane 60.
Further, a cooling tongue piece 51 is arranged on the inner side of the outlet of the throat of the main combustion stage, and guides airflow to blow off an oil film formed on the inner wall surface 55 of the outlet of the main combustion stage and then injects the oil film into a combustion zone for combustion; the spontaneous combustion and the tempering are prevented; the distance 46 between the inner wall surface of the outlet of the main combustion stage and the cooling tongue piece is between 0.5mm and 1.0 mm.
The head adapter section 62 is provided with an impingement cooling small hole 63 with the diameter of 0.8 mm-1.2 mm for cooling the splash plate 56;
the head of the lean oil partially premixed and pre-evaporated combustion chamber with the main combustion stage reinforced oil-gas mixture is characterized in that a large nozzle 30 and a main combustion stage secondary inclined radial swirler 37 which are composed of a pre-combustion stage 31, a main combustion stage primary axial swirler 34 and a main combustion stage discrete multipoint swirl pressure atomizing nozzle 56 are convenient to assemble and disassemble, wherein the main combustion stage inclined radial secondary swirler 37 and a head adapter section 62 are fixed on the flame tube 16.
The invention is described in detail below with reference to the drawings and specific examples.
Fig. 1 is a schematic view of a combustion chamber of a lean partially premixed and pre-evaporated combustion mode adopting a two-stage oil-way main combustion stage with central classification to strengthen oil-gas mixing, wherein a combustion chamber 10 comprises a diffuser 11, an outer casing 12, an inner casing 13, a nozzle 14, a head 15, a flame tube 16 and an electric nozzle 17, and the flame tube is provided with a main combustion hole 18 and a mixing hole 19 as required. The working conditions of the combustion chamber are: air enters the combustion chamber from the diffuser 11, more than 65% of the air enters the flame tube 16 from the head 15, the rest of the air enters the flame tube 16 through the outer ring 20 and the inner ring 21 of the combustion chamber, fuel oil enters the flame tube 16 through the nozzle 14, and after the electric nozzle 17 is ignited in the flame tube 16, the air and the fuel oil are combusted, and high-temperature fuel gas is discharged from the outlet 22 of the flame tube.
Fig. 2 shows a detail of the structure of the head 15 of the lean partially premixed and pre-evaporated combustor for enhancing the fuel-air mixture in the main combustion stage, wherein the head is composed of a pre-combustion stage 31 and a main combustion stage 32. The air inflow of the head part 15 approximately accounts for 65-80% of the total air flow of the combustion chamber 10, the specific air inflow is related to the total oil-gas ratio and the cooling air amount of the combustion chamber, the air inflow of the pre-combustion stage 31 approximately accounts for 10-20% of the total air inflow of the combustion chamber 10, and the specific air inflow is closely related to the oil-gas ratio of the slow-start state of the combustion chamber; the air input of the main combustion stage 32 is about 40-60% of the total air input of the combustion chamber 10, and the specific air input is closely related to the fuel-air ratio of the take-off state of the combustion chamber.
The pre-combustion stage 31 is composed of a pre-combustion stage one-stage axial swirler 33, a contraction and expansion section 43 and a pre-combustion stage nozzle 35. The effective flow area of the first-stage axial swirler 33 of the pre-combustion stage and the throat area of the contraction and expansion section 43 jointly determine the air flow of the pre-combustion stage. In all working conditions of the combustion chamber, the pre-combustion stage 31 works, and the pre-combustion stage is rich-oil diffusion combustion in starting and small states to play a role in stabilizing flame; the pre-combustion stage is lean diffusion combustion at large conditions, which contributes to efficient, stable combustion throughout the LTO cycle and can reduce polluting emissions.
The main combustion stage 32 is composed of a main combustion stage first-stage axial swirler 34, a main combustion stage second-stage inclined radial swirler 37, a main combustion stage inclined V-shaped slotted tongue piece 44 and a main combustion stage discrete multi-point swirl pressure atomizing nozzle 56. The swirl strength of the main combustion stage is about 0.6, and a stripping flame is formed at the outlet of the main combustion stage, which is helpful for preventing unstable combustion and backfire. According to different engine pressure ratios, the length 57 of the main combustion stage premixing section is 20-30 mm, so that the main combustion stage fuel oil can be effectively ensured to achieve the best partial premixing and pre-evaporation, and spontaneous combustion is avoided.
FIGS. 3-4 show details of the structure of the main combustion stage discrete multi-point swirl pressure atomizing nozzle 56. The main combustion stage discrete multipoint swirl pressure atomizing nozzle 56 is provided with a swirl core 47, fuel forms swirl with certain strength through the swirl core inclined cutting groove 50 of the main combustion stage nozzle, and flows out through the spray hole 52 of the main combustion stage nozzle to form a well atomized oil mist cone with a certain expansion angle; one part forms an oil film on the tongue piece, and the oil film is crushed and atomized under the common shearing action of the airflow of the primary axial swirler 34; the other part of the fuel flows through the inclined V-shaped slotted tongue piece 44 to be mixed with the airflow of the primary axial swirler 34, so that the oil-gas mixing is enhanced; finally spraying the mixture into a combustion area for combustion; the inner side of the outlet of the main combustion stage throat is provided with a cooling tongue piece 51 which guides airflow to blow off an oil film formed on the inner wall surface 55 of the outlet of the main combustion stage and then injects the oil film into a combustion zone for combustion; prevent spontaneous combustion and backfire.
Fig. 5 shows the cooling tongue piece 51 arranged inside the throat outlet of the main combustion stage to form interstage cooling between the pre-combustion stage and the main combustion stage, and at the same time, the air flow of the cooling tongue piece 51 is guided to vertically enter the main flow to blow off the adherent flow of the fuel at the inner wall surface 55 of the outlet of the main combustion stage, so as to prevent spontaneous combustion and backfire.
FIG. 6 is a positional relationship between the angled V-shaped slotted tongue 44 of the main combustion stage and the injection direction of the discrete multi-point swirl pressure atomizing nozzle 56 of the main combustion stage.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. The discrete multipoint swirl pressure atomizing nozzle is characterized by comprising an oil collecting cavity (45), a swirl core (47) and nozzle spray holes (52), wherein the swirl core (47) is arranged in the oil collecting cavity (45), the nozzle spray holes (52) are formed in the wall of the oil collecting cavity (45), the swirl core (47) and the nozzle spray holes (52) are coaxial, a tangential groove (50) is formed in the swirl core (47), and oil flows into the cavity of the swirl core (47) and flows out of the tangential groove (50).
2. A discrete multi-point swirl pressure atomizing nozzle according to claim 1, characterized in that the oil collecting chamber (45) has a plurality of nozzle spray holes (52), and each nozzle spray hole (52) corresponds to one swirl core (47).
3. The pressure atomizing nozzle of claim 1, wherein 2-5 tangential slots (50) are opened on the swirl core (47), and the swirl angle (49) of the tangential slots (50) is 40-50 °.
4. A combustor head for enhanced mixing of fuel and air in a primary combustion stage, characterized in that a discrete multi-point swirl pressure atomizing nozzle according to claims 1-3 is applied to the discrete multi-point swirl pressure atomizing nozzle (56) of the primary combustion stage.
5. A primary combustion stage enhanced oil and gas mixing combustor head as claimed in claim 4 wherein the primary combustion stage (32) is comprised of a primary combustion stage primary axial swirler (34), a primary combustion stage secondary inclined radial swirler (37), and a primary combustion stage discrete multi-swirl pressure atomizing nozzle (56), the primary combustion stage discrete multi-swirl pressure atomizing nozzle (56) being located between the primary combustion stage primary axial swirler (34) and the primary combustion stage secondary inclined radial swirler (37).
6. A combustion chamber head for enhanced oil and gas mixing of the main combustion stage as claimed in claim 5 wherein main combustion stage tongues (44) are provided between the main combustion stage first stage axial swirler (34) and the main combustion stage second stage inclined radial swirler (37).
7. The head of a combustion chamber for enhancing oil-gas mixing of a main combustion stage as claimed in claim 6, wherein the tongue piece (44) of the main combustion stage is provided with an inclined V-shaped slot (61).
8. A combustion chamber head for enhancing oil and gas mixing of a main combustion stage as claimed in claim 7, characterized in that the angle (53) of the inclined V-shaped slot (61) is consistent with the installation angle of the blades (60) of the main combustion stage secondary inclined radial swirler, and the opening direction of the inclined V-shaped slot (61) is consistent with the rotation direction of the blades (60) of the main combustion stage secondary inclined radial swirler.
9. The combustor head for enhancing oil and gas mixing of the main combustion stage as recited in claim 7, wherein the number of the inclined V-shaped slots (61) is an integral multiple of the number of the discrete multi-point swirl pressure atomizing nozzles (56) of the main combustion stage.
10. A combustion chamber for intensified fuel-air mixing of the main combustion stage, characterized in that a combustion chamber head for intensified fuel-air mixing of the main combustion stage according to claims 4 to 9 is used.
Priority Applications (1)
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113154449A (en) * | 2021-05-06 | 2021-07-23 | 中国航发湖南动力机械研究所 | Low-pollution combustion chamber for efficient mixing of oil and gas |
| CN113188153A (en) * | 2021-05-10 | 2021-07-30 | 中国航发湖南动力机械研究所 | Adopt strong shearing oil gas mixture burning tissue and use its combustion chamber |
| CN113932253A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Combustion chamber head, combustion chamber, gas turbine engine, and combustion control method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20110122262A (en) * | 2010-05-04 | 2011-11-10 | 국방과학연구소 | Rotating fuel nozzle for gas turbine |
| CN103047682A (en) * | 2012-12-27 | 2013-04-17 | 中国燃气涡轮研究院 | Partial pre-mixing and pre-evaporation burning chamber with prefilm type nozzle |
| CN107575890A (en) * | 2017-07-24 | 2018-01-12 | 西北工业大学 | A kind of axially staged lean premixed preevaporated low contamination combustion chamber |
| CN104566470B (en) * | 2014-12-03 | 2018-04-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The head of combustion chamber structure of distributed flame |
| CN108561897A (en) * | 2017-12-27 | 2018-09-21 | 中国航发四川燃气涡轮研究院 | A kind of partly-premixed prevapourising minimum discharge combustion chamber for strengthening air-fuel mixture |
-
2019
- 2019-12-05 CN CN201911234823.XA patent/CN110925794A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20110122262A (en) * | 2010-05-04 | 2011-11-10 | 국방과학연구소 | Rotating fuel nozzle for gas turbine |
| CN103047682A (en) * | 2012-12-27 | 2013-04-17 | 中国燃气涡轮研究院 | Partial pre-mixing and pre-evaporation burning chamber with prefilm type nozzle |
| CN104566470B (en) * | 2014-12-03 | 2018-04-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The head of combustion chamber structure of distributed flame |
| CN107575890A (en) * | 2017-07-24 | 2018-01-12 | 西北工业大学 | A kind of axially staged lean premixed preevaporated low contamination combustion chamber |
| CN108561897A (en) * | 2017-12-27 | 2018-09-21 | 中国航发四川燃气涡轮研究院 | A kind of partly-premixed prevapourising minimum discharge combustion chamber for strengthening air-fuel mixture |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113932253A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Combustion chamber head, combustion chamber, gas turbine engine, and combustion control method |
| CN113154449A (en) * | 2021-05-06 | 2021-07-23 | 中国航发湖南动力机械研究所 | Low-pollution combustion chamber for efficient mixing of oil and gas |
| CN113154449B (en) * | 2021-05-06 | 2022-05-31 | 中国航发湖南动力机械研究所 | Low-pollution combustion chamber for efficient mixing of oil and gas |
| CN113188153A (en) * | 2021-05-10 | 2021-07-30 | 中国航发湖南动力机械研究所 | Adopt strong shearing oil gas mixture burning tissue and use its combustion chamber |
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