CN110131750B - Gas turbine low-emission combustion chamber using gas fuel - Google Patents
Gas turbine low-emission combustion chamber using gas fuel Download PDFInfo
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- CN110131750B CN110131750B CN201910341915.1A CN201910341915A CN110131750B CN 110131750 B CN110131750 B CN 110131750B CN 201910341915 A CN201910341915 A CN 201910341915A CN 110131750 B CN110131750 B CN 110131750B
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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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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Abstract
A gas turbine low-emission combustion chamber using gas fuel belongs to the technical field of gas turbines and comprises an on-duty stage, a main combustion stage, a high-pressure igniter, a mixing hole, an exhaust outlet, a bearing casing, a flame tube outer casing, a flange, an on-duty stage gas fuel pipeline, a main combustion stage fuel main pipe, an on-duty stage fuel main pipe, a pipeline support, a second on-duty stage fuel main pipe, a second on-duty stage gas fuel pipeline, an air conditioning device, a first on-duty stage fuel groove, a second on-duty stage fuel groove and a main combustion stage fuel groove, wherein the on-duty stage only works alone when the gas turbine is in a small load state such as starting and the like, the on-duty stage and the main combustion stage work together when the gas turbine is in a large load state such as above starting and the like, diffusion combustion of the on-duty stage fuel provides a stable ignition source for a main combustion area, so that the low-emission requirement is ensured, and the combustion stability, the combustion efficiency and the like are fully considered, and the performance requirements of the combustion chamber are comprehensively met.
Description
Technical Field
The invention belongs to the technical field of gas turbine combustors, and particularly relates to a gas turbine low-emission combustor using gas fuel.
Background
The gas turbine originated in the 60's of the 20 th century, and it can utilize various fuels such as gas fuel and liquid fuel, and has the advantages of high thermal efficiency, small pollution discharge, small volume, quick start, less water consumption, and suitability for burning various fuels, so it has received attention from various countries. The power machine is widely applied to various industrial fields such as aviation, ships, electric power and the like, and plays a vital role in the development of national economy. Compared with other engines, the gas turbine has the advantages of great superiority in the aspects of fuel consumption rate, noise, emission, vibration and the like, can be used for traditional distributed power generation and can also be used for various modes such as grid-connected power generation and the like, and is suitable for cities and remote areas. And is worried by the industry and the society due to the advantages of cleanness and reliability. In recent years, gas turbines have been used in a wide range as advanced power machinery, and have been applied to various fields such as electromechanical machining and metal materials, in addition to transportation such as sea and land defense.
In recent years, concepts such as environmental protection and sustainable development can be deeply focused, and the global attention is paid to environmental problems such as haze and greenhouse effect. Environmental problems caused by combustion have attracted worldwide attention, and low-pollution combustion technology research has been conducted in countries around the world in order to solve the problems. Among them, the lean premixed combustion technology is a major low-emission combustion technology, and has been applied to advanced low-emission gas turbines. However, this technique has several problems as follows:
1. the combustible limit is narrow, and the flameout phenomenon is easy to occur particularly under the low working condition of the engine;
2. spontaneous combustion and tempering problems are easy to occur in the premixing process, so that the engine combustion chamber is damaged;
3. the lack of adaptability to gas fuels with a heat value fluctuating within a certain range does not guarantee that the equivalence ratio in the main combustion zone is maintained within the range of 0.6-0.8.
Disclosure of Invention
The invention provides a low-emission combustor capable of applying the central staged combustion and the lean premixed combustion of gas fuel, and the technical scheme can ensure the stable operation of a gas turbine when the gas turbine uses the gas fuel; meanwhile, the emission pollution of the combustion chamber can be effectively reduced. The increasing of the tapered partition plate is proposed to increase the gas mixing speed aiming at the problems of backfire and spontaneous combustion in premixed combustion. For fluctuations in the calorific value of the fuel, it has been proposed to add air conditioning devices to the head of the combustion chamber.
In order to achieve the purpose, the invention adopts the following technical scheme:
a gas turbine low-emission combustion chamber using gas fuel, wherein the head of the combustion chamber comprises an on-duty stage and a main combustion stage which are arranged in a concentric mode, the on-duty stage is arranged in the center, the main combustion stage is arranged on the periphery of the on-duty stage, the on-duty stage comprises a first-stage axial swirler and an on-duty stage fuel nozzle, the first-stage axial swirler is arranged in a central hole of the head of a flame tube, an outer casing of the flame tube is arranged outside the flame tube, the flame tube and the outer casing of the flame tube are coaxially arranged, an air channel is formed between the outer wall of the flame tube and the inner wall of the outer casing of the flame tube, high-pressure igniters are arranged at the centers of the outer casing of the flame tube and the first-stage swirler, the on-duty stage fuel nozzle comprises two parts, namely a first-duty stage fuel nozzle and a second-duty stage fuel nozzle, and the second-duty stage fuel nozzle is uniformly arranged at the position, close to the first-stage, the tail part of the first-stage swirler is uniformly provided with a first duty-level fuel nozzle along the circumferential direction, the main combustion level comprises a second-stage radial swirler, a main combustion level fuel nozzle and a partition plate, the second-stage radial swirler is arranged at the head part of the flame tube, the main combustion level fuel nozzle comprises two parts, namely a first main combustion level fuel nozzle and a second main combustion level fuel nozzle, the head part and the center part of the second-stage radial swirler are respectively and uniformly provided with the first main combustion level fuel nozzle and the second main combustion level fuel nozzle along the circumferential direction, a main combustion level fuel pipeline at the head part of the flame tube penetrates through the head part of the outer flame tube, the inlet end of the main combustion level fuel pipeline is connected with the gas outlet end of the main combustion level fuel header pipe through the main combustion level gas fuel pipeline, the head part of the outer flame tube is respectively provided with a first duty-level fuel pipeline and a second duty-level fuel pipeline, the first duty level fuel pipeline is connected with the gas outlet end of the first duty-level fuel header pipe through the first, the second duty fuel pipeline is connected with the air outlet end of the second duty fuel header pipe through a second duty gas fuel pipeline, the first duty fuel pipeline, the second duty fuel pipeline and the main fuel pipeline are fixedly arranged at the head part of the combustion chamber through flanges, the air inlet ends of the main fuel header pipe, the second duty fuel header pipe and the first duty fuel header pipe are all connected with an air source, the main fuel header pipe, the first duty fuel header pipe and the second duty fuel header pipe are all arranged on a pipeline bracket, the pipeline bracket is arranged on a compressor shell, the air outlet end of the flame tube is connected with a turbine guider through a bearing case, one end of the compressor is connected with the turbine shell, the other end of the compressor is fixed at the outlet section of the flame tube outer case, the flame tube and the turbine guider jointly form an exhaust outlet, and a swirler partition plate is arranged at the tail part of the second radial direction, the inner wall of the flame tube is provided with an air conditioning device which is positioned at one end of the tail part of the clapboard, and a plurality of mixing holes are distributed at the tail part of the flame tube.
The inner diameters of the first duty fuel nozzle and the second duty fuel nozzle are both 0.1-0.5mm, and the number of the first duty fuel nozzle and the second duty fuel nozzle is 16-24.
The included angle between the axis of the first-class on-duty fuel nozzle and the axis of the first-class axial swirler is 0-60 degrees.
The included angle between the axis of the second on-duty fuel nozzle and the axis of the first-stage axial swirler is 0-60 degrees.
The inner diameters of the first main combustion stage fuel nozzle and the second main combustion stage fuel nozzle are both 0.1-0.5mm, and the number of the first main combustion stage fuel nozzle and the second main combustion stage fuel nozzle is 16-24.
The installation angle between the central line of the flame tube and the central line of the engine is 0-30 degrees.
The lean combustion with the equivalence ratio of 0.6-0.8 in the main combustion area of the flame tube has the advantages of both lean premixing and lean direct injection, the temperature of the main combustion stage is lowered comprehensively, and the combustion temperature in the main combustion area of the flame tube is lower than 1800K, so that NO is effectively inhibitedXEspecially of the thermal type NOXAnd (4) generating.
The invention has the beneficial effects that:
1. the device adopts a fuel center grading supply mode, gas fuel is divided into two paths to enter the combustion chamber, wherein one path of gas fuel enters the combustion chamber from a central class nozzle, and the on-duty class adopts diffusion and premixed combustion; the gas fuel of the second path is directly injected into the cavity of the main mixing area axially and radially through the fuel nozzle of the main combustion stage, and the fuel in the cavity is uniformly mixed with the air coming from the secondary radial swirler; combustible gas of misce bene flows out the mixing area through the baffle, owing to introduced the baffle, make flow area reduce, avoided the low-speed district because central adverse pressure gradient forms on the one hand, the swirl strength of combustible mixture has been controlled, the mixing effect is better, on the other hand can prevent the tempering, natural and oscillatory combustion, avoid the damage of engine combustion chamber, combustible mixture gets into the flame tube head, form even premixed combustible gas mixture and burn in outside backward flow district, realize gas fuel's stable combustion, guaranteed high efficiency simultaneously, low-pollution's characteristics, the duty level is providing steady fire source, the main burning level realizes low pollution burning, can ensure the stability of gas turbine combustor when reducing pollution emission.
2. The air in the main combustion area of the flame tube can be adjusted by an air adjusting device, so that the equivalence ratio of the main combustion area is kept within 0.6-0.8 when fuels with different heat values are used, the temperature of a main combustion stage is comprehensively reduced, the combustion temperature of the main combustion area of the flame tube is controlled below 1800K, and NO is effectively inhibitedXCO, especially NO of the thermal typeXAnd (4) generating.
3. When the gas turbine is in a small load state such as starting, only the duty level works independently, when the gas turbine is in a large load state such as starting, the duty level and the main combustion level work together, and the diffusion combustion of duty level fuel provides a stable ignition source for a main combustion area, so that the low emission requirement is ensured, the combustion stability, the combustion efficiency and the like are fully considered, and the performance requirement of the combustion chamber is comprehensively met.
4. The low emission of the gas fuel combustion chamber is realized by adopting a lean-burn premixed combustion technology, and the purpose of reducing the emission of pollutants is achieved by controlling the equivalence ratio and the mixing uniformity of a combustion area in the combustion chamber. Adopt the hierarchical burning scheme in center, gaseous fuel gets into the combustion chamber through the nozzle of the level of on duty, adopts diffusion combustion to guarantee the combustion stability of whole combustion chamber, guarantees that the main burning level burns completely in wide equivalence ratio range, and the gaseous fuel that gets into the main burning zone through the fuel spout of the main burning level mixes at main burning zone and air, provides even combustible gas mixture for the combustion chamber to control the equivalence ratio and the homogeneity of whole combustion zone, realize the low emission of combustion chamber.
5. The inner diameters of the first duty fuel nozzle and the second duty fuel nozzle are both 0.1-0.5mm, and the number of the first duty fuel nozzle and the second duty fuel nozzle is 16-24; the inner diameters of the first main fuel nozzle and the second main fuel nozzle are both 0.1-0.5mm, and the number of the first main fuel nozzle and the second main fuel nozzle is 16-24; the greater the relative jet velocities of the fuel and air at the inlet, i.e., the greater the initial velocity field non-uniformity, the greater the momentum exchange, and the more favorable the mixing process. The diameter of the nozzle is changed under the condition of unchanged flow, so that the change of the relative speed of the initial jet flow can be realized. The pore size range of 0.1-0.5mm is selected to ensure that the jet velocity of the fuel is high enough to be fully premixed with the incoming air, the depth of the jet of the fuel is not enough above the range, the premixing uniformity of the fuel and the air is poor to reduce the combustion efficiency, the fuel is sprayed onto the wall surface of the flame tube below the range, the premixing uniformity of the fuel and the air is poor to cause the equivalence ratio of a main combustion area to be poor, the pollutant emission is increased, and the combustible mixture is easy to burn on the wall surface to damage the flame tube; the mixing capacity of the premixing section can be improved by increasing the number of the nozzles, mainly the distance from the nozzles to any point on the section is shortened after the number of the nozzles is increased, and the fuel diffusion can be completed in a shorter premixing section. However, the increase in the number of nozzles also has an effect on the structure of the concentration field. The mixing efficiency exhibited by a single nozzle becomes poor after the number of nozzles is increased, so that the number of nozzles cannot be too large. 6-24 spouts can ensure that the jet velocity of the fuel is enough, promote the convective diffusion of the fuel by utilizing the rotational flow and the strong turbulence effect, eliminate a local low-speed vortex structure, optimize the air flow in a premixing channel, keep uniform flow, match with the fuel supply amount, and avoid the phenomenon that the low-speed area is tempered and is lower than the range, the fuel is unevenly distributed, the phenomenon that the local air is excessive or the local fuel concentration is too high can possibly occur due to the insufficient utilization of the air, the jet depth of the fuel can not be ensured when the local air is over the range, and the premixing efficiency is greatly reduced.
6. The included angle between the axis of the first-class on-duty fuel nozzle and the axis of the first-class axial swirler is 0-60 degrees; the included angle between the axis of the second on-duty fuel nozzle and the axis of the first-stage axial swirler is 0-60 degrees. The mixing capacity of the premixing section is not changed by pure air swirl, and the influence of swirl on the mixing efficiency is mainly realized by changing the axial average speed and the turbulence of fuel and air. Therefore, the fuel jet direction and the air rotational flow direction have an angle change which influences the premixing effect. The air uniform flow can be optimized and the local vortex at the downstream of the fuel spray pipe can be reduced by 0-60 degrees, the air and the fuel have enough rotational flow strength, the fuel concentration is uniformly distributed, the full combustion is ensured, and the equivalence ratio is in a desired range; below the range, on one hand, a low-speed vortex area at the downstream of the spray pipe is enlarged, and the diffusion effect of the airflow on the fuel is directly weakened; on the other hand, making the fuel flow from two adjacent nozzles more concentrated also reduces the fuel premixing uniformity; beyond this range, the jet velocity of the fuel is not affected by the swirl of the air and in addition, the high fuel jet momentum will affect the local flow near the fuel nozzle, changing the swirl structure and the air flow, thereby affecting the concentration distribution of the fuel and causing the fuel with poor premixing uniformity to be not fully combusted.
7. The installation angle between the central line of the flame tube and the central line of the engine is 0-30 degrees, the flame tube is installed in the range, the installation of the flame tube is convenient, the maintenance is easy, and the exhaust section of the flame tube can fully utilize the diffusion effect of the diffuser; below the range, the overall layout of the gas turbine is unreasonable, and the tail gas of the flame tube needs to be discharged through an overlarge turn; above this range, the exhaust gas easily impacts the exhaust section and diffuser structure, potentially creating a hazard.
Drawings
FIG. 1 is a schematic view of a gas turbine of a low-emission combustor of a gas turbine according to embodiment 1 of the present invention;
FIG. 2 is a schematic view of a low-emission combustor of a gas turbine according to embodiment 1 of the present invention;
FIG. 3 is an enlarged schematic view of a gas turbine low-emission combustor A according to embodiment 1 of the present invention;
FIG. 4 is an enlarged schematic view of a gas turbine low-emission combustor B according to embodiment 1 of the present invention;
FIG. 5 is a schematic view of a gas turbine low-emission combustor in accordance with embodiment 2 of the present invention;
FIG. 6 is an enlarged schematic view of a gas turbine low-emission combustor C according to embodiment 2 of the present invention;
1. the gas compressor comprises a gas compressor shell, a first duty stage fuel nozzle, a second duty stage fuel nozzle, a first main combustion stage fuel nozzle, a second main combustion stage fuel nozzle, a first axial swirler, a second axial swirler, a high-pressure igniter, 8, a partition plate, 9, mixing holes, 10, an exhaust outlet, 11, a bearing casing, 12, a flame tube, 13, a second radial swirler and 14, the device comprises a flame tube outer casing, 15, a flange, 16, a first duty stage gas fuel pipeline, 17, a main combustion stage gas fuel pipeline, 18, a main combustion stage fuel main pipe, 19, a first duty stage fuel main pipe, 20, a pipeline bracket, 21, a second duty stage fuel main pipe, 22, a second duty stage gas fuel pipeline, 23, an air conditioning device, 24, a first duty stage fuel groove, 25, a second duty stage fuel groove, 26, a main combustion stage fuel groove and 27-diffuser.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Example 1
As shown in fig. 1 to 4, a gas turbine low-emission combustor using gas fuel, the head of the combustor comprises an on-duty stage and a main combustion stage which are concentrically arranged, the on-duty stage is arranged at the center, the main combustion stage is arranged at the periphery of the on-duty stage, combustion stability and low emission when using gas fuel are realized by adjusting fuel distribution of the on-duty stage and the main combustion stage and coordination between different nozzles, the on-duty stage comprises a primary axial swirler 6 and an on-duty fuel nozzle, the primary axial swirler 6 is arranged in a central hole of the head of a flame tube 12, a flame tube outer casing 14 is arranged outside the flame tube 12, the flame tube 12 and the flame tube outer casing 14 are coaxially arranged, a first on-duty stage fuel groove 24 and a second on-duty stage fuel groove 25 are respectively arranged on the flame tube outer casing 14, an air channel is formed between the outer wall of the flame tube 12 and the inner wall of the flame tube outer casing 14, the high-pressure igniter 7 is arranged at the centers of the flame tube outer casing 14 and the primary axial swirler 6, the class-on fuel nozzle comprises two parts, namely a class-on fuel nozzle 2 and a class-on fuel nozzle 3, the class-on fuel nozzle 3 is uniformly arranged at the head of the flame tube outer casing 14 along the circumferential direction, the axis of the class-on fuel nozzle 3 is parallel to the axis of the primary axial swirler 6, the class-on fuel nozzle 2 is uniformly arranged on the inner ring of the primary axial swirler 6 arranged at the head of the flame tube 12 along the circumferential direction, the primary combustion stage comprises a secondary radial swirler 13, a primary combustion stage fuel nozzle and a partition plate 8, the secondary radial swirler 13 is arranged at the head of the flame tube 12, the space formed between the two parts is a primary combustion stage fuel groove 26, the primary combustion stage fuel nozzle comprises two parts, namely a class-on fuel nozzle 4 and a class-on fuel nozzle 5, the head and the center of the secondary radial swirler 13 are respectively and uniformly provided with a first main combustion stage fuel nozzle 4 and a second main combustion stage fuel nozzle 5 along the circumferential direction, the jet flow direction of the first main combustion stage fuel nozzle 4 is the same as the incoming air, the jet flow direction of the second main combustion stage fuel nozzle 5 is vertical to the incoming air, a main combustion stage fuel pipeline at the head of the flame tube 12 penetrates through the head of the flame tube outer casing 14, the inlet end of the main combustion stage fuel pipeline is connected with the outlet end of the main combustion stage gas fuel pipeline 17, the inlet end of the main combustion stage gas fuel pipeline 17 is connected with the outlet end of the main combustion stage fuel header pipe 18, the head of the flame tube outer casing 14 is respectively provided with a first duty stage fuel pipeline and a second duty stage fuel pipeline, the first duty stage fuel pipeline is connected with the first duty stage gas fuel pipeline 16, the inlet end of the first duty stage gas fuel pipeline 16 is connected with the outlet end of the first duty stage fuel header pipe 19, the second duty fuel pipeline is connected with the outlet end of the second duty gas fuel pipeline 22, the inlet end of the second duty gas fuel pipeline 22 is connected with the outlet end of the second duty fuel header pipe 21, the first duty fuel pipeline, the second duty fuel pipeline and the main combustion stage fuel pipeline are fixedly arranged at the head part of the combustion chamber through a flange 15 arranged on a gas turbine shell, the inlet ends of the main combustion stage fuel header pipe 18, the second duty fuel header pipe 21 and the first duty fuel header pipe 19 are all connected with an air source, the main combustion stage fuel header pipe 18, the first duty fuel header pipe 19 and the second duty fuel header pipe 21 are all arranged on a pipeline bracket 20, the pipeline bracket 20 is arranged on the compressor shell 1, the outlet end of the flame tube 12 is connected with a turbine guider through a bearing machine box 11, one end of a diffuser 27 is connected with the compressor shell 1, the other end of the flame tube is fixed at the outlet section of an outer casing 14 of the flame tube, the flame tube 12 and the turbine guider jointly form an exhaust outlet 10, a partition plate 8 is installed at the tail part of a secondary radial swirler 13, the combustible mixture is accelerated by the partition plate 8 and then is guaranteed not to be tempered, an air adjusting device 23 located at one end of the tail part of the partition plate 8 is installed on the inner wall of the flame tube 12 and can be used for adjusting the air flow of a main combustion area of the flame tube 12 so as to change the equivalence ratio of the main combustion area of the flame tube 12, a plurality of mixing holes 9 are distributed at the tail part of the flame tube 12, and the installation.
The inner diameters of the first duty grade fuel nozzle 2 and the second duty grade fuel nozzle 3 are both 0.1-0.5mm, and the number of the first duty grade fuel nozzle and the second duty grade fuel nozzle is 16-24.
The inner diameters of the first main combustion stage fuel nozzle 4 and the second main combustion stage fuel nozzle 5 are both 0.1-0.5mm, and the number of the first main combustion stage fuel nozzle and the second main combustion stage fuel nozzle is 16-24. The lean combustion with the equivalence ratio of 0.6-0.8 in the main combustion area of the flame tube 12 has the advantages of both lean premixing and lean direct injection, the temperature of the main combustion stage is lowered comprehensively, the combustion temperature in the main combustion area of the flame tube 12 is lower than 1800K, and NO is effectively inhibitedXEspecially of the thermal type NOXAnd (4) generating.
The working principle of the invention is as follows:
the gas fuel flowing out from the gas source outlet respectively enters a main combustion stage fuel main pipe 18, a first duty stage fuel main pipe 19 and a second duty stage fuel main pipe 21 by adopting a central staged combustion mode, the gas in the main combustion stage fuel main pipe 18 enters a main combustion stage through a main combustion stage gas fuel pipeline 17 and a main combustion stage fuel pipeline, the gas entering the main combustion stage directly enters a cavity of a main mixing zone in the axial direction and the radial direction through a first main combustion stage fuel nozzle 4 and a second main combustion stage fuel nozzle 5, the fuel and the air from the secondary radial swirler 13 are evenly mixed in the main mixing area and then accelerated by the clapboard 8, the speed of the combustible mixed gas can be increased, the occurrence of backfire is guaranteed, the safety is guaranteed, the combustible mixed gas enters the head of the flame tube 12, the uniform premixed combustible gas is combusted in the combustion chamber, a lean premixed main combustion area is formed, and the low emission of the combustion chamber is realized; the gas fuel in the first duty fuel header pipe 19 enters the duty through the first duty gas fuel pipeline 16 and the first duty fuel pipeline, the gas fuel in the second duty fuel header pipe 21 also enters the duty through the second duty gas fuel pipeline 22 and the second duty fuel pipeline, the gas fuel entering the duty enters the combustion chamber through the first duty fuel nozzle 2 and the second duty fuel nozzle 3, diffusion and premixed combustion are carried out in the combustion chamber, and high combustion stability is ensured in a wide equivalence ratio range by adopting effective combination of diffusion combustion and premixed combustion; the on-duty combustion zone has the functions of improving ignition and starting under starting and low-power working conditions and improving combustion stability; the function of the premixing combustion area is to form uniformly distributed premixing mixed gas to realize low-emission combustion; the air in the flame tube 12 enters the combustion chamber in four strands, the first strand is the air needed for cooling the head of the combustion chamber and the flame tube 12, the second strand of air flows through the primary axial swirler 6 and the secondary radial swirler 13 and enters the combustion area of the flame tube 12, the third strand of air enters the main combustion area of the combustion chamber through the air adjusting device 23 positioned at the head of the flame tube 12 and is used for meeting the requirement that the equivalence ratio of the combustion area is in a low emission range when different heat value gas fuels are used, the fourth strand of air enters the combustion chamber through the mixing hole 9 positioned at the tail of the flame tube 12, so that the outlet temperature of the combustion chamber meets the requirement of a turbine inlet, the gas fuels are fully combusted in the flame tube 12 of the combustion chamber, and the air entering through the mixing hole 9 at the tail of the flame tube 12 is mixed and cooled and finally enters the.
Example 2
As shown in fig. 5 and 6, the outer casing 14 of the flame tube is located at the outer ring portion of the high-pressure igniter 7 and is provided with a second on-duty fuel nozzle 3 uniformly along the circumferential direction near one end of the primary axial swirler 6, and an axial angle between the axis of the second on-duty fuel nozzle 3 and the axial direction of the primary axial swirler 6 is 60 °. Other structures and connection methods are the same as those of embodiment 1.
Example 3
The installation angle of the central line of the flame tube 12 and the central line of the engine is 30 degrees. Other structures and connection methods are the same as those in embodiment 1 or embodiment 2.
Claims (7)
1. A gas turbine low emission combustor using gaseous fuel, characterized by: the combustion chamber head comprises an on-duty stage and a main combustion stage which are arranged in a concentric mode, the on-duty stage is arranged in the center, the main combustion stage is arranged on the periphery of the on-duty stage, the on-duty stage comprises a first-stage axial swirler and an on-duty stage fuel nozzle, the first-stage axial swirler is arranged in a central hole of the flame tube head, a flame tube outer casing is arranged outside the flame tube, the flame tube and the flame tube outer casing are coaxially arranged, an air channel is formed between the outer wall of the flame tube and the inner wall of the flame tube outer casing, high-pressure igniters are arranged at the centers of the flame tube outer casing and the first-stage swirler, the on-duty stage fuel nozzle comprises two parts, namely a first-duty stage fuel nozzle and a second-duty stage fuel nozzle, the head of the flame tube outer casing or the flame tube outer casing is close to the first-stage axial swirler, the second-duty stage fuel nozzles are uniformly arranged along the circumferential direction, and a first-duty stage fuel nozzle is, the main combustion stage comprises a secondary radial swirler, a main combustion stage fuel nozzle and a partition plate, the secondary radial swirler is arranged at the head part of the flame tube, the main combustion stage fuel nozzle comprises two parts, namely a first main combustion stage fuel nozzle and a second main combustion stage fuel nozzle, the head part and the center part of the secondary radial swirler are respectively and uniformly provided with the first main combustion stage fuel nozzle and the second main combustion stage fuel nozzle along the circumferential direction, a main combustion stage fuel pipeline of the head part of the flame tube penetrates through the head part of the outer casing of the flame tube, the inlet end of the main combustion stage fuel pipeline is connected with the gas outlet end of the main combustion stage fuel header pipe through a main combustion stage gas fuel pipeline, the head part of the outer casing of the flame tube is respectively provided with a first duty stage fuel pipeline and a second duty stage fuel pipeline, the first duty stage fuel pipeline is connected with the gas outlet end of the first duty stage fuel header pipe through a first duty stage gas fuel pipeline, the second duty fuel pipeline is connected with the air outlet end of the second duty fuel header pipe through a second duty gas fuel pipeline, the first duty fuel pipeline, the second duty fuel pipeline and the main fuel pipeline are fixedly arranged at the head part of the combustion chamber through flanges, the air inlet ends of the main fuel header pipe, the second duty fuel header pipe and the first duty fuel header pipe are all connected with an air source, the main fuel header pipe, the first duty fuel header pipe and the second duty fuel header pipe are all arranged on a pipeline bracket, the pipeline bracket is arranged on a compressor shell, the air outlet end of the flame tube is connected with a turbine guider through a bearing case, one end of the compressor is connected with the turbine shell, the other end of the compressor is fixed at the outlet section of the flame tube outer case, the flame tube and the turbine guider jointly form an exhaust outlet, and a swirler partition plate is arranged at the tail part of the second radial direction, the inner wall of the flame tube is provided with an air conditioning device which is positioned at one end of the tail part of the clapboard, and a plurality of mixing holes are distributed at the tail part of the flame tube.
2. A gas turbine low emission combustor using gaseous fuel as claimed in claim 1, wherein: the inner diameters of the first duty fuel nozzle and the second duty fuel nozzle are both 0.1-0.5mm, and the number of the first duty fuel nozzle and the second duty fuel nozzle is 16-24.
3. A gas turbine low emission combustor using gaseous fuel as claimed in claim 1, wherein: the included angle between the axis of the first-class on-duty fuel nozzle and the axis of the first-class axial swirler is 0-600。
4. A gas turbine low emission combustor using gaseous fuel as claimed in claim 1, wherein: the included angle between the axis of the second on-duty fuel nozzle and the axis of the first axial swirler is 0-600。
5. A gas turbine low emission combustor using gaseous fuel as claimed in claim 1, wherein: the inner diameters of the first main combustion stage fuel nozzle and the second main combustion stage fuel nozzle are both 0.1-0.5mm, and the number of the first main combustion stage fuel nozzle and the second main combustion stage fuel nozzle is 16-24.
6. A gas turbine low emission combustor using gaseous fuel as claimed in claim 1, wherein: the installation angle between the central line of the flame tube and the central line of the engine is 0-30 DEG0。
7. A gas turbine low emission combustor using gaseous fuel as claimed in claim 1, wherein: the equivalent ratio of the main combustion zone of the flame tube is 0.6-0.8, the lean-burn premixed lean-burn direct injection flame tube has the advantages of lean-burn premixing and lean-burn direct injection, and the combustion temperature of the main combustion zone of the flame tube is lower than 1800K.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910341915.1A CN110131750B (en) | 2019-04-26 | 2019-04-26 | Gas turbine low-emission combustion chamber using gas fuel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910341915.1A CN110131750B (en) | 2019-04-26 | 2019-04-26 | Gas turbine low-emission combustion chamber using gas fuel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110131750A CN110131750A (en) | 2019-08-16 |
| CN110131750B true CN110131750B (en) | 2020-08-11 |
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| JP7200077B2 (en) * | 2019-10-01 | 2023-01-06 | 三菱重工業株式会社 | Gas turbine combustor and its operation method |
| CN110779041B (en) * | 2019-10-09 | 2020-11-24 | 东方电气集团东方汽轮机有限公司 | Nozzle device of combustion chamber of gas turbine |
| CN110836383B (en) * | 2019-11-15 | 2021-10-26 | 中国科学院工程热物理研究所 | High-temperature flue gas generator and control method thereof |
| EP3929487A1 (en) * | 2020-06-25 | 2021-12-29 | General Electric Company | Combustor assembly for a gas turbine engine |
| CN112815356B (en) * | 2020-12-31 | 2022-07-15 | 哈尔滨工程大学 | Self-adaptive adjustable hydrogen-rich fuel low-emission micro-flame combustion chamber |
| CN114413283B (en) * | 2021-12-28 | 2023-05-12 | 北京动力机械研究所 | Integrated structure of cyclone sleeve and head plate |
| CN114992672B (en) * | 2022-06-11 | 2024-04-26 | 江苏中科能源动力研究中心 | Micro-premixing type combustion chamber of gas turbine |
| CN116293815A (en) * | 2023-03-22 | 2023-06-23 | 无锡明阳氢燃动力科技有限公司 | Low nitrogen hydrogen combustion chamber structure |
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