CN101799174B - Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber - Google Patents

Abstract

The invention relates to a main combustion stage tangential oil supply premix and pre-evaporation combustion chamber. The combustion chamber is in a single-ring chamber structure and is designed by adopting the conceptual design of staging combustion, and all the used amount of gas for combustion is supplied by the precombustion stage and the main combustion stage. The combustion chamber mainly comprises a flow-dividing type diffuser, a combustion chamber outer case, a combustion chamber inner case, a fuel nozzle, the precombustion stage, the main combustion stage, a flame tube outer wall and a flame tube inner wall. The precombustion stage utilizes a low-speed flow returning zone generated by swirl air entering the combustion chamber by a precombustion stage swirler component; the fuel needed by the main combustion stage is ejected by the tangential main combustion stage nozzle, is atomized under the air flow effect generated by entering of atomized air of the main combustion stage nozzle into a pipe, then flows into a premix and pre-evaporation ring pipe for evaporation, and is further blended with air; and even oil-gas mixed gas formed at the outlet of the premix and pre-evaporation ring pipe enters a flame tube and combusts under the pilot combustion of the precombustion stage flame. The combustion chamber has simple structure, and can effectively reduce the discharge of pollution simultaneously while guaranteeing that an aeroengine is in normal working state.

Description

Premixed pre-evaporative combustor with tangential oil supply to the main combustion stage

technical field

The invention relates to an aviation gas turbine combustor adopting a premixed pre-evaporative combustion organization mode. The combustor adopting the premixed pre-evaporative combustion organization mode has a simple structure, and can reduce combustion pollution emissions while ensuring efficient and stable operation of the combustor . the

Background technique

The basic performance and structural distribution of modern aero-engine combustors have reached a fairly high level, but for modern aero-engine combustors, there are still a lot of problems and challenges. The development of new materials, new processes, new structures, and new concepts Application is the source to ensure its continuous progress. the

The main development trend of modern aero-engine combustors is low-pollution combustion. Aeroengine combustors must meet increasingly stringent aeroengine pollution emission standards. The requirements of the currently adopted CAEP6 (Committee on Aviation Environmental Protection) standard are already very strict, especially for NOx pollution emission requirements, and as people's awareness of environmental protection increases, the future requirements will be more stringent. the

GE and PW, two well-known American aero-engine companies, have started research on low-pollution combustors. GE first developed a double-annular low-pollution combustion DAC (used in GE90 and CFM56), and PW adopted a similar RQL (rich combustion-quick combustion) Quench-lean burn, Rich burn-Quench-Lean burn, referred to as RQL) low-pollution combustor TALON II (for PW4000 and 6000 series). In terms of the next generation of low-pollution combustors, GE uses LDM (Lean Direct Mixing Combustion, Lean Direct Mixing Combustion) technology to develop the TAPS (Twin Annular Premixing Swirler) low-pollution combustor for its GEnx engine. In the bench full ring test verification of the combustion chamber, the NOx pollution emission is reduced by 50% compared with the CAEP2 emission standard. PW Company continues to adopt the RQL method and proposes a low-pollution combustion chamber that reduces NOx pollution emissions as TALON X. The head form used is the air atomizing nozzle developed by PW Company. The combustion chamber is a single annular cavity. In the fan-shaped test section of the V2500 engine The above test results are 50% lower than the CAEP2 standard. The low-pollution combustor developed by Rolls-Royce using LDM technology is ANTLE, which is a single-annular staged combustor. Its NOx pollution emissions are 50% lower than CAEP2 standards, and it is used in its new generation of engines with turbulence up to 1000. the

No matter what kind of advanced low-pollution combustion chamber, its key technology is to reduce NOx (nitrogen oxides), CO (carbon monoxide), UHC (unburned hydrocarbons) and smoke combustion technology, the core issue is to reduce the combustion area At the same time, the temperature field in the combustion zone is uniform, that is, the overall and local equivalence ratio control, and the uniformity of the equivalence ratio in the main combustion zone mainly depends on the uniformity of fuel atomization and oil-gas mixing. the

The invention is a new method for low-pollution combustion of aero-engines. According to the mechanism and test results of NOx and CO production, it can be known that the equivalent ratio of the main combustion zone of the combustion chamber in the range of 0.6-0.8 produces very little NOx and CO (the emission laws of UHC and CO are similar). Based on this principle, to take into account that the emissions of NOx, CO, and UHC are all in the low range, two factors should be considered: one is the average equivalence ratio of the main combustion zone, and the other is the uniformity of the average equivalence ratio of the main combustion zone. And this should be the case in all aero-engine work situations. The uniformity of the equivalence ratio in the main combustion zone mainly depends on the uniformity of fuel atomization and oil-gas mixing. This mainly depends on two aspects: one is the uniformity of fuel particle diameter distribution, that is, the uniformity of SMD distribution; the other is the uniformity of fuel oil mist concentration distribution. In terms of the combustion method, uniform premixed combustion should be adopted to meet the requirements of uniformity ratio of the main combustion zone to reduce pollution emissions. the

The current conventional combustion methods cannot reduce NOx, CO and UHC. The reason is determined by the current design method of the combustion chamber. For conventional combustors, in the high power state, due to the liquid mist diffusion combustion method, the local equivalence ratio of the combustion zone is always around 1, which is far beyond the range of equivalence ratio required for low-pollution combustion. At this time, although CO and The emission of UHC is low, but the emission of NOx reaches the maximum. In the low power state, the equivalence ratio of the combustion zone is very low, which is far below the equivalence ratio range required for low-pollution combustion. At this time, although NOx emissions are low, CO and UHC emissions are high. In addition, because the conventional combustion chamber generally adopts the diffusion combustion method, the local equivalence ratio is very uneven, so for the conventional combustion chamber, it cannot meet the low pollution requirements in the entire engine working range. the

Contents of the invention

The technical problem of the present invention is to provide an aero-engine combustor adopting a premixed pre-evaporative combustion organization mode of tangential fuel supply at the main combustion stage, which can effectively reduce the The pollution emissions from combustion in the combustion chamber include NOx, smoke, CO and UHC, and the structure is simple. the

The technical solution of the present invention: the premixed pre-evaporation combustor with tangential oil supply from the main combustion stage is a single-ring cavity structure, adopts the conceptual design of staged combustion, and the gas consumption for combustion is all supplied by the pre-combustion stage and the main combustion stage The fuel stage adopts the swirling stable diffusion flame combustion organization mode, the main combustion stage adopts the premixed pre-evaporation combustion organization mode of tangential oil supply, and the cooling gas and mixed gas are supplied from the flame tube. The premixed pre-evaporation combustor with tangential fuel supply in the main combustion stage is mainly composed of a split diffuser, a combustion chamber outside the combustion chamber, a combustion chamber inside the casing, a fuel nozzle, a flame tube head, a flame tube outer wall and a flame tube inner wall. The head of the flame tube is composed of the pre-combustion stage and the main combustion stage: the pre-combustion stage includes the pre-combustion stage swirler assembly, the pre-combustion stage nozzle, the end wall of the pre-combustion stage head and the inner deflector of the pre-combustion stage head, the pre-combustion stage The combustion stage uses the low-velocity recirculation area to stabilize the flame generated by the swirling air that enters the combustion chamber from the pre-combustion stage swirler assembly. The inner ring is connected, the pre-combustion stage nozzle is located in the pre-combustion stage swirler assembly, and is coaxial with the pre-combustion stage swirler assembly, and the inner deflector of the pre-combustion stage head is connected to the end wall of the pre-combustion stage head; The main combustion stage includes the main combustion stage nozzle, the main combustion stage premixing pre-evaporation section, the main combustion stage head integral end wall and the main combustion stage head integral deflector. The mixed pre-evaporation ring pipe and the main combustion stage nozzle atomization air inlet pipe are composed. The nozzle adopts the injection method of setting multiple single fuel nozzles on the same circumference, and the center of the circle is located on the axis of the pre-combustion stage nozzle. Correspondingly, after the fuel required by the main combustion stage is sprayed from the nozzle of the main combustion stage, it is first atomized by the airflow of the atomization air inlet pipe of the main combustion stage nozzle to form an oil-air mixture, and then flows into the premixing pre-evaporation ring pipe of the main combustion stage , the oil-air mixture evaporates in the premixed pre-evaporation loop of the main combustion stage, and is further mixed with air, and forms a uniform jet of oil-air mixture at the outlet of the premixed pre-evaporation loop of the main combustion stage and enters the flame tube. Combustion is carried out under the ignition of the flame of the pre-combustion stage. The pre-mixing and pre-evaporation section of the main combustion stage is connected with the outer wall of the flame tube and the outer wall of the flame tube through the overall end wall of the main combustion stage head. The overall end wall of the stage head is connected; the pre-combustion stage nozzle and the main combustion stage nozzle are connected to the fuel nozzle seat, and are connected to the casing outside the combustion chamber through the fuel nozzle seat. the

The principle of the present invention is: Generally speaking, the realization of low pollution emission from the combustion chamber of an aero-engine is mainly through two aspects, one is to control the overall equivalent ratio range of the combustion area in the entire combustion chamber; the other is to control the combustion of the entire combustion area in the combustion chamber Uniformity, that is, the uniformity of the equivalence ratio, because the local equivalence ratio is too large due to local rich oil will also greatly increase the pollution emissions of the engine. According to the above principles and considering the working characteristics of the aero-engine combustion chamber, the present invention adopts the design concept of staged combustion, so that the combustion gas is supplied into the combustion chamber from the pre-combustion stage and the main combustion stage respectively, and the fuel is supplied in stages, The equivalence ratio of the fuel in the combustion zone is controlled to be in the low-pollution combustion zone under different working conditions of the aero-engine, so as to achieve the purpose of reducing combustion pollutant emissions. The pre-combustion stage is started in a small state such as idling, and the equivalence ratio of the combustion zone falls in the above-mentioned low-pollution combustion equivalence ratio range when the small state is maintained, and the stability of combustion is good, and it is easy to start. The main combustion stage is started only when the engine is working in a large state. The main combustion stage adopts the premixed pre-evaporative combustion organization mode of tangential fuel supply, and the equivalence ratio of the combustion zone is controlled within the above-mentioned low-pollution combustion equivalence ratio range. The use of the above-mentioned low-pollution combustor can ensure that the equivalent ratio of the combustion zone of the aero-engine combustor is controlled within the range of low-pollution combustion under all working conditions. At the same time, it can control the uniformity, mixing degree and The degree of evaporation is used to control the uniformity of the equivalence ratio in the combustion zone, so as to meet the performance requirements of the aero-engine low-pollution combustion chamber with low pollution emissions and good stability. the

The advantages of the present invention compared with the prior art are as follows:

(1) The combustion chamber of the present invention is a single-ring cavity structure, adopts the conceptual design of staged combustion, and the gas consumption for combustion is all supplied by the pre-combustion stage and the main combustion stage. The flame tube is supplied, which increases the efficiency of the combustion chamber and simplifies the structure of the combustion chamber. the

(2) The main combustion stage of the present invention adopts a combustion organization mode of premixing and preevaporation with tangential fuel supply. Tangential fuel supply can simplify the structure of the main combustion stage while obtaining a good primary atomization effect of fuel. Premixing and pre-evaporation can further mix the atomized fuel and air evenly to form a uniform jet of fuel-air mixture. When the uniform jet of oil-air mixture is ignited, the oil-air mixture can be completely burned in a very short time, thereby reducing the pollution emission of the combustion chamber. the

(3) The pre-combustion stage of the present invention adopts a swirling stable diffusion flame combustion organization mode, and the main combustion stage adopts a premixed pre-evaporation combustion organization mode of tangential fuel supply. This combined combustion mode can realize the aeroengine combustion chamber in a wide It can work efficiently and stably within the working range, and at the same time can achieve low pollution emissions from the combustion chamber. the

Description of drawings

Fig. 1 is the working schematic diagram of the present invention;

Fig. 2 is a structural sectional view of the present invention;

Fig. 3 is a cross-sectional view of the flame tube head structure of the present invention;

Fig. 4 is the structural representation of main combustion stage premixed pre-evaporation section assembly of the present invention;

Fig. 5 is the structural cross-sectional view of the main combustion stage premixed pre-evaporation section assembly of the present invention;

Fig. 6 is the structural representation of the pre-combustion stage assembly of the present invention;

Figure 7 is a cross-sectional view of the pre-combustion stage assembly structure of the present invention;

Fig. 8 is a schematic structural view of the pre-combustion stage cyclone assembly of the present invention;

Fig. 9 is a structural sectional view of the pre-combustion stage cyclone assembly of the present invention;

Fig. 10 is a schematic view of the flame cylinder structure of a specific embodiment of the present invention;

Fig. 11 is the schematic diagram of the structure of the fuel nozzle used in the present invention;

Fig. 12 is a schematic diagram of the injection mode of the main combustion stage nozzle adopted in the present invention. the

In the figure: 1. Airflow at the inlet of the combustion chamber, 2. Airflow at the head of the flame tube, 3. Airflow in the annular cavity outside the combustion chamber, 4. Airflow in the annular cavity inside the combustion chamber, 5. Airflow at the outlet of the combustion chamber, 6. The combustion area of the pre-combustion stage, 7. Combustion area of main combustion stage, 8. Divider diffuser, 9. Outer casing of combustion chamber, 10. Case inside combustion chamber, 11. Fuel nozzle, 12. Integral end wall of main combustion stage head, 13. Main combustion chamber Integral deflector of the stage head, 14. head of the flame tube, 15. outer wall of the flame tube, 16. inner wall of the flame tube, 17. mixing holes on the outer wall of the flame tube, 18. mixing holes on the inner wall of the flame tube, 19. divergent cooling holes , 20. Pre-combustion stage, 21. Main combustion stage premixing pre-evaporation section, 22. Pre-combustion stage swirler assembly, 23. Pre-combustion stage head end wall, 24. Pre-combustion stage head deflector, 25 .Pre-combustion stage primary cyclone, 26. Pre-combustion stage primary cyclone pressure plate, 27. Pre-combustion stage secondary cyclone, 28. Main combustion stage premixing and pre-evaporation ring pipe, 29. Main combustion stage Nozzle atomizing air inlet tube, 30. Pre-firing stage nozzle, 31. Main firing stage nozzle, 32. Fuel nozzle seat, 33. Main firing stage. the

Detailed ways

As shown in Figure 1 and Figure 2, the premixed pre-evaporation combustor with tangential oil supply designed by the present invention has a single-ring cavity structure, adopts the conceptual design of staged combustion, and the gas consumption for combustion is all supplied by the pre-combustion stage and the main combustion stage. The pre-combustion stage adopts a swirling stable diffusion flame combustion organization, the main combustion stage adopts a pre-mixed pre-evaporation combustion organization with tangential oil supply, and the cooling gas and mixed gas are supplied from the flame tube. This combustion chamber comprises two combustion areas---the pre-combustion level combustion area 6 and the main combustion level combustion area 7, two combustion areas share the same inner and outer boundaries, the outer boundary of the combustion area is the outer wall 15 of the flame tube, and the inner boundary of the combustion area It is the inner wall 16 of the flame tube, and the outer wall 15 of the annular flame tube and the inner wall 16 of the flame tube are located between the annular casing 9 outside the combustion chamber and the casing 10 inside the combustion chamber. Flame tube outer wall mixing holes 17 are arranged on the flame tube outer wall 15, flame tube inner wall mixing holes 18 are arranged on the flame tube inner wall 16, and the gas for mixing passes through the flame tube outer wall mixing holes 17 and the flame tube inner wall mixing holes. 18 into the combustion chamber to adjust the outlet temperature distribution of the combustion chamber. The flame tube outer wall 15 and the flame tube inner wall 16 are also arranged with cooling, and the cooling method can adopt film cooling, divergent cooling or composite cooling mode, which is used to cool the flame tube wall surface to ensure the life of the combustion chamber. In a specific embodiment, the cooling mode of the outer wall 15 of the flame tube and the inner wall 16 of the flame tube adopts divergent cooling, and the outer wall 15 of the flame tube and the inner wall 16 of the flame tube are provided with divergent cooling holes 19. 2 shown. the

Upstream of the combustion zone 6 of the pre-combustion stage is the flame tube head 14, which includes the pre-combustion stage 20 and the main combustion stage 39, the flame tube head 14, as shown in FIG. 3 . the

The main combustion stage 33 includes the main combustion stage nozzle 31 , the main combustion stage premixing and pre-evaporation section 21 , the main combustion stage head integral end wall 12 and the main combustion stage head integral deflector 13 . The premixing and pre-evaporating section 21 of the main combustion stage is connected to the outer wall 15 of the flame tube and the inner wall 16 of the flame tube through the integral end wall 12 of the head of the main combustion stage, and the connection method can be welding, thread or bolt. The premixing and pre-evaporation section 21 of the main combustion stage is shown in FIG. 4 and FIG. 5 . The shape of the air inlet hole on the main combustion stage premixed pre-evaporator ring pipe 28 can be a round hole, a half hole, a square hole or a groove, and the opening angle is -90 to 90 degrees. The specific implementation is shown in Fig. 4 and Fig. 5, taking the air inlet hole on the premixing pre-evaporation ring pipe 28 of the main combustion stage as a circular hole as an example. During installation, the atomized air inlet pipe 29 of the main combustion stage nozzle and the main combustion stage premixed pre-evaporation ring pipe 28 are combined into a main combustion stage premixed pre-evaporation section 21 by integral manufacturing or threaded or bolted or welded connections. The installation of the premixing and preevaporating section 21 of the main combustion stage can be completed. the

The pre-combustion stage 20 includes a pre-combustion stage swirler assembly 22, a pre-combustion stage nozzle 30, a pre-combustion stage head end wall 23, and a pre-combustion stage head deflector 24. The pre-combustion stage 20 is shown in Figures 6 and 7 As shown, the pre-combustion stage swirler assembly 22 is shown in FIGS. 8 and 9 . The pre-combustion stage swirler assembly 22 is connected to the inner ring 29 of the main combustion stage premixing and pre-evaporation section through the pre-combustion stage head end wall 23 . The connection mode between the head end wall 23 of the pre-combustion stage and the inner ring 29 of the pre-mixing and pre-evaporation section of the main combustion stage can be integrally manufactured or threaded, bolted or welded. The number of stages of the swirlers used by the pre-combustion stage swirler assembly 22 is 1≤n≤5. Each cyclone can adopt the structure of the cyclone, which can be an axial cyclone, a radial cyclone, or a tangential cyclone. When the number of stages of the pre-combustion level swirler assembly 22 is n=1, the swirler can be directly connected to the pre-combustion level head end wall 23 by welding, bolts or threads; when the pre-combustion level swirler When the number of stages of the component 18 is 1<n≤5, while ensuring the coaxiality of the cyclones at all levels, the cyclones at all levels are first connected into a whole by welding, bolts or threads to form a pre-combustion stage cyclone The flow device assembly 22 is then connected to the end wall 23 of the pre-combustion stage head. In a specific embodiment, taking the pre-combustion stage cyclone assembly 22 as an example using a secondary cyclone solution, as shown in Figure 6, Figure 7, Figure 8 and Figure 9, the pre-combustion stage cyclone assembly 22 includes a pre-combustion stage cyclone The primary cyclone 25 of the combustion stage, the pressure plate 26 of the primary cyclone of the pre-combustion stage and the secondary cyclone 27 of the pre-combustion stage. During installation, the pre-combustion stage head end wall 23 and the main combustion stage premixed pre-evaporation ring pipe 28 are connected together by integral manufacturing or threaded or bolted or welded; then the pre-combustion stage head deflector 24 It is connected with the end wall 23 of the head of the pre-combustion stage by thread, bolt or welding; while ensuring that the primary cyclone 25 of the pre-combustion stage is coaxial with the secondary cyclone 27 of the pre-combustion stage, welding or threaded Or the way of bolt connection, so that the pressure plate 26 of the pre-combustion stage primary cyclone is connected with the pre-combustion stage secondary cyclone 27, and the pre-combustion stage primary cyclone 25 is clamped between the pre-combustion stage primary cyclone Between the pressure plate 26 of the flow device and the secondary cyclone 27 of the pre-combustion stage, the three parts are connected as a whole to form the pre-combustion stage cyclone assembly 22; then the pre-combustion stage cyclone is welded or threaded or bolted The swirler assembly 22 is fixed to the end wall 23 of the head of the pre-combustion stage, and the swirler assembly 22 of the pre-combustion stage is connected to the inner ring of the pre-mixing and pre-evaporating ring pipe 28 of the main combustion stage through the end wall 23 of the head of the pre-combustion stage , connect and fix the pre-combustion stage swirler assembly 22 and the main combustion stage premixing and pre-evaporation section 21 , thereby completing the installation of the pre-combustion stage 20 . the

After the main combustion stage premixing pre-evaporation section 21 and the precombustion stage swirler assembly 22 are installed, the main combustion stage nozzle 31 and the precombustion stage nozzle 30 are inserted at the corresponding positions, thereby completing the installation of the flame tube head 14 . the

As shown in Figures 1 and 2, the pre-combustion stage nozzle 30 and the main combustion stage nozzle 31 are all installed on the fuel nozzle seat 32 to form a whole fuel nozzle 11. After the installation of the flame tube head 14 is completed, from The opening of the casing 9 outside the combustion chamber stretches into the combustion chamber and is inserted into the corresponding position, thereby completing the installation of the combustion chamber. The single fuel nozzle (34) adopted by the pre-combustion stage nozzle 30 and the main combustion stage nozzle 31 can be a pressure atomization nozzle, a pneumatic atomization nozzle, or a combined nozzle. The structure of the fuel nozzle 11 in the specific embodiment is shown in FIG. 11 . The pre-combustion stage nozzle 30 corresponds to the pre-combustion stage primary swirler 25 , and the axis of the pre-combustion stage nozzle 30 coincides with the axis of the pre-combustion stage primary swirler 25 . The main combustion stage nozzle 31 is located at the inlet of the main combustion stage nozzle atomization air inlet pipe 29, and is coaxial with the main combustion stage nozzle atomization air inlet pipe 29. The main combustion stage nozzle 31 adopts a plurality of single fuel nozzles 34 arranged on the same circumference The injection method, the center of the circle is located on the axis of the pre-combustion stage nozzle 30, the number of single fuel nozzles 34 used by the main combustion stage nozzle 31 corresponds to the number of the main combustion stage nozzle atomized air entering the pipe 29, the main combustion stage The number of single fuel nozzles 34 used in the nozzle 31 is 0 < p ≤ 50, and the cutting angle A between the injection line of a single fuel nozzle 34 and the circumference is -90 to 90 degrees. The injection diagram of the main combustion stage nozzle 31 is shown in FIG. the

After the inlet airflow 1 of the combustion chamber enters the combustion chamber, it is divided into three streams after being decelerated and diffused by the split diffuser 8: the airflow 2 at the head of the flame tube, the airflow 3 outside the combustion chamber and the airflow 4 inside the combustion chamber to meet the The demand for air flow in each part of the combustion chamber, the reasonable organization of the flow field in the combustion chamber, facilitates the efficient and stable organization of combustion. the

The flame tube head airflow 2 is all combustion gas, accounting for 40% to 80% of the combustion chamber inlet airflow 1, except that 0% to 25% of the flame tube head airflow 2 is used for the pre-combustion stage head end wall 23 and Except for the cooling of the integral end wall 12 of the head of the main combustion stage, the rest are supplied by the pre-combustion stage 20 and the main combustion stage 33 respectively, and are used for the atomization and combustion of fuel corresponding to the pre-combustion stage 20 and the main combustion stage 33, and the pre-combustion stage 20 The required gas volume accounts for 10% to 40% of the total combustion gas volume, and the rest is supplied by the main combustion stage 39 . After the fuel oil required by the pre-combustion stage 20 is sprayed out by the pre-combustion stage nozzle 30, it is sheared and broken by the air swirl flow from the pre-combustion stage swirler assembly 22 to form oil mist, and then enters the pre-combustion stage swirler assembly 22 The low-velocity recirculation zone formed by the air swirl—the pre-combustion stage combustion zone 6 forms diffusion combustion. The pre-combustion nozzle 30 can be a pressure atomization nozzle, a pneumatic atomization nozzle, or a combined nozzle. The atomization and dispersion effect under the combined action of the air swirl of the component 22 determines: the better the atomization and dispersion effect, the more uniform the oil mist distribution, the more conducive to organizing efficient, stable and low-pollution combustion in the pre-combustion stage combustion area 6. After the fuel oil required by the main combustion stage 33 is sprayed through the main combustion stage nozzle 31, it is first atomized under the action of the airflow passing through the main combustion stage nozzle atomizing air inlet pipe 29 to form an oil-air mixture, and then flows into the main combustion stage premixed premixed gas. Evaporation ring 28, the atomized oil-air mixture evaporates and spreads in the main combustion stage premixing pre-evaporation ring 28, and forms a uniform oil-air mixture jet at the outlet of the main combustion stage premixing pre-evaporation section 21. The jet of oil-air mixture is ignited under the ignition of the pre-combustion stage flame to form the combustion zone 7 of the main combustion stage. The main combustion stage nozzle 31 is located at the entrance of the main combustion stage nozzle atomization air inlet pipe 29, and is coaxial with the main combustion stage nozzle atomization air inlet pipe 29. method, the center of the circle is located on the axis of the pre-combustion stage nozzle 30, the number of nozzles used corresponds to the number of atomized air inlet pipes 29 of the main combustion stage nozzle, and the number of fuel nozzles used is 0<p≤50 The injection of a single nozzle The cutting angle A between the line and the circumference is -90 to 90 degrees. The main combustion stage nozzle 31 can be a pressure atomization nozzle, it can also be a pneumatic atomization nozzle, and it can also be a combined nozzle. Under the joint action of the atomized air entering the pipe 29 and the vaporized mixed gas flow from the premixed pre-evaporation ring pipe 28 of the main combustion stage, the uniformity of the oil-air mixture formed at the outlet of the premixed preevaporation section 21 of the main combustion stage determines: The more uniform the oil-air mixture formed, the more conducive it is to organize rapid, efficient, stable and low-pollution combustion in the combustion zone 7 of the main combustion stage. the

The airflow 3 of the annular cavity outside the combustion chamber includes the cooling gas of the outer wall 13 of the flame tube and the gas for mixing in the mixing holes 15 of the outer wall of the flame tube. The annular cavity airflow 4 in the combustion chamber includes the cooling gas of the inner wall 14 of the flame tube and the mixing gas of the mixing hole 16 of the inner wall of the flame tube. Wherein the cooling gas of the outer wall 13 of the flame tube or the inner wall 14 of the flame tube accounts for 0% to 20% of the inlet airflow 1 of the combustion chamber, and the mixing gas of the mixing hole 15 of the outer wall of the flame tube or the mixing hole 16 of the inner wall of the flame tube accounts for 0% to 20% of the inlet airflow of the combustion chamber. 10% to 30% of 1. the

The overall structure of the combustion chamber and the fuel nozzle structure of the specific embodiment are shown in Figure 10, Figure 11 and Figure 12. FIG. 10 is a schematic diagram of the structure of the flame tube, FIG. 11 is a schematic diagram of the structure of the fuel nozzle 11 used at this time, and FIG. 12 is a schematic diagram of the injection of the main fuel stage nozzle 31 . As shown in FIG. 10 , the flame tube head 14 is connected to the flame tube outer wall 15 and the flame tube inner wall 16 through the integral end wall 12 of the main stage head. The flame tube head 14 is composed of a pre-combustion stage 20 and a main combustion stage 33: the main combustion stage 33 includes a main combustion stage nozzle 31, a main combustion stage premixing pre-evaporation section 21, a main combustion stage head integral end wall 12 and a main combustion stage The overall deflector 13 of the stage head, the premixing and pre-evaporation section 21 of the main combustion stage are shown in Figure 4 and Figure 5; The head end wall 23, the pre-combustion stage head deflector 24, and the pre-combustion stage swirler assembly 22 are shown in FIGS. 8 and 9 . The pre-combustion stage swirler assembly 22 is coaxial with the main combustion stage premixing pre-evaporation section 21, and the fuel nozzle 11 used at this time is shown in Figure 11, and the pre-combustion stage nozzle 30 is opposite to the pre-combustion stage primary swirler 25 , the main fuel stage nozzle 31 corresponds to the main fuel stage nozzle atomization air inlet hole 29 . When the aero-engine works in a low power state, only the pre-combustion stage 20 supplies fuel to the combustion chamber, and the main combustion stage 33 only passes through air without supplying fuel. Diffusion combustion is formed inside, thereby ensuring reliable stability and starting characteristics of the engine combustion chamber, and reducing CO and UHC pollution emissions. When the aero-engine is working in a high-power state, the pre-combustion stage 20 and the main combustion stage 33 supply oil simultaneously, the pre-combustion stage 20 forms diffusion combustion in the pre-combustion stage combustion zone 6, and the main combustion stage 33 is in the pre-combustion stage combustion zone 6 The periphery of the main combustion stage forms the combustion zone 7 of the main combustion stage. The main combustion stage 33 adopts the premixing and pre-evaporation method of tangential fuel supply. On the one hand, the fuel required by the main combustion stage 33 can be quickly and evenly mixed in the main combustion stage premixing and pre-evaporation section 21 to form an oil-air mixture. After the mixed gas enters the flame tube, it can be burned quickly and well, thereby reducing the formation of NOx. On the other hand, it can burn the unburned CO and UHC in the pre-combustion stage. It can be seen that the pre-mixed pre-evaporative combustor can effectively reduce the pollution emissions of the combustor while ensuring efficient and stable combustion within the wide operating range of the aero-engine, and can also obtain a better outlet temperature distribution with the assistance of the mixing hole airflow performance. the

Parts not described in detail in the present invention belong to common knowledge in the field. the

The above is only a preferred embodiment of the present invention, it should be pointed out that, for those of ordinary skill in the art, without departing from the principle of the present invention, some improvements and modifications can also be made, and these improvements and modifications can also be made. It should be regarded as the protection scope of the present invention. the

Claims (8)

1. the premix and pre-evaporation combustion chamber of main combustible stage tangential oil supply; It is characterized in that: said combustion chamber is the monocycle cavity configuration; Adopt the fractional combustion mode, the burning gas consumption is all infeeded by pre-combustion grade and main combustion level, and pre-combustion grade adopts swirl stabilized diffusion flame burning organizational form; Main combustion level adopts the premix and pre-evaporation burning organizational form of tangential oil supply, and cold gas and mixed gas infeed from burner inner liner; The premix and pre-evaporation combustion chamber of said main combustible stage tangential oil supply mainly is made up of casing (10), fuel nozzle (11), burner inner liner head (14), burner inner liner outer wall (15) and burner inner liner inwall (16) in shunting diffuser (8), outer combustion case (9), the combustion chamber; Burner inner liner head (14) is made up of pre-combustion grade (20) and main combustion level (33): pre-combustion grade (20) comprises deflector (24) in pre-combustion grade swirler assembly (22), pre-combustion grade nozzle (30), pre-combustion grade head end wall (23) and the pre-combustion grade head; Pre-combustion grade (20) is utilized the low speed recirculating zone retention flame that is got into the rotational flow air generation of combustion chamber by pre-combustion grade swirler assembly (22); Pre-combustion grade swirler assembly (22) is connected with main combustion level premix and pre-evaporation endless tube (28) through pre-combustion grade head end wall (23); Pre-combustion grade nozzle (30) is positioned at pre-combustion grade swirler assembly (22); And coaxial with pre-combustion grade swirler assembly (22), deflector (24) links to each other with pre-combustion grade head end wall (23) in the pre-combustion grade head; Main combustion level (33) comprises main combustion level nozzle (31), main combustion level premix and pre-evaporation section (21), the main whole end wall (12) of combustion level head and the whole deflector (13) of main combustion level head; Main combustion level premix and pre-evaporation section (21) gets into pipe (29) by main combustion level premix and pre-evaporation endless tube (28) and main combustion level nozzle atomization air and forms; Main combustion level nozzle (31) is positioned at main combustion level nozzle atomization air and gets into pipe (29) inlet; And it is coaxial with main combustion level nozzle atomization air entering pipe (29); Main combustion level nozzle (31) is employed in the spray regime that a plurality of single fuel nozzles (34) are set on the same circumference; The center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle (30), and the quantity of the single fuel nozzle (34) of main combustion grade nozzle (31) employing is corresponding with the quantity that (29) are managed in the entering of main combustion level nozzle atomization air, after the required fuel oil of main combustion level (33) fires level nozzle (31) ejection by the master; The aerodynamic atomization that is at first got into pipe (29) by main combustion level nozzle atomization air forms fuel-air mixture; Flow into a main combustion level premix and pre-evaporation endless tube (28) then, fuel-air mixture evaporates in main combustion level premix and pre-evaporation endless tube (28), and with the further blending of air; Form uniform fuel-air mixture jet gets in the burner inner liner in the exit of main combustion level premix and pre-evaporation endless tube (28); Under the igniting of pre-combustion grade flame, burn, main combustion level premix and pre-evaporation section (21) links to each other with burner inner liner inwall (16) with burner inner liner outer wall (15) through the main combustion level whole end wall of head (12), and the main combustion level whole deflector of head (13) links to each other with the main combustion level whole end wall of head (12); Pre-combustion grade nozzle (30) and main combustion level nozzle (31) all are connected on the fuel nozzle seat (32), form fuel nozzle (11), and fuel nozzle (11) links to each other with outer combustion case (9) through fuel nozzle seat (32).

2. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: be provided with burner inner liner outer wall blending hole (17) at described burner inner liner outer wall (15) rear portion; Be provided with burner inner liner inwall blending hole (18) at described burner inner liner inwall (16) rear portion; Blending usefulness gas gets into burner inner liner from burner inner liner outer wall blending hole (17) and burner inner liner inwall blending hole (18) respectively, with control combustor exit Temperature Distribution.

3. premix and pre-evaporation combustion chamber according to claim 1 and 2; It is characterized in that: described shunting diffuser (8) is divided into three strands with combustion chamber inlet air flow (1): ring cavity air-flow (4) in ring cavity air-flow (3) and the combustion chamber outside burner inner liner head air-flow (2), the combustion chamber, and to satisfy the demand of combustion chamber each several part to air mass flow.

4. premix and pre-evaporation combustion chamber according to claim 1 and 2 is characterized in that: the single fuel nozzle (34) that said pre-combustion grade nozzle (30) and main combustion level nozzle (31) adopt is pressure atomized fog jet, pneumatic nozzle or combined nozzle.

5. premix and pre-evaporation combustion chamber according to claim 1 is characterized in that: progression 1≤n≤5 of the cyclone that said pre-combustion grade swirler assembly (22) adopts; It is axial swirler that every grade of cyclone adopts the structure of cyclone, or radial swirler, or the tangential swirl device; When the progression n=1 of pre-combustion grade swirler assembly (22), cyclone directly is connected with pre-combustion grade head end wall (23); When the progression 1＜n of pre-combustion grade swirler assembly (22)≤5, cyclones at different levels connect into an integral body earlier, are connected with pre-combustion grade head end wall (23) after forming pre-combustion grade swirler assembly (22) again.

6. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: said main combustion level nozzle (31) is employed in the spray regime that a plurality of single fuel nozzles (34) are set on the same circumference; The center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle (30); The quantity of the single fuel nozzle (34) that adopts is corresponding with the quantity that main combustion level nozzle atomization air gets into pipe (29); Quantity 0＜p≤50 of single fuel nozzle (34), the spray line of single fuel nozzle (34) and the corner cut A of circumference are-90～90 degree.

7. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: the burning usefulness gas of said combustion chamber is all infeeded by burner inner liner head (14); Burner inner liner head air-flow accounts for 40%～80% of combustion chamber inlet air flow: the cooling institute air demand of pre-combustion grade head end wall (23) and the main combustion level whole end wall of head (12) accounts for 0%～25% of burner inner liner head air-flow; Pre-combustion grade (20) institute air demand accounts for 10%～40% of whole burning tolerance, and all the other main combustion level premix and pre-evaporation sections (21) by main combustion level (33) infeed.

8. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: the burner inner liner outer wall (15) of said combustion chamber and the type of cooling of burner inner liner inwall (16) adopt the air film cooling, disperse the cooling or the compound type of cooling, wall surface temperature is controlled the life-span that prolongs burner inner liner.

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