CN101285591A - Integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion-chamber - Google Patents

Abstract

An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber, the combustion chamber is a single-ring cavity structure, composed of a combustion chamber head and a flame tube, wherein the combustion chamber head includes a pre-combustion stage in the center and the peripheral main combustion stage; the main combustion stage includes a direct-injection air atomization nozzle and a main combustion stage radial swirler; the injection of the main combustion stage fuel and the main combustion stage radial swirler are integrated, and the direct injection The main combustion grade fuel sprayed by the air atomizing nozzle enters the main combustion stage radial swirler vane channel of the main combustion stage radial swirler vane and mixes with the swirling air of the main combustion stage radial swirler , the premixed oil-air mixture enters the combustion zone through the main fuel stage mixing chamber for combustion. This combustion method can effectively reduce the emission of pollutants in the combustion chamber, and at the same time can reduce the length of the combustion chamber; the invention is mainly used for aero-engines Combustion chambers can also be used in industrial gas turbine and marine gas turbine combustion chambers to reduce pollutants discharged into the atmosphere.

Description

An Integrated Fuel Injection Radial Swirler Premixing Preevaporation Low Pollution Combustion Chamber

technical field

The invention relates to a low-pollution emission combustion chamber, in particular to an integrated fuel injection radial swirler premixing pre-evaporation low-pollution combustion chamber.

Background technique

The main development trend of aero-engine combustors is low-pollution combustion. Aeroengine combustors must meet increasingly stringent aeroengine pollution emission standards. The currently adopted CAEP4 (Committee on Aviation Environmental Protection) standard has very strict requirements, especially for NOx pollution emission requirements, while the CAEP6 standard that will be adopted after 2008 is even more stringent. The pollution emission requirements of industrial gas turbines reach single digits—one ten-thousandth concentration emission requirements.

In general, aeroengine pollutants can be divided into two categories: nitrogen oxides (NOx) due to high flame temperatures; carbon monoxide and unburned hydrocarbons (CO and UHC). According to the mechanism of pollutant generation and the experimental results, the equivalent ratio of the combustion zone of the combustion chamber is within a small range (0.6-0.8), and the emission of the above two types of pollutants reaches the minimum. For conventional combustors, in high power state, due to the liquid mist diffusion combustion method, the local equivalence ratio of the combustion zone is always around 1, far exceeding the equivalence ratio range requirements for low-pollution combustion mentioned above, so CO and UHC The emission is small, but the emission of NOx reaches the maximum. In low power state, the equivalence ratio of the combustion zone is very low, far below the equivalence ratio range required for low-pollution combustion. NOx emissions are low, but CO and UHC emissions are high, so for conventional combustion chambers, it cannot meet the requirements. Low pollution requirements over the entire engine operating range.

GE Engine Company proposed a low-pollution combustor - TAPS (Twin Annular Premixing Swirler). The head of the combustor includes a main combustion stage and a pre-combustion stage. Following this line of thinking, GE applied for several US patents. The US patents with application numbers 6389815, 6354072, 0178732 and 6381964 respectively proposed the main combustion stage scheme: the main combustion stage fuel oil is injected into a certain position after the turn at the rear of the radial swirler to form a premixed pre-evaporated oil-gas mixture . It can be seen from the drawings of these patents that the distance from the fuel injection point to the entrance of the combustion zone is about half the height of the head structure of the combustion chamber. For this staged combustion chamber, the height of the head structure is greater than that of the conventional combustion chamber. , so the axial length of the combustion chamber head is too long, which affects the length and weight requirements of the combustion chamber and even the engine. This problem also exists in the US Patent Application No. 6453660. The distance from the fuel injection point to the entrance of the combustion zone is about one-third of the height of the head structure of the combustion chamber, and the fuel injection system of the main fuel stage is very complicated, causing the combustion chamber The head structure is very complex. The above-mentioned US patents all achieve low pollution requirements in the entire engine operating range, but the fuel injection point of the main combustion stage is a certain distance from the outlet of the radial swirler, and this distance increases the axial length of the combustion chamber head .

Contents of the invention

The technical problem to be solved by the present invention is: to overcome the deficiencies of the above-mentioned prior art, adopt the integrated fuel injection/radial swirler scheme, through the fuel injection method in the radial swirler blade channel and the radial swirler The oil-air mixture in the channel flows at the turn of the outlet of the radial swirler, reducing the distance from the fuel injection point to the entrance of the combustion zone, thereby reducing the axial length of the combustion chamber head structure, and effectively reducing the pollution emissions of the combustion chamber

The technical solution adopted by the present invention to solve the technical problem is: an integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber, which is composed of a combustion chamber head 26 and a flame tube, and is characterized in that: the combustion chamber It is a single-annular cavity structure, and the combustion chamber head 26 includes a pre-combustion stage 24 in the center and a main combustion stage 25 on the outer ring; device 34; the injection of the main fuel oil 41 is integrated with the main fuel radial swirler 34, and the main fuel oil 41 ejected from the direct air atomizing nozzle 33 enters the main fuel radial swirler The main combustion stage radial swirler vane channel 42 of the blade 37 is mixed with the swirling air of the main combustion stage radial swirler 34, and the premixed oil-air mixture enters the combustion zone through the main combustion stage mixing chamber 36 Combustion in 16 to realize the integrated fuel injection/radial swirler scheme.

The injection points 38 of the main combustion stage 25 direct jet air atomizing nozzles 33 are located on the left side wall 43 of the radial swirler of the main combustion stage, and the number of injection points is the same as the number of blades.

The injection points 39 of the main combustion stage 25 direct injection air atomizing nozzles 33 are located at any position on both sides of the main combustion stage radial swirler blade 37, and the number of injection points on each blade can be 1, or 2, or multiple combinations.

The injection points 40 of the main combustion stage 25 direct jet air atomizing nozzles 33 are located on the right side wall 44 of the radial swirler of the main combustion stage, and the number of injection points is the same as the number of vanes.

The position of the direct air atomizing nozzle 33 of the main combustion stage 25 includes any one of the injection point 38 , the injection point 39 and the injection point 40 , a combination of two or three.

The relationship between the distance 49x from the main combustion stage fuel injection point to the entrance of the combustion zone and the height 48y of the combustion chamber head structure is: $x\≤\frac{1}{5}\mathrm{the\; y}.$

The gas volume of the main combustion stage 25 accounts for 65%-95% of the gas volume at the head of the combustion chamber, and the gas volume of the pre-combustion stage 24 accounts for 5%-35%.

The amount of gas used for combustion is all supplied from the combustion chamber head 26, and there is no main combustion hole on the flame tube, only cooling holes, outer mixing holes 21 and inner mixing holes 22.

The retraction angle 47 of the main combustion stage retractable member 35 is adjustable from 0° to 180°.

The working principle of the present invention: the fuel oil in the radial swirler channel of the main combustion stage forms a premixed pre-evaporated oil-gas mixture under the action of the swirler airflow and enters the combustion zone for combustion, forming a premixed combustion mode. The pre-combustion stage adopts The centrifugal nozzle and swirler structure form a diffusion combustion mode, taking into account the two contradictory performance requirements of combustion stability and pollution emission. This combustion method can control the equivalence ratio of the combustion chamber in different states, so that the equivalence ratio can always be kept in the range of low pollution emissions, which is beneficial to control pollution emissions. There are no main combustion holes on the flame tube of the combustion chamber, only cooling holes and mixing holes, and all the gas used for combustion enters from the head of the combustion chamber. The main combustion stage and the pre-combustion stage maintain an appropriate gas volume distribution to meet the requirements of different engine combustion chamber conditions. Control the flow of cooling air to avoid excessive CO and UHC.

The pre-combustion stage is started under low-power conditions such as idling, and the equivalent ratio of the combustion zone falls within the above-mentioned low-pollution combustion equivalent ratio range when the low-power condition is maintained, so that the combustion stability is good and it is easy to start. The main combustion stage is started only when the engine is working in a high power state, and the equivalence ratio of the combustion zone is controlled to be within the above low-pollution combustion equivalence ratio range. The main combustion stage is in the premixing and pre-evaporation mode, which can ensure the uniformity of the local equivalence ratio in the combustion zone . The head structure of this low-pollution combustor can ensure that the equivalence ratio of the combustion zone is controlled within the range of low-pollution combustion under all working conditions of the aero-engine combustor. The equivalence ratio uniformity of the combustion zone is controlled by controlling the degree of evaporation and the degree of evaporation, so as to meet the performance requirements of the aero-engine combustor such as low pollution emissions and good stability.

Under a certain parameter (inlet flow rate, temperature and pressure, etc.), the distance required for the fuel to reach a certain degree of mixing is defined as L. From the perspective of pollution emissions, the longer the length, the better, but from the perspective of tempering and spontaneous combustion , this length should not be too large, so when corresponding to a certain parameter, considering the above two factors comprehensively, this length should be a fixed value. For the TAPS main fuel stage radial swirler scheme, the length from the main fuel stage fuel injection point to when the fuel reaches a certain degree of mixing is L, while the distance from the swirler outlet to the injection point is Lsi, and the length of the swirler is Ls, so the length from the swirler inlet to when the fuel reaches a certain degree of mixing is L+Lsi+Ls. The present invention adopts the integrated fuel injection/radial swirler scheme, the fuel injection and the radial swirler are integrated, and under the same inlet parameters of the radial swirler, the length when the same mixing degree is achieved is L1+L , where L1 is not greater than Ls, which not only removes the distance Lsi from the swirler outlet to the injection point, but also makes full use of the length Ls of the swirler, thereby greatly shortening the length of the combustion chamber head and reducing the combustion chamber length and weight.

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

1. When the injection of the main combustion grade fuel oil of the present invention in the radial swirler channel reaches the same mixing degree and evaporation degree, the required distance is greatly shortened, and the length of the combustion chamber is reduced.

2. The oil-gas mixture in the radial swirler of the main combustion stage of the present invention, due to the turning flow downstream of the radial swirler, when reaching the same degree of mixing and evaporation, the required distance is further shortened, thereby further reducing the combustion chamber length.

3. The combustion gas volume of the combustion chamber of the present invention is all supplied from the head, and the gas used for cooling and mixing enters from the flame tube, which increases the efficiency of the combustion chamber and simplifies the structure of the combustion chamber.

4. The combined combustion mode of the pre-combustion stage diffusion combustion and the main combustion stage premixed pre-evaporative combustion of the present invention realizes the performance requirements such as wide stable working range and low pollution emission of the aeroengine combustion chamber.

Description of drawings

Fig. 1 is a schematic diagram of the engine structure;

Fig. 2 is the schematic diagram of combustion chamber structure;

Figure 3 is an enlarged schematic view of area 3 of the combustion chamber;

Fig. 4 is a schematic diagram of the injection situation of the fuel injection point of the first main combustion stage; wherein Fig. 4a is a front view, and Fig. 4b and Fig. 4c are positive second-class side views (three-dimensional views);

Fig. 5 is a schematic diagram of the injection situation of the fuel injection point of the second main combustion stage; wherein Fig. 5a is a front view, Fig. 5b is a sectional view in the front view of Fig. 5a, Fig. 5c is a sectional view in the front view of Fig. 5b, and Fig. 5d is a positive two Isometric view (3D view);

Fig. 6 is a schematic diagram of the injection situation of the fuel injection point of the third main combustion stage; wherein Fig. 6a is a main view, Fig. 6b is a cross-sectional view in the main view of Fig. 6a, and Fig. 6c is a second isometric view (three-dimensional view);

Fig. 7 is a schematic diagram of the rectification ring of the main fuel stage oil circuit; Fig. 7a is a front view of the rectification ring, and Fig. 7b is a cross-sectional view of the front view of Fig. 7a;

Fig. 8 is a schematic diagram of a fuel injection system, wherein Fig. A is a schematic diagram of fuel injection into a transverse jet, Fig. B is a schematic diagram of TAPS main combustion stage fuel injection, and Fig. C is a schematic diagram of main combustion stage fuel injection of the present invention;

In the figure: 10 engine, 11 low-pressure compressor, 12 high-pressure compressor, 13 combustion chamber, 14 high-pressure turbine, 15 low-pressure turbine, 16 combustion zone, 17 outer casing, 18 inner casing, 19 outer flame tube wall, 20 inner Flame cylinder wall, 21 outer mixing hole, 22 inner mixing hole, 23 head end wall, 24 pre-combustion level, 25 main combustion level, 26 head structure, 27 pre-combustion level centrifugal nozzle, 28 pre-combustion level swirl Device, 29 pre-combustion level expansion parts, 30 pre-combustion level mixing chamber, 31 pre-combustion level centrifugal nozzle fuel oil, 32 pre-combustion level swirler blades, 33 direct-firing air atomizing nozzles, 34 main combustion level radial swirl Device, 35 main combustion stage retractable parts, 36 main combustion stage mixing chamber, 37 main combustion stage radial swirler blades, 38 injection points, located on the left side wall of the main combustion stage radial swirler, 39 injection points, Located at any position on both sides of the radial swirler vane of the main combustion stage, 40 injection points, located on the right side wall of the radial swirler of the main combustion stage, 41 fuel oil of the main combustion stage, 42 radial swirler blades of the main combustion stage Channel, 43 left side wall of main combustion stage radial swirler, 44 main combustion stage radial swirler right side wall, 45 main combustion stage nozzle inlet, 46 main combustion stage oil circuit rectification ring, 47 main combustion stage retraction and expansion Component shrinkage angle, 48 height of the combustion chamber head structure, 49 distance from the fuel injection point of the main combustion stage to the entrance of the combustion zone.

Detailed ways

The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

FIG. 1 is a schematic diagram of an engine 10 . The engine 10 includes a low-pressure compressor 11 , a high-pressure compressor 12 , a combustion chamber 13 , a high-pressure turbine 14 and a low-pressure turbine 15 . When the engine 10 is working, the air is compressed by the low-pressure compressor 11 and then enters the high-pressure compressor 12. The high-pressure air enters the combustion chamber 13 for combustion. Combustion, high-temperature and high-pressure gas is formed after combustion, and enters the high-pressure turbine 14 and the low-pressure turbine 15, thereby driving the turbines to do work. Fig. 2 is a schematic diagram of the combustion chamber 13, and the combustion chamber is a single-ring cavity structure. Fig. 3 is an enlarged view of area 3 in Fig. 2, which is the detailed structure of the combustion chamber head. The combustion chamber 13 includes a combustion zone 16, the outer boundary of the combustion zone 16 is the outer flame tube wall 19, and the inner boundary is the inner flame tube wall 20, and the annular inner flame tube wall 20 and the outer flame tube wall 19 are in the annular inner casing 18 and the outer casing 17. Inner mixing holes 22 and outer mixing holes 21 are arranged on the walls of the inner and outer flame tubes to adjust the outlet temperature distribution of the combustion chamber. Cooling holes (not shown) are also arranged on the walls of the inner and outer flame tubes for Cool the wall of the flame tube to ensure the life of the combustion chamber. Upstream of the combustion zone 16 is a head structure 26 which is connected to the flame tube wall via the head end wall 23 . The head structure 26 includes a pre-combustion stage 24 and a main combustion stage 25. Because there is no main combustion hole, all the combustion gas is added from the head of the combustion chamber, so that the head of the combustion chamber is a lean head, which is conducive to reducing Small NOx pollution emission, the gas volume of the pre-combustion stage 24 accounts for 5% to 35% of the gas volume at the head of the combustion chamber, and the gas volume of the main combustion stage 25 accounts for 65% to 95% of the gas volume at the head of the combustion chamber.

The central pre-combustion stage 24 includes a central nozzle 27 , a pre-combustion stage swirler 28 and a diverter 29 . The diverter 29 forms a pre-combustion stage mixing chamber 30 . The center nozzle 27 adopts a centrifugal nozzle, and the pre-combustion level centrifugal nozzle fuel 31 sprayed out by the centrifugal nozzle is mixed with the swirling air of the pre-combustion level swirler 28 in the pre-combustion level mixing chamber 30 and then enters the combustion zone of the combustion chamber combustion.

The main combustion stage 25 of the outer ring includes a direct-injection air atomizing nozzle 33, a radial swirler 34 of the main combustion stage, and a shrinkage and expansion piece 35. The shrinkage and expansion piece 35 forms a main combustion stage The mixing chamber 36 and the constriction angle 47 of the contracting and expanding member 35 are adjustable within 0° to 180°, so as to adapt to different engine combustion chamber working conditions. The main combustion grade fuel oil 41 sprayed by the direct jet air atomizing nozzle 33 enters the main combustion stage radial swirler vane channel 42 of the main combustion stage radial swirler vane 37, and radially swirls with the main combustion stage The swirling air of the device 34 is mixed, and the premixed oil-air mixture enters the combustion zone through the main combustion stage mixing chamber 36 for combustion. The radial swirler 34 of the main combustion stage is a first-stage radial swirler. The injection point 38, the injection point 39 and the injection point 40 of the main combustion stage air atomizing nozzle 33 have three distribution positions in the main combustion stage radial swirler vane channel 42: the left side wall of the main combustion stage radial swirler The injection point 38 on 43, the injection point 39 on both sides of the main combustion stage radial swirler blade 37 and the injection point 40 on the right side wall 44 of the main combustion stage radial swirler are shown in Fig. 4, Fig. 5 and Fig. 6 respectively shown. Corresponding to three different injection points 38, injection points 39 and injection points 40, the inlet of the main combustion stage fuel oil 41 enters from the main combustion stage nozzle inlet 45, and the rectification ring 46 is used to evenly distribute the fuel oil of each injection point, rectifying The diameter and number of small holes on the ring are adjusted according to the atomization conditions of the main combustion stage. In Fig. 4, the main fuel oil 41 enters the left side wall 43 of the radial swirler of the main fuel through the main fuel inlet 45, and the fuel is evenly distributed to the rear of the rectifier through the rectification ring 46 of the main fuel circuit In the oil collection ring at the bottom, it is sprayed into the radial swirler vane channel 42 of the main combustion stage through the injection point 38, where Fig. 4a is a front view at the position of the injection point 38, and Fig. 4b and Fig. 4c are positive secondary sides Diagram (3D view). In Fig. 5, the main combustion stage fuel oil 41 enters the left side wall 43 of the main combustion stage radial swirler through the main combustion stage nozzle inlet 45, and the fuel oil is evenly distributed to the rectification ring through the main combustion stage oil circuit rectification ring 46 In the oil collecting ring at the bottom, the oil collecting ring communicates with the inner channel of the vane, and the fuel is sprayed into the vane channel 42 at the injection point 39 through this connected channel, and the injection point 39 is any position on both sides of the vane; where Fig. 5a is The front view at the position of injection point 39, Fig. 5b is the cross-sectional view in the front view of Fig. 5a, Fig. 5c is the cross-sectional view in the front view of Fig. 5b, and Fig. 5d is an isometric view (three-dimensional view). In Fig. 6, the main combustion stage fuel oil 41 enters the left side wall 43 of the main combustion stage radial swirler through the main combustion stage nozzle inlet 45, and the fuel oil is evenly distributed to the back of the rectification ring through the main combustion stage oil circuit rectification ring 46 In the oil collecting ring at the bottom, the oil collecting ring on the left side wall 43 of the main combustion stage radial swirler and the oil collecting ring on the right side wall 44 of the main combustion stage radial swirler communicate through the inner channel of the blade, and the fuel passes through this channel into the oil collecting ring on the right side wall 44 of the radial swirler of the main combustion stage, and then sprayed into the vane channel 42 at the injection point 40, wherein Fig. 6a is a front view at the position of the injection point 40, and Fig. 6b is a diagram 6a is a cross-sectional view in the main view, and Fig. 6c is an isometric view (three-dimensional view). Wherein the schematic diagram of the rectifying ring of the main fuel stage oil circuit is shown in Figure 7, Figure 7a is a front view of the rectifying ring, and Figure 7b is a cross-sectional view in the front view of Figure 7a; the main fuel stage radial swirler blade channel 42 and the main fuel stage fuel oil The number of nozzle injection points 38, injection points 39 and injection points 40 depends on the number of blades. The position of the injection point of the main fuel stage air atomizing nozzle 33 may be any one, a combination of two or three of the injection point 38 , the injection point 39 and the injection point 40 . The distance 49 from the fuel injection point of the main combustion stage to the entrance of the combustion zone is one-fifth of the height 48 of the combustion chamber head structure. These injection points are located in the radial swirler vane channel of the main combustion stage, and the radial swirler The distance Lsi from the outlet to the injection point, as shown in Figure 8C, compares the schematic diagram of fuel injection into the lateral jet shown in Figure 8A, and the schematic diagram of fuel injection of the TAPS main combustion stage shown in Figure 8B, and at the same time due to the radial direction of the main combustion stage The swirler downstream bends the flow, and it can be known that the present invention can greatly shorten the axial length of the head structure of the combustion chamber, thereby reducing the length and weight of the combustion chamber and the engine.

When the engine 10 is in a low-power state such as starting or idling, only the pre-combustion stage 24 of the combustion chamber supplies fuel, and the main combustion stage 25 only passes through air without supplying fuel. The centrifugal nozzle 27 of the pre-combustion stage makes the combustion zone 16 of the combustion chamber form diffusion combustion way, thereby ensuring the reliable stability and starting characteristics of the engine combustion chamber, and reducing CO and UHC pollution emissions. When the engine 10 is working in a high-power state such as take-off or climbing, the main combustion stage 25 and the pre-combustion stage 24 supply fuel at the same time, and the fuel oil 41 of the direct injection air atomizing nozzle 33 of the main combustion stage enters the radial swirler of the main combustion stage In the vane channel 42, the swirling flow of the radial swirler 34 of the main combustion stage makes the oil and gas form a premixed and pre-evaporated state, and then enters the combustion zone 16 for combustion, forming a premixed combustion method, which can effectively reduce NOx pollution emissions of aeroengines , while ensuring high combustion efficiency and uniform combustion chamber outlet temperature distribution and other properties. And the main combustion stage retractable part 35 and the pre-combustion stage retractable part 29 of the main combustion stage 25 and the pre-combustion stage 24 can well prevent nozzle carbon deposition and tempering.

The installation and connection form of the combustion chamber is as follows: the vane 32 of the pre-combustion stage swirler 28 is connected with the expansion part 29 and the inner wall of the pre-combustion stage swirler. The left side wall 43 of the main combustion stage radial swirler is divided into two parts, the left part separates the oil collecting ring and the oil hole of the main combustion stage nozzle inlet 45, and then the rectifying ring 46 is connected inside the oil collecting ring, and then the left side wall The left and right parts are connected into one body, and finally the entire left side wall 43 of the radial swirler of the main combustion stage is connected with the expansion part 29 of the pre-combustion stage into one body. There are holes on the left side wall of the radial swirler of the main combustion stage to facilitate the passage of fuel. The radial swirler blades 37 of the main combustion stage are respectively connected to the left side wall 43 of the radial swirler of the main combustion stage and the expansion member 35 of the main combustion stage, so that the pre-combustion stage and the main combustion stage swirler form an integral body, Finally, the fuel nozzle 27 is inserted into the pre-combustion stage swirler and connected with the main combustion stage nozzle inlet 45 . When the engine combustion chamber is installed, after the flame tube and the casing are installed, insert the above-mentioned head structure from the nozzle mounting seat at the front end of the combustion chamber, and connect with the head end wall 23, and the head end wall 23 and the head structure 26 pass through A movable ring connection avoids axial and radial thermal stress of the combustion chamber.

Claims (9)

1. An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber, which is composed of a combustion chamber head (26) and a flame tube, characterized in that: the combustion chamber is a single-ring cavity structure, and the combustion chamber head The part (26) includes the pre-combustion stage (24) at the center and the main combustion stage (25) on the outer ring; device (34); the injection of the main fuel oil (41) is integrated with the radial swirler (34) of the main fuel level, and the main fuel oil (41) sprayed by the direct injection air atomizing nozzle (33) Enter into the main combustion stage radial swirler vane channel (42) of the main combustion stage radial swirler blade (37), and mix with the swirl air of the main combustion stage radial swirler (34), pre- The mixed oil-air mixture enters the combustion zone (16) for combustion through the main fuel stage mixing chamber (36), realizing the integrated fuel injection/radial swirler scheme. 2. An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber according to claim 1, characterized in that: the injection point of the main combustion stage (25) direct air atomizing nozzle (33) (38) is located on the left side wall (43) of the radial swirler of the main combustion stage, and the number of injection points is the same as the number of blades. 3. An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber according to claim 1, characterized in that: the injection point of the main combustion stage (25) direct air atomizing nozzle (33) (39) Located at any position on both sides of the radial swirler vane (37) of the main combustion stage, the number of injection points on each vane can be 1, or 2, or a combination of multiples. 4. An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber according to claim 1, characterized in that: the injection point of the main combustion stage (25) direct air atomizing nozzle (33) (40) is located on the right side wall (44) of the radial swirler of the main combustion stage, and the number of injection points is the same as the number of blades. 5. An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber according to any one of claims 1-4, characterized in that: the main combustion stage (25) direct-injection air atomization The position of the nozzle (33) includes any one of injection point (38), injection point (39) and injection point (40), a combination of two or three. 6. An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber according to claim 1, characterized in that the distance (49)x from the fuel injection point of the main combustion stage to the entrance of the combustion zone is equal to The relationship between the height (48)y of the combustion chamber head structure is: $x\≤\frac{1}{5}\mathrm{the\; y}.$ 7. An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustion chamber according to claim 1, characterized in that the gas volume of the main combustion stage (25) accounts for 65% of the gas volume at the head of the combustion chamber ~95%, the gas volume of the pre-combustion stage (24) accounts for 5%~35%. 8. An integrated fuel-injection radial swirler premixed pre-evaporation low-pollution combustion chamber according to claim 1, characterized in that: all the combustion gas is supplied from the combustion chamber head (26), and the flame tube There are no main combustion holes on the top, only cooling holes, outer mixing holes (21) and inner mixing holes (22). 9. An integrated fuel injection radial swirler premixed pre-evaporation low-pollution combustor according to claim 1, characterized in that: the constriction angle (47) of the main combustion stage expansion part (35) is at 0° Adjustable within 180°.

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