A low emission combustor head structure employing vane tail ends

Abstract

The application discloses a low-emission combustion chamber head structure with V-shaped blade tail ends, relates to the technical field of a staged low-pollution combustion chamber of a gas turbine, and solves the problems of short service life of the combustion chamber head structure and poor combustion stability caused by uneven outlet airflow. The combustion chamber head structure is composed of a pilot stage and a main combustion stage, wherein the pilot stage is composed of a swirler, a venturi and a centrifugal nozzle; and the main combustion stage is composed of an inclined radial swirler, a swirl vane, a V-shaped tail end blade, an annular oil collecting cavity and a direct injection nozzle. The main combustion stage uses the inclined radial swirler, which can reduce the axial length of the head of the swirler while ensuring the swirl intensity. The main combustion stage uses the discrete multi-point direct injection nozzle for initial pressure atomization, and then the V-shaped tail end structure is used to strengthen the breaking and mixing of fuel droplets, and the fuel is fully premixed in the swirl channel, so that the pollutant emission can be greatly reduced, and thus the ultra-low emission is realized. The combustion chamber head structure is designed in an integrated mode, and is convenient to replace and maintain.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of gas turbine staged low emission combustor, and particularly relates to a low emission combustor head structure with V-shaped blade tail end. BACKGROUND

[0002] The source of gas turbine pollutant emission comes from the combustor, so developing low pollution combustion technology is the key to reduce the gas turbine pollution emission. The main pollutants of the combustor include nitrogen oxides, carbon monoxide and unburned hydrocarbons, and the most important one is to reduce the generation amount of nitrogen oxides. In the combustor, the thermal type nitrogen oxides generation mechanism plays a dominant role, so reducing the combustion temperature of the combustion zone is one of the effective means to reduce the generation amount of nitrogen oxides. The lean oil combustion technology can effectively reduce the combustion temperature of the combustion zone, thereby reducing the generation amount of nitrogen oxides. The ability of the advanced low emission combustor to reduce pollution emission is largely due to the technical design of the advanced head organization combustion. For the lean oil low emission combustor, due to the need of air partition fuel staging combustion, most of the advanced low emission combustor nozzles are mainly composed of duty class nozzles (centrifugal type) and main combustion stage (direct injection type) nozzles. For the lean oil combustion technology, foreign researchers have proposed lean oil premixed pre-vaporization combustion technology, and have carried out extensive research on it. The technology can effectively control the combustion temperature of the main combustion zone, and has great potential in reducing nitrogen oxides.

[0003] GE company's TAPS combustor has applied for many patents in the United States, the technical solutions of the low emission combustor head patents with patent numbers US6453660B1, US6381964B1, US6389815B1, etc. are as follows: the duty stage is composed of a centrifugal nozzle, two-stage axial swirler, a venturi and a sleeve, and the main combustion stage is composed of a straight jet nozzle and one or two-stage radial swirler. The head large nozzle is composed of the duty stage single oil path centrifugal nozzle and the main combustion stage straight jet nozzle. Beijing University of Aeronautics and Astronautics and China Gas Turbine Research Institute have also applied for many patents of lean oil partial premixing and pre-vaporization combustor, such as patents CN101169252A, CN101275751A, CN101275750A, CN202032612U, CN202032613U and CN202082953U, etc. NOx is one of the pollutants that the gas turbine combustor designers need to consider, in the combustor, NOx is mainly determined by the flame temperature and the gas residence time in the combustion zone. At present, the low pollution combustor adopts the center staged lean oil premixing and pre-vaporization technology to reduce pollution emission, the head of the low emission combustor is composed of the duty stage and the main combustion stage surrounding the duty stage, the head needs to make the fuel and air well mixed to obtain good low emission effect, the fuel and air need to be mixed in a limited space distance, the existing technology mostly adopts fuel transverse jet to obtain good atomization and mixing effect, but the jet penetration of the transverse jet has a great relationship with the momentum ratio of the fuel and air, the transverse jet penetration is different under different working conditions of the gas turbine, which will cause uneven radial distribution of the fuel, the fuel atomization effect deviates from the design requirement, and problems such as high pollution emission and insufficient combustion. SUMMARY

[0004] In view of the above problems of the existing combustor, such as uneven radial distribution of fuel, poor fuel atomization effect, high pollution emission and insufficient combustion, the purpose of the present application is to provide a low emission combustor head structure adopting V-shaped blade tail end.

[0005] In order to achieve the above purpose, the technical scheme adopted by the present application is as follows:

[0006] A low emission combustor head structure adopting V-shaped blade tail end, comprising: a main combustion stage, a duty stage, a heat shield 12 and a flame tube 13, the main combustion stage and the duty stage are coaxially arranged, the duty stage and the front end middle part of the main combustion stage are connected, the rear end outer edge of the main combustion stage and the flame tube 13 are connected through the heat shield 12, and the rear end of the main combustion stage, the heat shield 12 and the flame tube 13 form a combustor; the main combustion stage is used for injecting fuel into the combustor.

[0007] The low emission combustor head structure with V-shaped blade tail end, wherein the value class comprises: a value swirler inner ring 7 and a centrifugal nozzle 10, the centrifugal nozzle 10 is internally installed at the rear end of the value swirler inner ring 7, and one fuel conduit 11 is in communication with the front end of the value swirler inner ring 7.

[0008] The low emission combustor head structure with V-shaped blade tail end, wherein the value class comprises: a value swirler inner ring 7 and a centrifugal nozzle 10, the centrifugal nozzle 10 is internally installed at the rear end of the value swirler inner ring 7, and one fuel conduit 11 is in communication with the front end of the value swirler inner ring 7.

[0009] The low emission combustor head structure with V-shaped blade tail end, wherein the front end of the value swirler inner ring 7 is provided with a plurality of blowing flow channels 9 in the circumferential direction, and the plurality of blowing flow channels 9 are in communication with the combustor.

[0010] The low emission combustor head structure with V-shaped blade tail end, wherein the main combustion stage comprises: a main combustion stage outer ring 1 and a main combustion stage inner ring 5, the main combustion stage outer ring 1 and the main combustion stage inner ring 5 are coaxially arranged, the rear end of the outer wall of the main combustion stage outer ring 1 is connected with the flame tube 13 through the heat shield 12, the main combustion stage inner ring 5 is internally provided with a main combustion stage annular oil collecting cavity 6, and the other fuel conduit 11 is in communication with the main combustion stage annular oil collecting cavity 6.

[0011] The low emission combustor head structure with V-shaped blade tail end, wherein the value class further comprises: a swirler blade 8, the inner wall of the main combustion stage inner ring 5 and the rear end of the outer wall of the value swirler inner ring 7 are connected through a plurality of swirler blades 8, and the plurality of swirler blades 8 are arranged at equal intervals in the circumferential direction around the axis of the value swirler inner ring 7.

[0012] The low emission combustor head structure with V-shaped blade tail end, wherein the main combustion stage further comprises: a main combustion stage swirler blade 2 and a main combustion stage V-shaped tail end blade 3, the outer wall of the main combustion stage inner ring 5 and the inner wall of the main combustion stage outer ring 1 are connected through a plurality of main combustion stage swirler blades 2 and a plurality of main combustion stage V-shaped tail end blades 3, the plurality of main combustion stage swirler blades 2 are arranged at equal intervals in the circumferential direction around the axis of the value swirler inner ring 7, the plurality of main combustion stage V-shaped tail end blades 3 are arranged at equal intervals in the circumferential direction around the axis of the value swirler inner ring 7, and one main combustion stage V-shaped tail end blade 3 is arranged between any two adjacent main combustion stage swirler blades 2.

[0013] The low emission combustor head structure with V-shaped blade tail end, wherein the swirler blade 8 is internally provided with a first swirler passage, one end of the first swirler passage is in communication with the inside of the value swirler inner ring 7, and the other end of the first swirler passage is in communication with the main combustion stage annular oil collecting cavity 6.

[0014] The low emission combustion chamber head structure with V-shaped tail end vane as described above, wherein at least one main combustion stage oil injection hole 4 is arranged on the main combustion stage V-shaped tail end vane 3, and the third passage and the combustion chamber are communicated through the main combustion stage oil injection hole 4; each main combustion stage oil injection hole 4 is located in a V-shaped groove.

[0015] The low emission combustion chamber head structure with V-shaped tail end vane as described above, wherein a plurality of circumferentially distributed cooling small holes are arranged on the heat shield 12, the angle between the axis of the cooling small hole and the axis of the duty stage is 0°-30°, the diameter of the cooling small hole is 0.4-0.6 mm, and the number of the cooling small holes is 150-300.

[0016] The low emission combustion chamber head structure with V-shaped tail end vane as described above, wherein a plurality of circumferentially distributed cooling small holes are arranged on the heat shield 12, the angle between the axis of the cooling small hole and the axis of the duty stage is 0°-30°, the diameter of the cooling small hole is 0.4-0.6 mm, and the number of the cooling small holes is 150-300.

[0017] (1) The main combustion stage of the present application adopts the inclined radial swirler and the lean oil premixing and pre-vaporization technology, the inclined radial swirler combines the low flow resistance of the axial swirler and the short axial length of the radial swirler, the main combustion stage swirler vane is staggered with the main combustion stage V-shaped tail end vane, the downstream of the main combustion stage V-shaped tail end vane forms a backflow vortex, the main combustion stage oil injection hole is arranged in the V-shaped groove of the V-shaped tail end vane, the main combustion stage fuel is injected into the backflow vortex formed downstream of the V-shaped tail end vane through the main combustion stage oil injection hole, the velocity difference of the two sides of the V-shaped vane forms a speed difference to strengthen the breaking of the fuel droplets, the backflow vortex strengthens the mixing of the atomized fuel downstream of the nozzle, and the downstream injection mode effectively avoids the collision of the common transverse jet fuel droplets with the swirler wall structure, thereby avoiding the aggregation of the oil droplets, ensuring the uniformity of the main combustion stage outlet airflow, and being beneficial to uniform combustion.

[0018] (2) The present application adopts the design that the tail part of the Venturi tube expansion section is flush with the height of the main combustion stage inner ring, the inter-stage section of the aero-engine usually has a step structure with a height of about 3-5 mm, the step backflow area is formed through the step structure of the inter-stage section, which is helpful to broaden the lean blowout limit range, since the lean blowout limit range requirement of the gas turbine combustion chamber is lower than that of the aero-engine combustion chamber, the step backflow area is not needed, the design of the present application can avoid the formation of the step backflow area, reduce the resistance loss, and also avoid the ablation of the high temperature area formed by the step backflow area to the outlet of the inter-stage section and the main combustion stage inner ring, thereby prolonging the service life of the head part.

[0019] (3) The present application adopts the staged combustion concept, the pre-combustion stage provides a stable fire source, and the main combustion stage realizes low pollution combustion, which can ensure the stability of the combustion chamber while reducing pollution emissions. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is a structure schematic diagram of an integrated head part of the low emission combustion chamber head structure with V-shaped tail end vane of the present application.

[0021] Figure 2It is a structure diagram of an integrated fuel nozzle of a low emission combustor head structure with V-shaped blade tail end of the present application.

[0022] Figure 3 It is a partial enlarged view of Figure 2 .

[0023] Figure 4 It is an assembly diagram of an integrated head and flame tube of a low emission combustor head structure with V-shaped blade tail end of the present application.

[0024] In the drawing: 1, main combustion stage outer ring; 2, main combustion stage swirling vane; 3, main combustion stage V-shaped tail end vane; 4, main combustion stage oil injection hole; 5, main combustion stage inner ring; 6, main combustion stage annular oil collecting cavity; 7, value swirling inner ring; 8, swirling vane; 9, purge flow channel; 10, centrifugal nozzle; 11, fuel guide pipe; 12, heat shield; 13, flame tube. DETAILED DESCRIPTION

[0025] The present application will be further described below in conjunction with the drawing and specific embodiments, but not as a limitation of the present application.

[0026] Please refer to Figures 1 to 4 , a low emission combustor head structure with V-shaped blade tail end is shown, which comprises: main combustion stage, value stage, heat shield 12 and flame tube 13, the main combustion stage and the value stage are coaxially arranged, the value stage and the front end middle part of the main combustion stage are connected, the rear end outer edge of the main combustion stage and the flame tube 13 are connected through the heat shield 12, the rear end of the main combustion stage, the heat shield 12 and the flame tube 13 form a combustion chamber; the main combustion stage is used for injecting fuel into the combustion chamber.

[0027] Further, in a preferred embodiment, it further comprises: fuel guide pipe 11, one fuel guide pipe 11 is used for conveying fuel to the value stage, and another fuel guide pipe 11 is used for conveying fuel to the main combustion stage.

[0028] Further, in a preferred embodiment, the value stage comprises: value swirling inner ring 7 and centrifugal nozzle 10, the centrifugal nozzle 10 is installed inside the rear end of the value swirling inner ring 7, and one fuel guide pipe 11 is in communication with the front end of the value swirling inner ring 7.

[0029] Further, in a preferred embodiment, a plurality of purge flow channels 9 are arranged on the front end of the value swirling inner ring 7 in the circumferential direction, and the plurality of purge flow channels 9 are in communication with the combustion chamber.

[0030] Further, in a preferred embodiment, the main combustion stage further comprises: a main combustion stage outer ring 1 and a main combustion stage inner ring 5, the main combustion stage outer ring 1 and the main combustion stage inner ring 5 are coaxially arranged, a rear end outer edge of the main combustion stage outer ring 1 and the flame tube 13 are connected by the heat shield 12, the main combustion stage inner ring 5 is internally provided with a main combustion stage annular oil collecting cavity 6, and the other fuel guide pipe 11 and the main combustion stage annular oil collecting cavity 6 are communicated.

[0031] Further, in a preferred embodiment, the main combustion stage further comprises: a main combustion stage outer ring 1 and a main combustion stage inner ring 5, the main combustion stage outer ring 1 and the main combustion stage inner ring 5 are coaxially arranged, a rear end outer edge of the main combustion stage outer ring 1 and the flame tube 13 are connected by the heat shield 12, the main combustion stage inner ring 5 is internally provided with a main combustion stage annular oil collecting cavity 6, and the other fuel guide pipe 11 and the main combustion stage annular oil collecting cavity 6 are communicated.

[0032] Further, in a preferred embodiment, the main combustion stage further comprises: a main combustion stage outer ring 1 and a main combustion stage inner ring 5, the main combustion stage outer ring 1 and the main combustion stage inner ring 5 are coaxially arranged, a rear end outer edge of the main combustion stage outer ring 1 and the flame tube 13 are connected by the heat shield 12, the main combustion stage inner ring 5 is internally provided with a main combustion stage annular oil collecting cavity 6, and the other fuel guide pipe 11 and the main combustion stage annular oil collecting cavity 6 are communicated.

[0033] Further, in a preferred embodiment, the main combustion stage further comprises: a main combustion stage outer ring 1 and a main combustion stage inner ring 5, the main combustion stage outer ring 1 and the main combustion stage inner ring 5 are coaxially arranged, a rear end outer edge of the main combustion stage outer ring 1 and the flame tube 13 are connected by the heat shield 12, the main combustion stage inner ring 5 is internally provided with a main combustion stage annular oil collecting cavity 6, and the other fuel guide pipe 11 and the main combustion stage annular oil collecting cavity 6 are communicated.

[0034] Further, in a preferred embodiment, the main combustion stage further comprises: a main combustion stage outer ring 1 and a main combustion stage inner ring 5, the main combustion stage outer ring 1 and the main combustion stage inner ring 5 are coaxially arranged, a rear end outer edge of the main combustion stage outer ring 1 and the flame tube 13 are connected by the heat shield 12, the main combustion stage inner ring 5 is internally provided with a main combustion stage annular oil collecting cavity 6, and the other fuel guide pipe 11 and the main combustion stage annular oil collecting cavity 6 are communicated.

[0035] Further, in a preferred embodiment, the main combustion stage further comprises: a main combustion stage outer ring 1 and a main combustion stage inner ring 5, the main combustion stage outer ring 1 and the main combustion stage inner ring 5 are coaxially arranged, a rear end outer edge of the main combustion stage outer ring 1 and the flame tube 13 are connected by the heat shield 12, the main combustion stage inner ring 5 is internally provided with a main combustion stage annular oil collecting cavity 6, and the other fuel guide pipe 11 and the main combustion stage annular oil collecting cavity 6 are communicated.

[0036] The above is only a preferred embodiment of the present application, and does not limit the implementation and protection scope of the present application.

[0037] The present application further has the following implementation on the basis of the above:

[0038] In a further embodiment of the present application, a low emission combustor head structure with V-shaped tail end vanes is disclosed. The structure is composed of a pilot stage, a main combustion stage, etc. The pilot stage is composed of a swirler, a venturi and a centrifugal nozzle 10. The main combustion stage is composed of a slanting radial swirler, main combustion stage swirler vanes 2, main combustion stage V-shaped tail end vanes 3, main combustion stage annular oil collecting cavity 6 and main combustion stage fuel injection holes 4. The main combustion stage fuel injection holes 4 are straight injection nozzles. The slanting radial swirler is composed of a main combustion stage outer ring 1, main combustion stage swirler vanes 2 and a main combustion stage inner ring 5. The slanting radial swirler combines the advantages of radial and axial swirler, which can reduce the axial length of the swirler head while ensuring the swirling intensity. The main combustion stage uses discrete multi-point straight injection nozzles for initial pressure atomization, and then uses the V-shaped tail end structure to strengthen the fuel droplet breaking and mixing. The fuel is fully premixed downstream of the main combustion stage V-shaped tail end vanes 3, which can greatly reduce the emission of pollutants, and thus achieve ultra-low emission. The combustor head structure is designed as an integrated structure, which is convenient for replacement and maintenance.

[0039] In a further embodiment of the present application, a low emission combustor head structure with V-shaped tail end vanes is disclosed. The structure is composed of a pilot stage, a main combustion stage, etc. The pilot stage is composed of a swirler, a venturi and a centrifugal nozzle 10. The main combustion stage is composed of a slanting radial swirler, main combustion stage swirler vanes 2, main combustion stage V-shaped tail end vanes 3, main combustion stage annular oil collecting cavity 6 and main combustion stage fuel injection holes 4. The main combustion stage fuel injection holes 4 are straight injection nozzles. The slanting radial swirler is composed of a main combustion stage outer ring 1, main combustion stage swirler vanes 2 and a main combustion stage inner ring 5. The slanting radial swirler combines the advantages of radial and axial swirler, which can reduce the axial length of the swirler head while ensuring the swirling intensity. The main combustion stage uses discrete multi-point straight injection nozzles for initial pressure atomization, and then uses the V-shaped tail end structure to strengthen the fuel droplet breaking and mixing. The fuel is fully premixed downstream of the main combustion stage V-shaped tail end vanes 3, which can greatly reduce the emission of pollutants, and thus achieve ultra-low emission. The combustor head structure is designed as an integrated structure, which is convenient for replacement and maintenance.

[0040] In a further embodiment of the present application, Figure 1 With Figure 2 A cross-sectional view of a low emission combustor head structure with V-shaped tail end vanes according to an embodiment of the present application is shown. As shown in Figure 1 With Figure 2 A straight injection / centrifugal nozzle and a central staging structure are used. The main combustion stage fuel injection holes 4 are straight injection nozzles, and the centrifugal nozzle is a centrifugal nozzle 10. The main combustion stage includes a main combustion stage outer ring 1, main combustion stage swirler vanes 2, main combustion stage V-shaped tail end vanes 3, main combustion stage fuel injection holes 4, a main combustion stage inner ring 5 and a main combustion stage annular oil collecting cavity 6. The pilot stage includes a pilot swirler inner ring 7, swirler vanes 8, a purge flow passage 9 and a centrifugal nozzle 10. The head structure also includes a fuel guide pipe 11 and a heat shield 12. The pilot stage is connected to the main combustion stage through the main combustion stage inner ring 5 and is concentric with the main combustion stage. The main combustion stage swirler vanes 2 and the main combustion stage V-shaped tail end vanes 3 are arranged alternately, and a backflow vortex is formed downstream of the main combustion stage V-shaped tail end vanes 3. The main combustion stage fuel injection holes 4 are arranged in the V-shaped groove of the V-shaped tail end vanes. The main combustion stage fuel is injected into the backflow vortex formed downstream of the V-shaped tail end vanes through the main combustion stage fuel injection holes 4, and is fully mixed with air in the main combustion stage premixing passage after being ejected through the main combustion stage fuel injection holes 4. The pilot stage fuel forms an oil mist through the centrifugal nozzle 10 and is diffused and combusted at the outlet of the pilot stage.

[0041] In a further embodiment of the present application, the main combustion stage adopts an inclined radial swirler structure, having 8-16 circumferentially-distributed main combustion stage swirler vanes 2 with a thickness of 1.0-4.0 mm, 8-16 circumferentially-distributed main combustion stage V-shaped tail end vanes 3 with a thickness of 3.0-8.0 mm, a V-shaped tail end included angle of 45°-120°, the main combustion stage swirler vanes 2 and the main combustion stage V-shaped tail end vanes 3 being arranged alternately and identically in number, the main combustion stage swirler vanes 2 being longer in axial length than the main combustion stage V-shaped tail end vanes 3, and the swirler number being 0.5-1.5, for forming swirled air; the main combustion stage swirler inlet and the combustion chamber centerline direction included angle being 30°-60°, the swirler spacing being 25-35 mm, and the axial length being 50-60 mm.

[0042] In a further embodiment of the present application, the on-duty stage swirler has 8-12 circumferentially-distributed swirler vanes 8 with a thickness of 2-10 mm, the swirler number being 0.5-1.5, for forming strong swirl, the swirl intensity being obtained by an empirical formula, and the blade thickness being obtained according to the effective flow area of the on-duty stage swirler, and the flow area being obtained according to the distribution ratio of the on-duty stage air flow.

[0043] In a further embodiment of the present application, the on-duty stage centrifugal nozzle 10 has a spray cone angle of 60°-90°, the spray cone angle being too small to have poor atomization effect, and the spray cone angle being too large to cause fuel droplets to impact the convergent section of the main combustion stage inner ring 5, resulting in the fuel droplets splashing upward; the main combustion stage fuel injection hole 4 is a straight injection nozzle, the main combustion stage fuel injection hole 4 is arranged in the V-shaped groove of the main combustion stage V-shaped tail end vane 3, the main combustion stage fuel injection hole 4 is arranged at a position of 10%-90% of the height of the V-shaped groove, there are 1-2 main combustion stage fuel injection holes 4 on each main combustion stage V-shaped tail end vane 3, the main combustion stage fuel injection hole 4 has a diameter of 0.01-0.8 mm, and the number and diameter of the main combustion stage fuel injection hole 4 are selected according to the fuel flow of the design condition of the combustion chamber; the injection direction and the axial direction included angle range is 0°-30°, the injection direction is the same as the direction of the swirled air, the injection angle being too large to cause the fuel to splash onto the main combustion stage inner ring 5, resulting in coking, the main combustion stage fuel injection hole 4 is supplied with fuel through an annular oil collecting chamber, the main combustion stage annular oil collecting chamber 6 is arranged in the main combustion stage inner ring 5, the annular oil collecting chamber has a radial width of 2-6 mm and an axial length of 20-35 mm, the proportion of the main combustion stage fuel in the total fuel is 50%-100%, the axial distance between the main combustion stage fuel injection hole 4 and the swirler outlet is 10-20 mm, and the sufficient axial distance can ensure that the fuel and the air are fully mixed. Under the action of the V-shaped groove, a vortex is formed downstream of the vane, the main combustion stage fuel injection hole 4 adopting the structure can inject fuel into the vortex formed downstream of the V-shaped groove, compared with directly injecting fuel into the air flowing downstream, the disturbance and shearing action of the vortex can strengthen the fuel and air mixing effect.

[0044] In further embodiments of the application, the main combustion stage, the duty stage, the fuel duct 11, and the heat shield 12 form a low-emission combustion chamber head structure, the heat shield 12 is in clearance fit with the flame tube 13; the heat shield 12 has circumferentially distributed cooling holes for passing cooling air flow, the cooling holes have an angle of 10°-30° with the direction of the center line of the combustion chamber, the diameter of the cooling holes is 0.4-0.6 mm, and the number of the cooling holes is 150-300; a smaller angle can obtain a uniform cooling air film on the heat shield 12, and avoid high-temperature ablation of the heat shield 12; the diameter and the number of the cooling holes are adjusted according to the distributable cooling air flow of the combustion chamber.

[0045] In further embodiments of the application, the working principle of the application is as follows: the main combustion stage adopts lean oil partial premixing and pre-vaporization combustion technology; the main combustion stage swirl vanes 2 and the main combustion stage V-shaped tail end vanes 3 are arranged in a staggered manner, and a backflow vortex is formed downstream of the main combustion stage V-shaped tail end vanes 3; the main combustion stage oil injection holes 4 are arranged in the V-shaped grooves of the main combustion stage V-shaped tail end vanes 3; the main combustion stage fuel is injected into the backflow vortex formed downstream of the main combustion stage V-shaped tail end vanes 3 through the main combustion stage oil injection holes 4; the speed difference formed by the sharp wedges on both sides of the main combustion stage V-shaped tail end vanes 3 strengthens the breaking of fuel droplets; the backflow vortex strengthens the mixing of atomized fuel downstream of the nozzle; after being ejected through the main combustion stage oil injection holes 4, the fuel is fully mixed with air in the main combustion stage premixing channel, which can greatly reduce the emissions of pollutants such as NOx, UHC, CO, and soot particles; the design of the main combustion stage swirler takes into account the prevention of backfire and spontaneous combustion; by using an inclined radial swirler, the equivalent flow area of the inclined section is controlled to be greater than that of the flat section, so that the main combustion stage air flow has an acceleration effect, combining the low flow resistance of an axial swirler and the short axial length of a radial swirler; the duty stage adopts diffusion combustion mode to ensure stable operation of the combustion chamber under low working conditions, and to enhance the ignition performance of the combustion chamber; the design of the combustion chamber head takes into account the uniformity of the intake air, the aerodynamic atomization of the main combustion stage fuel, and the installation and removal of the head; the flame tube 13 is in clearance fit with the head; the integrated head nozzle structure does not need to disassemble the flame tube 13 during installation and maintenance; the clearance fit allows the head and the flame tube 13 to be separated without the aid of tools, which has high practical value. The NOx emission can be maintained below 50 ppm within 0.5-1.0 working conditions.

[0046] In a further embodiment of the present application, the main combustion stage adopts an inclined radial swirler and lean premixed pre-vaporization technology, the inclined radial swirler combines the low flow resistance of the axial swirler and the short axial length of the radial swirler, the main combustion stage swirler blades 2 are staggered with the main combustion stage V-shaped tail blade 3, the main combustion stage V-shaped tail blade 3 downstream forms a backflow vortex, the main combustion stage oil injection hole 4 is arranged in the V-shaped groove of the main combustion stage V-shaped tail blade 3, the main combustion stage fuel is injected into the backflow vortex formed downstream of the main combustion stage V-shaped tail blade 3 by the main combustion stage oil injection hole 4, the speed difference between the two sides of the main combustion stage V-shaped tail blade 3 forms a speed difference to strengthen the breaking of fuel droplets, the backflow vortex strengthens the mixing of atomized fuel downstream of the nozzle, and the downstream injection mode effectively avoids the collision of common transverse jet fuel droplets with the swirler wall structure, and the oil droplet aggregation is avoided, while the uniformity of the main combustion stage outlet airflow is ensured, which is beneficial to uniform combustion.

[0047] In a further embodiment of the present application, the tail of the Venturi tube expansion section is designed to be flush with the height of the main combustion stage inner ring 5, the interstage section of the aero-engine usually has a step structure with a height of about 3-5mm, and the step backflow area is formed by the structure of the interstage section, which helps to widen the lean blowout limit range, and since the lean blowout limit range requirement of the gas turbine combustion chamber is lower than that of the aero-engine combustion chamber, it is not necessary to form a step backflow area, the design of the present application can avoid the formation of the step backflow area, reduce the resistance loss, and at the same time, avoid the ablation of the step backflow area to the outlet of the interstage section and the main combustion stage inner ring 5, and prolong the service life of the head.

[0048] In a further embodiment of the present application, the present application adopts the concept of staged combustion, the pre-combustion stage provides a stable flame source, and the main combustion stage realizes low-pollution combustion, which can ensure the stability of the combustion chamber while reducing pollution emissions.

[0049] In a further embodiment of the present application, fuel enters the on-duty stage centrifugal nozzle 10 from the fuel conduit 11, and the fuel is atomized to form an oil mist under the action of the centrifugal nozzle 10 and enters the combustion chamber for combustion, the fuel conduit 11 and the on-duty stage centrifugal nozzle 10 are connected by threads, the centrifugal nozzle 10 can be individually disassembled and replaced, the connection thread size is smaller than the pipe outer diameter of the fuel conduit 11 and the centrifugal nozzle 10, the pipe inner diameter size of the connection can be selected according to the selection of the thread size to reduce the processing difficulty, and the internal pipe structure of the centrifugal nozzle 10 is selected according to the working condition and equipment condition.

[0050] The above is only a preferred embodiment of the present application, and does not limit the implementation and protection scope of the present application. For those skilled in the art, it should be realized that any equivalent replacement and obvious changes made according to the content of the present application can be included in the protection scope of the present application.

Claims

1. A low emission combustor head structure employing a V-shaped vane tail end, characterized by, The application relates to a gas turbine combustor, which comprises a main combustion stage, a standby stage, a heat shield (12) and a flame tube (13), the main combustion stage and the standby stage are coaxially arranged, the standby stage and the middle part of the front end of the main combustion stage are connected, the outer edge of the rear end of the main combustion stage and the flame tube (13) are connected through the heat shield (12), and the rear end of the main combustion stage, the heat shield (12) and the flame tube (13) jointly form a combustion chamber. The application further comprises fuel conduits (11), one fuel conduit (11) is used for conveying fuel to the standby stage, and the other fuel conduit (11) is used for conveying fuel to the main combustion stage. The main combustion stage comprises a main combustion stage outer ring (1) and a main combustion stage inner ring (5), the main combustion stage outer ring (1) and the main combustion stage inner ring (5) are coaxially arranged, the outer edge of the rear end of the main combustion stage outer ring (1) and the flame tube (13) are connected through the heat shield (12), and the main combustion stage inner ring (5) is internally provided with a main combustion stage annular oil collecting cavity (6), the other fuel conduit (11) and the main combustion stage annular oil collecting cavity (6) are communicated. The main combustion stage further comprises main combustion stage swirl vanes (2) and main combustion stage V-shaped tail end vanes (3), the outer wall of the main combustion stage inner ring (5) and the inner wall of the main combustion stage outer ring (1) are connected through the main combustion stage swirl vanes (2) and the main combustion stage V-shaped tail end vanes (3), the main combustion stage swirl vanes (2) are circumferentially and equidistantly arranged around the axis of the value swirler inner ring (7), the main combustion stage V-shaped tail end vanes (3) are circumferentially and equidistantly arranged around the axis of the value swirler inner ring (7), and one main combustion stage V-shaped tail end vane (3) is arranged between any two adjacent main combustion stage swirl vanes (2). The main combustion stage V-shaped tail end vane (3) is provided with at least one main combustion stage fuel injection hole (4), a third passage and the combustion chamber are communicated through the main combustion stage fuel injection hole (4), the main combustion stage fuel injection hole (4) is arranged in a V-shaped groove of the main combustion stage V-shaped tail end vane (3), and the main combustion stage fuel injection hole (4) is supplied with oil through the main combustion stage annular oil collecting cavity (6). The standby stage comprises a value swirler inner ring (7) and a centrifugal nozzle (10), the rear end of the value swirler inner ring (7) is internally provided with the centrifugal nozzle (10), and one fuel conduit (11) and the front end of the value swirler inner ring (7) are communicated.

2. The low emission combustor head with V-shaped vane tips of claim 1, wherein, A plurality of blowing flow channels (9) are circumferentially arranged on the front end of the value swirler inner ring (7), and the blowing flow channels (9) are communicated with the combustion chamber.

3. The low emission combustor head with V-shaped vane tips of claim 2, wherein, The standby stage further comprises swirl vanes (8), the inner wall of the main combustion stage inner ring (5) and the rear end outer wall of the value swirler inner ring (7) are connected through the swirl vanes (8), and the swirl vanes (8) are circumferentially and equidistantly arranged around the axis of the value swirler inner ring (7).

4. The low emission combustor head with V-shaped vane tips of claim 3, wherein, The swirl vane (8) is internally provided with a first swirl passage, one end of the first swirl passage is communicated with the inside of the value swirler inner ring (7), and the other end of the first swirl passage is communicated with the main combustion stage annular oil collecting cavity (6).

5. The low emission combustor head with V-shaped vane tips of claim 4, wherein, The heat shield (12) is provided with a plurality of circumferentially distributed cooling small holes, the included angle between the axis of the cooling small hole and the axis of the standby stage is 0-30 DEG, the diameter of the cooling small hole is 0.4-0.6 mm, and the number of the cooling small holes is 150-300.

6. The low emission combustor head with V-shaped vane tips of claim 1, wherein, ​

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