CN106287814A - A kind of ground gas turbine can burner of axial admission - Google Patents

Abstract

The invention discloses a ground gas turbine single-pipe combustor with axial air intake, which comprises a combustor inlet pipe, a casing, and a combustor exit section. A flame tube is installed on the outlet section of the combustion chamber; the flame tube is connected to the combustion chamber intake pipe through a natural gas inlet pipe; a natural gas burner is installed on the top of the flame tube head, and a primary cyclone is set on the natural gas burner Components, secondary swirler components; multiple natural gas injection holes are set on the natural gas burner; the main combustion hole is installed on the upper side of the middle section of the flame tube, and the igniter installation assembly is installed on the upper end of the main combustion hole; the lower side of the middle section of the flame tube is installed Blending holes; the present invention also discloses the internal structure of the swirler assembly; the combustion chamber of the present invention can facilitate the rapid and uniform mixing of fuel and air, and the head of the flame tube forms a stable recirculation zone, and improves the overall efficiency of the combustion chamber. service life.

Description

A single-tube combustor of a ground gas turbine with axial intake

technical field

The invention belongs to the field of ground gas turbines, and in particular relates to a single-pipe combustion chamber of the ground gas turbine with axial air intake.

Background technique

In the past ten years, the use value and application prospects of ground gas turbines have been fully proved by scholars at home and abroad. And with the increasing energy consumption, distributed power has gradually gained attention. Distributed power supply does not require long-distance power transmission and distribution equipment, can use energy nearby, and can conveniently realize heat, electricity, and cooling triple production according to user requirements, and has the advantages of being able to meet the power and electricity requirements of special application environments. The ground gas turbine is one of the most fast, stable and convenient energy conversion devices with high power density to convert the chemical energy of fuel into electrical energy. The fuel used by the ground gas turbine can be gaseous fuel or liquid fuel, wherein the gaseous fuel is mostly natural gas, and the liquid fuel includes diesel oil and heavy oil. The development and application of ground gas turbine technology is motivated by the development of aviation gas turbine technology and theory, the development of ground gas turbine technology, the development of related disciplines and technology, and market demand.

At present, domestic research on ground gas turbine combustors mainly refers to relatively mature technologies abroad, and most of the fuels used are gaseous fuels. Gaseous fuels are different from liquid and solid fuels. The combustion process consists of three stages: (1) mixing of fuel and air, (2) heating and ignition of the mixed gas, and (3) completion of the combustion chemical reaction. Gas turbine combustors mostly use diffusion combustion, and the mixed combustible gas is ignited by an external ignition source. In order to prevent flameout and flameout, in addition to matching the gas ejection speed with the flame propagation speed, measures should also be taken to form a strong flame. Powerful ignition source, relying on the heat generated by itself to achieve continuous and stable combustion. In order to improve the overall performance of the ground gas turbine, the combustion chamber is generally made of high-temperature alloy materials, and the stable flame in the recirculation area is formed by means of multi-stage swirling flow, and a relatively uniform outlet temperature field is formed by combining the main combustion hole and the mixing hole. The wall surface of the flame tube is cooled by means of a method, so as to ensure the life of the flame tube. For ground gas turbines, the combustors in the form of recirculation rings and baffles are mostly used. Compared with aviation gas turbine combustors, the size is longer, and it has the advantages of insensitivity to the flow field at the outlet of the compressor and relatively uniform outlet temperature, and there is no need to overthink combustion. The complex structure and weight of the chamber. However, the backflow combustor has the disadvantages of large cooling area of the flame tube, additional pressure loss when turning, and asymmetric flow. Especially for ground gas turbines that use natural gas as fuel, since the content of methane and other natural gas in different regions is not the same, this leads to certain changes in the parameters such as the calorific value of the fuel, which requires that the combustion chamber should have a certain width of fuel heat. value adaptability. In the design process of the ground gas turbine combustor, the above-mentioned characteristics should be fully considered in the design, and its advantages should be used to overcome its disadvantages. Therefore, designing a combustion chamber that can improve the service life of the combustion chamber as a whole, realize rapid and uniform mixing between natural gas and air flow, and form a stable recirculation zone at the head of the flame tube, which is conducive to the stability of the combustion chamber flame has always been Technical problems to be solved by those skilled in the art.

Contents of the invention

Aiming at the problems existing in the prior art, the present invention proposes a ground gas turbine single-pipe combustor with axial air intake, which can facilitate the rapid and uniform mixing of fuel and air, and the head of the flame tube uses a swirler to form a stable backflow zone, which is beneficial to the flame stability of the combustion chamber and improves the service life of the combustion chamber as a whole.

The present invention is achieved in this way, a ground gas turbine single-pipe combustion chamber with axial air intake, comprising a combustion chamber intake pipe, a casing, and a combustion chamber outlet section, characterized in that the upper end of the casing is connected to a combustion chamber Intake pipeline, the lower end of the casing is connected with the outlet section of the combustion chamber, and the outlet section of the combustion chamber is equipped with a flame cylinder; the flame cylinder is connected with the intake pipeline of the combustion chamber through a natural gas inlet pipeline; A natural gas burner is installed on the top of the flame tube head, and the primary cyclone assembly and the secondary cyclone assembly are set on the natural gas burner, and there is a gap; when the flame tube is heated and expanded, the natural gas burner is fixed , the flame tube can move up a certain axial distance, thereby eliminating the thermal stress of the combustion chamber flame tube; the natural gas burner is provided with a plurality of natural gas injection holes; the upper side of the flame tube is equipped with a main combustion hole, The upper end of the main combustion hole is equipped with an igniter installation assembly; the lower side of the middle section of the flame tube is equipped with a mixing hole; through the arrangement of the natural gas burner and the swirler assembly, the gas flow between the natural gas and the swirling air flow of the head swirler can be realized. The rapid and uniform mixing is beneficial to the combustion organization of the head; the design of the main combustion hole can effectively cut off the head recirculation area, and supplement the head with oxygen to participate in the combustion, so that the natural gas ejected from the nozzle can be completely combusted; the mixing hole The setting can make the air and the mainstream high-temperature gas evenly mixed, and form a temperature field that satisfies the inlet of the turbine, reducing the high-temperature hot spot at the outlet of the combustion chamber, thereby improving the life of the turbine; designing multiple mixing holes along the circumference of the flame tube to adjust the outlet of the combustion chamber Temperature distribution; the air flowing out of the first-stage swirler assembly and the second-stage swirler assembly begins to rapidly rotate and expand outward at high speed, resulting in a decrease in the pressure in the center of the flame tube, causing the rear airflow to counterflow to supplement, thus forming a The stable recirculation zone provides aerodynamic conditions for the formation of a stable ignition source.

Further, the nozzle hole has a certain angle with the axial direction; the diameter of the gas nozzle hole on the natural gas burner is 0.3-3.5mm; the number is 6-20; the gas nozzle hole on the burner The spraying angle is 30°～150°.

Further, the intake pipe of the combustion chamber is connected to the casing through the inlet flange of the combustion chamber and the flange of the intake section of the combustion chamber; the outlet section of the combustion chamber is connected to the casing through the inlet flange of the turbine and the outlet flange of the combustion chamber.

Further, the igniter mounting assembly can be moved on the outer wall of the flame tube; considering the thermal expansion of the flame tube and the processing and installation errors of the parts, an igniter mounting assembly is designed on the outer wall of the flame tube, and the igniter mounting assembly can be moved along the circumference of 360° There is a certain movement space in both directions, so as to facilitate the installation of the igniter and the free expansion of heat after combustion.

Further, the surface of the head of the flame tube is equipped with small holes for film cooling at the head of the flame tube, the surface of the middle section of the flame tube is equipped with small holes for film cooling in the middle section of the flame tube, and the surface of the tail of the flame tube is equipped with air film cooling holes for the shrinking section of the flame tube Small holes; the full-coverage film cooling holes are designed on the wall of the flame tube to improve the life of the flame tube.

Further, the head of the flame tube is matched with the natural gas inlet pipe through a certain gap; the natural gas inlet pipe and the combustion chamber intake pipe are connected by welding or flange connection; the sealing is ensured to prevent the combustion chamber intake pipe from The high-pressure air in the leaks out.

Further, the connection between the outlet section of the combustion chamber and the tail of the flame tube is provided with a flame tube support plate and a turbine support plate in turn; the entire combustion chamber is designed to be placed vertically on the turbine inlet support plate, and is fixed by the flame tube support plate The flame tube, the flame tube support plate at the tail is the main force-bearing part, and the gravity of the entire flame tube is transmitted from the flame tube support plate to the turbine support plate to bear; there is a certain gap between the flame tube head and the natural gas burner. Fixed, so as to ensure that the flame tube expands freely upward after being heated.

The invention also discloses a single-pipe combustor of a ground gas turbine with axial air intake. Combination or chamfered radial swirler combination.

Further, the first-stage cyclone and the second-stage cyclone can also be combined into a single-stage axial cyclone.

Further, the primary swirler assembly and the secondary swirler assembly of the single-tube combustion chamber are respectively equipped with primary swirler blades and secondary swirler blades; the primary swirler blades, The blades of the secondary cyclone are straight blades or helical type, the installation angle is 20°-80°, and the number of blades is 6-30.

The beneficial effects of the present invention and prior art are:

(1) Through the arrangement of the structure of the swirler, the main combustion hole and the mixing hole, the two swirling airflows at the head enter the flame tube to form a shear layer, which is conducive to the rapid and uniform mixing of fuel and air, and the head of the flame tube Form a stable recirculation zone, which is conducive to the stability of the flame in the combustion chamber;

(2) By designing the structure of the natural gas burner and the number and angle of the natural gas injection holes, the rapid and uniform mixing between the natural gas and the swirling airflow of the head swirler is realized, which is beneficial to the organization of the head combustion;

(3) Reasonably design the size and number of main combustion holes and mixing holes. By changing the size of the main combustion hole to adjust the depth of the jet, cut off the recirculation zone of the combustion center, and shorten the combustion length. Adjust the jet depth by changing the size of the mixing hole, and evenly mix with the mainstream high-temperature gas to form a temperature field that meets the turbine inlet, reduce the high-temperature hot spots at the outlet of the combustion chamber, and improve the life of the turbine

(4) Through the design of the vertically placed combustion chamber, it has a reasonable mechanical stress and thermal stress mechanism to ensure the load bearing and free expansion of the flame tube, so the gravity of the entire flame tube is supported by the welding of the tail of the flame tube Plate to bear; while the thermal expansion of the overall flame tube, upward expansion and contraction, through the free movement between the head burner and the swirler assembly to achieve thermal free expansion.

(5) The wall of the flame tube is designed with fully covered cooling holes, forming an air film near the inner wall of the flame tube, cooling the wall of the flame tube, reducing the temperature and temperature gradient of the wall surface of the flame tube, thereby improving the overall service life of the combustion chamber.

(6) A two-stage axial swirler is designed through the first-stage axial swirler and the second-stage axial swirler, and the airflow rotates in the opposite direction, which can form a strong airflow shear layer, which is beneficial to the separation of fuel and air. Rapid mixing makes the gaseous fuel and air mix quickly and evenly. The mixed combustible gas forms a stable recirculation zone at the head of the flame tube after high-speed rotation, which plays a role in stabilizing the flame. The combustible gas is ignited by the igniter for stable combustion; or Combined into a single-stage axial swirler to ensure that the structure of the head recirculation zone and the mixing with natural gas remain unchanged, the structure of the head of the single-tube combustion chamber is simple, thereby reducing the processing cost.

Description of drawings

Fig. 1 is a schematic view of the structure of a single-pipe combustor of a ground gas turbine with axial air intake according to the present invention.

Fig. 2 is a schematic structural diagram of a swirler for a ground gas turbine combustor of a single-pipe combustor of a ground gas turbine with axial air intake according to the present invention.

Among them, 1-combustion chamber intake pipe, 2-natural gas intake pipe, 3-first-stage swirler assembly, 4-secondary swirler assembly, 5-natural gas burner, 6-igniter installation hole assembly, 7 -main combustion hole, 8-flame tube, 9-mixing hole, 10-flame tube support plate, 11-turbine inlet support plate, 12-combustion chamber outlet section, 13-turbine inlet flange, 14-combustion chamber outlet method Lan, 15-small hole for film cooling in the contraction section of the flame tube, 16-casing, 17-small hole for film cooling in the middle section of the flame tube, 18-small hole for film cooling in the head of the flame tube, 19-inlet flange of the combustion chamber, 20-flange of combustion chamber intake section, 21-first-stage swirler blade, 22-second-stage swirler blade, 23-natural gas injection hole.

detailed description

The invention will be further described below in conjunction with the accompanying drawings and embodiments.

As shown in Figure 1, a kind of ground gas turbine single-pipe combustor of axial air intake of the present invention comprises combustor inlet pipe 1, casing 16, and the upper end of casing 16 described in combustor outlet section 12 is connected with combustor inlet. Gas pipeline 1, the lower end of the casing 16 is connected with the outlet section 12 of the combustion chamber, and the hollow end surrounded by the three is equipped with a flame cylinder 8, and the flame cylinder 8 is installed on the upper end of the outlet section 12 of the combustion chamber; The flame cylinder 8 is fixed with the combustion chamber intake pipeline 1 through the natural gas inlet pipeline 2; the natural gas burner 5 is installed on the top of the flame cylinder 8 head; one end of the natural gas inlet pipeline 2 is connected with the natural gas burner 5; The first-stage swirler assembly 3 and the second-stage swirler assembly 4 are set on the natural gas burner 5, and there is a gap; the natural gas burner 5 is provided with a plurality of natural gas injection holes 23, and the natural gas injection holes are connected with the axial air intake The air flow has a certain angle, the diameter of the natural gas injection holes 23 is between 0.3-3.5mm, the number is between 6-20 and the injection angle is between 30°-150°, even the structure of the nozzles can be used Make appropriate adjustments according to the required working conditions, so that the injected fuel can be mixed with air as quickly as possible. The upper side of the middle section of the flame tube 8 is equipped with a main combustion hole 7, and the upper end of the main combustion hole 7 is provided with an igniter installation assembly 6; the lower side of the middle section of the flame tube 8 is equipped with a mixing hole 9; Part air film cooling aperture 18, flame cylinder 8 middle segment air film cooling aperture 17 is installed on the surface of flame cylinder 8, and flame cylinder shrinkage segment air film cooling aperture 15 is installed on flame cylinder 8 afterbody surface.

After the high-pressure gas from the centrifugal compressor is collected by the volute, it enters the single-tube combustion chamber from the inlet pipe 1 of the axial combustion chamber, and then enters the combustion chamber flame tube in four parts, respectively flowing through the first-stage cyclone Component 3, the secondary cyclone component 4, the main combustion hole 7 on the flame tube, the mixing hole 9 and the fully covered film cooling holes on the wall surface of the flame tube, that is, the film cooling holes 15 in the shrinking section of the flame tube, The surface of the middle section is equipped with small film cooling holes 17 in the middle section of the flame tube and small film cooling holes 18 at the head of the flame tube to enter the flame tube. The combustion chamber intake pipe 1 is connected to the casing 16 through the combustion chamber inlet flange 19 and the combustion chamber intake section flange 20; the combustion chamber outlet section 12 is connected to the casing 16 through the turbine inlet flange 13 and the combustion chamber outlet flange 14, It can ensure sealing and prevent air leakage; the natural gas inlet pipe 2 at the head is provided with threads to facilitate connection with the natural gas pipeline, which can ensure sealing and prevent air leakage, and the natural gas inlet pipe 2 is welded with the combustion chamber inlet pipe 1 or through flange connection to ensure sealing and prevent the high-pressure air in the combustion chamber intake pipe from leaking out; due to the overall design requirements of the entire gas turbine, the entire combustion chamber is designed to be placed vertically on the turbine inlet support plate 11, so its mechanical stress and thermal stress need to be considered The design of the load-bearing parts is mainly fixed by the connection between the primary cyclone assembly 3 at the head, the secondary cyclone assembly 4 and the natural gas burner 5, and the flame cylinder support plate 10 at the tail of the flame cylinder 8, wherein the tail The flame tube support plate 10 is the main force-bearing part, and the gravity of the entire flame tube is transmitted to the turbine support plate 11 by the flame tube support plate to bear; to ensure the bearing capacity and free expansion of the flame tube; the gravity of the entire flame tube passes through The support plate welded at the end of the flame tube bears it; while the thermal expansion of the whole flame tube is guaranteed by the free axial movement between the burner designed at the head and the swirler assembly.

The primary cyclone assembly 3 and the secondary cyclone assembly 4 are set on the natural gas burner 5 and have a certain gap space. When the flame tube is heated and expanded, the natural gas burner 5 is fixed, and the flame tube 8 can move upwards A certain axial distance, so as to eliminate the thermal stress of the combustion chamber flame tube. Considering the thermal expansion of the flame tube and the parts processing and installation errors, an igniter installation assembly 6 is designed in the front section of the middle part of the flame tube. The moving space makes it easy to install the igniter.

About 10% to 40% of the air enters from the primary cyclone assembly 3 and the secondary cyclone assembly 4, fully mixes with the natural gas ejected from the burner, and forms a stable recirculation zone under the action of the two-stage cyclone airflow After being ignited by the igniter on the wall, a stable combustion flame is formed; about 10% to 40% of the air enters the main flow area from the main combustion hole, and the jet flow through the main combustion hole cuts off the high temperature recirculation area of the head, thereby controlling the length of the reflow area , and supplement fresh air to completely burn the natural gas ejected from the burner; about 10% to 40% of the air enters from the mixing hole, adjust the outlet temperature distribution, and make the temperature field meet the design requirements of the turbine, thereby increasing the life of the turbine; The air entering from the full-coverage air film cooling holes on the flame tube forms a full-coverage air film on the inner wall of the flame tube, thereby improving the life of the flame tube.

As shown in Figure 2, the main structure of the combustion chamber head is a two-stage swirler structure, including a primary swirler assembly 3 and a secondary swirler assembly 4, a primary swirler assembly 3 and a secondary swirler assembly The filter assembly 4 may be a combination of biaxial swirlers, a combination of dual radial swirlers or a combination of chamfered radial swirlers. The primary cyclone assembly 3 is mainly designed as an axial swirler, the secondary cyclone assembly 4 is designed as an axial swirler, and its blades are spiral blades or straight blades, and the inlet of the two-stage cyclone The cyclone direction is opposite or the same, and the two-stage cyclone intake forms a shear layer to ensure the rapid and uniform mixing of natural gas and air. The air flowing out from the primary swirler assembly 3 and the secondary swirler assembly 4 begins to rapidly rotate and expand outward at high speed, which causes the pressure in the center of the flame tube to drop, causing the rear airflow to counterflow to supplement, thus forming a The stable recirculation zone provides aerodynamic conditions for the formation of a stable ignition source; the mixed gas burns rapidly after being ignited by the igniter assembly 6 at the head of the combustion chamber, releases heat, accelerates the airflow, and jets out at a high speed from the outlet section 12 of the combustion chamber flame tube , to drive the turbine behind the combustion chamber to do work, converting heat energy into mechanical energy.

The primary cyclone component 3 can be processed by integral casting or machining, the secondary cyclone component 4 can be processed by integral machining, integral casting or welding, and the components such as the cyclone blade can be processed by welding It is connected with the inner and outer walls of the cyclone, and the two-stage cyclone is connected by welding; the first-stage cyclone assembly 3, the second-stage cyclone assembly 4, and the combustion chamber flame tube 8 are connected by welding; the wall of the flame tube The small film cooling holes 15 in the shrinking section of the flame tube, the small film cooling holes 17 in the middle section of the flame tube installed on the surface of the middle section, and the small film cooling holes 18 in the head of the flame tube can be processed by laser drilling or mechanical drilling technology. The relatively large hole 7 and the mixing hole 9 can be processed by machining; by designing a reasonable size and quantity of the main combustion hole and the mixing hole, a reasonable jet flow depth and air intake of the main combustion hole can be organized, The main combustion hole jet can cut off the recirculation zone, so that the combustion chemical reaction mainly takes place in the recirculation zone. Organize a reasonable mixing hole jet depth and gas volume to form a temperature field that meets the requirements of the turbine inlet, thereby reducing high-temperature hot spots. The flame tube support plate 10 is connected to the flame tube outlet section 12 by welding, so that the overall load of the flame tube passes through the support plate 10 and sits on the turbine inlet support plate 11 .

The primary swirler 3 is an axial swirler, the swirl angle is between 20° and 80°, and the number of blades is between 6 and 30. These settings can be adjusted appropriately. The direction can be clockwise or counterclockwise; the secondary cyclone 4 is also designed as an axial blade type cyclone, and the blade installation angle is between 20°～80° and the number of blades is between 6 and 30. Make appropriate adjustments. The airflow of the first-stage swirler assembly 3 and the second-stage swirler assembly 4 swirl in opposite directions, which can form a strong airflow shear layer, which is conducive to the rapid mixing of fuel and air, and the blades of the two-stage swirler can be straight Blade type or helical blade type; air film cooling holes 15 in the shrinking section of the flame tube on the wall surface of the flame tube above the flame tube 8, and small film cooling holes 17 in the middle section of the flame tube and film cooling holes in the head of the flame tube are installed on the surface of the middle section The included angle between 18 and the incoming flow wall is between 15° and 45°, and the compound angle is between 30° and 60°. These settings are properly adjusted according to the actual situation, so as to achieve the best cooling effect.

Under the condition that the flow area of the two-stage cyclone remains unchanged, the first-stage cyclone 3 and the second-stage cyclone 4 can also be combined into a single-stage axial cyclone in engineering. By designing the single-stage cyclone The swirl number is matched with the natural gas burner to ensure a stable combustion flow field at the head of the combustion chamber, thereby achieving a simple structure and reducing its processing cost.

The air volume at the head of the combustion chamber, including the air intake volume of the primary cyclone 3, the secondary cyclone 4 and the cooling air volume of the cooling hole 18 at the head of the flame tube accounts for 12% to 40% of the total air volume at the inlet Left and right, the head of the combustion chamber is generally fuel-rich combustion, so as to ensure better combustion stability.

Claims (10)

1. a ground gas turbine can burner for axial admission, including combustion chamber charge pipeline (1), casing (16), combustion Burn room outlet section (12), it is characterised in that described casing (16) upper end connects combuster admission line (1), described machine Casket (16) lower end connects combuster outlet section (12), and described combustor exit section (12) is provided with burner inner liner (8)；Described Burner inner liner (8) be connected with combustion chamber charge pipeline (1) by Imported gas pipeline (2)；Described Imported gas pipeline (2) top is provided with natural gas combustion nozzle (5), and be enclosed within natural gas combustion nozzle (5) one-level swirler assembly (3), two grades On swirler assembly (4), and one-level swirler assembly (3), second cyclone assembly (4) and Imported gas pipeline (2) Natural gas combustion nozzle (5) is fixed by certain matched in clearance；On described natural gas combustion nozzle (5), multiple gas spraying is set Hole (23)；Being provided with primary holes (7) on the upside of described burner inner liner (8) stage casing, the upper end of primary holes (7) is provided with lighter and installs Assembly (6)；On the downside of described burner inner liner (8) stage casing, blending hole (9) is installed.

The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described sky So gas spurt (23) and axial admission air-flow have certain angle；The described natural gas spray orifice on natural gas combustion nozzle (5) (23) aperture is 0.3～3.5mm；Quantity is 6～20；The angle of described burner injection is 30 °～150 °.

The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described combustion Burn room admission line (1) to be connected with casing (16) by combustor suction flange (19) and combustion chamber charge section flange (20)； Described combustor exit section (12) is connected with casing (16) by turbine inlet flange (13) and combustor exit flange (14) Connect.

The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described point Firearm mounting assembly (6) can move on burner inner liner (8) outer wall.

The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described fire Flame cylinder (8) head surface is provided with burner inner liner head gaseous film control aperture (18), and in burner inner liner (8), section surface is provided with burner inner liner Stage casing gaseous film control aperture (17), burner inner liner (8) tail surface is provided with burner inner liner contraction section gaseous film control aperture (15).

The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described sky So gas inlet pipeline (2) is right-angle structure, and described Imported gas pipeline (2) passes through to weld with combustion chamber charge pipeline (1) Connect or Flange joint.

The ground gas turbine can burner of axial admission the most according to claim 1, it is characterised in that described combustion The junction burning room outlet section (12) and burner inner liner (8) afterbody is sequentially provided with burner inner liner gripper shoe (10) and turbine support plate , and can burner is vertically to place (11).

8. the ground gas turbine can burner of an axial admission as claimed in claim 1, it is characterised in that described One-level swirler assembly (3), second cyclone assembly (4) combine for the combination of biaxially cyclone, biradial cyclone or cut sth. askew Radial swirler combines.

The ground gas turbine can burner of axial admission the most according to claim 8, it is characterised in that described one Level cyclone (3) and second cyclone (4) can also merge into single-stage axial swirler.

The ground gas turbine can burner of axial admission the most according to claim 8, it is characterised in that described It is separately installed with one-level swirler blades (21), second cyclone on one-level swirler assembly (3), second cyclone assembly (4) Blade (22)；Described one-level swirler blades (21), second cyclone blade (22) are prismatic blade formula or spiral, install Angle is 20 °～80 °, and lobe numbers is 6～30.