CN213746854U - Swirl nozzle device suitable for combustion chamber of gas turbine - Google Patents
Swirl nozzle device suitable for combustion chamber of gas turbine Download PDFInfo
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- CN213746854U CN213746854U CN202022711178.0U CN202022711178U CN213746854U CN 213746854 U CN213746854 U CN 213746854U CN 202022711178 U CN202022711178 U CN 202022711178U CN 213746854 U CN213746854 U CN 213746854U
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Abstract
The utility model discloses a swirl nozzle device suitable for gas turbine combustion chamber, this swirl nozzle include parts such as the diffusion air chamber that can independently process, dismantle, diffusion fuel chamber, nozzle dustcoat, premix whirl subassembly, diffusion whirl subassembly, nozzle inner core to arrange at the nozzle dustcoat and mix the fuel inlet port in advance and mix the air inlet port in advance. When the combustion chamber of the gas turbine runs, premixed fuel is directly supplied to a premixing channel in the swirl nozzle through a premixed fuel air inlet, and is preliminarily mixed with compressed air at the upstream of the swirl vanes, and the preliminarily premixed gas is further mixed in the premixing channel after being swirled by the swirl vanes. When the fuel nozzle component is replaced, the fuel nozzle component can be replaced according to the damage condition of the fuel nozzle component. The utility model does not need to arrange a fuel cavity inside the swirl vane, which can reduce the processing difficulty of the swirl nozzle; because of the utility model provides a each part of fuel nozzle can independently process, dismantle and the installation is with trading, can reduce gas turbine power plant's whirl nozzle's maintenance, replacement cost.
Description
Technical Field
The utility model belongs to the technical field of gas turbine, especially, relate to a whirl nozzle device suitable for gas turbine combustion chamber.
Background
A gas turbine is widely used in the industrial field as a high-efficiency source conversion device. Gas turbine fuel nozzles, which are one of the core components of a combustor, are replaced during minor, intermediate, major repairs of the engine and damage to the combustor components. At present, DLN swirl nozzles (or DLN combustors) mainly comprise a nozzle outer cover, a nozzle central body, nozzle swirl blades, a purging pipe and the like, wherein the nozzle swirl blades are arranged on the nozzle central body. The nozzle outer cover, the nozzle central body and the swirl vanes form an annular passage, and compressed air enters the annular passage from the upstream of the nozzle and flows in the annular passage; a premixing and diffusion fuel channel is arranged in the central body of the nozzle; the inside of the swirl vane is provided with a premixed fuel cavity which is communicated with a premixed fuel supply channel inside the nozzle central body, the surface of the swirl vane is provided with a fuel hole and is communicated with the premixed fuel cavity, the premixed fuel is injected into the premixed fuel cavity of the swirl vane through the premixed fuel channel of the nozzle central body and is injected into the annular cavity through the fuel hole on the surface of the swirl vane, and the premixed fuel is premixed with compressed air in a premixing section at the downstream of the swirl vane and then is injected into the combustion chamber for combustion. The diffusion fuel is injected into the combustion chamber through the diffusion swirl passage at the head of the central body through the passages of the pair inside the central body of the diffusion nozzle.
The swirl nozzle of the combustion chamber of the in-service combustion engine has the following problems: 1) the nozzle swirl vane is a hollow vane, a fuel cavity and a diffusion air cavity are arranged in the nozzle swirl vane, and the nozzle swirl vane is provided with a fuel hole, so that the processing technology of the swirl vane is complex, and the design and processing difficulty of the swirl nozzle is high and the cost is high; 2) except the inner core of the nozzle, all parts of the nozzle are connected into a whole in a welding or tight matching mode, when the swirl nozzle of the combustion chamber is replaced by small repair, medium repair and large repair of the combustion engine every time, no matter whether the hot end part and the cold end part of the swirl nozzle are damaged, the swirl nozzle must be integrally repaired or replaced, and the combustion engine power generation enterprise needs to additionally spend a large amount of expenses every year.
SUMMERY OF THE UTILITY MODEL
For solving the big, and change the higher scheduling problem of maintenance cost of the big degree of difficulty of labour gas turbine combustion chamber fuel nozzle central body processing, the utility model provides a swirl nozzle device suitable for gas turbine combustion chamber.
The utility model discloses a following technical scheme realizes:
a swirl nozzle apparatus suitable for a gas turbine combustor includes a diffusion air cavity, a diffusion fuel cavity, a nozzle outer shroud, a premix swirl assembly, a diffusion swirl assembly, and a nozzle inner core; the diffusion air cavity, the diffusion fuel cavity and the nozzle outer cover are sequentially connected, the nozzle inner core is positioned in the diffusion rotational flow assembly, the diffusion rotational flow assembly is positioned in the premixing rotational flow assembly, and the premixing rotational flow assembly is positioned in the nozzle outer cover; the nozzle inner core is arranged on the diffusion rotational flow end cover by adopting a nozzle inner core pressing strip positioned at the front end of the nozzle inner core; the diffusion rotational flow component is connected with the diffusion fuel cavity by adopting internal threads at the upper end of a diffusion fuel end cover of the diffusion rotational flow component; the premixing cyclone assembly and the diffusion fuel cavity are tightly connected with an external thread at the upper end of a premixing cyclone assembly front cavity of the premixing cyclone assembly through the external thread at the lower end of the diffusion fuel cavity; the nozzle outer cover and the diffusion fuel cavity are tightly connected by a flange on the nozzle outer cover and a diffusion fuel cavity end cover;
the diffusion air cavity is provided with a diffusion air inlet hole, the diffusion fuel cavity is provided with a diffusion fuel inlet hole, the nozzle outer cover is provided with a premixed air inlet hole and a premixed fuel inlet hole, the premixed swirl component is provided with swirl vanes, the diffusion fuel cavity, the premixed swirl component and the nozzle outer cover jointly form a premixed swirl channel, the diffusion swirl component is provided with a diffusion swirl channel, the diffusion fuel cavity, the diffusion swirl component and the premixed swirl component jointly form a diffusion fuel channel, and the diffusion air cavity, the nozzle inner core and the diffusion swirl component jointly form a diffusion air channel.
The utility model discloses further improvement lies in, diffusion air end cover center department of diffusion air chamber has the diffusion air inlet port.
The utility model discloses further improvement lies in, diffusion fuel chamber end cover reserves has the tongue depressor for further fixed nozzle inner core layering realizes the zonulae occludens between nozzle inner core and the diffusion whirl subassembly, ensures that the nozzle inner core is not hard up.
The utility model discloses further improvement lies in, diffusion fuel chamber end cover lower extreme is reserved has recessed seal groove, and the reservation has the sealing washer of epirelief on the flange of nozzle dustcoat, and seal groove and sealing washer cooperation are used, strengthen the sealing between the flange of diffusion fuel chamber end cover and nozzle dustcoat.
The utility model discloses further improvement lies in, and the diffusion fuel inlet port has a plurality ofly along diffusion fuel end cover circumference tangential equipartition.
The utility model discloses further improvement lies in, the nozzle dustcoat is provided with in week in advance mixes air gas collecting chamber and mixes fuel gas collecting chamber in advance.
The utility model discloses further improvement lies in, mixes the air inlet in advance and all has put a plurality ofly along mixing air gas collection chamber circumference tangential.
The utility model discloses further improvement lies in, mixes the fuel inlet port in advance and all has put a plurality ofly along mixing fuel gas collection chamber circumference tangential.
The utility model discloses further improvement lies in, between the nozzle shell of nozzle dustcoat and the premixed fuel gas collecting chamber to and all seted up the aperture between nozzle shell and the premixed fuel gas collecting chamber, and the aperture adopts the honeycomb holes of densely covered.
The utility model discloses at least, following profitable technological effect has:
the utility model provides a pair of swirl nozzle device suitable for gas turbine combustion chamber, including parts such as diffusion air chamber, diffusion fuel chamber, nozzle dustcoat, premixed swirl subassembly, diffusion swirl subassembly and nozzle inner core. Wherein, the diffusion air cavity is connected with the diffusion fuel cavity, and the diffusion air cavity is provided with a diffusion air inlet hole, and the diffusion fuel cavity is provided with a diffusion fuel inlet hole. The nozzle housing is connected with the diffusion fuel cavity and is provided with a premixed air inlet hole and a premixed fuel inlet hole. The premixing cyclone assembly is positioned in the nozzle outer cover and connected with the diffusion fuel cavity, and the premixing cyclone assembly is provided with cyclone blades; in addition, the diffusion fuel cavity, the premixing rotational flow assembly and the nozzle outer cover jointly form a premixing rotational flow channel, and premixed fuel and premixed air are mixed in the premixing rotational flow channel and are injected into the combustion chamber. The diffusion cyclone assembly is positioned in the premixing cyclone assembly and connected with the diffusion cavity, and the diffusion cyclone assembly is provided with a diffusion cyclone channel; in addition, the diffusion fuel cavity, the diffusion rotational flow component and the premixing rotational flow component jointly form a diffusion fuel channel, and diffusion fuel is injected into the combustion chamber through the diffusion rotational flow channel to be mixed with air injected into the combustion chamber and combusted. The nozzle inner core is positioned in the diffusion rotational flow component and connected with the diffusion fuel cavity; in addition, the diffusion air cavity, the nozzle inner core and the diffusion rotational flow component jointly form a diffusion air channel, and diffusion air is injected into the combustion chamber through the diffusion rotational flow channel to be mixed with diffusion fuel injected into the combustion chamber and combusted.
Drawings
Fig. 1 is a schematic diagram of the system structure of the present invention.
Fig. 2 is a cross-sectional view of the swirler of the present invention.
Fig. 3 is a cross-sectional view of the diffusion air chamber of the present invention.
Fig. 4 is a cross-sectional view of a diffusion fuel chamber of the present invention.
Fig. 5 is a cross-sectional view of the nozzle housing of the present invention.
Fig. 6 is a cross-sectional view of a pre-mixing swirler assembly according to the present invention.
Fig. 7 is a cross-sectional view of the middle diffusion vortex assembly of the present invention.
Fig. 8 is a cross-sectional view of the inner core of the nozzle of the present invention.
Fig. 9 is a schematic view of an embodiment of the present invention.
Description of reference numerals:
1 a diffusion air cavity; 1-1 diffusing air cavity end caps; 1-2 diffusion air inlet holes; 2 a diffusion fuel chamber; 2-1 diffusion fuel chamber end caps; 2-2 diffusion fuel inlet holes; 3, a nozzle housing; 3-1 nozzle housing flange; 3-2 premixing air inlet holes; 3-3 premixing fuel air inlet holes; 3-4 premixing air collecting cavity; 3-5 premixing fuel gas-collecting cavity; 3-6 nozzle housings; 4, premixing swirl component; 4-1 premixing swirl component front cavity; 4-2 swirl vanes; 4-3, premixing the rotational flow inner pipe; 5, a diffusion rotational flow component; 5-1, a diffusion rotational flow end cover; 5-2 diffusion inner tube; 5-3, a diffusion rotational flow spray head; 6, a nozzle inner core; 6-1, pressing a nozzle inner core strip; 6-2 nozzle core rod.
Detailed Description
The invention will be further described with reference to the drawings and the following detailed description, but the invention is not limited to this embodiment.
The utility model discloses an application area is as shown in figure 4 gas turbine swirler. As shown in fig. 1 to 9, the present invention provides a swirl nozzle device suitable for a gas turbine combustor, which comprises a nozzle diffusion air cavity 1, a diffusion fuel cavity 2, a nozzle housing 3, a premixing swirl component 4, a diffusion swirl component 5 and a nozzle inner core 6.
The diffusion air cavity 1 is connected with the diffusion fuel cavity 2, the diffusion fuel cavity 2 is connected with the nozzle outer cover 3, the nozzle inner core 6 is positioned in the diffusion cyclone assembly 5, the diffusion cyclone assembly 5 is positioned in the premixing cyclone assembly 4, and the premixing cyclone assembly 4 is positioned in the nozzle outer cover 3; the nozzle inner core 6 is provided with a nozzle inner core pressing strip 6-1 and a nozzle inner core rod 6-2, and the nozzle inner core pressing strip 6-1 is arranged at the front end of the nozzle inner core rod 6-2; the nozzle inner core pressing strip 6-1 is arranged in a pressing groove at the upper end of the diffusion rotational flow end cover 5-1 so as to realize the close fit connection between the nozzle inner core 6 and the diffusion rotational flow component 5; the diffusion rotational flow component 5 is provided with a diffusion rotational flow end cover 5-1, a diffusion inner pipe 5-2 and a diffusion rotational flow spray head 5-3, the diffusion rotational flow end cover 5-1 is positioned at the front end of the diffusion inner pipe 5-2, and the diffusion rotational flow spray head 5-3 is positioned at the downstream of the diffusion inner pipe 5-2; the diffusion rotational flow component 5 and the diffusion fuel cavity 2 are in close fit connection by means of internal threads at the upper end of a diffusion fuel end cover 5-1;
the premixing cyclone assembly 4 is provided with a premixing cyclone assembly front cavity 4-1, cyclone blades 4-2 and a premixing cyclone inner tube 4-3, and the premixing cyclone blades 4-2 are circumferentially and uniformly distributed on the outer wall surface of the premixing cyclone inner tube 4-3; the premixing cyclone assembly 4 and the diffusion fuel cavity 2 are in close fit connection with the external thread at the upper end of the premixing cyclone assembly front cavity 4-1 through the external thread at the lower end of the diffusion fuel end cover 2-1;
the nozzle outer cover 3 is provided with a nozzle outer cover flange 3-1, a premixed air inlet 3-2 and a premixed fuel inlet 3-3; the nozzle housing 3 and the diffusion fuel cavity 2 are in close fit connection through a nozzle housing flange 3-1 and a diffusion fuel cavity end cover 2-1.
A diffusion air inlet 1-2 is arranged at the center of a diffusion air end cover 1-1 of the diffusion air cavity 1; a diffusion fuel end cover 2-1 of the diffusion fuel cavity 2 is provided with a diffusion fuel air inlet 2-2; the diffusion fuel cavity 2, the premixing cyclone assembly 4 and the nozzle outer cover 3 jointly form a premixing cyclone channel, the diffusion cyclone assembly 4 is provided with a diffusion cyclone channel, the diffusion fuel cavity 2, the diffusion cyclone assembly 5 and the premixing cyclone assembly 4 jointly form a diffusion fuel channel, and the diffusion air cavity 1, the nozzle inner core 6 and the diffusion cyclone assembly 5 jointly form a diffusion air channel.
When the swirl nozzle works, diffusion air is injected into the nozzle from diffusion air inlet holes 1-2 on a diffusion air cavity 1, and is guided by a diffusion swirl nozzle 5-3 to form swirl flow through a diffusion air channel formed by the diffusion air cavity 1, a diffusion swirl component 5 and a nozzle inner core 6, and is injected into a combustion chamber, mixed with diffusion fuel and combusted; the diffusion fuel is injected into a nozzle from a diffusion fuel air inlet 2-2 on a diffusion fuel cavity 2, flows through a diffusion fuel channel consisting of the diffusion fuel cavity 2, a diffusion rotational flow component 5 and a premixing rotational flow component 4, is guided by a diffusion rotational flow nozzle 5-3 to form rotational flow, is injected into a combustion chamber, and is mixed with diffusion air and premixing air to form flow field conditions suitable for diffusion combustion; premixed air is injected into a premixed air collecting cavity 3-4 through a premixed air inlet hole 3-2 on a nozzle outer cover 3, then is injected into a nozzle through a small hole between a nozzle shell 3-6 and the premixed air collecting cavity 3-4, is primarily mixed with premixed fuel at the upstream of a swirl vane 4-2, is guided by the swirl vane 4-2 to form a swirl, is mixed with the premixed fuel in a premixing channel formed by the nozzle outer cover 3 and a premixed swirl component 4, and is injected into a combustion chamber for combustion; the premixed fuel is firstly injected into a premixed fuel gas-collecting cavity 3-5 through a premixed fuel gas inlet 3-3 on a nozzle outer cover 3, then is injected into a nozzle through a small hole between a nozzle shell 3-6 and the premixed fuel gas-collecting cavity 3-5, is primarily mixed with premixed air at the upstream of a swirl vane 4-2, is guided by the swirl vane 4-2 to form swirl, is mixed with the premixed air in a premixing channel formed by the nozzle outer cover 3 and a premixed swirl component 4, and is injected into a combustion chamber to form flow field conditions suitable for premixed combustion.
Preferably, a pressure tongue can be reserved on the diffusion fuel end cover 2-1, when the diffusion fuel cavity 2 is connected with the diffusion rotational flow component 5, the nozzle inner core pressure strip 6-2 fixed in the diffusion rotational flow end cover 5-1 is further compressed through the pressure tongue, so that the tight connection between the nozzle inner core 6 and the diffusion rotational flow component 5 is realized, and the nozzle inner core 6 is ensured not to be loosened.
Preferably, a concave sealing groove can be reserved at the lower end of the diffusion fuel end cover 2-1, and an convex sealing ring can be reserved on the nozzle outer cover flange 3-1, so that the sealing between the diffusion fuel end cover 2-1 and the nozzle outer cover flange 3-1 is further enhanced.
Preferably, a plurality of diffusion fuel air inlet holes 2-2 are distributed along the circumference of the diffusion fuel end cover 2-1 in a tangential direction, the diffusion fuel flow resistance is reduced while the diffusion fuel flow is guaranteed, and a pre-swirl flow is formed before the fuel enters a diffusion fuel air inlet channel, so that the turbulence of the diffusion fuel is increased, and the mixing between the diffusion fuel and air is promoted.
Preferably, a plurality of premixed air inlets 3-2 can be arranged in a circumferential tangential direction along the premixed air collecting cavity 3-4, the flow resistance of the premixed air is reduced while the flow rate of the premixed air is ensured, and a pre-swirl flow is formed before the premixed air enters the premixed air inlet channel so as to increase the turbulence degree of the premixed air and promote the mixing between the premixed air and the premixed fuel.
Preferably, a plurality of premixed fuel air inlets 3-3 can be arranged along the circumferential tangential direction of the premixed fuel air collecting cavity 3-5, the flow resistance of the premixed fuel is reduced while the flow of the premixed fuel is ensured, and a pre-swirl flow is formed before the premixed fuel enters the premixed fuel air inlet channel so as to increase the turbulence degree of the premixed fuel and promote the mixing between the premixed fuel and the premixed air.
Preferably, the small holes between the nozzle casing 3-6 and the premix air collecting chamber 3-4 and the small holes between the nozzle casing 3-6 and the premix fuel collecting chamber 3-5 are replaced by densely distributed honeycomb holes to ensure the flow of premix air and fuel and promote the uniform injection of premix air and premix fuel into the premixing passage of the swirl nozzle.
Examples
As shown in fig. 9, the present invention provides a swirler suitable for a gas turbine, which includes a nozzle diffusion air cavity 1, a diffusion fuel cavity 2, a nozzle outer cover 3, a premixed swirl component 4, a diffusion swirl component 5 and a nozzle inner core 6. The diffusion air cavity 1 is connected with the diffusion fuel cavity 2, the diffusion fuel cavity 2 is connected with the nozzle outer cover 3, the nozzle inner core 6 is positioned in the diffusion cyclone assembly 5, the diffusion cyclone assembly 5 is positioned in the premixing cyclone assembly 4, and the premixing cyclone assembly 4 is positioned in the nozzle outer cover 3; the nozzle inner core pressing strip 6-2 is arranged in a pressing groove at the upper end of the diffusion rotational flow end cover 5-1; the diffusion rotational flow component 5 and the diffusion fuel cavity 2 are in close fit connection by means of internal threads at the upper end of a diffusion fuel end cover 5-1; the premixing cyclone assembly 4 and the diffusion fuel cavity 2 are in close fit connection with the external thread at the upper end of the premixing cyclone assembly front cavity 4-1 through the external thread at the lower end of the diffusion fuel end cover 2-1; the nozzle housing 3 and the diffusion fuel cavity 2 are in close fit connection through a nozzle housing flange 3-1 and a diffusion fuel cavity end cover 2-1.
When the swirl nozzle works, diffused air is injected into the nozzle from a diffusion air inlet 1-2 on a diffusion air cavity 1, flows through a diffusion air channel formed by the diffusion air cavity 1, a diffusion swirl component 5 and a nozzle inner core 6, is guided by a diffusion swirl nozzle 5-3 to form swirl, is injected into a combustion chamber, is mixed with diffusion fuel and is combusted; the diffusion fuel is injected into a nozzle from a diffusion fuel air inlet 2-2 on a diffusion fuel cavity 2, flows through a diffusion fuel channel consisting of the diffusion fuel cavity 2, a diffusion rotational flow component 5 and a premixed rotational flow component 4, is guided by a diffusion rotational flow nozzle 5-3 to form rotational flow, is injected into a combustion chamber, and is mixed with diffusion air and premixed air to form a flow field condition suitable for diffusion combustion; premixed air is injected into a premixed air collecting cavity 3-4 through a premixed air inlet hole 3-2 on a nozzle outer cover 3, then is injected into a nozzle through a small hole between a nozzle shell 3-6 and the premixed air collecting cavity, is mixed with premixed fuel in a premixing channel formed by the nozzle outer cover 3 and a premixed cyclone assembly 4, and is injected into a combustion chamber for combustion; the premixed fuel is injected into a premixed fuel gas-collecting cavity 3-5 from a premixed fuel gas inlet 3-3 on a nozzle outer cover 3, then is injected into a nozzle from a small hole between the nozzle outer cover 3-6 and the premixed fuel gas-collecting cavity 3-5, is mixed with premixed air in a premixing channel formed by the nozzle outer cover 3 and a premixed cyclone assembly 4, and is injected into a combustion chamber to form flow field conditions suitable for premixed combustion.
Preferably, a pressure tongue can be reserved on the diffusion fuel end cover 2-1, when the diffusion fuel cavity 2 is connected with the diffusion rotational flow component 5, the nozzle inner core pressure strip 6-2 fixed in the diffusion rotational flow end cover 5-1 is further compressed through the pressure tongue, so that the tight connection between the nozzle inner core 6 and the diffusion rotational flow component 5 is realized, and the nozzle inner core 6 is ensured not to be loosened.
Preferably, a concave sealing groove can be reserved at the lower end of the diffusion fuel end cover 2-1, and an convex sealing ring can be reserved on the nozzle outer cover flange 3-1, so that the sealing between the diffusion fuel end cover 2-1 and the nozzle outer cover flange 3-1 is further enhanced.
Preferably, 4 diffusion fuel air inlets 2-2 are distributed along the circumference of the diffusion fuel end cover 2-1 in a tangential direction, the diffusion fuel flow resistance is reduced while the diffusion fuel flow is guaranteed, and a pre-swirl flow is formed before the fuel enters a diffusion fuel air inlet channel, so that the turbulence of the diffusion fuel is increased, and the mixing between the diffusion fuel and air is promoted.
Preferably, 8 premixed air inlets 3-2 can be arranged tangentially along the circumference of the premixed air collecting cavity 3-4, the aperture is 12 mm-18 mm, the flow resistance of premixed air is reduced while the flow rate of premixed air is ensured, and a pre-swirl flow is formed before the premixed air enters the premixed air inlet channel so as to increase the turbulence degree of the premixed air and promote the mixing between the premixed air and the premixed fuel.
Preferably, 4 premixed fuel air inlets 3-3 can be arranged in the circumferential tangential direction of the premixed fuel air collecting cavity 3-5, the aperture is 6-10 mm, the flow resistance of the premixed fuel is reduced while the flow of the premixed fuel is guaranteed, and a pre-swirl flow is formed before the premixed fuel enters the premixed fuel air inlet channel so as to increase the turbulence degree of the premixed fuel and promote the mixing between the premixed fuel and the premixed air.
Preferably, the small holes between the nozzle shell 3-6 and the premixed air collecting cavity 3-4 and the small holes between the nozzle shell 3-6 and the premixed fuel collecting cavity 3-5 can be replaced by densely distributed honeycomb holes, and the equivalent aperture is 4 mm-6 mm, so that the flow of premixed air and fuel is ensured, and the premixed air and premixed fuel are uniformly injected into the premixing channel of the swirl nozzle.
Claims (9)
1. A swirl nozzle device suitable for a combustion chamber of a gas turbine is characterized by comprising a diffusion air cavity, a diffusion fuel cavity, a nozzle outer cover, a premixing swirl component, a diffusion swirl component and a nozzle inner core; wherein the content of the first and second substances,
the diffusion air cavity, the diffusion fuel cavity and the nozzle outer cover are sequentially connected, the nozzle inner core is positioned in the diffusion rotational flow assembly, the diffusion rotational flow assembly is positioned in the premixing rotational flow assembly, and the premixing rotational flow assembly is positioned in the nozzle outer cover; the nozzle inner core is arranged on the diffusion rotational flow end cover by adopting a nozzle inner core pressing strip positioned at the front end of the nozzle inner core; the diffusion rotational flow component is connected with the diffusion fuel cavity by adopting internal threads at the upper end of a diffusion fuel end cover of the diffusion rotational flow component; the premixing cyclone assembly and the diffusion fuel cavity are tightly connected with an external thread at the upper end of a premixing cyclone assembly front cavity of the premixing cyclone assembly through the external thread at the lower end of the diffusion fuel cavity; the nozzle outer cover and the diffusion fuel cavity are tightly connected by a flange on the nozzle outer cover and a diffusion fuel cavity end cover;
the diffusion air cavity is provided with a diffusion air inlet hole, the diffusion fuel cavity is provided with a diffusion fuel inlet hole, the nozzle outer cover is provided with a premixed air inlet hole and a premixed fuel inlet hole, the premixed swirl component is provided with swirl vanes, the diffusion fuel cavity, the premixed swirl component and the nozzle outer cover jointly form a premixed swirl channel, the diffusion swirl component is provided with a diffusion swirl channel, the diffusion fuel cavity, the diffusion swirl component and the premixed swirl component jointly form a diffusion fuel channel, and the diffusion air cavity, the nozzle inner core and the diffusion swirl component jointly form a diffusion air channel.
2. A swozzle assembly adapted for use in a gas turbine combustor as claimed in claim 1 wherein the diffusion air intake is provided centrally in the diffusion air end cap of the diffusion air chamber.
3. The swozzle assembly for a gas turbine combustor as claimed in claim 1, wherein the diffusion fuel chamber end cap is reserved with a tongue depressor for further fixing the nozzle core depression bar, thereby achieving a tight connection between the nozzle core and the diffusion swozzle assembly and ensuring that the nozzle core does not loosen.
4. The swozzle assembly suitable for a gas turbine combustor as claimed in claim 1, wherein a lower end of the diffusion fuel chamber end cap is provided with a concave sealing groove, a flange of the nozzle housing is provided with an upper convex sealing ring, and the sealing groove and the sealing ring are used together to enhance the sealing between the diffusion fuel chamber end cap and the flange of the nozzle housing.
5. A swozzle assembly adapted for use in a gas turbine combustor as claimed in claim 1 wherein there are a plurality of diffusion fuel inlet holes distributed tangentially along the circumference of the diffusion fuel end cap.
6. A swozzle assembly adapted for use in a gas turbine combustor as claimed in claim 1, wherein the nozzle housing is circumferentially provided with a premix air plenum and a premix fuel plenum.
7. A swozzle apparatus suitable for use in a gas turbine combustor as claimed in claim 6, wherein there are a plurality of premixed air intake ports tangentially along the circumference of the premixed air plenum.
8. A swozzle apparatus suitable for use in a gas turbine combustor as claimed in claim 6, wherein there are a plurality of premixed fuel inlet holes tangentially along the circumference of the premixed fuel plenum.
9. A swirler device as claimed in claim 6, wherein small holes are provided between the nozzle casing of the nozzle housing and the premixed fuel gas-collecting chamber and between the nozzle casing and the premixed fuel gas-collecting chamber, and the small holes are densely arranged honeycomb holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022711178.0U CN213746854U (en) | 2020-11-21 | 2020-11-21 | Swirl nozzle device suitable for combustion chamber of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022711178.0U CN213746854U (en) | 2020-11-21 | 2020-11-21 | Swirl nozzle device suitable for combustion chamber of gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN213746854U true CN213746854U (en) | 2021-07-20 |
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| CN202022711178.0U Active CN213746854U (en) | 2020-11-21 | 2020-11-21 | Swirl nozzle device suitable for combustion chamber of gas turbine |
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| CN (1) | CN213746854U (en) |
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